Space Probes

Full text

© 2019 Relly Victoria Vi rgil Petrescu. This open access article is distributed u nder a Creative Comm ons Attributi on (CC-
BY) 3.0 license.
Journal of Mechatronics and Robotics
Review
Space Probes
Relly Victoria Virgil Petrescu
ARoTMM-IFToMM, Bucharest Polytechnic University, Bucharest, (CE), Romania
Article history
Received: 29-04-2019
Revised: 10-05-2019
Accepted: 20-05-2019
E-mail: rvvpetrescu@gmail.com
Abstract: A space probe is an unmanned space vehicle launched into space
to study more or less distant different celestial objects: The Sun, the
planets, dwarf planets and small bodies, their satellites, the interplanetary
medium or the interstellar medium. A space probe is distinguished from
other unmanned spacecraft that remain in Earth orbit. Space probes can
take a large number of forms to fulfill their mission: Orbiter placed in orbit
around the observed celestial body, lander who explores in situ the soil of
the target planet, impactor, etc. A probe can carry autonomous devices to
increase its field of investigation: Sub-satellite, impactor, rover, balloon. A
space probe has to travel great distances and operate far from the Earth and
the Sun, which requires specific equipment. It must have enough energy
to operate in regions where solar radiation provides only limited power,
have a great autonomy of decision because the remoteness of the control
center no longer allows human operators to react in real time at events,
solving telecommunication problems made difficult by distances that
reduce flow and resist radiation and extreme temperatures that malfude
embedded electronics and mechanisms. Finally, to reach a destination at a
cost and within an acceptable time, the spacecraft is led to use
sophisticated methods of navigation and propulsion: Gravitational
assistance, airbrake, ion propulsion. The first space probes are the Luna
probes launched to the moon by the Soviet Union in 1959. In 1961, the
Soviet Union launched Venera, the first probe to study another planet
than the Earth, in this case, Venus. Russia, which was a leader at the
beginning of the space age, has not had an active role since 1988 and left
this place in the United States. The European Space Agency (Mars Express,
Venus Express, Rosetta, participation in the Cassini-Huygens spacecraft)
and Japan (Hayabusa, SELENE) are also becoming increasingly important.
Finally, since the end of the 2000s, China and India have also been
producing space probes. To offset a high development cost (an amount that
can exceed one billion euros), the realization of space probes is now often
the subject of international cooperation.
Keywords: Robots, Mechatronic Systems, Machines, Space, Space Probes
Introduction
A space probe is an unmanned space vehicle
launched into space to study more or less distant
different celestial objects: The Sun, the planets, dwarf
planets and small bodies, their satellites, the
interplanetary medium or the interstellar medium. A
space probe is distinguished from other unmanned
spacecraft that remain in Earth orbit. Space probes can
take a large number of forms to fulfill their mission:
Orbiter placed in orbit around the observed celestial
body, lander who explores in situ the soil of the target
planet, impactor, etc. A probe can carry autonomous
devices to increase its field of investigation: Sub-
satellite, impactor, rover, balloon.
A space probe has to travel great distances and
operate far from the Earth and the Sun, which requires
specific equipment. It must have enough energy to
operate in regions where solar radiation provides only
limited power, have a great autonomy of decision
because the remoteness of the control center no longer
allows human operators to react in real time at events,
solving telecommunication problems made difficult by
distances that reduce flow and resist radiation and

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
302
extreme temperatures that malfude embedded electronics
and mechanisms. Finally, to reach a destination at a cost
and within an acceptable time, the spacecraft is led to use
sophisticated methods of navigation and propulsion:
Gravitational assistance, airbrake, ion propulsion.
The first space probes are the Luna probes launched
to the moon by the Soviet Union in 1959. In 1961, the
Soviet Union launched Venera, the first probe to study
another planet than the Earth, in this case, Venus.
Russia, which was a leader at the beginning of the
space age, has not had an active role since 1988 and left
this place in the United States. The European Space
Agency (Mars Express, Venus Express, Rosetta,
participation in the Cassini-Huygens spacecraft) and
Japan (Hayabusa, SELENE) are also becoming
increasingly important. Finally, since the end of the
2000s, China and India have also been producing space
probes. To offset a high development cost (an amount
that can exceed one billion euros), the realization of
space probes is now often the subject of international
cooperation (Rulkov et al., 2016; Agarwala, 2016;
Babayemi, 2016; Gusti and Semin, 2016; Mohamed et al.,
2016; Wessels and Raad, 2016; Maraveas et al., 2015;
Khalil, 2015; Rhode-Barbarigos et al., 2015;
Takeuchi et al., 2015; Li et al., 2015; Vernardos and
Gantes, 2015; Bourahla and Blakeborough, 2015;
Stavridou et al., 2015; Ong et al., 2015; Dixit and Pal,
2015; Rajput et al., 2016; Rea and Ottaviano, 2016;
Zurfi and Zhang, 2016a; 2016b; Zheng and Li, 2016;
Buonomano et al., 2016a; 2016b; Faizal et al., 2016;
Cataldo, 2006; Ascione et al., 2016; Elmeddahi et al.,
2016; Calise et al., 2016; Morse et al., 2016;
Abouobaida, 2016; Rohit and Dixit, 2016; Kazakov et al.,
2016; Alwetaishi, 2016; Riccio et al., 2016 a-b; Iqbal,
2016; Hasan and El-Naas, 2016; Al-Hasan and Al-
Ghamdi, 2016; Jiang et al., 2016; Sepúlveda, 2016;
Martins et al., 2016; Pisello et al., 2016; Jarahi, 2016;
Mondal et al., 2016; Mansour, 2016; Al Qadi et al.,
2016b; Campo et al., 2016; Samantaray et al., 2016;
Malomar et al., 2016; Rich and Badar, 2016; Hirun,
2016; Bucinell, 2016; Nabilou, 2016b; Barone et al.,
2016; Chisari and Bedon, 2016; Bedon and Louter,
2016; Santos and Bedon, 2016; Minghini et al., 2016;
Bedon, 2016; Jafari et al., 2016; Chiozzi et al., 2016;
Orlando and Benvenuti, 2016; Wang and Yagi, 2016;
Obaiys et al., 2016; Ahmed et al., 2016; Jauhari et al.,
2016; Syahrullah and Sinaga, 2016; Shanmugam, 2016;
Jaber and Bicker, 2016; Wang et al., 2016; Moubarek
and Gharsallah, 2016; Amani, 2016; Shruti, 2016; Pérez-
de León et al., 2016; Mohseni and Tsavdaridis, 2016;
Abu-Lebdeh et al., 2016; Serebrennikov et al., 2016;
Budak et al., 2016; Augustine et al., 2016; Jarahi and
Seifilaleh, 2016; Nabilou, 2016a; You et al., 2016; Al
Qadi et al., 2016a; Rama et al., 2016; Sallami et al.,
2016; Huang et al., 2016; Ali et al., 2016; Kamble and
Kumar, 2016; Saikia and Karak, 2016; Zeferino et al.,
2016; Pravettoni et al., 2016; Bedon and Amadio, 2016;
Chen and Xu, 2016; Mavukkandy et al., 2016; Gruener,
2006; Yeargin et al., 2016; Madani and Dababneh,
2016; Alhasanat et al., 2016; Elliott et al., 2016;
Suarez et al., 2016; Kuli et al., 2016; Waters et al.,
2016; Montgomery et al., 2016; Lamarre et al., 2016;
Daud et al., 2008; Taher et al., 2008; Zulkifli et al.,
2008; Pourmahmoud, 2008; Pannirselvam et al., 2008;
Ng et al., 2008; El-Tous, 2008; Akhesmeh et al., 2008;
Nachiengtai et al., 2008; Moezi et al., 2008; Boucetta,
2008; Darabi et al., 2008; Semin and Bakar, 2008;
Al-Abbas, 2009; Abdullah et al., 2009; Abu-Ein, 2009;
Opafunso et al., 2009; Semin et al., 2009a; 2009b;
2009c; Zulkifli et al., 2009; Marzuki et al., 2015; Bier
and Mostafavi, 2015; Momta et al., 2015; Farokhi and
Gordini, 2015; Khalifa et al., 2015; Yang and Lin, 2015;
Chang et al., 2015; Demetriou et al., 2015; Rajupillai et al.,
2015; Sylvester et al., 2015; Ab-Rahman et al., 2009;
Abdullah and Halim, 2009; Zotos and Costopoulos,
2009; Feraga et al., 2009; Bakar et al., 2009; Cardu et al.,
2009; Bolonkin, 2009a; 2009b; Nandhakumar et al.,
2009; Odeh et al., 2009; Lubis et al., 2009; Fathallah and
Bakar, 2009; Marghany and Hashim, 2009; Kwon et al.,
2010; Aly and Abuelnasr, 2010; Farahani et al., 2010;
Ahmed et al., 2010; Kunanoppadon, 2010; Helmy and
El-Taweel, 2010; Qutbodin, 2010; Pattanasethanon,
2010; Fen et al., 2011; Thongwan et al., 2011;
Theansuwan and Triratanasirichai, 2011; Al Smadi, 2011;
Tourab et al., 2011; Raptis et al., 2011; Momani et al.,
2011; Ismail et al., 2011; Anizan et al., 2011; Tsolakis
and Raptis, 2011; Abdullah et al., 2011; Kechiche et al.,
2011; Ho et al., 2011; Rajbhandari et al., 2011; Aleksic
and Lovric, 2011; Kaewnai and Wongwises, 2011;
Idarwazeh, 2011; Ebrahim et al., 2012; Abdelkrim et al.,
2012; Mohan et al., 2012; Abam et al., 2012; Hassan et al.,
2012; Jalil and Sampe, 2013; Jaoude and El-Tawil, 2013;
Ali and Shumaker, 2013; Zhao, 2013; El-Labban et al.,
2013; Djalel et al., 2013; Nahas and Kozaitis, 2013;
Petrescu and Petrescu, 2014a; 2014b; 2014c; 2014d;
2014e; 2014f; 2014g; 2014h; 2014i; 2015a; 2015b; 2015c;
2015d; 2015e; 2016a; 2016b; 2016c; 2016d; Fu et al.,
2015; Al-Nasra et al., 2015; Amer et al., 2015;
Sylvester et al., 2015b; Kumar et al., 2015; Gupta et al.,
2015; Stavridou et al., 2015b; Casadei, 2015; Ge and
Xu, 2015; Moretti, 2015; Wang et al., 2015; Antonescu
and Petrescu, 1985; 1989; Antonescu et al., 1985a;
1985b; 1986; 1987; 1988; 1994; 1997; 2000a; 2000b;
2001; Aversa et al., 2017a; 2017b; 2017c; 2017d; 2017e;
2016a; 2016b; 2016c; 2016d; 2016e; 2016f; 2016g;
2016h; 2016i; 2016j; 2016k; 2016l; 2016m; 2016n;
2016o; Cao et al., 2013; Dong et al., 2013; Comanescu,
2010; Franklin, 1930; He et al., 2013; Lee, 2013; Lin et al.,
2013; Liu et al., 2013; Padula and Perdereau, 2013;
Perumaal and Jawahar, 2013; Petrescu, 2011; 2015a;
2015b; Petrescu and Petrescu, 1995a; 1995b; 1997a;
1997b; 1997c; 2000a; 2000b; 2002a; 2002b; 2003; 2005a;

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
303
2005b; 2005c; 2005d; 2005e; 2011a; 2011b; 2012a;
2012b; 2013a; 2013b; 2013c; 2013d; 2013e; 2016a;
2016b; 2016c; Petrescu et al., 2009; 2016; 2017a; 2017b;
2017c; 2017d; 2017e; 2017f; 2017g; 2017h; 2017i; 2017j;
2017k; 2017l; 2017m; 2017n; 2017o; 2017p; 2017q;
2017r; 2017s; 2017t; 2017u; 2017v; 2017w; 2017x;
2017y; 2017z; 2017aa; 2017ab; 2017ac; 2017ad; 2017ae;
2018a; 2018b; 2018c; 2018d; 2018e; 2018f; 2018g;
2018h; 2018i; 2018j; 2018k; 2018l; 2018m; 2018n).
Materials and Methods
A space probe is a space vehicle launched without
human crew that aims to explore one or more celestial
bodies - planet, moon, comet, the asteroid - or the
interplanetary or interstellar medium. Its payload
consists of scientific instruments of various kinds -
cameras operating or not in visible light, spectrometers,
radiometers, magnetometers - which allow collecting
data in situ or at a distance which are then transmitted to
the Earth. If in its general architecture a space probe is
often close to an artificial satellite orbiting the Earth,
several characteristics make it special machines:
• The distance between the operators on the ground
and the machine which imposes both a large
autonomy and a communication system that is both
powerful and precise
• The complexity of the tasks to be linked: Landing on
celestial objects provided with an atmosphere or
having very low gravity, the precise pointing of the
instruments on high-speed moving targets, collection
of samples, backup procedures in case of failure
• The accuracy and complexity of the navigation;
• Cosmic ray exposure
• The sophistication of scientific instrumentation
related to the need to reduce payload and
performance requirements
• The weakness of available solar energy if the probe
is intended for the outer planets
• Much more extreme temperatures when the probe is
sent to the outer planets or below the orbit of Mercury
• The duration of the mission which can begin after a
transit of up to ten years
The missions of exploration of the solar system are
expensive and therefore rare (some missions per year all
space agencies combined) while the subjects of study are
multiplying as and when the scientific advances. The
selection process is therefore severe and highly
regulated. The main space agencies rely to determine
their space exploration strategy on documents produced
by the main scientific authorities. For NASA is the
Planetary Science Decadal Survey produced every ten
years while the European Space Agency has had a
similar document produced for its scientific program
Cosmic Vision set up in 2004 for projects ending in
2015-2025. The French CNES, although having a research
budget that does not allow it to carry out exploration of
the solar system autonomously, proceeds in the same way.
In this framework, a purely prospective call for ideas can
be launched by the space agency followed by a call for
proposals (AO). The latter normally leads to the selection
and development of a mission. It is launched in a pre-
established budget framework. At NASA, this budget
line for a mission type is available periodically, as in the
case of New Frontiers or Discovery, which allows
developing respectively 2 and 4/5 missions per decade.
ESA (which has only a fraction of NASA's budget)
selects the missions very long before they are launched.
The launch date is often postponed to cope with budget
constraints. Teams that respond to tenders include
engineers and scientists. They submit proposals detailing
both scientific objectives, technical characteristics and
financial aspects. The choice is made by scientific
committees that take into account the long-term scientific
strategy set by the documents produced by the academic
authorities at the beginning of this process.
The exploration method used for a space probe is
essentially determined by the scientific objectives
pursued and the cost constraints. For example, if it is the
first study of a planet, the idea is to place the space probe
in orbit around it to make observations on the entire
planet over long periods. But the setting in orbit requires
adding a propulsion loaded braking which represents a
major cost. For this reason, we can choose to perform a
simple overview of the lens by optimizing the
trajectory for scientific instruments to collect the
maximum amount of data. Finally, the choice of a
method of exploration is conditioned by the level of
expertise of the nation or group of nations developing
the space probe. The lowest level of difficulty is flying
over an inner planet of the solar system. The removal
of a partially autonomous rover on the planet Mars,
characterized by a high gravity and an atmosphere, was
only achieved in 2013 by NASA.
Results and Discussion
Depending on the exploration method used, space
probes can be arranged in 9 main categories. Some space
probes relate to several categories at once for example
when they combine an orbiter and a landing gear
(Viking, Fig. 1).
The Viking program consisted of a pair of American
space probes sent to Mars, Viking 1 and Viking 2. Each
ship was made up of two main parts: An orbiter
designed to photograph the surface of Mars in orbit and
ground to protect the planet on the surface. Orbits have
also served as communication relays for those who
have reached the threshold.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
304
Fig. 1: Viking probe
The Viking program has grown from NASA's older,
more ambitious program, Voyager Mars, which was not
linked to Voyager's successful space probes in the late
1970s. Viking 1 was released on August 20, 1975 and
Viking 1 was launched on September 9, 1975, both Titan
IIIE missiles with superior Centaur instruments. Viking
1 entered Mars orbit on June 19, 1976, with Viking 2
following on August 7.
After they marched Mars for more than a month and
turned the images used to select the landing places, the
shutters and detachments were detached; the descent
then entered into the Martian atmosphere and landed
gently in the places that had been chosen. Viking 1
arrived on Mars on July 20, 1976 and joined Viking
Landing on September 2. 3. Orbit continued to
photograph and perform other orbital scientific
operations, while the vessels used surface instruments.
The project cost about $ 1 billion in US dollars in
1970, equivalent to about $ 5 billion in $ 2018. The
mission was considered successful and is credited to help
build the most knowledge about Mars by the late 1990s
and early 2000s.
The primary objectives of the two Vikings were to
transport Mars hooks, to recognize the location and
certification of landing sites, to act as landing
communications relays and to conduct their own
scientific research. Each dazzling, based on Mariner 9,
was an octagon of about 2.5 m. The dazzling pocket,
with a complete fire, had a mass of 3527 kg. After
separation and landing, the soil had a mass of about 600
kg and an orbit of 900 kg. The total weight of the launch
was 2328 kg, of which 1445 kg was the attitude of fuel
and gas control. The eight sides of the ring structure
have a height of 0.4572 m and have alternate widths of
1.397 and 0.508 m. The overall height was 3.29 m from
the ground clamping points to the bottom of the vehicle's
grip points launched at the top. There were 16 modular
compartments, 3 on each of the four long faces and one
on each short face. Four wings of solar panels were
extended from the axis of the orbit, the distance from the
top to the top of two extended solar panels was 9.75 m.
The main propulsion unit was mounted above the
orbital bus. The propulsion was provided by a rocket
engine with bipropellant (monomethyl hydrazine and
nitrogen tetroxide), which could be trained up to 9
degrees. The engine was capable of a displacement of
1,323 N (297 lbf), offering a speed change of 1480 m/s.
Attitude control was achieved by 12 small jets of
compressed nitrogen.
An acquisition sun sensor, a cruise flight sensor, a
Star Canopus tracker and an inertial reference unit,
composed of six gyroscopes, allowed three-axis
stabilization. There were two accelerometers on board.
Communications were conducted via 20 WS (2.3 GHz)
transmitters and two 20W TWTA transmitters. An X
band (8.4 GHz) was also added specifically to radio
communications and experiments. Uplink was through
the S-band (2.1 GHz). A two-axis parabolic antenna with
a diameter of approximately 1.5 m was attached to an
edge of the orbital base and a fixed low gain antenna was
extended from the top of the bus. Two tape recorders
were able to store 1280 megabytes. A 381 MHz relay
radio was also available.
The power of the two orbital boats was assured by
eight solar panels of 1.57×1.23 m, two on each wing.
Solar panels have a total of 34,800 solar cells and
produced 620 powers on Mars. Power was also stored in
two nickel-cadmium batteries 30-A · h.
The combined area of the four panels was 15 square
meters (160 square meters) and provided both regular
and irregular power; unregulated power was provided to
the radio transmitter and take-off device.
Two 30-hour nickel-cadmium rechargeable batteries
provided energy when the spacecraft was not facing the
sun and Mars's correction and obfuscation maneuvers.
Discovering many geological forms commonly
formed of large amounts of water, the images of the
blind have revolutionized our ideas about Mars water.
Large river dwellings have been found in many areas.
They have shown that water floods have broken dams,
deeply carved valleys, eroded canals and thousands of
kilometers. The large hemisphere in the southern
hemisphere contains branched-flow networks,
suggesting that the rain fell once. It is believed that the
flanks of some volcanoes have been exposed to
precipitation because it resembles those produced on
Hawaiian volcanoes. Many craters show that the impact
element has fallen into the mud. When they were
formed, the ice in the soil would melt, turn the earth into
the mud and then cross the surface. Normally, the
material from an impact increases, then down. It does not
flow over the surface, going around the obstacles, as is

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
305
the case with martial craters. The regions, termed chaotic
Terrain, seemed to have quickly lost large volumes of
water, causing large channels to form. The amount of
water involved was estimated at ten thousand times
larger than the Mississippi River. Underground
volcanism can be melted by ice; the water then leaked
and the earth collapsed to leave the chaotic terrain.
Each platform consisted of a six-sided aluminum
base with long sides of 1.09 and 0.56 m (3 ft 7 in and 1 ft
10 in) supported on three extended legs attached to the
shorter sides. The legs of the legs formed the vertices of
an equilateral triangle with the sides of 2.21 m, seen
from above, the long sides of the base being formed by a
straight line with the two adjacent legs. The
instrumentation was attached to the inside and above the
base, raised above the surface by the extended legs.
Each landing device was closed in a thermal
ventilation screen designed to slow the discharge during
the intake phase. To prevent contamination with Mars by
the Earth's organisms, each landing was closed in a "bio-
shield" under pressure and then sterilized at a
temperature of 111°C (40°F) for 40 hours. For thermal
reasons, the cover of the bio-shield was removed after
the Centaur upper phase powered the Viking
orbiter/lander combination into the Earth's orbit.
Each landing arrived on Mars attached to the orbit.
The ensemble has blinded itself to Mars several times
before the soil is released and detached from orbit to
descend to the surface. The descent contained four
distinct phases, starting with burning. The creditor then
experienced top-of-the-air warming, which took place a
few seconds after the start of friction heating with the
Martian atmosphere. At an altitude of about 6 km and
traveling at a speed of 900 km/h (600 mph), the
parachute was launched, the aerosol was released and the
hips weakened. At an altitude of about 1.5 kilometers,
the lander activated his three retro-engines and was
released from the parachute. The lender immediately
used the buttons to slow down and control the descent,
with a soft landing on Mars' surface.
Propulsion was provided by mono propel hydrazine
(N2H4) through a 12-ship rocket disposed of in four
groups of three, providing a force of 32 newtons (7.2
lbf), translating a change of 180 m (590) and rotation of
the landing gear.
Lowering the terminals (after using a parachute) and
landing allowed the use of three single-propelled
hydraulic motors (one mounted on each side of the base,
separated by 120 degrees). The engines had 18 nozzles
to disperse the exhaust gases and to minimize the effects
on the soil and were sparkling from 276 to 2667 newtons
(62 to 600 lbf). Hydrazine was purified to prevent
contamination of Martian surface with microbes in the
earth. Lander transported 85 kg of fuel containing two
titanium glass tanks mounted on the opposite sides of the
soil under the X-ray windshield, giving a total launch
weight of 657 kg (1448 lb). The control was performed
using an inertial reference unit, four gyroscopes, a radar
altimeter, one terminal take-off radar and a landing, as
well as a commander's propulsion.
Power was provided by two radio-isotopic units of
thermoelectric generators (RTGs) containing 239
plutonium fixed to the opposite sides of the ground and
covered with windscreens. Each generator had a height
of 28 cm (11 inches), 58 cm (23 in) in diameter, had a
mass of 13.6 kg (30 lb) and provided a continuous
power of 30 W at 4.4 V Four layers of 28,800 nickel-
nickel coulombs, 28 volt rechargeable batteries were
loaded to charge peak loads.
The communications were conducted through a 20 W
transmitter S using two displacement wave tubes. A two-
axis parabolic antenna with high maneuverability was
mounted on an arm near the landing edge. An
omnidirectional low gain antenna extends from the base.
Both antennas allow direct communication with the
Earth, allowing Viking 1 to continue working long after
both failures. The UHF antenna (381 MHz) provided a
single relay using a 30-watt relay radio. Data storage was
on a 40 Mbit tape recorder and the creditor's computer
had a memory of 6,000 words for command instructions.
The instructor used tools to achieve the primary
science objectives of the lander mission: The study of
biology, chemical composition (organic and inorganic),
meteorology, seismology, magnetic properties,
appearance and physical properties of the Martian
surface and atmosphere. Two 360-degree cylindrical
scanning cameras were mounted near alongside the base.
From the center of this section extends the sampling arm,
with a collector head, temperature sensor and magnet at
the end. A meteorological arm, retention temperature,
wind direction and wind speed sensors have expanded
and expanded from the top of one of the grip legs. A
seismometer lens, magnet and test chamber and
magnifying mirror are mounted in front of the cameras,
near the high gain antenna. A compartment controlled
with the inner environment held the biological experiment
and mass spectrometer with a gas chromatograph. The X-
ray fluorescence spectrometer was also mounted in the
structure. A pressure sensor was attached under the body.
The scientifically useful volume had a total weight of
approximately 91 kg (201 lb).
Viking Plot has conducted biological experiments
designed to detect the life of Martian soil (if any) with
experiments designed by three separate teams led by
NASA chief scientist Gerald Soffen. One experiment
was positive for the detection of metabolism (current
life), but based on the results of the two other
experiments that failed to reveal any organic molecule in
the soil, most scientists were convinced that positive
results are probably due to strong soil oxidation.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
306
Although there is a consensus that Viking results
have shown a lack of ground biosignals at the two
landing sites, test results and boundaries are still under
evaluation. The validity of LR is based entirely on the
absence of an oxidizing agent in Martian soil but was
subsequently discovered by Phoenix soil as perchlorate
salts. It was proposed that organic compounds be present
in the soil analyzed by both Viking 1 and Viking 2 but
remained unnoticed due to the presence of perchlorate
detected by Phoenix in 2008. Researchers found that
perchlorate would destroy organic substances when
heated and produce chloromethane and dichloromethane,
the same chlorine compounds discovered by both Viking
flights when performing the same tests on Mars.
The issue of microbial life on Mars remains
unresolved. However, on April 12, 2012, an international
team of scientists reported studies based on
mathematical speculation, analyzing the complexity of
experiments launched on Labeled in the 1976 Viking
Mission, which may suggest detecting "existing
microbial existence on Mars.
The leader of the imaging team was Thomas Mutch, a
geologist at Brown University in Providence, Rhode
Island. The camera uses a mobile mirror to illuminate 12
photodiodes. Each of the 12 silicon diodes is designed to
be sensitive to different frequencies of light. Several
diodes are positioned to accurately focus at distances
between 6 and 43 m away from the ground.
Scanned devices have a scan rate per second, each
with 512 pixels. The 300-degree panoramic images were
composed of 9,150 lines. Scanning the cameras was slow
enough that, in a team, more members.
Spatial probes can be designed to perform a simple
overview of the celestial object to be studied. In the
simplest cases, these probes must only be placed on a
precise trajectory from the Earth to carry out their
missions at the cost of a few small corrections during
transit. The first interplanetary probes like Mariner 4
(Fig. 2) were of this type.
Mariner 4 (along with Mariner 3, known as Mariner-
Mars 1964) was the fourth in a series of spacecraft
designed for planetary exploration in a flyby way. It was
designed to make close scientific observations of Mars
and transmit these observations to Earth. Launched on
November 28, 1964, Mariner 4 made Marte's first
successful navigation plan, transforming the first
background images of the Martian surface. He
captured the first images of another planet ever turned
from deep space; their description of a dark and
seemingly dead world has greatly changed the vision
of the scientific community about life on Mars. Other
objectives of the mission were space and space
measurements and the provision of experience and
knowledge about engineering capabilities for long-term
interplanetary flights. On December 21, 1967,
communications with Mariner 4 ceased.
Fig. 2: Spacecraft Mariner 4
Spacecraft Mariner 4 consisted of an octagonal frame
with a diagonal of 127 cm and a height of 45.7 cm. Four
solar panels were attached to the top of the frame, having
an end of 6.88 m, including solar pressure slides
extending from the ends. A parabolic antenna of the high
height of 116.8 cm was mounted at the top of the frame.
The omnidirectional low gain antenna was mounted at a
height of 7 inches, 223.5 cm high, near the high gain
antenna. The total height of the spacecraft was 2.89
meters. The octagonal frame was equipped with
electronic equipment, harnesses, timely propulsion and
gas supply and attitude controllers.
Scientific Instruments Included
A helium magnetometer mounted on the waveguide
that drives the omnidirectional antenna to measure the
magnitude and other features of the interplanetary and
planetary magnetic fields.
A Geiger ion/ion counter mounted on the waveguide
that drives the omnidirectional antenna closer to the
spacecraft's body to measure the intensity and
distribution of charged particles in the interplanetary
space and Mars.
A captured radiation detector, mounted on the body
with counter-axes oriented at 70° and 135° in the
direction of the sun, to measure the intensity and
direction of the low-energy particles.
A cosmic ray telescope, mounted inside the body,
indicating an anti-solar direction to measure the direction
and energy spectrum of protons and alpha particles.
A solar plasma probe mounted on the body at 10
degrees to the sun to measure the flow of charged
particles of very low solar energy.
A cosmic dust detector, mounted on the body with a
microphone plate approximately perpendicular to the
plane of the orbit, to measure the impulse, distribution,
density and direction of the cosmic dust.
A television camera, mounted on a scanning platform
in the center of the ship's center, to get close-up images
of Mars. This subsystem comprises 4 parts, a Cassegrain

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
307
telescope with a viewing range of 1.05° to 1.05°, a
shutter and a set of red/green filters with an exposure
duration of 0.08 s and 0.20 s, a vidicon scan tube that
translates the video signal and the electronic systems
needed to convert the analog signal into a digital
bitstream for transmission.
The power tool and the Mariner 4 radio transmitter
were delivered by 28,224 solar cells contained in the
four 176×90 cm solar panels that could provide a 310-
watt edge. A rechargeable 1200 W·h silver-zinc battery
was used and for maneuvers and reserve. Hydraulic
propulsion was used for propulsion through a four-jet
vector control engine with a pressure of 222 newtons (50
lbf) installed on one of the sides of the octagonal
structure. The control of the probe space attitude was
assured by 12 cold nitrogen gas jets mounted at the ends
of the solar panels and three gyroscopes. The solar
pressure panels, each with a surface of seven ft², were
attached to the top of the solar panels. Position
information was provided by four sun sensors and a
Terra, Marte or Canopus Star sensor, depending on the
time spent in its space. Mariner 4 was the first spacecraft
to need a star for a navigation reference, as Earth, Moon
or Venus earlier missions saw either the brilliant face of
the planet of origin, the burning target. During this flight,
both the Earth and Mars would be too weak to block.
Another source of light at a wide angle from the Sun was
necessary and Canopus fulfilled this heaven.
Mariner's telecommunication devices consist of S-
band transmitters (a seven-watt three-dimensional cavity
amplifier or a 10-watt protective amplifier) and a single
radio receiver that together can send and receive 8-bit or
33-bit data per second. The data could also be stored on
a 5.24-million-bit tape recorder for subsequent
transmission. All electronic operations were controlled
by a command subsystem that could process any of the
29 direct command words or three command words for
maneuvers midway. The central computer and sequence
command the stored timestamps using a 38.4 kHz
synchronization frequency as a reference. Temperature
control was achieved by using adjustable slots mounted on
six electronic assemblies, plus multilayer insulating
sheets, polished aluminum shields and surface treatments.
Other measurements that can be performed include:
• Radio has appeared
• Heavenly technology based on precision tracking
After Mariner 3 was a total loss due to the failure of
the payload, JPL engineers suggested that there was a
failure caused by the outer separation of the metal plates
from the glass fiber inner liner due to the pressure
differences between the inner and outer part of the
shroud and that this could have caused the arc separation
mechanism to get tangled and not detached properly.
Testing at JPL has confirmed this failure and efforts
have been made to develop a new metal edition. The
downside was that the new platform would be
significantly larger and reduce the capacity of the Atlas-
Agena lift. Convair and Lockheed-Martin were supposed
to do more performance improvements to get more
power out of it. Despite fears that the work could not be
completed before the window of March 1964 was
closed, the new shroud was ready by November.
After launching the Cape Canaveral 12 launch
complex, Mariner 4 was removed and the Agena-
D/Mariner 4 combination was separated from the Atlas-
D rocket at 14:27:23 UTC on November 28, 1964. The
first firing of the Agena had place in 14: 28: 14 and
14:30:38. The initial launch put the spacecraft in a
ground parking orbit and the second burning at 15:02:53
at 15:04:28 injected the craft into a transfer orbit on
Mars. Mariner 4 broke away from Agena at 15:07:09 and
began to travel. The solar panels installed and the
scanning platform was disconnected at 15:15:00. The
accumulation of the sun occurred after 16 minutes.
After Sun's acquisition, the Star Canopus tracker
searched for Canopus. The Star Tracking System has
been set to respond to any object more than one eighth
and less than eight times lighter than Canopus. Including
Canopus, there were seven such objects visible to the
sensor. It took more than a day of "hip-hop" to find
Canopus because the sensor was blocked by other stars:
in front of Canopus an exterior model, Alderamin,
Regulus, Naos and Gamma Velorum.
A consistent problem that affected the spacecraft
during the first part of its mission was that the transitions
of the roll error signal would occur frequently and would
occasionally cause the loss of the Canopus star block.
The first half-race attempt was canceled by a loss of lock
shortly after the gyroscopes began to spin. Canopus's
blocking has been lost six times in less than three weeks
of launch and each time a series of radio commands are
needed to recover the star. After a study of the problem,
the investigators concluded that the behavior was due to
the small particles of dust that were released by
spacecraft by some means and traveling through the field
of vision of the sensor. The light of the sun scattered
from the particles appears as an illumination equivalent
to that of a bright star. This would result in a transient
rolling error because the object passed through the field
of view while the sensor was blocked on Canopus. When
the object was brilliant enough to exceed the gate limit
of eight times the Canopus intensity, the ship will
automatically initiate a search for a new star. Finally, a
radio command was sent on December 17, 1964, which
eliminated the upper limit of the gate. There was no
further loss of Canopus lock, although there were 38
passes before meeting with Mars.
Mission return dates were 5.2 million bits
(approximately 634 KB). All instruments worked

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
308
successfully, with the exception of one part of the
ionization chamber, namely the Geiger-Müller tube,
which failed in February 1965. In addition, the plasma
probe had the degraded performance of a defect of
resistance on December 8, 1964, but experimenters have
been able to recalibrate the instrument and continue to
interpret the data. Returned images showed a land similar
to the Moon, which scientists did not expect, although
amateur astronomer Donald Cyr predicted craters. Later,
missions showed that craters were not typical of Mars, but
only for the older region recorded by Mariner 4, a pressure
of 4.1-7.0 millibars (410-700 Pascal) and a temperature of
-100 degrees Celsius. There are no magnetic fields or
Martian radiation belts or, surprisingly, the surface water
was again detected at that time.
The objectives that can be achieved by this type of
mission are however limited: The observation time is
very short because the probe is flying over a speed of
several km / s, often only one side of the celestial body is
visible at the time of over-flight and lighting conditions
are not optimal. This method of observation may be the
only one that can be used for the most distant celestial
objects (see Pluto by New Horizons, Fig. 3).
New Horizons is an interplanetary space probe
launched as part of NASA's New Frontiers program.
Designed by Johns Hopkins University, the Applied
Physics Laboratory (APL) and the South West Research
Institute (SwRI), with a team led by S. Alan Stern, the
ship was launched in 2006 with the primary mission of
conducting a study of Pluto 2015 and a secondary
mission to fly and study one or more Kuiper belt items in
the next, including MU69 2014 in 2019. It is the fifth
space probe to achieve the evacuation speed required to
leave the system solar.
Fig. 3: New horizons
On January 19, 2006, New Horizons was launched
from Cape Canaveral Air Station by an Atlas V rocket
directly on a trajectory of the earth and the sun at a speed
of 10.10 mi/s and 58,500 km/h; 36,400 mph). This was
the fastest anthropic object ever produced on Earth. After
a brief encounter with the asteroid 132524 APL, New
Horizons proceeded to Jupiter, approaching the nearest
approach on February 28, 2007, at a distance of 2.3
million kilometers. Jupiter flyby has provided gravity
assistance that has increased New Horizons speed; has
also allowed a general test of the scientific capabilities of
New Horizons, which returns data about the planet's
atmosphere, the moon and the magnetosphere.
Most of the post-Jupiter trip was spent in
hibernation mode to keep the systems on board,
except for short annual leaks. On December 6, 2014,
new horizons were brought online for Pluto's meeting
and began checking. On 15 January 2015, the
spacecraft began its approach with Pluto.
On 14 July 2015, at 11:49 UTC, he flew 12,500 km
(7,800 mi) above Pluto, becoming the first spacecraft to
explore the dwarf planet. On October 25, 2016, 21:48
UTC, Pluto's latest data was received from New
Horizons. After completing his trip to Pluto, New
Horizons maneuvered 2014 2014 2014 "The Last Thule"
(486958) 2014, which took place on January 1, 2019,
when it was 43.4 AU from the Sun. In August 2018,
NASA quoted Alice's results on New Horizons to
confirm the existence of a "hydrogen wall" at the outer
edges of the Solar System. This "wall" was first detected
in 1992 by the two spacecraft Voyager.
In August 1992, JPL scientist Robert Staehle
named Pluto discoverer Clyde Tombaugh asking for
permission to visit the planet. "I told him he was
welcome," Tombaugh later remembered, "though he
has to go on a long and cold journey." The appeal
eventually led to a series of proposed Pluto missions
that led to New Horizons.
Stomatios "Tom" Krimigis, head of the Division of
Applied Physics Laboratories, one of the most
participants in the New Frontiers program, formed the
New Horizons team with Alan Stern in December 2000.
As the main investigator of the project, Stern was
described by Krimigis as "personification of the Pluto
mission". New Horizons relies heavily on Stern Pluto
350's work and involves most of the team at Pluto
Kuiper Express. The proposal for the new horizons was
one of the five, which was officially presented to NASA.
Later, he was selected as one of the two finalists to
undergo a three-month conception study in June 2001.
The other finalist, Pluto and Outdoor Solar System
Explorer (POSSE), was a separate concept in Colorado
Boulder, led by lead researcher Larry W. Esposito,
supported by JPL, Lockheed Martin and the University
of California. However, APL, in addition to being

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
309
supported by Pluto Kuiper Express developers at
Goddard Space Flight Center and Stanford University,
was a good one; have recently developed NEAR
Shoemaker for NASA, which successfully entered orbit
around 433 Eros earlier this year and later landed on the
asteroid for science and fanfare engineering.
In November 2001, New Horizons was officially
selected for funding as part of the New Frontiers
program. However, NASA's new administrator,
appointed by the Bush Administration, Sean O'Keefe,
did not support the New Horizons and in fact, canceled
it by not including it in NASA's 2003 budget. NASA,
Ed Weiler Sciences, led Stern to lobby for New
Horizons, hoping the mission would appear in the
Decadal Study of Planetary Sciences; a priority list of
wishes, developed by the United States National
Research Council, which reflects the views of the
scientific community.
New Horizons is the first mission of the New
Frontiers mission, larger and more expensive than
Discovery missions, but less than the Flagship program.
The cost of the mission (including spacecraft and
instrument development, vehicle launch, mission
operations, data analysis and education/public
information) is approximately $ 700 million over 15
years (2001-2016). Spacecraft was built primarily by the
Southwest Research Institute (SwRI) and Johns Hopkins
Applied Physics Laboratory. The Head of Mission is
Alan Stern of the South West Research Institute (former
NASA Associate Administrator).
After separation from the launch vehicle, general
control was performed by the Mission Operations Center
(MOC) at the Applied Physics Laboratory in Howard
County, Maryland. The scientific instruments are
operated at the Clyde Tombaugh Science Center (T-
SOC) in Boulder, Colorado. Navigation takes place in
different contractor facilities, while navigational
position data and Celestian reference frames are
provided by the Flagstaff Observatory via NASA and
JPL headquarters; KinetX is the leader of the New
Horizons navigation team and has the task of planning
route trajectories as the speed of the spacecraft extends
to the outer solar system. Coincidentally, Flagstaff's
ship observation station was the one where
photographic plates were taken to find the moon of
Pluto Charon and the Naval Observatory is not far from
Lowell Observatory, where Pluto was discovered.
New horizons were originally planned as a trip to the
only unexplored planet in the Solar System. At the
launch of the spacecraft, Pluto was still classified as a
planet reclassified by the International Astronomers
Union (IAU) as a dwarf planet. Some New Horizons
team members, including Alan Stern, disagree with the
IAU definition and still describe Pluto as the new planet.
The Pluto Nix and Hydra satellites also have a connection
with the spacecraft: The first letters of their names (N and
H) are the initials of New Horizons. Monthly discoverers
chose these names for this reason, plus Nix and Hydra's
relationship with the mythological platoon.
In addition to scientific equipment, there are several
cultural artifacts that travel with the spacecraft. These
include a collection of 434,738 names stored on a
compact disc, a SpaceShipOne piece from Scaled
Composites, a USPS "Not yet explored" and a US flag
along with other reminders.
About 30 grams of ash by Clyde Tombaugh is on
board the commemoration of Pluto's discovery in 1930.
A Florida State Coin whose design commemorates
human exploration is officially included as a final
weight. One of the scientific packs (a dust counter) is
named after Venice Burney, who, as a child, suggested
the name "Pluto" after his discovery.
The aim of the mission is to understand the formation
of the plutonic system, the Kuiper belt and the
transformation of the early solar system. Spacecraft
collected data on Pluto's atmosphere, surfaces, interiors
and environments, as well as about its moons. He will
also study other Kuiper belt objects. "By comparison,
New Horizons gathered 5000 times more data about
Pluto that Mariner made at Red Planet."
Some of the questions the mission is trying to answer
are: What is Pluto's atmosphere and how does it behave?
How does his surface look like? Are there large
geological structures? How does solar wind particles
interact with Pluto's atmosphere?
Specifically, mission science objectives are:
• The composition of Pluto and Charon's maps
• Characterizes the geology and morphology of Pluto
and Charon, characterize Pluto's neutral atmosphere
and escape rate, look for an atmosphere around
Charon, map of surface temperatures on Pluto and
Charon, look for rings and additional satellites
around Pluto, conducts similar investigations of one
or more Kuiper belt objects
The space ship is comparable in size and shape to a
large piano and was compared to a piano locked in a
cocktail bar antenna. As a starting point, his team was
inspired by the space ship Ulysses, which also carried a
Radio-isotope Thermoelectric (RTG) and a ship on a
box-in-box structure through the external solar system.
Many subsystems and components have FLO mosaic in
the CONTOUR space vessel, which in turn has the
patrimony of the spacecraft APL TIMED.
The New Horizons body forms a triangle with a
thickness of nearly 0.76 m (2.5 ft). (The pioneers have
hexagonal bodies, while Voyagers, Galileo and Cassini-
Huygens have decorative and bare bodies.) An alloy tube
7075 forms the main structural column between the "6"

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
310
11 step radio antenna, the titanium offers resistance and
thermal insulation, the rest of the triangle being mainly
aluminum sandwich panels (under 1/64 or 0.40 mm)
glued into an aluminum honeycomb structure larger than
the strictly necessary interior space. The structure is
designed to act as shielding, reducing electronic errors
caused by X-rays. Also, the mass distribution required
for a spacecraft requires a wider triangle.
The interior structure is painted in black to equalize the
temperature by radiant heat transfer. In general, spacecraft
are crowded to keep the heat. Unlike pioneers and
travelers, the radio mine is also enclosed in blankets that
extend to the body. The heat from the RTG adds heat to
the ship as it is in the outer solar system. While in the
internal solar system, spacecraft must prevent overheating,
electronic activity is limited, power is diverted to travel
with attached radiators and shutters are open to radiate
excess heat. While spacecraft move inactive in cold
outside the solar system, the shutters are closed and the
shunt regulator redirects energy to electric heaters.
The new horizons have both stabilization modes (cruise)
and three stabilized (scientific) axes, fully controlled by
monopropyl hydrazine. Due to an internal 77 kg (170 lb)
tank, an extra plus of 290 m/s (1000 km/h, 650 mph) is
provided. The helium is used as a gasifier with an
elastomeric membrane that helps expel. Spacecraft
circulating in orbit, including fuel, are over 470kg (1,040 lb)
on Jupiter, but it would have been just 445kg (981lb) for the
direct reserve option to Pluto. Significantly, if the backup
option was taken, this would have meant less fuel for
subsequent Kuiper band operations.
There are 16 holes on the new horizons: Four 4.4 N
(1.0 lbf) and twelve 0.9 N (0.2 lbf) plumbed in redundant
branches. The larger ones are mainly used to correct the
paths and the smallest ones (previously used for Cassini
and Voyager) are mainly used for spin-spindown
maneuvers and spindown maneuvers. Two-star rooms
are used to measure the attitude of the spacecraft. They
are mounted on the ship's side and provide information
in 3 or 3 directions. Between starboard reading, the
orientation of the spacecraft is provided by redundant
inertial measurement units in miniature. Each unit
contains three solid gyroscopes and three accelerometers.
Two Adcole Sun sensors ensure the determination of
attitude. The angle is detected in the Sun, while the other
measures measure clock rotation and speed.
A radial radial radial radiator (X-ray radiator) extends
into a triangular plane on a triangle tip. RTG delivered
245.7 watts at launch and was estimated to fall by about
3.5 watts each year to 202 watts when it meets the
plutonic system in 2015 and will drop too much to power
the transmitters in 2030 There are no batteries at board
as an X-ray output is predictable and transient loads are
treated through a series of capacitors and short circuit
breakers. Starting in January 2019, the output power of
the RTG is about 190 W.
RTG, the "GPHS-RTG" model, was originally a
reserve from the Cassini mission. RTG contains 9.75 kg
(21.5 lb) of plutonium oxide-238 pellets. Each pellet is
dressed in iridium, then wrapped in a graphite shell. It
was developed by the US Department of Energy. of the
Materials and Fuels Complex, part of the Idaho National
Laboratory. The original RTG project required 10.9
kilograms of plutonium, but a unit less powerful than the
original target was due to delays from the US
Department of Energy, including security activities that
delayed plutonium production. Mission parameters and
observation sequence had to be modified for reduced
power; however, not all instruments.
The amount of radioactive plutonium in RTG
represents about one-third of the amount of Cassini-
Huygens on board when it was launched in 1997. This
launch was protested by some of them. The US
Department of Energy has estimated the chance of a
launch accident that would release atmospheric radiation
to 1 in 350 and will monitor the launch, as is always the
case with the involvement of RTGs. It was estimated that
the worst-case scenario of on-board plutonium
dispersion would produce radiation equivalent to 80% of
the average annual radiation dose in North America over
a 105 km (65 m) radius.
The spacecraft transports two computer systems: The
data control and manipulation system and the control and
control processor. Each of the two systems is doubled
for redundancy, for a total of four computers. The
processor used for its flight computers is Mongoose-V,
a 12 MHz version with MIPS R3000 processor-
resistant radiation. Multiple redundant clocks and
synchronization routines are implemented in hardware
and software to prevent malfunctions and downtime.
For storage of heat and mass, spacecraft and electronic
tools are housed together in integrated electronic
modules (IEMs). There are two redundant IEMs.
Including other functions, such as instrument electronics
and radio, each IEM contains 9 panels. The probe
software runs on the Nucleus RTOS operating system.
There Were Two "Safe" Events that Sent the Ship
Safely
On March 19, 2007, the data manipulation and data
processing computer encountered a memory error that
could not be recovered and resumed, causing the
spacecraft to enter secure mode. The boat was
completely recovered in two days, with a loss of data
about Jupiter's magneto. No impact on the subsequent
mission was expected.
On July 4, 2015, a secure CPU event occurred due to
over-allocation of scientific operations commissioned on
Pluto craft. Fortunately, craft managed to recover in two
days without having a major impact on its mission.
Communication with the spacecraft is done via X
band. Boats had a communication rate of 38 kbit/s for

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
311
Jupiter; at Pluto's distance, a transmission of about 1
kbit/s was expected. In addition to the low data rate,
Pluto's distance determines a latency of about 4.5 hours
(in a certain sense). 70-foot NASA Deep Space (DSN)
network levels are used to control the relays once they
are outside Jupiter. Spacecraft use modular transmitters
and modular receivers and circular polarization to the
right or left. The downlink signal is amplified by two
small 12 W (TWTA) gabion amplifiers mounted on the
antenna body. Receivers are new models with low
power. The system can be controlled to simultaneously
power both TWTAs and transmit a downward polarized
signal to the DSN that nearly doubles the downlink rate.
DSN tests at the beginning of the mission with this dual
polarization combining technique have been successful
and capability is now considered operational (when the
ship's power budget allows the use of both TWTAs).
In addition to the high gain antenna, there are two
low gain rescue antennas and a medium gain vessel.
High-quality food has a Cassegrain reflective design, a
composite structure of 2.1 m (7 ft), which provides a
gain of over 42 dBi and a power beam width of about a
certain degree. The average gain antenna with a 0.3-
meter diaphragm and a 10-degree beam width is
mounted on the rear side of the high-beam antenna's
secondary reflector. The low gain antenna is stacked
above the average gain antenna. The small gain hook
antenna is mounted in the launch adapter behind the
spacecraft. This antenna was used only for Earth's early
missions, immediately after launch and for emergencies,
if the spacecraft lost control of the attitude.
The new horizons recorded the data of the scientific
instrument to the solid memory buffer at each meeting,
then transmitted the data to Terra. The data is stored on
two low-power semiconductors (one primary, one
available) with a capacity of up to 8 gigabytes each.
Due to the extreme distance from Pluto and the Kuiper
belt, only a buffer load can be saved in those meetings.
This is due to the fact that the new horizons will take
about 16 months after they left the Pluto approach to
transmitting the buffer load.
Part of the reason for the delay between data
collection and transmission is that all New Horizons are
mounted on the body. For the cameras to record data, the
entire probe must return and the high-velocity beam of
the high gain antenna does not go to Earth. Previous
antennas, such as the Voyager probes, had a rotating tool
platform (a "scanning platform") that could measure
almost any angle without losing the radio contact with
the Earth. The new horizons have been mechanically
simplified to save weight, shorten the schedule and
improve reliability during its 15-year life.
The Voyager 2 scanning platform was blocked at
Saturn and the long-term exposure requirements on the
outer planets led to a change of plan so that the entire
probe was rotated to take Uranus and Neptune, similar to
how the horizons rotate.
The new horizons have seven instruments: Three
optical instruments, two plasma instruments, a dust
sensor and a radio/radiometer receiver. The instruments
will be used to investigate global geology, surface
composition, surface temperature, atmospheric pressure,
atmospheric temperature and discharge rate of Pluto and
its moons. The nominal power is 21 watts, although not
all instruments work simultaneously. In addition, New
Horizons has an Ultrastable Oscillator subsystem that
can be used to study and test the Pioneer anomaly
towards the end of spacecraft life.
The Remote Recognition Detector (LORRI) is a focal
point for wavelengths with high and sensitive resolution.
The instrument is equipped with a pixel of 1024x1024
pixels, with a 12-bit per pixel monochrome CCD that
offers a resolution of 5 µrad (~ 1 arc). The CCD is frozen
by a passive radiator on the ship's antisolar space. This
temperature difference requires isolation and isolation
from the rest of the structure. Ritchey-Chretien The
208.3 mm dosing structure and dosing structure are
made of silicon carbide to increase stiffness, reduce
weight and prevent deformation at low temperatures.
The optical elements are in a composite light shield and
are mounted with titanium and fiberglass for thermal
insulation. The total weight is 8.6 kg, the OTA tube
weighing about 5.6 kg (12lb) for one of the largest
silicon-carbide telescopes flying at that time (now
overtaken by Herschel). For viewing on public sites, 12
bit per pixel LORRI images are converted to JPEG
images at 8 pixels per pixel. These public images do not
contain the full range of brightness information available
from raw LORRI image files.
Solar Wind Through Pluto (SWAP) is a toroidal
electrostatic analyzer and a potential delay analyzer
(RPA), one of the two instruments, including Plasma
New Horizons and a Speakometer High Peak, the other
being PEPSSI. SWAP measures particles of up to 6.5
keV and, due to the weak solar wind at Pluto's distance,
the instrument is designed with the largest opening of
any such instrument ever flown.
Particle Energy Spectrometer (PEPSSI) is a time
sensor for flight and electron ions, one of two
instruments that include PAM (New Horizons Plasma
Spectrometer), the other being SWAP. Unlike SWAP,
which measures particles up to 6.5 keV, PEPSSI
increases to 1 MeV.
Alice is an ultrasound imaging spectrometer, one of
two photographic tools, including the New Horizons Pluto
Exploration Remote Sensing Investigation (PERSI)
remote sensing; the other being the Ralph telescope.
Solves bands with a wavelength of 1024 in the last and
extreme ultraviolet (from 50-180 nm), over 32 viewing
fields. Its purpose is to determine the composition of

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
312
Pluto's atmosphere. This Alice instrument is derived from
another Alice ship on ESA's Rosetta ship.
The 75-mm diaphragm Ralph telescope is one of the
two photographic tools that make up the New Horizons
Investigation (PERSI) and the other is the Alice tool.
Ralph has two separate channels: MVIC (Multispectral
Visible Imaging Camera), a visible CCD with wideband
and color channels; Spectral Ralph was named after
month Honey Alice designed by Alice.
The new horizons used LORRI to make Jupiter's first
photos on September 4, 2006, from a distance of 291
million kilometers. The more detailed exploration of the
system began in January 2007, with an infrared image of
Callisto, as well as several Jupiter black and white
images. New horizons received gravitational help from
Jupiter, with the closest approach at 05:43:40 UTC on
February 28, 2007, when it was 2.3 million kilometers
from Jupiter. Flight increased to New Horizons at 4 km/s
(14,000 km/h, 9,000 mph), accelerated the probe at a
speed of 23 km/s (83,000 km/h, 51,000 mph).
The flight was at the center of an intensive four-
month observation campaign that took place between
January and June. As a constantly changing scientific
target, Jupiter was intermittently observed at the end of
the Galileo mission in September 2003. The knowledge
of Jupiter benefited from the fact that New Horizons
was built using the latest technology, especially in the
field of cameras, representing a significance to the
improvement of Galileo's chambers, which were
modified versions of the Voyager chambers, which in
turn were modified by the Mariner chambers. Jupiter's
encounter also served as a rehearsal of shakedown and
clothing for the encounter with Pluto. Since Jupiter is
much closer to Earth than Pluto, the communication link
can transmit more memory storage tasks; therefore the
mission returned more data from the Jovian system than
it was expected to transmit from Pluto.
One of Jupiter's main objectives was to observe its
atmospheric conditions and to analyze the structure and
composition of its clouds. Heat losses induced by light in
polar regions and "waves" indicating violent storm
activity were observed and measured. The small red dot,
which covers up to 70% of the Earth's diameter, was
recorded almost for the first time. The various angles and
lighting conditions, New Horizons, have made detailed
images of Jupiter's free world and system, revealing the
remnants of recent clashes or other unexplained
phenomena. Looking for months undiscovered in the
rings did not work. Traveling through Jupiter's
magnetosphere, New Horizons gathers valuable particle
readings. Plasma "Bubble", which is believed to be
composed of the material ejected by moon Io, was
observed in the magnetotail.
Jupiter's four largest months were in weak positions
for observation; the necessary path of assistance for
gravity meant that the New Horizons passed millions of
miles from any of the months of Galilee. However, its
tools were designed for small and small targets, so they
were scientifically useful for the long and distant
months. The emphasis was on the most intimate moon of
Jupiter, Io, whose active volcanoes give the Jupiter
magnetosphere tonal tones and beyond. Of the eleven
eruptions observed, three were seen for the first time.
Tvashtar has reached an altitude of up to 330 km. The
event gave scientists an unprecedented look at the
structure and movement of growing snow and its
subsequent fall to the surface. The infrared signals of 36
other volcanoes were observed. The Callisto surface was
analyzed using LEISA, illustrating how illumination and
visualization conditions affect surface readings. Minor
satellites, such as Amalthea, have improved orbital
solutions. The rooms have determined their positions,
acting as "reverse optical navigation".
After Jupiter passed, New Horizons spent most of
their journey to Pluto in hibernation mode: Redundant
components, as well as guidance and control systems,
were shut down to prolong the life cycle to reduce
operations cost and to release the Deep Space network for
other missions. During hibernation, the onboard computer
monitored the probe systems and sent a signal back to
Earth: A "green" code if everything worked as expected or
a "red" code if mission control assistance was needed. The
probe was activated for approximately two months a year
so that the instruments could be calibrated and the systems
checked. The first hibernation cycle started on 28 June
2007, the second cycle started on 16 December 2008, the
third cycle on 27 August 2009 and the fourth cycle on 29
August 2014, after a 10-week test.
New horizons passed into Saturn's orbit on June 8,
2008 and on Uranus on March 18, 2011. After
astronomers announced a new month in Pluto, Kerberos
and Styx systems, mission planners began to
contemplate the possibility of unexpected old ships and
collisions. An 18-month study on computer simulations,
telescopic observations and occult observations based on
Pluto showed that the possibility of a catastrophic
collision with debris or dust was less than 0.3% during
probe planning. If the danger increases, New Horizons
could have used one of two possible emergency plans,
the so-called Safe Haven by Other Trajectories: The
probe could have continued on the current trajectory
with the input particle antenna, the systems would be
protected or could position the antenna to make a course
correction that would take it just 3,000 miles from Pluto,
where the atmospheric tract is expected to clean the
surrounding surface of any debris.
During hibernation in July 2012, New Horizons
began collecting scientific data with SWAP, PEPSSI and
VBSDC. Although initially only VBSDC was planned,
other tools were propelled by the initiative of principal
investigator Alan Stern, who decided to use the

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
313
opportunity to collect valuable data about the
heliosphere. Prior to the activation of the other two tools,
ground tests were carried out to ensure that extensive
data collection at this phase of the mission would not
limit the amount of energy, memory and fuel available in
the future and that all systems operate during the flight.
The first set of data was submitted in January 2013
during a three week hibernation activation. The data
control and data processing software has been updated to
resolve the issue of restarting your computer.
Other possible targets were Trojans from Neptune.
The trajectory of the probe to Pluto passed Lagrange
Point ("L5"), which can accommodate hundreds of
resonant resemblances of 1: 1. At the end of 2013, New
Horizons were in the 1.2 UA range (180,000,000 km,
110,000,000 mi) L5 Neptune 2011 HM102, identified
shortly before the New Horizons KBO Search research
team while searching for more distant objects for New
Horizons after Pluto's 2015 meeting. This range, HM102
2011, would have been brilliant enough to be detectable
by the New Horizons LORRI tool; however, the New
Horizons team eventually decided that it would not
target HM102 for comments, as preparations for Pluto's
approach had priority.
The LORRI images from July 1 to July 3, 2013 were
the first probes to solve Pluto and Charon as separate
objects. On July 14, 2014, mission controllers launched a
sixth trajectory (TCM) to allow the ship to reach Pluto.
Between 19 and 24 July 2014, LORRI of New Horizons
broke 12 Charon images, circulating around Pluto,
covering a total rotation of 429 to 422 million kilometers
(267,000,000 to 262,000,000). In August 2014,
astronomers carried out high precision measurements of
Pluto's position and orbit around the Sun using the
Atalcama Large Millimeter/Submillimeter Array
(ALMA) arc to help NASA New Horizons navigate
Pluto accurately. On December 6, 2014, mission
controllers sent a signal to the ship to "wake up" from
the final hibernation to Pluto's approach and began
regular operations. The ship's response to "awake"
arrived on Earth on December 7, 2014 at 14:30 UTC.
Pluto's remote operations began on January 4, 2015.
At this point, targets on the LORRI plus Ralph telescope
are just a few pixels. Investigators have begun to take
Pluto's background images to assist mission navigators
in designing engine correction maneuvers that would
accurately change the New Horizons trajectory to target
the approach. On January 15, 2015, NASA presented a
brief update of the approach and departure phases.
On February 12, 2015, NASA released new Pluto
images (January 25 - January 31) from the nearby probe.
The new horizons were more than 203 million
kilometers away from Pluto when they began taking
pictures, which he showed to Pluto and the tallest month,
Charon. The exposure time was too short to observe the
smaller, much weaker, months of Pluto.
Investigators took a series of photos from the Nix and
Hydra months between January 27 and February 8, 2015,
starting at a distance of 201 million kilometers (125
million kilometers). Pluto and Charon appear as a single
overexposed object in the center. The correct image was
processed to remove the background. The smallest two
months, Kerberos and Styx, were seen on photos taken
on April 25th. Starting May 11, a search for dangers was
carried out, searching for unknown objects that could
pose a threat to space ships, such as rings or moons, to
avoid changing the course.
Also, as far as the January 2015 approach is
concerned, the team has announced that it will spend
time trying out long-distance observations of the Kuiper
belt object, temporarily called VNH0004 (now called
KW48 2011). 75 gigameters (0.50 UA). The object
would be too distant to solve surface characteristics or to
take spectroscopy, but it could make observations that
can not be made from Earth, namely a phase curve and a
search for small satellites. A second object was planned
to be respected in June 2015 and the third in September
after the flight; the team hoped to observe a dozen of
such objects by 2018. On April 15, 2015, Pluto was
recorded with a possible polar head.
The new horizons have passed 12,500 km from Pluto,
this approach being the closest on July 14, 2015, at 11:50
UTC. The new horizons had a relative speed of 13.78
km/s (49,600 km/h, 30,800 mph) at the closest approach
and reached Charon at 28,800 km (17,900 mi). Starting
3.2 days before the closest approach, long-range imaging
included the mapping of Pluto and Charon at a resolution
of 40 km (25 mi). This is half the rotation period of the
Pluto-Charon system and allows the image of all sides of
both bodies. Approximately twenty days were repeated
images of proximity to looking for surface changes
caused by the fall of localized snow or surface
cryovolcanism. Because of Pluto's inclination, some of
the northern hemispheres would always be in the shadows.
During the meeting, engineers expected LORRI to get
selected images with a resolution of up to 50 m/pixel if the
nearest distance was 12,500 km and the MVIC would
have a resolution of 1.6 kilometers. LORRI and MVIC
have tried to overlap these areas to form stereo pairs.
LEISA has obtained infrared hyperspectral maps at a
distance of 7 km/px (4.3 mi/px) globally and 0.6 km/px
(0.37 mi/px) for the selected areas.
Meanwhile, Alice characterized the atmosphere, both
by atmospheric emissions and diminishing backgrounds,
while behind Pluton (occult). During and after the
closest approach, SWAP and PEPSSI analyzed the high
atmosphere and its effects on solar wind. VBSDC
searched for dust, lowering meteoroid collision rates and
any invisible rings. REX has made active and passive
radio science. Earth Antenna measured the
disappearance and reappearance of the radiant signal as

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
314
the probe flew behind Pluto. The results solved the Pluto
diameter (by synchronization) and its density and
atmospheric composition (by its slimming and curing
model). (Alice can perform similar occlusions using
sunlight instead of radio beacons.) Previous missions
have transmitted the spacecraft via the Earth
("downlink"). The distribution of masses and masses in
Pluto was assessed by the spacecraft gravity tug. As the
spacecraft accelerates and slows down, the radio signal
has shown a Doppler shift. Doppler modulation was
measured by comparison to the ultrastable oscillator in
communications electronics.
It is also used for sophisticated reconnaissance
missions whose objective is to link the study of several
planets or moons (Voyager probes, Fig. 4). Finally, it
may be the only way to study minor objects - comets and
asteroids - whose relative speed is too great to allow go
into orbit (Stardust mission).
The Voyager program is an American science
program that uses two robotic probes, Voyager 1 and
Voyager 2, to study the outdoor solar system. The probes
were launched in 1977 to take advantage of a favorable
alignment of Jupiter, Saturn, Uranus and Neptune.
Although their initial mission was to study only the
planetary systems of the planets Jupiter and Saturn,
Voyager 2 continued with Uranus and Neptune.
Voyagers are now exploring the outer boundary of the
heliosphere in interstellar space; their mission has been
extended three times and continues to provide useful
scientific data. Neither Uranus nor Neptune was visited
by a bell, but by Voyager 2.
On August 25, 2012, Voyager 1 data indicated that it
became the first human object to enter interstellar space,
traveling "more than anyone or anything else in history."
Starting in 2013, Voyager 1 moved to the Sun at a speed
of 17 kilometers per second (11 mi/s).
On November 5, 2018, data from Voyager 2
indicated that it also entered interstellar space.
Data and photographs made by cameras,
magnetometers and other Voyager tools revealed
unknown details about each of the four giant planets and
their moons. The images of the nearby spacecraft were
complex forms of clouds, winds and storms of Jupiter
and discovered a volcanic activity per month. Saturn's
rings have been discovered to have enigmatic spaces,
scratches and peaks and have been accompanied by
countless "straps." At Uranus, Voyager 2 discovered a
substantial magnetic field around the planet and another
ten months. His field in Neptune discovered three rings
and six months previously unknown, a complex and
widespread magnetic field. Voyager 2 is the only
spacecraft to visit the two ice giants. In August 2018,
NASA confirmed, based on the results of the spacecraft
New Horizons, a "hydrogen wall" at the outer edge of
the solar system, first detected in 1992 by the two
spacecraft Voyager.
Fig. 4: Voyager probes
Low-energy
charged particle Ultraviolet spectrom eter
Imaging narrow angle
and imagin g wide angle
High-gai n antenna
(3.7-meter diameter ) Plasma
Cosmic ray
Magnetometer
boom Photopolarim eter
Infrared
interferomete r
spectrometer
Radioisotope thermoe lectric
generator (3)
Optical calibratio n
target
'Bus' hous ing
electronics
Planetary radio astrono my and
plasma wave antenna (2)

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
315
Voyager Spacecraft was built at South California's Jet
Propulsion Laboratory and funded by Cape Canaveral,
funded by NASA, Florida, following all the other wells.
The initial cost of the program was $ 865 million and
the initial cost of the Voyager Interstellar program cost
an extra $ 30 million.
The two Voyager probes were originally designed as
part of the Mariner program and were originally called
Mariner 11 and Mariner 12. They were then moved to a
separate program called "Mariner Jupiter-Saturn",
renamed the Voyager Program by Design Thinking Two
Ship have progressed much more than the Mariner
family to deserve a separate name.
The Voyager program was similar to that of the
Grand Planet tournament planned in the late 1960s and
early 1970s. The Grand Tour will take advantage of the
alignment of the exterior plans discovered by Gary
Flandro, an aerospace engineer at the Jet Propulsion
Laboratory. This 175-year alignment will take place in
the late 1970s and will make it possible to use
gravitational assistance to explore Jupiter, Saturn,
Uranus, Neptune and Pluto. The planet's big tournament
was to send more pairs of probes to fly on all outer
planets (including Pluto, then considered a planet) on
different trajectories, including Jupiter-Saturn-Pluto and
Jupiter-Uranus-Neptune. Limited funding has completed
the Grand Tour program, but they have been included in
the Voyager program, which has met many of the Grand
Tour's flight objectives, except for a visit to Pluto.
Voyager 2 was the first to release. Its trajectory was
designed to allow Jupiter, Saturn, Uranus and Neptune
flights. The Voyager 1 was launched after the Voyager 2
but on a shorter and faster trajectory designed to provide
the optimal Saturn navigation, Titan, known to be quite
large and possess a dense atmosphere. This meeting sent
Voyager 1 out of the ecliptic plane, ending his planetary
scientific mission. If Voyager 1 could not fly to Titan,
the Voyager 2 trajectory could have been modified to
explore Titan by giving up any visit to Uranus and
Neptune. Voyager 1 was not launched on a trajectory
that would allow them to continue on to Uranus and
Neptune but could have gone from Saturn to Pluton
without exploring Titan.
In the 1990s, Voyager 1 passed the slowest spacecraft
Pioneer 10 and Pioneer 11 to become the farthest human
object on earth, a record that will keep it in the near
future. The New Horizons probe, which had a higher
launch speed than Voyager 1, travels slower with the
Voyager 1 supplement from Jupiter and Saturn. Voyager
1 and Pioneer 10 are the most often separate human
objects from anywhere moving in opposite directions to
the solar system.
In December 2004, Voyager 1 experienced the final
shock, where the solar wind slowed to subsonic speed
and entered the heliosheath where the solar wind is
compressed and turbulent due to interactions with the
interstellar environment. On Dec. 10, 2007, Voyager 2
also reached the termination shock, about 1 billion miles
closer to the Sun than the one in which the first Voyager
1 passed, indicating that the solar system is asymmetric.
In 2010, Voyager 1 reported that the outside speed of
the solar wind has fallen to zero and scientists have
predicted that it is approaching interstellar space. In
2011, Voyager data found that the heliosheath is not
smooth but filled with huge magnetic bubbles, theorized
to form when the Sun's magnetic field becomes
deformed to the edge of the solar system.
On June 15, 2012, NASA scientists reported that
Voyager 1 was very close to entering the interstellar
space, indicated by a sharp increase in high energy
particles outside the solar system. In September 2013,
NASA announced that Voyager 1 crossed the heliopause
on August 25, 2012, becoming the first spacecraft to
enter the interstellar space.
In December 2018, NASA announced that Voyager 2
crossed the heliopause on November 5, 2018, becoming
the second spacecraft to enter interstellar space.
Starting in 2017, Voyager 1 and Voyager 2 continue
to monitor the external conditions of the solar system. It
is assumed that the spacecraft Voyager will be able to
operate scientific instruments by 2020 when a limited
power will require disarmament tools one by one.
Sometime, around 2025, there will be little power to
operate any scientific instrument.
Voyager spacecraft each weigh 773 pounds (1,704
pounds). Of this total weight, each spacecraft transported
105 kilograms (231 kilograms) of scientific instruments.
The same spacecraft uses three-axis stabilized guidance
systems using gyro and accelerometer inputs for their
attitude control computers to straighten terrestrial
antennas and their scientific instruments to their targets,
sometimes with the help of a small mobile platform and
digital systems digital.
The diagram shows the High-heeled Antenna (HGA)
with a 3.7 m (12 ft) diameter vessel attached to the
empty decanter. There is also a spherical reservoir
containing hydrazine propellant monohydrate.
The Gold Voyager record is attached to one of the
sides of the bus. Square-square to the right is the optical
calibration target and the excessive heat radiator. The
three radioisotope thermoelectric generators (RTGs) are
mounted at the end of the lower arm.
The scanning platform Includes Infrared
Interferometer (IRIS) spectrometer (upper chamber);
Ultraviolet (UVS) just above IRIS; the two Vidicon
video cameras (ISS); and the Photopolarimeter System
(PPS) within the ISS.
Only five investigative teams are still accepted,
although data is collected for two additional tools. The
Data Flight Subsystem (FDS) and a single digital device
(DTR) offer data processing functions.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
316
FDS configures each instrument and controls the
operations of the instrument. It also collects engineering
and science data and forms data for transmission. DTR is
used to record a High-Speed Waveguide (PWS)
subsystem. The data are presented every six months.
The Imaging Science Subsystem made up of a wide
angle and a narrow-angle device, is a modified version
of the Vidicon slow scanning models that were used in
previous Mariner flights. The Imaging Science
Subsystem consists of two television cameras, each with
eight filters in a commendable filter wheel mounted in
front of the vidicon. One has a small lens size of 200 mm
wide (7.9 inches) with an f/3 (wide angle) lens, while the
other uses a resolution of more than 1500 mm with
f/narrow-angle camera).
Voyager's primary mission was completed in 1989
with Neptune's close flight by Voyager 2. The Voyager
Interstellar (VIM) mission is a prolongation of the
mission that began when the two ships disappeared for
over 12 years. The Heliophysics Division of the
Heliophysics Division made a top magazine for
heliophysics in 2008. The group found that VIM "is an
absolutely imperative mission to continue" and that VIM
funding is approaching the optimal level and increase in
the number of DSNs. "
The main objective of the VIM is to extend the
exploration of the solar system beyond the outer planets
to the outer boundary and, if possible, even beyond it.
Voyagers continue to search for the limit of the
heliopause, which is the outer limit of the Sun's magnetic
field. Passing through the limit of heliopause will allow
the spacecraft to measure interstellar fields, particles and
waves that are not affected by the solar wind.
The entire Voyager 2 scan platform, including all
platforms, was shut down in 1998. All tools on the
Voyager 1 platform, except the Ultrasound (UVS)
spectrometer, were also closed.
The Voyager 1 scanning platform was scheduled to
take off at the end of 2000 but was left to investigate the
UV emission from the wind. UVS data is still captured,
but scans are no longer possible.
Gyro activities were completed in 2016 for Voyager
2 and 2017 for Voyager 1. Gyro operations are used to
rotate the 360-degree probe six times a year to measure
the magnetic field of the spacecraft, which is then
removed from the science of the magnetometer.
The two spacecraft continue to operate, with some
losses in subsystem redundancy, but retain the ability to
return scientific data from the completion of the Voyager
Mission Mission Interstellar (VIM) mission.
Both ships also have adequate power and propulsion
control to continue to operate until around 2025, after
which there can be no electricity to support the
functioning of scientific instruments; the return of
scientific data and the operations of spacecraft will cease.
At the beginning of VIM, Voyager 1 was 40 AA
from Earth, while Voyager 2 was at 31 AU. VIM has
three phases: Final shock, heliosheath exploration,
interstellar exploration phase. Spacecraft launched
VIM in a medium controlled by the Sun's magnetic
field, the plasma particles being dominated by the
supersonic wind. This is the characteristic of the final
shock phase. At a certain distance from the Sun, the
supersonic solar wind will be prevented by the later
expansion of the interstellar wind. The first feature
encountered by a spacecraft as a result of this
interstellar solar-solar interaction was the final shock
if the solar wind slowed to subsonic speed and there
were large changes in the direction of plasma flux and
magnetic field orientation.
Voyager 1 finished the last shock phase in December
2004 at a distance of 94 AU, while Voyager 2 finished in
August 2007 at a distance of 84 AU. After entering the
heliosheath, the spacecraft is in an area dominated by the
Sun's magnetic field and solar wind particles. After
crossing the heliosheath, the two voyagers will begin the
interstellar exploration phase. The outer limit of
heliosheath is called heliopause, where the spacecraft is
now. This is the region where the influence of the Sun
begins to decrease and the interstellar space can be
detected. Voyager 1 escapes from the solar system at a
rate of 3.6 AU per year, 35 degrees north of the ecliptic
in the general direction of the Hercule peak, while the
Voyager 2 is about 3.3 AU per year at 48 degrees south
of the ecliptic. The Voyager of the ship will eventually
get to the stars. In about 40,000 years, Voyager 1 will
be below 1.6 light (LY) of AC + 79 3888, also known
as the Gliese 445, which is approaching the sun. At
40,000 years, the Voyager 2 will be within 1.7 liters of
Ross 248 (another star approaching the sun) and in
296,000 years will pass into 4.6 liters of Sirius, the
brightest star of the night sky.
An orbiter is a space probe that, having transited to
its goal, orbits around the celestial body to be studied.
This is the second major category of space probes with
those overflights. To be able to go into orbit, the
spacecraft must greatly reduce its speed when it arrives
close to its objective. The propellants used for this
braking operation can represent a significant fraction of
the total weight of the vehicle (typically around 50% for
Mars). The orbiter allows regular observations of almost
the entire surface of the celestial body for several years.
The orbiter is the step that logically follows the sending
of a probe performing a simple overflight. The orbit of
the space probe is chosen according to the objectives
pursued but also to mass constraints. Missions with a
constrained budget like Mars Express will choose a less
efficient but less expensive elliptical orbit propellant
than a low circular orbit retained for the majority of
NASA's Martian orbiters.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
317
An atmospheric probe is a space probe that crosses
the atmosphere of a planet to study it. Its mission is
relatively brief since it usually lasts the time of its
descent (not propelled) to the ground. During this phase,
it only needs a limited amount of energy, so it pulls
batteries. The atmospheric probe is usually transported
to the planet explored by a mother ship. The planet
Venus has been studied in particular by this method
with the series of Soviet probes of the Venera program.
Other notable atmospheric probes are Huygens who
studied the atmosphere of Titan, the atmospheric probe
of Galileo that plunged into the upper layers of the
giant gas planet Jupiter. The very thick atmosphere of
Venus allowed the implementation of the balloons of
the program Vega Soviet which could transmit data for
several tens of hours.
An undercarriage is a type of spacecraft designed to
survive the landing on the ground of a planet or moon
and then collect with its scientific instruments data on
the surface that is transmitted to the Earth directly or
indirectly (via another spacecraft in orbit). The Moon
and the Mars planet have been particularly explored by
spacecraft of this type with for example the probes of the
Surveyor program the two probes of the Viking program
or the Phoenix lander. The soft landing is the main
difficulty faced by designers of this type of gear. The use
of a parachute, implemented for example by Huygens on
Titan, requires the presence of a sufficiently thick
atmosphere and is therefore not suitable for Mars.
Reduced mass and cost compared to other methods, the
parachute does not allow a completely controlled landing.
To land on celestial bodies devoid of atmosphere, it
is necessary to resort to rocket engines which gradually
reduce the speed of the spacecraft. These, however,
require the carriage of a large amount of fuel. For Mars,
NASA has developed special landing techniques: The
airbags first implemented by Mars Pathfinder and a
highly sophisticated one-stage ground-level landing
system, implemented as a "flying crane". 2012 by Mars
Science Laboratory probe.
An astro-mobile or rover after landing on the ground
of a celestial body moves to carry out studies in situ in
different points of scientific interest. It can carry real
small laboratories to analyze collected samples like Mars
Science Laboratory. Its energy can be produced by solar
panels or RTGs. It is remote controlled if the distance is
not too important (Moon).
On the other hand, the distance is too important for
the Martian rovers and they have a certain autonomy for
their displacements which relies on programs of analysis
of the ground. The movements on a day do not exceed a
hundred meters.
A sample return mission is to bring samples of
another celestial body - planet, comet, the asteroid - or
interplanetary or interstellar particles back to Earth for
analysis.
Compared to an on-site study by robot instruments
like the Curiosity Martian rover, returning a soil sample
to Earth allows much more accurate analysis,
manipulation of the sample and to modify the
experimental conditions as the progress of technology
and knowledge progresses.
This type of mission involves major difficulties: It is
necessary, depending on the target, to capture particles
traveling at several km/s, to make an automatic landing
on a body practically devoid of gravity or, on the
contrary, to be able to land and take off again from a
well of serious gravity and in all cases, return to the
Earth's atmosphere at high speed and with great
precision. The return to Earth of Martian soil samples,
which in 2016 is one of the most important objectives for
the study of the solar system, has still not been realized
for both financial and technological reasons.
An indenter is a small spacecraft designed to penetrate
the ground of a celestial body (planet, moon, asteroid or
comet) at high speed undergoing a deceleration of several
hundred grams. The information gathered by onboard
scientific instruments is traditionally transmitted by a
small transmitter to the orbiting parent ship which in turn
transmits it to stations on Earth.
The concept of the indenter makes it possible to avoid
the carrying of parachutes and rockets necessary for a soft
landing and thus to lighten the mass of the undercarriage
considerably. But it must be able to withstand the impact
which in turn creates many constraints on its mass, its
structure and the design of its payload.
Several penetrator projects have not gone beyond the
study phase and, in 2013, only two missions have
implemented penetrators with no results due to the loss of
motherships: Two Deep Space 2 penetrators were onboard
Mars Polar Lander and two others on board March 96.
A telecommunications satellite responsible for
relaying communications between the surface of a
celestial body where there is a lander or a rover and the
Earth. These devices have until now always been orbits
having their own scientific goals such as the 2001 Mars
Odyssey or Mars Reconnaissance Orbiter. Some space
probes fall into several categories such as Viking probes
that have both landing gear and an orbiter.
A technological demonstrator is a spacecraft whose
objective is to validate a new technique. For example,
Deep Space 1 whose main objective was to validate the
use of ion propulsion for interplanetary missions.
To operate a space probe needs to have energy
permanently.
The recently developed machines must have an
electrical power between 300 and 2500 watts to power
onboard computers, radio transceiver, motors,
scientific instruments, radiators and much other
equipment. There are only three possible sources of
energy for an interplanetary spacecraft: Solar panels,

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
318
RTGs only solutions for external planets too far from
the Sun and batteries.
These can be a source of energy charged before
launch or be used as a temporary energy storage
system produced by solar panels to cope for example
periods of an eclipse.
Solar panels consist of a set of photovoltaic cells that
each transform solar energy by photoelectric effect into a
continuous electric current. Each solar cell consists of a
semiconductor material connected with electrical
connections. Several types of materials can be used such
as silicon or GaAs more efficient but more expensive.
The most efficient cells consist of several very thin
layers of semiconductor materials, each capable of
converting a large part of the spectrum of solar energy,
which makes it possible to achieve, in combination with
other devices, a 47% (47% of the Sun's energy is
converted into electrical current). The solar cell yield of
the early 1960s satellites was 6%.
By connecting the solar cells in series (the positive
pole of one cell is connected to the negative pole of
another cell) the voltage of the product current is
increased, while connecting them in parallel (all the
positive poles are connected together and all the negative
poles are connected together) the intensity of the current
is increased. The solar panel serves as physical support
for the solar cells, has the electrical circuits connecting
the cells together and keeps the cells in an acceptable
temperature range. Several solar panels can be connected
together to form a "wing".
Generally, solar panels are articulated and their
orientation can be changed with one or two degrees of
freedom. Generally, by constantly changing the
inclination of the solar panels, it is sought to obtain as
the case the maximum energy if we make sure that the
sun's rays strike perpendicular to the panel. But this
facility can also be used to reduce the angle of incidence
of the solar rays in order to limit the rise in temperature
or to adapt the production of current to a weaker demand
(the electrical energy produced decreases like the cosine
of the angle incidence of solar rays). On a spinned probe,
the solar panels line the body of cylindrical shape and
the half is in the shade while the majority of the cells do
not receive the Sun under an optimum angle.
At the Earth's orbit, the theoretically available
electrical energy is 1,371 W/m2, of which 50% can be
converted into electrical energy with the most advanced
solar cells. Abundant at the level of the inner planets, the
quantity of energy available is inversely proportional to
the square of the distance to the Sun.
Thus a probe like Juno sent into orbit around Jupiter
five times farther from the Sun than Earth receives 25
(5×5) times less solar energy than at Earth. NASA has
nevertheless chosen to equip this probe with solar panels
that thanks to their surface (45 m2 of solar cells) and
their advanced technology manage under these
conditions to provide 428 watts (and 15 kW at the
Earth's orbit). But at this distance from the Sun, the use
of RTG is more frequent.
The performance of solar panels of a space probe
degrades under the action of several phenomena. The
energy received by the solar panel that is not
converted into electrical energy is partly reflected and
partly converted into heat which increases the
temperature of the cells. When its temperature
increases the solar cell produces a current of higher
voltage but the amperage decreases as well as the
power produced (W = V × I). This decrease in overall
performance is 1% per degree Celsius for silicon cells
and 0.5% for cells in GaAs. Moreover, a few hundred
hours after its deployment, the performance of a solar
panel decreases by 1% due to the chemical changes
generated by the light. Finally, the factor that
produces the most damage is the action of energy
particles produced by the solar wind or solar storms
that progressively damage the crystalline structure.
Thus the solar panels of the Magellan probe, placed in
orbit around Venus, lost two-thirds of their capacity
during their operational life.
This progressive degradation is taken into account in
the design of the solar panels at the time of the design of
the space probe.
When the solar energy becomes too weak because of
the distance of the Sun one or more thermoelectric
generator with radioisotope replaces the solar panels for
the production of electricity. This electric generator
produces electricity from the heat released by the
radioactive decay of materials rich in one or more
radioisotopes, usually plutonium 238 in the form of
plutonium dioxide 238PuO2. The heat is converted into
electricity via thermocouples.
The energy efficiency is reduced: Less than 10% of
the heat produced is converted into electricity and the
rest must be evacuated by radiators. To improve this
performance, current research is moving towards thermo
in toroidal converters and Stirling radioisotope
generators, which could multiply the overall efficiency
by four but would impose moving mechanical parts that
can become blocked over time. The thermoelectric
radioisotope generator is particularly well suited to
producing a stable power supply, over a long time
required for the instruments embedded in the
interplanetary probes. Thus, the generator on the New
Horizons probe is able to provide a stable power supply
of 200 W over more than 50 years.
However, the presence of plutonium 238 in a
machine likely to be the victim of a launcher failure,
raises strong fears in part of the public opinion despite
protective devices (shielding) which have proved in
practice effective.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
319
Fig. 5: Cassini
Space probes launched to Jupiter or beyond such as
Voyager 1, Cassini (Fig. 5) or New Horizons use
thermoelectric radioisotope generators for their power
supply.
The Cassini-Huygens mission, commonly referred to
as Cassini, was a collaboration between NASA, the
European Space Agency (ESA) and the Italian Space
Agency (ASI) to send a test to study the planet Saturn
and its satellite system. The oldest robotic spacecraft
includes both NASA's Cassini probe and ESA's Huygens
soil, which landed Titan's biggest month. Cassini was the
fourth space probe to visit Saturn and the first to enter
his orbit. Botites were named by astronomers Giovanni
Cassini and Christiaan Huygens.
Launched on a Titan IVB/Centaur on October 15,
1997, Cassini has been active in space for nearly 20
years, 13 years in orbit on Saturn, studying the planet
and its system after it enters orbit on July 1, 2004 (Trip
to Saturn Venus flights, April 1998 and July 1999, Earth
August 1999, asteroid 2685 Masursky and Jupiter
December 2000). His mission ended on September 15,
2017, when Cassini's trajectory led to Saturn's upper
atmosphere and burned to prevent any risk of Saturn's
contamination, which could have provided living
environments to terrestrial microbes on the space ship.
The mission is widely perceived as successful beyond
expectations. Cassini-Huygens was described by
NASA's planetary scientist as a "rewarding mission" that
revolutionized Saturn's human understanding, including
its moons and rings, as well as our understanding of the
place where life is in the solar system.
Cassini's initial mission was scheduled to last for four
years, from June 2004 to May 2008. The mission was
extended for two more years until September 2010,
marking the Cassini Equinox mission. The mission was
expanded for the second time and last time for the
Cassini Solstice mission, which lasted seven years until
September 15, 2017, when Cassini was willing to burn
into Saturn's upper atmosphere.
The Huygens module traveled with Cassini until its
probe was disconnected on December 25, 2004; was
landed on Titan on January 14, 2005. He returned the
data to Terra for about 90 minutes, using the relay as a
relay. This was the first landing ever made in the outer
solar system and the first landing in a month other than
the Earth's Moon.
At the end of his mission, the Cassini crew executed
the "Great Finale" of his mission: A series of risky passes
through Saturn's gap with Saturn's inner rings. The
purpose of this phase was to maximize Cassini's scientific
results prior to the destruction of the spacecraft. Cassini's
atmospheric inputs ended the mission, but the return of the
data returned will continue for many years.
Teams from 28 countries formed the joint team
responsible for designing, building, flying and collecting
data from Cassini and Huygens.
The mission was managed by the NASA Jet
Propulsion Laboratory in the United States where the orbit
was assembled. Huygens was developed by the European
Center for Space Research and Technology. The main
contractor of the Aérospatiale Center in France (now Thales
Alenia Space) has assembled the probe with equipment and
instruments provided by many European countries
(Huygens batteries and two US scientific instruments). The
Italian Space Agency (ASI) has provided a Cassini orbiter
radio antenna with the incorporation of a low gain antenna
(to provide Earth telecoms during the mission), a compact
and easy radar, using radar antenna synchronization, radar
altimeter, RSS radio subsystem) in the VIMS-V channel of
the VIMS spectrometer.
The VIMS infrared counterpart was provided by
both NASA and the Main Electronic Assembly, which
includes electronic subassemblies provided by CNES
in France.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
320
On April 16, 2008, NASA announced a two-year
extension of ground operations for this mission when it
renamed the Cassini Equinox mission. The funding
round was once again expanded in February 2010 with
the Cassini Solstice Mission.
Cassini had several goals, including:
• Determination of the three-dimensional structure
and dynamic behavior of the Saturn rings
• Determining the composition of the satellite surfaces
and the geological history of each object
• Determining the nature and origin of dark matter in
the Iapetus hemisphere
• Measurement of the three-dimensional structure and
dynamic behavior of the magnetosphere
• Studying the dynamic behavior of Saturn's
atmosphere at cloud level
• Studying the time variability in the clouds and
dangers of Titan
• Characterization of the Titan surface on a regional
scale
Cassini-Huygens was launched on October 15, 1997,
from the Cape Canaveral Space Force spacecraft, using
the US Air Force Titan IVB/Centaur aerial force. The
complete launch consisted of a Titan IV two-speed
rocket, two solid rocket engines on the belt, the Centaur
support gear and a useful shield or a useful shield.
The total cost of this exploration mission was about $
3.26 billion, including $ 1.4 billion for development
before launch, $ 704 million for mission operations, $ 54
million for tracking and $ 422 million for vehicles that
start. The United States has contributed $ 2.6 billion
(80%), $ 500 million (15%) and $ 160 million (5%).
However, these figures come from the press kit drafted
in October 2000. They do not include inflation during a
very long mission and do not include the cost of
extensive missions.
Cassini's primary mission was completed on July 30,
2008. The mission was extended until June 2010
(Cassini Equinox Mission). This has studied the Saturn
system in detail during the planet's equinox, which
happened in August 2009.
On February 3, 2010, NASA announced a new
extension for Cassini, which lasted six and a half until
2017, ending Cassini solo solo solo Cassini in summer.
The extension allowed another 155 revolutions around
the planet, 54 Titan flights and 11 flights from
Enceladus. In 2017, a meeting with Titan changed the
orbit so close to Saturn that it was just 3,000 miles above
the planet's clouds below the inner edge of the ring D.
This sequence of "proximal orbits" ended when the last
encounter with Titan Saturn sent the atmosphere to the
probe to be destroyed.
The origins of Cassini-Huygens date back to 1982,
when the European Foundation for Science and the
American Academy of Sciences formed a working group
to investigate future co-operation missions. Two
European scientists have suggested that a pair of Saturn
Orbiter and Titan Probe could be a possible joint
mission. In 1983, the NASA Solar System Exploration
Committee recommended the same pair of Orbiter and
Probe probes as a basic NASA project. NASA and the
European Space Agency (ESA) conducted a joint study
of the potential mission from 1984 to 1985. ESA
continued its own study in 1986, while American
astronomer Sally Ride, in his influential report of 1987,
led the future NASA US Cassini mission.
While Ride's report described Saturn's orbit and
probe as a NASA solo mission, the Len Fisk associate
space administrator reverted to the idea of a joint NASA
and ESA mission in 1988. He wrote to ESA counterpart
Roger Bonnet, strongly suggesting that ESA chose
Cassini's mission from the three candidates at hand and
promises that NASA will engage in a mission as soon as
ESA has done so.
At that time, NASA became more sensitive to the
strain that emerged between US and European space
programs as a result of European perceptions that NASA
did not treat it as equality during previous collaborations.
The NASA authorities and advisers involved in the
promotion and planning of Cassini-Huygens attempted
to correct this trend, highlighting the desire to equally
share the scientific and technological benefits of the
mission. In part, this new spirit of co-operation with
Europe was driven by a sense of competition with the
Soviet Union, which began to cooperate more closely
with Europe, while ESA withdrew from NASA. In
1988, ESA chose Cassini-Huygens as the next major
mission and in the following year, the program received
major funding in the US.
Collaboration not only improved the relationship
between the two space programs but also helped Cassini-
Huygens survive the US Congress budget cuts. Cassini-
Huygens fired in 1992 and 1994, but NASA convinced the
US Congress that it would not be wise to stop the project
after ESA had already poured funds into development
because frustration with space exploration promised that
breaks could become relationship areas external. The
project has continued to be politically problematic since
1994, although groups of citizens concerned about the
potential environmental impact have tried to derail it
through protests and trials until its launch in 1997.
The ship was planned to be the 2nd Marine II,
stabilized with three axes, equipped with RTG, a class
of spacecraft developed for missions beyond the orbit
of Mars. Cassini was developed simultaneously with
Comet Rendezvous Asteroid Flyby (CRAF), but budget
cuts and reorganization projects forced NASA to stop

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
321
CRAF development to save Cassini. As a result,
Cassini became more specialized. The Mariner Mark II
series has been canceled.
The Orbiter and the combined probe are the third of
the largest unmanned spacecraft, interplanetary,
successfully launched behind Phobos 1 and 2 Mars,
among the most complex. The Orbiter had a 2150 kg
(4740 lb) mass, a 350 kg (770 lb) probe. With a launch
engine of 3132 kg (6905 lb) and propulsion engines at
launch, the ship had a mass of 5,600 kg (12,300 lb).
The Cassini ship's way was 6.8 meters (22 ft) high
and 4 meters (13 ft) wide. The complexity of space has
been increased by its trajectory (the flight path) to Saturn
and the ambitious science at the destination. Cassini had
1,630 interconnected electronic components, 22,000 wire
connections and 14 kilometers of cables. The CPU of the
central control computer was a redundant MIL-STD-
1750A system. The main propulsion system consisted of
an R-4D with a primary bipolar and reserve missile.
Engine power was 490 newtons and the delta-v was
about 2040 meters per second. Smaller rockets with
propulsion have provided control of attitude.
Cassini was fed with 32.7 kg of plutonium-238 - the
heat of radioactive degradation of the material was
transformed into electricity. Huygens was supported by
Cassini during a cruise but used chemical batteries when
he was independent.
The probe contained a DVD of more than 616,400
signatures from citizens in 81 countries, collected in a
public campaign.
Until September 2017, the Cassini probe continued
on orbit Saturn at a distance of 8.2 and 10.2 astronomical
units on Earth. It took 68 to 84 minutes for radio signals
to travel from Earth to spacecraft and vice versa. So,
ground controllers could not provide "real-time"
instructions for day-to-day operations or unexpected
events. Even if the answer was correct, it should have
been more than two hours before a problem occurred and
the satellite engineers received the answer.
Cassini's measuring instruments consisted of: A
diaphragm synthetic radar mapping, an imaging system
with charge devices, a visible/infrared recording
spectrometer, a composite infrared spectrometer, a cosmic
dust analyzer, a radio experiment and a spectrometer with
plasma, plasma spectrometer, ultraviolet imaging
spectrograph, magnetosphere imaging instrument, a
magnetometer and an ion/neutral mass spectrometer.
Telemetry from the communications antenna and from
other special transmitters (an S-band transmitter and a
dual frequency band system) has also been used to
observe Titan's and Saturn's atmospheres and to measure
the gravitational fields of the planet and its satellites.
CAPS was an in-situ instrument that measures the flow
of charged particles at the spacecraft's location, depending
on direction and energy. The ionic composition was also
measured using a time-to-flight mass spectrometer. CAPS
measured the particles produced by ionizing the molecules
in the Saturn and Titan ionospheres, as well as the
Enceladus chickens. CAPS has also investigated plasma
in these areas, along with solar wind and interaction with
Saturn's magnetosphere. CAPS was closed in June 2011
as a precaution because of a "soft" shortcut that appeared
in the tool. He has fired again in March 2012, but after
78 days another deficit forced the instrument to be
permanently closed.
The CDA was an in-situ instrument that measured the
size, velocity and direction of small particles of dust near
Saturn. It could also measure the chemical elements of
the berries. Some of these particles have blinded Saturn,
while others have come from other star systems. CDA in
orbit was designed to learn more about these particles,
materials from other heavenly bodies and possibly the
origins of the universe.
CIRS was a remote detection tool that measures
infrared radiation in objects to learn about temperatures,
thermal properties and compositions. Throughout the
Cassini-Huygens mission, CIRS measured infrared
emissions from the atmosphere, rings and surfaces of
the vast Saturn system. He mapped the atmosphere of
Saturn in three dimensions to determine the
temperature and pressure profiles with altitude, gas
composition and aerosol and clouds distribution. He also
measured the thermal characteristics and composition of
satellite surfaces and rings.
INMS was an in situ instruments that measured the
composition of charged particles (protons and heavier
ions) and neutral particles (atoms and molecules) near
Titan and Saturn to learn more about their atmosphere.
The instrument used a quadrupole mass spectrometer.
INMS has also been designed to measure the positive
and neutral ionic environments of satellites and rings
frozen by Saturn.
ISS was a remote detection tool that captured most of
the images in visible light, as well as some infrared
images and ultraviolet images. SIS took hundreds of
thousands of images of Saturn, its rings and satellites.
The ISS system has both a Wide-Angle Camera (WAC)
and a Narrow-Angle Camera (NAC). Each of these
cameras used an electromagnetic wave (CCD) sensor.
Each CCD had a pixel matrix of 1024, 12 µm on one side.
Both cameras allow many data collection modes including
chip compression and have been equipped with spectral
filters that rotate on a wheel to see different bands in the
electromagnetic spectrum from 0.2 to 1.1 µm.
MAG was an in situ instruments that measured the
strength and direction of the magnetic field around
Saturn. The magnetic fields are partly generated by the
melted core in the center of Saturn. Measurement of the
magnetic field is one of the ways of exploring the
nucleus. MAG aimed to develop a three-dimensional
model of Saturn's magnetosphere and to determine

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
322
Titan's magnetic state and atmosphere as well as frozen
satellites and their role in Saturn's magnetosphere.
MIMI was both an in-situ and remote detection tool
that produces images and other data about particles
trapped in the giant magnetic field or Saturn's
magnetosphere. The in-situ component measured energy
ions and electrons, while the remote detection component
(ionic and neutral camera, INCA) was a neutral energy
imager. This information was used to study the general
configuration and dynamics of the magnetosphere and its
interactions with the solar wind, the atmosphere of Saturn,
Titan, rings and frozen satellites.
The onboard radar was an active and passive
detection tool that produced maps of Titan's surface. The
radar waves were strong enough to penetrate into the
thick veil of fog surrounding Titan. By measuring the
time of sending and returning signals, it is possible to
determine the height of large surface features such as
mountains and canyon. The passive radar listened to the
radio waves that Saturn or its moons can emit.
RPWS was an on-site tool and a remote detection
tool that receives and measures radio signals from
Saturn, including radio waves given by solar wind
interaction with Saturn and Titan. The RPWS measured
the fields of electric and magnetic waves in the
interplanetary environment and planetary magnetospheres.
It also determined the density and temperature of electrons
near Titan and some regions of the Saturn magnetosphere
using either waveforms in plasma at characteristic
frequencies (e.g., the upper hybrid line) or a Langmuir
probe. The RPWS studied Saturn's magnetic field
configuration and its relationship with Saturn's Kilometer
Radiation (SKR), as well as monitoring and mapping
Saturn's ionosphere, plasma and lightning in Saturn's
atmosphere (and possibly Titan).
The RSS was a remote detection tool that used radio
antennas on Earth to see how the spacecraft's radio
signals changed while they were sent through objects
such as Titan's atmosphere or Saturn rings or even in the
Sun's back. The RSS study also studied atmospheric and
ionospheric compositions, pressures and temperatures,
radial structure and particle size distribution in rings,
mass and body systems and gravitational field. The
instrument used the X-band communication link as well
as the uplink and downlink of the S-band and tape.
UVIS was a remote detection tool that captured
images of ultraviolet light reflected by an object such as
Saturn's clouds and/or its rings to learn more about their
structure and composition. Designed to measure
ultraviolet light at wavelengths between 55.8 and 190
nm, this instrument was also a tool to determine the
composition, distribution, aerosol particle content and
atmospheric temperatures. Unlike other types of a
spectrometer, this sensitive instrument can take both
spectral and spatial readings. He was particularly adept
at determining the composition of the gases. Spatial
observations have had a broad and narrow vision, with a
single large pixel and 64 pixels. The spectral size was
1,024 pixels per pixel space. It could also take many
pictures to create movies about how this material is
moved by other forces.
VIMS was a remote detection tool that captured
images using visible and infrared light to learn more
about Saturn's composition and the surface of Titan's
moon, ring and atmosphere. It consisted of two chambers
- one used to measure visible light, the other in infrared.
VIMS measured radiation reflected and emitted by
atmospheres, rings and wavelengths from 350 to 5100
nm to determine their compositions, temperatures and
structures. He also noticed the light of the sun and the
light of the stars passing through the rings to learn more
about their structure. Scientists have used VIMS for
long-term studies on cloud movement and morphology
in the Saturn system to determine Saturn's
meteorological patterns.
Due to the distance between the Saturn sun, solar
networks were not feasible as energy sources for this
space probe. To generate enough power, such arteries
would have been too big and too heavy. Instead, the
Cassini orbit was fed by three Radio-isotopic
thermoelectric Generators (RTGs) with natural calorific
heat of approximately 33 kg of plutonium-238 (as
plutonium dioxide) to generate direct electrical energy
through thermoelectric power. Cassini X-ray has the
same design as those used in the New Horizons, Galileo
and Ulysses probes and designed to last a long life. At
the end of the 11-year nominal allocation, Cassini
managed to produce electricity from 600 to 700 watts.
One of the Cassini reserve backup radiographs was used
to force the New Horizons mission to Pluto and the
Kuiper belt, designed and launched later.
To get a boost while flying, the Cassini mission
trajectory includes several dust-engraved maneuvers:
Two passes of Venus, another part of the Earth, then one
of the planet Jupiter. The ground fly was the last case the
probe puts any danger imaginable for human beings. The
maneuver was successful and Cassini passed 1771 km
above Earth on August 18, 1999. If there had been a
failure that would cause the probe to collide with the
Earth, the full NASA environmental impact study
estimated that the worst case with a significant amount
of 23kg of plutonium gauze dispersed in the Earth's
atmosphere, so up to five billion people in the country),
5,000 cancer deaths in the coming decades, 0.0005%,
representing a fraction of 0, 000005 billion deaths in
cancer; however, the chance of this happening was
estimated at less than one million.
The Cassini space route was able to transmit in
several different telemetry formats. The telemetry
subsystem is probably the most important subsystem
because without it there could be no data returns.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
323
Telemetry has been developed from the bottom
because of the use of a more modern set of computers
than previous missions. Cassini was, therefore, the first
spacecraft to adopt mini-packages to reduce the
complexity of the Telemetry Dictionary and the software
development process led to the creation of a Telemetry
Manager for the mission.
Approximately 1088 channels (in 67 mini-packages)
were assembled in the Cassini Telemetry dictionary. Of
the 67 mini-packages of reduced complexity, six mini-
packages containing the elements of the covariance
subsystem and the Kalman gain (161 s) that were not
used in normal mission missions. In 61 mini-packages,
947 measurements remain.
A total of seven telemetry maps corresponding to 7
AACS telemetry modes were built. These modes are: (1)
Recording; (2) Cruise Nominal; (3) Cruise Medium
Slow; (4) Slow Cruise; (5) Orbital Ops; (6) Av; (7) ATE
Calibration (Attitude Estimator). These 7 maps cover all
spacecraft telemetry modes.
The Huygens survey commissioned by the European
Space Agency (ESA) and named after the 18th-century
Dutch astronomer who first discovered that Titan
Christiaan Huygens investigated the clouds, atmosphere
and the surface of Titan Saturn on January 15, 2005, to
interrupt and to stop the atmosphere Titan leaves a robot
lab robot on the surface.
The probe system consisted of the probe itself that
descended to Titan and the Probe Support (PSE), which
remained attached to the orbital spacecraft. PSE
includes probe electronics, recovers data collected
during descent and processes and transmits data to
Terra Blind. The base computer's CPU was a redundant
MIL-STD-1750A control system.
The data was transmitted via a Huygens-Cassini radio
link provided by the Relay Data Relay (PDR) subsystem.
Since the probe's mission could not be commanded by
Earth's telecommunication due to its long distance, it
was automatically managed by the Data Command
Management (CDMS) subsystem. PDRS and CDMS
were provided by the Italian Space Agency (ASI).
After Cassini's launch, it was found that the data
transmitted from the polls to the European Space
Agency mission control center was largely difficult to
read. It was found that Cassini's receiver failed to
accurately process the frequency and wavelength
changes of the signal he would have received from
Huygens during his descent to Titan. The problem was
corrected by changing the distance and the Cassini
route to Huygens during the landing.
The Cassini field has made two roofs of gravity
assistance from Venus on April 26, 1998 and June 24,
1999. The space ship provided sites with sufficient
impulse to reach the asteroid belt. At that moment, the
gravity of the Sun drew the space probe back into the
inner solar system.
On August 18, 1999, at 03:28 UTC, the craft made a
gravitational accompaniment of the Earth. With an hour
and 20 minutes before approaching, Cassini approached
the tone of the month at 377,000 kilometers and made a
series of calibration photos.
On January 23, 2000, Cassini performed a flyby of
the asteroid Mastersky 2685 at 10:00 UTC. He took
pictures five to seven hours before the flight at a distance
of 1.6 million kilometers and for the asteroid was
estimated diameter of 15-20 km.
Cassini made Jupiter's closest approach on December
30, 2000 and made numerous scientific measurements.
Approximately 26,000 images of Jupiter, its thin rings
and the moon were taken over the six months. It
produced the most comprehensive global color portrait
in the world (see image on the right), where the smallest
visible features are about 60 km (37 mi) above.
Cassini photographed Io crossing Jupiter on January
1, 2001.
An important discovery of the plane announced on
March 6, 2003, was Jupiter's atmospheric movement.
Tents alternate dark areas of "light" in the atmosphere
and scientists have long considered palm clouds in the
surrounding air, partly because of the many clouds on
Earth where the air is growing.
Other atmospheric observations included a dark, dark,
high-fog oval, the magnitude of the Big Spot near the
northern field of Jupiter. Infrared images have revealed
aspects of motion near wind racks around the world, with
adjacent bands moving in opposite directions.
The same announcement also discussed the nature of
Jupiter's rings. The lack of light in the particles of rings
has shown that the particles have an irregular shape
(rather than spherical) and probably originate from the
micrometeorite impact on the moons of Jupiter, perhaps
Metis and Adrastea.
On October 10, 2003, the mission scientist announced
the results of Albert Einstein's theory of general relativity,
made using the radio waves transmitted by the Cassini
space probe. Radio scientists measured a radio frequency
shift to and from the space ship as it passes through the
Sun. According to the general theory of relativity, a
massive object, such as the Sun, produces space-time to
curve, causing a beam of radio waves (or light or any form
of electromagnetic radiation) passing through the Sun to
shift to Shapiro's delay.
Although some deviations measured against the
values calculated using the general theory of relativity
are predicted by some unusual cosmological models, no
deviations have been found in this experiment. Previous
tests using the radio waves transmitted by Viking and
Voyager probes were consistent with the values
calculated from general relativity to a thousand accuracy.
Several refined measurements from the Cassini probe
have improved this accuracy to around 51,000. The data
firmly support the general theory of Einstein's relativity.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
324
In total, the Cassini mission discovered seven new
moons in Saturn's orbit. Using Cassini imagery,
researchers discovered Methone, Pallene and Polydeuces
in 2004, though later analysis showed that Voyager 2
photographed Pallene in 1981 when he flew the ringtone.
On May 1, 2005, Cassini discovered a new moon in
Keeler Bay. It was called S/2005 S 1 before being named
Daphnis. The fifth month was discovered by Cassini on
May 30, 2007 and was provisionally named S/2007 S 4.
It is now known as Anthe. A press release dated
February 3, 2009, showed a new Cassini new month.
The moon represents about 1/3 of the diameter of the
annular ring G of Saturn's annular system and is now
called Aegaeon (formerly S/2008 S 1). A press release
dated November 2, 2009, mentions the seventh new
month found by Cassini on July 26, 2009. It is currently
labeled S/2009 S 1 and is about 300 m (1000 ft) in
diameter in the B-ring system.
On April 14, 2014, NASA scientists reported the
possibility of starting a new month in Saturn A.
On June 11, 2004, Cassini flew a month, Phoebe.
This was the first opportunity for in-depth studies this
month (Voyager 2 made a distant journey in 1981 but
did not return detailed images). It was also possible for
Cassini, for Phoebe, due to the orbital mechanics
available around Saturn.
The first photos were received on June 12, 2004 and
mission scientists immediately realized that the Phoebe
surface was different from the asteroids visited by
spacecraft. Parts of the very crafted surface look very
bright in these images and it is believed that there is a
large amount of water under its immediate surface.
In an announcement of June 28, 2004, Cassini
scientists described the measurement of Saturn's rotation
period. Since there are no fixed surface characteristics
that can be used to achieve this period, the repetition of
radio emissions has been used. These new data have
agreed to the latest measured values on Earth and have
been a puzzle for scientists. It seems that the rotation
period of the radio has changed since it was first
measured in 1980 by Voyager 1 and it was now 6
minutes longer. This, however, does not indicate a
change in the global rotation of the planet. It is believed
to be due to variations in the upper atmosphere and the
ionosphere at latitudes that are magnetically connected to
the radio source region.
On July 1, 2004, the spacecraft flew through the gap
between the F and G rings and obtained orbit after a
seven-year journey. It was Saturn's first spacecraft ever.
Cassini's Orbital Insertion (SOI) was complex,
requiring the ship to route the High-Gain antenna away
from Earth and along its flight path to protect the
particles of Saturn's ring. Once the boat crossed the ring
plane, it had to rotate again to straighten the engine along
the flight path and then the engine began to detect the
load with 622 meters/s to allow Saturn to capture it.
Cassini was captured by Saturn's gravity at 8:54 am
Pacific on June 30, 2004. During the maneuver, Cassini
crossed over 20,000 km of Saturn clouds.
When Cassini was in Saturn's orbit, the appreciation
of the Saturn system was assessed in 2008 at the end of
mission planning.
Cassini had the first flights of Titan on July 2, 2004,
the day after the orbital insertion, when he approached
Titan in the 339,000 kilometers. Images made by special
filters (able to see through the fog of the moon) showed
southern polar clouds considered methane and surface
characteristics with a very different glow. On October
27, 2004, the spacecraft executed Titan's first planned
flight, over 1,200 miles above the moon. Almost four-
gigabit data were collected and transmitted to Earth,
including the first radar images of the misty surface. He
showed that the surface of the Titanium (at least the area
covered by radar) is relatively level, the topography
reaching a maximum of 50 meters in altitude. Coverage
provided a remarkable increase in image resolution over
previous coverage. Up to 100 times more resolutions
were made and are typical of Titan flight plan
resolutions. Cassini gathered the images of Titan and the
methane lakes were similar to the lakes on Earth.
Cassini launched the Huygens probe on December
25, 2004, by means of arched and spiral tracks designed
to rotate the probe for greater stability. He entered
Titan's atmosphere on January 14, 2005 and after a two-
and-a-half-hour descent, he landed on solid ground.
Although Cassini managed to successfully pass the 350
images he received from Huygens on his landing and
landing site, a software error failed to activate one of the
Cassini receivers and caused the loss of another 350
images. During the landing, for caution, NASA loaded
Huygens with 3 parachutes.
In the first two intersections of Enceladus in 2005,
Cassini discovered a deviation of the local magnetic field
that is characteristic of the existence of a thin but
significant atmosphere. Other measurements obtained at
that time in ionized water vapor as the main constituent.
Cassini also noticed the ice geysers that broke out of the
southern pole of Enceladus, which gives more credibility
to the idea that Enceladus supplies the particles in the
Saturn E ring. Scientists in the mission have begun to
suspect that water pockets may appear liquids close to
the surface of the month that feeds rash.
On March 12, 2008, Cassini moved to Enceladus, 50
km from the surface of the moon. Spatial vessels
crossing the pits that extend from the southern geysers
detect water, carbon dioxide and various hydrocarbons
with the mass spectrometer, while surface characteristics
are characterized by temperature much higher than the
infrared spectrometer environment. Cassini failed to
collect data with his cosmic dust analyzer due to an
unknown software error.
On November 21, 2009, Cassini made the eighth trip
from Enceladus, this time with a different geometry

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
325
approaching 1,600 kilometers of surface. The Composite
Infrared Spectrum (CIRS) produced the Bagdad Sulcus
thermal emission map. The data obtained contributed to
the creation of a detailed and high-resolution image of
the Southern Moon, Saturn.
On April 3, 2014, nearly ten years after Cassini enters
Saturn's orbit, NASA has proven to be a large and rich
sea of liquid water in Enceladus. The presence of a salty
inner ocean, in contact with the rocky core of the moon,
places Enceladus "among the most probable places in the
solar system to host a foreign microbial life." On June
30, 2014, NASA celebrated the 10-year exploration of
Cassini, Saturn and its moons, highlighting the discovery
of Enceladus's water activity among other discoveries.
In September 2015, NASA announced that Cassini
gravity and imaging data were used to analyze the
Enceladus perennial orbital plants and determined that
the surface of the moon was not rigidly associated
with its nucleus, concluding that the underground
ocean must, therefore.
On October 28, 2015, Cassini approached Enceladus,
coming in 49 km (30 mi) of surface and crossing the ice
over the southern pole.
In May 2005, Cassini began a series of radio-occult
experiments to measure the particle size distribution in
Saturn's rings and measure Saturn's atmosphere. For four
months, the boat was designed for this purpose. During
these experiments, he flew the plane of Saturn's ring, as
seen on Earth and transmitted radio waves through
particles. Radio signals received on Terra were analyzed
to change the frequency, phases and signal strength to
determine the structure of the rings.
In the images captured on September 5, 2005, Cassini
detected the Saturn rings (Fig. 6), previously observed
only by Stephen James O'Meara's visual observer in
1977 and subsequently confirmed by Voyager spacecraft
in the early 1980s.
The radar images obtained on July 21, 2006, seem to
show liquid hydrocarbon lakes (such as methane and
ethane) in the northern latitudes of Titan. This is the first
discovery of existing lakes anywhere on earth. Lakes
vary from one to one hundred kilometers.
On March 13, 2007, the Jet Propulsion Laboratory
announced that it found solid evidence of methane and
ethane in Titan's northern hemisphere. At least one of these
is larger than any of the Great Lakes in North America.
In November 2006, scientists discovered a storm at
the southern pole of Saturn, with a distinct eyewall. This
is characteristic of a hurricane on Earth and has never
been seen on another planet. Unlike a terrestrial
hurricane, the storm seems to be stationary at the pole.
The storm has a height of 8,000 kilometers and a height
of 70 kilometers (43 miles), with the wind blowing at
560 kilometers per hour (350 mph).
On September 10, 2007, Cassini wrapped the walnut-
shaped Iapetus roof in two tones. The images were taken
from 1,600 km above the surface. When he sent the
images to Earth, he was hit by a cosmic ray that
temporarily forced it. All flight data was recovered.
On April 15, 2008, Cassini received funding for an
extended mission of 27 months. It consisted of 60 orbits
of Saturn, with 21 planes near Titan, seven of Enceladus,
six of Mimas, eight of Tethys and a destination in Dione,
Rhea and Helene. The expanded mission began on July
1, 2008 and was renamed the Cassini Equinox mission,
while the mission coincided with Saturn's equinox.
A proposal was submitted to NASA for a second
extension of the mission (September 2010 - May 2017),
provisionally referred to as the extended mission or
XXM. This ($ 60 million a year) was approved in
February 2010 and was renamed the Cassini Solstice
Mission. He included Cassini in Saturn's orbit several
times, making 54 additional flights of Titan and 11
Enceladus.
On October 25, 2012, Cassini witnessed the massive
storm from White, which is about 30 years old on
Saturn. Data from the Infrared Spectrometer Composite
Instrument (CIRS) indicated a strong storm discharge
that caused a rise in the temperature of the Saturn 83K
(83 ° C, 149 ° F) stratosphere compared to normal. At
the same time, a huge increase in ethylene gas has been
detected by NASA researchers at Goddard Research
Center in Greenbelt, Maryland. Ethylene is a colorless
gas that is extremely unusual on Saturn and is produced
both naturally and by anthropogenic sources on Earth.
The storm that caused this unloading was first observed
by the spacecraft on December 5, 2010, in the northern
hemisphere of Saturn. The storm is the first of its kind
observed by a spacecraft in orbit around Saturn, as well
as the first observed in infrared wavelengths, allowing
scientists to observe the atmosphere of Saturn and
observe the phenomena that are invisible to the naked
eye. Condensation of ethylene gas produced by the storm
has reached levels 100 times higher than those thought
possible for Saturn. Scientists have also determined that
the storm was the largest and most powerful
stratospheric vortex ever detected in the solar system,
initially being larger than Jupiter's Greate Red Spot.
On December 21, 2012, Cassini noticed a transit of
Venus over the Sun. The VIMS instrument analyzed
the sunlight passing through the Venusian
atmosphere. VIMS previously noticed the transit of
the exoplanet HD 189733 b.
On July 19, 2013, the probe was directed to Earth to
capture an image of the Earth and the Moon, as part of
the natural light, of the multiple images of the entire
Saturn system. The event was unique because it was the
first time that NASA informed the public that a long
distance photo was made in advance. The imaging team
said he wanted people to smile and join the sky and
Cassini researcher Carolyn Porco described time as a
chance to "celebrate blue life."

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
326
Fig. 6: The Saturn rings
Cassini last launched Hyperion on 31 May 2015, at a
distance of about 34,000 km (21,000 mi).
Between 2012 and 2016, the persistent hexagonal
cloud pattern at Saturn's northern pole changed from a
blue color, especially in a golden color. A theory for this is
a seasonal change: Exposure to sunlight can create opacity
when the pole returns to the sun. It was previously noted
that during 2004-2008 it was less white on Saturn.
Cassini's end involved a series of steps close to
Saturn, approaching the rings, then entering Saturn's
atmosphere on September 15, 2017, to destroy the space
ship. This method has been chosen because it is
imperative to ensure protection and to prevent biological
contamination in any of the moons of Saturn considered
to provide potential habitats.
In 2008, a number of options were assessed to
achieve this objective, each with different funding,
scientific and technical challenges. A brief impact on
Saturn's impact at the end of the mission was rated
"excellent" because "the D-Ring option meets AO
targets that are unrealized, cheap and easy to access,"
while a frozen collision of the month was "time".
On November 29, 2016, the ship made a Titan flight
that led to the orbital portion of the F ring: This was the
beginning of the Grand Finale phase, culminating in its
impact on the planet. An ultimate Titan flyby on April
22, 2017, changed orbit again to fly through the gap
between Saturn and his inner rings later on April 26.
Cassini passed over 3100 km (1900 mi) above the Saturn
cloud and 320 km) the inner ring; successfully captured
the images of Saturn's atmosphere and began to return
the data the next day. After another 22 orbits, the
mission ended with a dive in Saturn's atmosphere on
September 15; the signal was lost at 7:55:46 AM EDT
on September 15, 2017, just 30 seconds later than
expected. It is estimated that the spacecraft burnt about
45 seconds after the last transmission.
In September 2018, NASA won an Emmy Award for
an original interactive program for the Grand Final
presentation of the Cassini Saturn mission.
In January 2019, new research was published using
data collected during Cassini's Grand Finale phase:
Stopping the last round allows scientists to measure
the duration of a day on Saturn: 10 h, 33 min and 38 sec.
Saturn's rings are relatively new, 10 to 100 million
years old. Perhaps they were formed in the era of
dinosaurs on Earth.
However, thanks to the increasing yields of solar
cells, the last two spacecraft developed for the
exploration of Jupiter - Juno and JUICE use solar panels
which are however very large (60 m2 for Juno). These
generators were also used on two machines launched to
the surface of Mars - Viking 1 and 2 and the Curiosity
rover because they make it possible to get away from the
day/night cycle and are insensitive to the deposits of
dust. The generators provide modest power: 100 W (45
kg) for Curiosity, 300 W (~ 56 kg) for US space probes
in service at the beginning of the 21st century. To meet
their electrical needs some probes ship up to three
generators (Cassini, Voyager).
The space probe to fulfill its mission needs a
propulsion system. This one can fulfill several roles
which depend on the objectives of the mission and
certain choices of the architecture of the space probe:
• Placed in orbit around the planet to be studied
(orbiter)
• Course corrections
• Desaturation of the reaction wheels if the space
probe uses this system to control its orientation
• Orientation control in the absence of reaction wheels
• Control of the velocity vector when the main
propulsion is used
These different types of use require thrusters with
very different characteristics (thrust, number of firings,
duration). Also, the spacecraft usually has several types
of thrusters to deal with these needs. In a relatively
conventional way, a space probe comprises the main
rocket engine with a thrust of several hundred Newtons
for launching, clusters of small thrusters whose thrust
ranges from a few tenths to a few N. for orientation
control and thrusters of a few dozen Newtons for
trajectory or orbit corrections.
These are generally mono-ergol liquid propellant
engines burning hydrazine or pergolas (usually
hydrazine + hydrogen peroxide) which have the
advantage of being storable for long periods of time and
of being hypergolic (to burn spontaneously without
firing device). These propellants are generally
pressurized by helium itself stored in tanks under high
pressure. Smaller cold gas thrusters (used to avoid
pollution of instruments or collected samples, ionic
engines (Deep Space 1 demonstrator, Dawn) are also

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
327
more rarely found which require a suitable mission
architecture and solid propellant engines (for insertion
into orbit) used at the beginning of the space age (lunar
landers of the Surveyor program).
The telecommunication system of a space probe is
responsible for the exchange of data between it and the
stations on Earth. These include in the sense spacecraft-
Earth periodically provided telemetry data that can
monitor the status of the spacecraft and the data collected
by the scientific instruments that materialize the results
of the mission. In the direction, Earth-spacecraft passes
the instructions given to the probe as well as any
software updates. The characteristics of the
telecommunication system depend on the distance
between the space probe and the Earth, the amount of
energy available, the mass of the probe. The most
visible component of the system is the large gain
satellite dish. The higher the diameter of this antenna,
the more the radio beam emitted can be concentrated
and the flow rate is high, which is vital when the
distance to the Earth causes a sharp drop in the flow
rate. The antenna can be fixed or steerable to allow it to
point to the Earth independently of the orientation
selected for the probe often constrained by the direction
of the Sun (energy production) or with respect to the
object under study (cameras).
For the radio link to work, the radio beam emitted by
the large gain antenna must be pointed precisely towards
the Earth. The spacecraft also has omnidirectional low-
gain antennas that allow only a very low data rate but do
not require pointing. These antennas are implemented at
a short distance from the Earth but they allow above all
to maintain the radio link in the event of failure of the
pointing problem of the large gain antenna for example
when the space probe can no longer maintain its
orientation at following a failure of his computer or his
attitude control system. There are also antennas with
intermediate characteristics called gain means that emit a
wide beam of 20 to 30° with average flow rates. The
radio transmitter transmits in S, X or Ka-band.
The majority of scientific instruments aboard a
spacecraft, especially aboard an orbiter, rely on the
analysis of the electromagnetic radiation emitted by the
objects observed. These instruments are, for example,
cameras, spectrometers, radars. They exploit the fact that
matter in all its states (gas, solid...) emits radiations
which constitute a signature allowing to identify and to
quantify its components (molecules or at fault type of
atom). Indeed, space is permanently crossed by the
electromagnetic radiation produced by celestial objects
(stars, planets) but also resulting from past events (star
explosion, Big Bang...). This radiation is more or less
energetic (radio waves less energy to gamma rays
through microwave radiation, infrared, visible light,
ultraviolet and X-rays) depending on the phenomenon
that gave birth. The material interacts with this
radiation: Depending on the wavelength of the incident
radiation it can absorb this radiation (absorption lines)
or it can re-emit it with a stronger intensity in other
wavelengths (emission lines). The phenomenon of
fluorescence in which a material is struck by non-
visible radiation and re-emitted in the visible radiation
is the most popularized case.
The instruments are classified into 4 main categories
according to the observation method used:
Remote sensing/Direct observation
Remote sensing is the observation of an object at a
distance. The cameras make it possible to obtain by this
method an image of a distant object and a spectrometer
measures the wavelengths of the radiation emitted by
this object.
Direct, or in situ observation is the measurement of
phenomena in contact with the instrument's sensors: A
magnetometer measures the magnetic field in the
immediate vicinity of the instrument and a dust detector
measures the particles that strike its sensor directly.
Passive/Active Instrument
Instruments that make direct observations, such as those
that use remote sensing, are either passive or active.
An active instrument uses energy to probe an object;
this is, for example, the case of a radar which emits radio
waves which are reflected by the studied object; these
are then analyzed. This is also the case for the alpha
particle X-ray spectrometer, which emits high-energy
particles from a radioactive source. These last come to
strike the object put in contact with it (a rock) and the
instrument analyzes the X-rays returned by the object.
A passive instrument merely observes what is already
there without providing energy to probe the object. This is
the case of a camera unless a bright spot comes to
illuminate the object (case of the camera onboard Huygens).
Some molecules, such as nitrogen or argon interact
little with electromagnetic radiation. Heavy molecules,
on the other hand, interact in a complex manner with
emissions distributed over the entire spectral band,
which makes their interpretation and the identification of
the original molecule difficult. The mass spectrometer is
an instrument used to identify and quantify molecules of
this type. It is an instrument that is also well suited to
cases where the density of molecules is low9. The mass
spectrometer works in contact with the material used
which limits its use to atmospheric probes and devices
that land on the surface of the studied celestial objects
(lander, rover). Its operation is based on the
measurement of the mass of molecules. Different
techniques can be used. After being ionized the material
to be analyzed passes into a detector which can be a
quadrupole analyzer, (analysis of the trajectory in a
magnetic field) or a speed measuring system, etc.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
328
Conclusion
A space probe is a robotic spacecraft that does not
orbit Earth, but instead, explores further into outer space.
A space probe may approach the Moon; travel through
interplanetary space; flyby, orbit, or land on other
planetary bodies; or enter interstellar space.
The space agencies of the USSR (now Russia and
Ukraine), the United States, the European Union, Japan,
China, India and Israel have collectively launched probes
to several planets and moons of the Solar System, as
well as to a number of asteroids and comets.
Approximately 15 missions are currently operational.
Once a probe has left the vicinity of Earth, its
trajectory will likely take it along an orbit around the
Sun similar to the Earth's orbit. To reach another planet,
the simplest practical method is a Hohmann transfer
orbit. More complex techniques, such as gravitational
slingshots, can be more fuel-efficient, though they may
require the probe to spend more time in transit. Some
high Delta-V missions (such as those with high
inclination changes) can only be performed, within the
limits of modern propulsion, using gravitational
slingshots. A technique using very little propulsion, but
requiring a considerable amount of time, is to follow a
trajectory on the Interplanetary Transport Network.
The Mars Exploration Rovers, Spirit and Opportunity
landed on Mars to explore the Martian surface and
geology and searched for clues to past water activity on
Mars. They were each launched in 2003 and landed in
2004. Communication with Spirit stopped on Sol 2210
(March 22, 2010). JPL continued to attempt to regain
contact until May 24, 2011, when NASA announced that
efforts to communicate with the unresponsive rover had
ended. Opportunity arrived at Endeavour crater on 9
August 2011, at a landmark called Spirit Point named
after its rover twin, after traversing 13 miles (21 km) from
Victoria crater, over a three-year period. After a planet-
wide dust storm in June 2018, the final communication
was received on June 10, 2018 and Opportunity was
declared dead on February 13, 2019. The rover lasted for
almost fifteen years on Mars - although the rover was
intended to last only three months.
The first dedicated missions to a comet; in this case,
to Halley's Comet during its 1985-86 journey through the
inner Solar System. It was also the first massive
international coordination of space probes on an
interplanetary mission, with probes specifically launched
by the Soviet (now Russian) Space Agency, European
Space Agency and Japan's ISAS (now integrated with
NASDA to JAXA).
Originally a solar observatory in the International
Sun-Earth Explorer series, it was sent into solar orbit to
make the first close observations of a comet, Comet
Giacobini–Zinner, in 1985 as a prelude to studies of
Halley's Comet.
Vega, the Russian/French spacecraft. They dropped
landers and balloons (first weather balloons deployed on
another planet) at Venus before their rendezvous with
Halley's Comet.
This Japanese probe, Sakigake, was the first non-US,
non-Soviet interplanetary probe.
Giotto, the first space probe to penetrate a comet's
coma and take close-up images of its nucleus.
Genesis was the first solar wind sample return probe
from sun-earth L1.
Stardust was the first sample return probe from a
comet tail.
NEAR Shoemaker was the first probe to land on an
asteroid.
The Rosetta space probe flew by two asteroids and
made a rendezvous and orbited comet 67P/Churyumov-
Gerasimenko in November 2014.
Pioneer 10 first probe to Jupiter. Radio
communications were lost with Pioneer 10 on January
23, 2003, because of the loss of electric power for its
radio transmitter, with the probe at a distance of 12
billion kilometers (80 AU) from Earth.
Pioneer 11 first probe to fly by Saturn.
Communications were later lost due to power constraints
and vast distance.
Voyager 1 is a 733-kilogram probe launched
September 5, 1977. It visited Jupiter and Saturn and was
the first probe to provide detailed images of the moons
of these planets.
Voyager 1 is the farthest human-made object from
Earth, traveling away from both the Earth and the Sun at
a relatively faster speed than any other probe.
As of September 12, 2013, Voyager 1 is about 12
billion miles (19 billion kilometers) from the Sun.
Voyager 2 was launched by NASA on August 20, 1977.
The probe's primary mission was to visit the ice
giants, Uranus, Cassini–Huygens was a 5,712 kg (12,593
lb) space probe designed to study gas giant Saturn, along
with its ringed system and moons.
The NASA probe was launched with ESA lander
Huygens on October 1, 1997, from Cape Canaveral. The
Cassini probe entered Saturn orbit on July 1, 2004 and
Huygens landed on Titan, Saturn's largest moon, on
January 14, 2005.
On September 15, 2017, the probe was de-orbited
and burned up in Saturn's atmosphere, after almost 20
years in space.
New Horizons first probe to be launched to Pluto.
Launched on January 19, 2006, it flew by the Pluto–
Charon system on July 14, 2015.
Dawn was the first spacecraft to visit and orbit a
protoplanet (4 Vesta), entering orbit on July 16, 2011.
Juno was the first probe to Jupiter without atomic
batteries, launched August 8, 2011.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
329
Change 2 was deployed to orbit the Moon, visit Sun-
Earth L2 Lagrangian point and make a flyby of asteroid
4179 Toutatis.
Along with Pioneer 10, Pioneer 11 and its sister space
probe Voyager 2, Voyager 1 is now an interstellar probe.
Voyager 1 and 2 have both achieved solar escape
velocity, meaning that their trajectories will not return
them to the Solar System.
Acknowledgement
This text was acknowledged and appreciated by Dr.
Veturia CHIROIU Honorific member of Technical
Sciences Academy of Romania (ASTR) PhD supervisor
in Mechanical Engineering.
Funding Information
Research contract: 1-Research contract: Contract
number 36-5-4D/1986 from 24IV1985, beneficiary
CNST RO (Romanian National Center for Science and
Technology) Improving dynamic mechanisms.
2-Contract research integration. 19-91-3 from
29.03.1991; Beneficiary: MIS; TOPIC: Research on
designing mechanisms with bars, cams and gears, with
application in industrial robots.
3-Contract research. GR 69/10.05.2007: NURC in
2762; theme 8: Dynamic analysis of mechanisms and
manipulators with bars and gears.
4-Labor contract, no. 35/22.01.2013, the UPB, "Stand
for reading performance parameters of kinematics and
dynamic mechanisms, using inductive and incremental
encoders, to a Mitsubishi Mechatronic System" "PN-II-
IN-CI-2012-1-0389".
All these matters are copyrighted! Copyrights: 394-
qodGnhhtej, from 17-02-2010 13:42:18; 463-
vpstuCGsiy, from 20-03-2010 12:45:30; 631-
sqfsgqvutm, from 24-05-2010 16:15:22; 933-
CrDztEfqow, from 07-01-2011 13:37:52.
Ethics
This article is original and contains unpublished
material. Authors declare that are not ethical issues and
no conflict of interest that may arise after the publication
of this manuscript.
References
Ab-Rahman, M.S., H. Guna, MH. Harun, SD. Zan and
K. Jumari, 2009. Cost-effective fabrication of self-
made 1×12 polymer optical fiber-based optical
splitters for automotive application. Am. J. Eng.
Applied Sci., 2: 252-259.
DOI: 10.3844/ajeassp.2009.252.259
Abam, F.I., I.U. Ugot and D.I. Igbong, 2012. Performance
analysis and components irreversibilities of a (25
MW) gas turbine power plant modeled with a spray
cooler. Am. J. Eng. Applied Sci., 5: 35-41.
DOI: 10.3844/ajeassp.2012.35.41
Abdelkrim, H., S.B. Othman, A.K.B. Salem and S.B.
Saoud, 2012. Dynamic partial reconfiguration
contribution on system on programmable chip
architecture for motor drive implementation. Am. J.
Eng. Applied Sci., 5: 15-24.
DOI: 10.3844/ajeassp.2012.15.24
Abdullah, M.Z., A. Saat and Z. Hamzah, 2011.
Optimization of energy dispersive x-ray
fluorescence spectrometer to analyze heavy metals
in moss samples. Am. J. Eng. Applied Sci., 4: 355-
362. DOI: 10.3844/ajeassp.2011.355.362
Abdullah, M., A. F.M. Zain, Y. H. Ho and S. Abdullah,
2009. TEC and scintillation study of equatorial
ionosphere: A month campaign over sipitang and
parit raja stations, Malaysia. Am. J. Eng. Applied
Sci., 2: 44-49. DOI: 10.3844/ajeassp.2009.44.49
Abdullah, H. and S.A. Halim, 2009. Electrical and
magnetoresistive studies Nd doped on La-Ba-Mn-O3
manganites for low-field sensor application. Am. J.
Eng. Applied Sci., 2: 297-303.
DOI: 10.3844/ajeassp.2009.297.303
Abouobaida, H., 2016. Robust and efficient controller to
design a standalone source supplied DC and AC
load powered by photovoltaic generator. Am. J.
Eng. Applied Sci., 9: 894-901.
DOI: 10.3844/ajeassp.2016.894.901
Abu-Ein, S., 2009. Numerical and analytical study of
exhaust gases flow in porous media with
applications to diesel particulate filters. Am. J. Eng.
Applied Sci., 2: 70-75.
DOI: 10.3844/ajeassp.2009.70.75
Abu-Lebdeh, M., G. Pérez-de León, S.A. Hamoush,
R.D. Seals and V.E. Lamberti, 2016. Gas
atomization of molten metal: Part II. Applications.
Am. J. Eng. Applied Sci., 9: 334-349.
DOI: 10.3844/ajeassp.2016.334.349
Agarwala, S., 2016. A perspective on 3D bioprinting
technology: Present and future. Am. J. Eng. Applied
Sci., 9: 985-990.
DOI: 10.3844/ajeassp.2016.985.990
Ahmed, M., R. Khan, M. Billah and S. Farhana, 2010. A
novel navigation algorithm for hexagonal hexapod
robot. Am. J. Eng. Applied Sci., 3: 320-327.
DOI: 10.3844/ajeassp.2010.320.327
Ahmed, M.K., H. Haque and H. Rahman, 2016. An
approach to develop a dynamic job shop scheduling
by fuzzy rule-based system and comparative study
with the traditional priority rules. Am. J. Eng.
Applied Sci., 9: 202-212.
DOI: 10.3844/ajeassp.2016.202.212

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
330
Akhesmeh, S., N. Pourmahmoud and H. Sedgi, 2008.
Numerical study of the temperature separation in the
ranque-hilsch vortex tube. Am. J. Eng. Applied Sci.,
1: 181-187. DOI: 10.3844/ajeassp.2008.181.187
Akubue, A., 2011. Appropriate technology for
socioeconomic development in third world
countries. J. Technol. Stud., 26: 33-43.
DOI: 10.21061/jots.v26i1.a.6
Al-Abbas, I.K., 2009. Reduced order models of a current
source inverter induction motor drive. Am. J. Eng.
Applied Sci., 2: 39-43.
DOI: 10.3844/ajeassp.2009.39.43
Al-Hasan and A.S. Al-Ghamdi, 2016. Energy balance
for a diesel engine operates on a pure biodiesel,
diesel fuel and biodiesel-diesel blends. Am. J. Eng.
Applied Sci., 9: 458-465.
DOI: 10.3844/ajeassp.2016.458.465
Al Smadi, T.A., 2011. Low cost smart sensor design.
Am. J. Eng. Applied Sci., 4: 162-168.
DOI: 10.3844/ajeassp.2011.162.168
Al Qadi, A.N.S., M.B.A. ALhasanat, A. AL Dahamsheh
and S. AL Zaiydneen, 2016a. Using of box-benken
method to predict the compressive strength of self-
compacting concrete containing Wadi Musa
bentonite, Jordan. Am. J. Eng. Applied Sci., 9: 406-
411. DOI: 10.3844/ajeassp.2016.406.411
Al Qadi, A.N.S., M.B.A. Alhasanat and M. Haddad,
2016b. Effect of crumb rubber as coarse and fine
aggregates on the properties of asphalt concrete.
Am. J. Eng. Applied Sci., 9: 558-564.
DOI: 10.3844/ajeassp.2016.558.564
Aleksic, S. and A. Lovric, 2011. Energy consumption
and environmental implications of wired access
networks. Am. J. Eng. Applied Sci., 4: 531-539.
DOI: 10.3844/ajeassp.2011.531.539
Alhasanat, M.B., A.N. Al Qadi, O.A. Al Khashman and
A. Dahamsheh, 2016. Scanning electron
microscopic evaluation of self-compacting concrete
spalling at elevated temperatures. Am. J. Eng.
Applied Sci., 9: 119-127.
DOI: 10.3844/ajeassp.2016.119.127
Ali, K.S. and JL. Shumaker, 2013. Hardware in the loop
simulator for multi-agent unmanned aerial vehicles
environment. Am. J. Eng. Applied Sci., 6: 172-177.
DOI: 10.3844/ajeassp.2013.172.177
Ali, G.A.M., O. Fouad and S.A. Makhlouf, 2016.
Electrical properties of cobalt oxide/silica
nanocomposites obtained by sol-gel technique. Am.
J. Eng. Applied Sci., 9: 12-16.
DOI: 10.3844/ajeassp.2016.12.16
Al-Nasra, M. Daoudb and T.M. Abu-Lebdeh, 2015. The
use of the super absorbent polymer as water blocker
in concrete structures. Am. J. Eng. Applied Sci., 8:
659-665. DOI: 10.3844/ajeassp.2015.659.665
Alwetaishi, M.S., 2016. Impact of building function on
thermal comfort: A review paper. Am. J. Eng.
Applied Sci., 9: 928-945.
DOI: 10.3844/ajeassp.2016.928.945
Aly, W.M. and M.S. Abuelnasr, 2010. Electronic design
automation using object oriented electronics. Am. J.
Eng. Applied Sci., 3: 121-127.
DOI: 10.3844/ajeassp.2010.121.127
Amani, N., 2016. Design and implementation of
optimum management system using cost evaluation
and financial analysis for prevention of building
failure. Am. J. Eng. Applied Sci., 9: 281-296.
DOI: 10.3844/ajeassp.2016.281.296
Amer, S., S. Hamoush and T.M. Abu-Lebdeh, 2015.
Experimental evaluation of the raking energy in
damping system of steel stud partition walls. Am. J.
Eng. Applied Sci., 8: 666-677.
DOI: 10.3844/ajeassp.2015.666.677
Anizan, S., K. Yusri, C.S. Leong, N. Amin and S. Zaidi
et al., 2011. Effects of the contact resistivity
variations of the screen-printed silicon solar cell.
Am. J. Eng. Applied Sci., 4: 328-331.
DOI: 10.3844/ajeassp.2011.328.331
Angeles, J. and C. Lopez-Cajun, 1988. Optimal synthesis
of cam mechanisms with oscillating flat-face
followers. Mechanism Mach. Theory, 23: 1-6.
DOI: 10.1016/0094-114X(88)90002-X
Antonescu, P., 2000. Mechanisms and Handlers. 1st
Edn., Printech Publishing House, Bucharest.
Antonescu, P. and F.I.T. Petrescu, 1985. An analytical
method of synthesis of cam mechanism and flat
stick. Proceedings of the 4th International
Symposium on Theory and Practice of Mechanisms,
(TPM’ 85), Bucharest.
Antonescu, P. and F.I.T. Petrescu, 1989. Contributions to
cinetoelastodynamic analysis of distribution
mechanisms. Bucharest.
Antonescu, P., M. Oprean and F.I.T. Petrescu, 1985a.
Contributions to the synthesis of oscillating cam
mechanism and oscillating flat stick. Proceedings of
the 4th International Symposium on Theory and
Practice of Mechanisms, (TPM’ 85), Bucharest.
Antonescu, P., M. Oprean and F.I.T. Petrescu, 1985b. At
the projection of the oscillate cams, there are
mechanisms and distribution variables. Proceedings
of the 5th Conference of Engines, Automobiles,
Tractors and Agricultural Machines, (AMA’ 58), I-
Motors and Cars, Brasov.
Antonescu, P., M. Oprean and F.I.T. Petrescu, 1986.
Projection of the profile of the rotating camshaft
acting on the oscillating plate with disengagement.
Proceedings of the 3rd National Computer-aided
Design Symposium in the field of Mechanisms and
Machine Parts, (MMP’ 86), Brasov.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
331
Antonescu, P., M. Oprean and F.I.T. Petrescu, 1987.
Dynamic analysis of the cam distribution
mechanisms. Proceedings of the 7th National
Symposium on Industrial Robots and Space
Mechanisms, (RSM’ 87), Bucharest.
Antonescu, P., M. Oprean and F.I.T. Petrescu, 1988.
Analytical synthesis of Kurz profile, rotating the flat
cam. Mach, Build. Rev.
Antonescu, P., F.I.T. Petrescu and O. Antonescu, 1994.
Contributions to the synthesis of the rotating cam
mechanism and the tip of the balancing tip. Brasov.
Antonescu, P., F.I.T. Petrescu and D. Antonescu, 1997.
Geometrical synthesis of the rotary cam and balance
tappet mechanism. Bucharest, 3: 23-23.
Antonescu, P., F.I.T. Petrescu and O. Antonescu, 2000a.
Contributions to the synthesis of the rotary disc-cam
profile. Proceedings of the 8th International
Conference on the Theory of Machines and
Mechanisms, (TMM’ 00), Liberec, Czech Republic,
pp: 51-56.
Antonescu, P., F.I.T. Petrescu and O. Antonescu, 2000b.
Synthesis of the rotary cam profile with balance
follower. Proceedings of the 8th Symposium on
Mechanisms and Mechanical Transmissions,
(MMT’ 00), Timişoara, pp: 39-44.
Antonescu, P., F. Petrescu and O. Antonescu, 2001.
Contributions to the synthesis of mechanisms with
rotary disc-cam. Proceedings of the 8th IFToMM
International Symposium on Theory of Machines
and Mechanisms, (TMM’ 01), Bucharest,
ROMANIA, pp: 31-36.
Ascione, F., N. Bianco, R.F. De Masi, F. de Rossi and C.
De Stasio et al., 2016. Energy audit of health care
facilities: dynamic simulation of energy
performances and energy-oriented refurbishment of
system and equipment for microclimatic control.
Am. J. Eng. Applied Sci., 9: 814-834.
DOI: 10.3844/ajeassp.2016.814.834
Augustine, A., R.D. Prakash, R. Xavier and M.C.
Parassery, 2016. Review of signal processing
techniques for detection of power quality events.
Am. J. Eng. Applied Sci., 9: 364-370.
DOI: 10.3844/ajeassp.2016.364.370
Aversa, R., R.V.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2017a. Nano-diamond hybrid materials for
structural biomedical application. Am. J. Biochem.
Biotechnol., 13: 34-41.
DOI: 10.3844/ajbbsp.2017.34.41
Aversa, R., R.V. Petrescu, B. Akash, R.B. Bucinell and
J.M. Corchado et al., 2017b. Kinematics and forces
to a new model forging manipulator. Am. J. Applied
Sci., 14: 60-80. DOI: 10.3844/ajassp.2017.60.80
Aversa, R., R.V. Petrescu, A. Apicella, F.I.T. Petrescu
and J.K. Calautit et al., 2017c. Something about the
V engines design. Am. J. Applied Sci., 14: 34-52.
DOI: 10.3844/ajassp.2017.34.52
Aversa, R., D. Parcesepe, R.V.V. Petrescu, F. Berto and
G. Chen et al., 2017d. Process ability of bulk
metallic glasses. Am. J. Applied Sci., 14: 294-301.
DOI: 10.3844/ajassp.2017.294.301
Aversa, R., R.V.V. Petrescu, B. Akash, R.B. Bucinell and
J.M. Corchado et al., 2017e. Something about the
balancing of thermal motors. Am. J. Eng. Applied Sci.,
10: 200.217. DOI: 10.3844/ajeassp.2017.200.217
Aversa, R., F.I.T. Petrescu, R.V. Petrescu and A.
Apicella, 2016a. Biomimetic FEA bone modeling
for customized hybrid biological prostheses
development. Am. J. Applied Sci., 13: 1060-1067.
DOI: 10.3844/ajassp.2016.1060.1067
Aversa, R., D. Parcesepe, R.V. Petrescu, G. Chen and
F.I.T. Petrescu et al., 2016b. Glassy amorphous
metal injection molded induced morphological
defects. Am. J. Applied Sci., 13: 1476-1482.
DOI: 10.3844/ajassp.2016.1476.1482
Aversa, R., R.V. Petrescu, F.I.T. Petrescu and A.
Apicella, 2016c. Smart-factory: Optimization and
process control of composite centrifuged pipes. Am.
J. Applied Sci., 13: 1330-1341.
DOI: 10.3844/ajassp.2016.1330.1341
Aversa, R., F. Tamburrino, R.V. Petrescu, F.I.T.
Petrescu and M. Artur et al., 2016d.
Biomechanically inspired shape memory effect
machines driven by muscle like acting NiTi alloys.
Am. J. Applied Sci., 13: 1264-1271.
DOI: 10.3844/ajassp.2016.1264.1271
Aversa, R., E.M. Buzea, R.V. Petrescu, A. Apicella and
M. Neacsa et al., 2016e. Present a mechatronic
system having able to determine the concentration
of carotenoids. Am. J. Eng. Applied Sci., 9: 1106-
1111. DOI: 10.3844/ajeassp.2016.1106.1111
Aversa, R., R.V. Petrescu, R. Sorrentino, F.I.T. Petrescu
and A. Apicella, 2016f. Hybrid ceramo-polymeric
nanocomposite for biomimetic scaffolds design and
preparation. Am. J. Eng. Applied Sci., 9: 1096-1105.
DOI: 10.3844/ajeassp.2016.1096.1105
Aversa, R., V. Perrotta, R.V. Petrescu, C. Misiano and
F.I.T. Petrescu et al., 2016g. From structural colors
to super-hydrophobicity and achromatic transparent
protective coatings: Ion plating plasma assisted TiO2
and SiO2 nano-film deposition. Am. J. Eng. Applied
Sci., 9: 1037-1045.
DOI: 10.3844/ajeassp.2016.1037.1045
Aversa, R., R.V. Petrescu, F.I.T. Petrescu and A.
Apicella, 2016h. Biomimetic and evolutionary
design driven innovation in sustainable products
development. Am. J. Eng. Applied Sci., 9: 1027-
1036. DOI: 10.3844/ajeassp.2016.1027.1036
Aversa, R., R.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2016i. Mitochondria are naturally micro
robots - a review. Am. J. Eng. Applied Sci., 9: 991-
1002. DOI: 10.3844/ajeassp.2016.991.1002

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
332
Aversa, R., R.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2016j. We are addicted to vitamins C and
E-A review. Am. J. Eng. Applied Sci., 9: 1003-
1018. DOI: 10.3844/ajeassp.2016.1003.1018
Aversa, R., R.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2016k. Physiologic human fluids and
swelling behavior of hydrophilic biocompatible
hybrid ceramo-polymeric materials. Am. J. Eng.
Applied Sci., 9: 962-972.
DOI: 10.3844/ajeassp.2016.962.972
Aversa, R., R.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2016l. One can slow down the aging
through antioxidants. Am. J. Eng. Applied Sci., 9:
1112-1126. DOI: 10.3844/ajeassp.2016.1112.1126
Aversa, R., R.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2016m. About homeopathy or ≪Similia
Similibus Curentur≫. Am. J. Eng. Applied Sci., 9:
1164-1172. DOI: 10.3844/ajeassp.2016.1164.1172
Aversa, R., R.V. Petrescu, A. Apicella and F.I.T.
Petrescu, 2016n. The basic elements of life's. Am. J.
Eng. Applied Sci., 9: 1189-1197.
DOI: 10.3844/ajeassp.2016.1189.1197
Aversa, R., F.I.T. Petrescu, R.V. Petrescu and A.
Apicella, 2016o. Flexible stem trabecular
prostheses. Am. J. Eng. Applied Sci., 9: 1213-1221.
DOI: 10.3844/ajeassp.2016.1213.122
Babayemi, A.K., 2016. Thermodynamics, non-linear
isotherms, statistical modeling and optimization of
phosphorus adsorption from wastewater. Am. J.
Eng. Applied Sci., 9: 1019-1026.
DOI: 10.3844/ajeassp.2016.1019.1026
Bakar, R.A., M.K. Mohammed and M.M. Rahman,
2009. Numerical study on the performance
characteristics of hydrogen fueled port injection
internal combustion engine. Am. J. Eng. Applied
Sci., 2: 407-415.
DOI: 10.3844/ajeassp.2009.407.415
Barone, G., A. Buonomano, C. Forzano and A. Palombo,
2016. WLHP systems in commercial buildings: A
case study analysis based on a dynamic simulation
approach. Am. J. Eng. Applied Sci., 9: 659-668.
DOI: 10.3844/ajeassp.2016.659.668
Bedon, C., 2016. Review on the use of FRP composites
for facades and building skins. Am. J. Eng. Applied
Sci., 9: 713-723.
DOI: 10.3844/ajeassp.2016.713.723
Bedon, C. and C. Amadio, 2016. A unified approach for
the shear buckling design of structural glass walls
with non-ideal restraints. Am. J. Eng. Applied Sci.,
9: 64-78. DOI: 10.3844/ajeassp.2016.64.78
Bedon, C. and C. Louter, 2016. Finite-element numerical
simulation of the bending performance of post-
tensioned structural glass beams with adhesively
bonded CFRP tendons. Am. J. Eng. Applied Sci., 9:
680-691. DOI: 10.3844/ajeassp.2016.680.691
Bier, H. and S. Mostafavi, 2015. Structural optimization
for materially informed design to robotic production
processes. Am. J. Eng. Applied Sci., 8: 549-555.
DOI: 10.3844/ajeassp.2015.549.555
Bolonkin, A., 2009a. Femtotechnology: Nuclear matter
with fantastic properties. Am. J. Eng. Applied Sci.,
2: 501-514. DOI: 10.3844/ajeassp.2009.501.514
Bolonkin, A., 2009b. Converting of matter to nuclear
energy by ab-generator. Am. J. Eng. Applied Sci., 2:
683-693. DOI: 10.3844/ajeassp.2009.683.693
Boucetta, A., 2008. Vector control of a variable
reluctance machine stator and rotor discs imbricates.
Am. J. Eng. Applied Sci., 1: 260-265.
DOI: 10.3844/ajeassp.2008.260.265
Bourahla, N. and A. Blakeborough, 2015. Similitude
distortion compensation for a small scale model of a
knee braced steel frame. Am. J. Eng. Applied Sci.,
8: 481-488. DOI: 10.3844/ajeassp.2015.481.488
Bucinell, R.B., 2016. Stochastic model for variable
amplitude fatigue induced delamination growth in
graphite/epoxy laminates. Am. J. Eng. Applied Sci.,
9: 635-646. DOI: 10.3844/ajeassp.2016.635.646
Budak, S., Z. Xiao, B. Johnson, J. Cole and M. Drabo et
al., 2016. Highly-efficient advanced thermoelectric
devices from different multilayer thin films. Am. J.
Eng. Applied Sci., 9: 356-363.
DOI: 10.3844/ajeassp.2016.356.363
Buonomano, A., F. Calise and M. Vicidomini, 2016a. A
novel prototype of a small-scale solar power plant:
Dynamic simulation and thermoeconomic analysis.
Am. J. Eng. Applied Sci., 9: 770-788.
DOI: 10.3844/ajeassp.2016.770.788
Buonomano, A., F. Calise, M.D. d'Accadia, R. Vanoli
and M. Vicidomini, 2016b. Simulation and
experimental analysis of a demonstrative solar
heating and cooling plant installed in Naples (Italy).
Am. J. Eng. Applied Sci., 9: 798-813.
DOI: 10.3844/ajeassp.2016.798.813
Cao, W., H. Ding, Z. Bin and C. Ziming, 2013. New
structural representation and digital-analysis
platform for symmetrical parallel mechanisms. Int.
J. Adv. Robotic Sys. DOI: 10.5772/56380
Calise, F., M.D. dâ' Accadia, L. Libertini, E. Quiriti and
M. Vicidomini, 2016b. Dynamic simulation and
optimum operation strategy of a trigeneration
system serving a hospital. Am. J. Eng. Applied Sci.,
9: 854-867. DOI: 10.3844/ajeassp.2016.854.867
Campo, T., M. Cotto, F. Marquez, E. Elizalde and C.
Morant, 2016. Graphene synthesis by plasma-
enhanced CVD growth with ethanol. Am. J. Eng.
Applied Sci., 9: 574-583.
DOI: 10.3844/ajeassp.2016.574.583
Cardu, M., P. Oreste and T. Cicala, 2009. Analysis of the
tunnel boring machine advancement on the Bologna-
Florence railway link. Am. J. Eng. Applied Sci., 2:
416-420. DOI: 10.3844/ajeassp.2009.416.420

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
333
Casadei, D., 2015. Bayesian statistical inference for
number counting experiments. Am. J. Eng. Applied
Sci., 8: 730-735.
DOI: 10.3844/ajeassp.2015.730.735
Cataldo, R., 2006. Overview of planetary power system
options for education. ITEA Human Exploration
Project Authors, Glenn Research Center. Brooke
Park, OH.
Chang, S.P., M.C. Chen and J.D. Lin, 2015. Study of
heat-treated steel and related applications. Am. J.
Eng. Applied Sci., 8: 611-619.
DOI: 10.3844/ajeassp.2015.611.619
Chen, G. and L. Xu, 2016. A general strategy to enhance
up conversion luminescence in rare-earth-ion-doped
oxide nanocrystals. Am. J. Eng. Applied Sci., 9: 79-
83. DOI: 10.3844/ajeassp.2016.79.83
Chiozzi, A., G. Milani, N. Grillanda and A. Tralli, 2016.
An adaptive procedure for the limit analysis of FRP
reinforced masonry vaults and applications. Am. J.
Eng. Applied Sci., 9: 735-745.
DOI: 10.3844/ajeassp.2016.735.745
Chisari, C. and C. Bedon, 2016. Multi-objective
optimization of FRP jackets for improving the
seismic response of reinforced concrete frames. Am.
J. Eng. Applied Sci., 9: 669-679.
DOI: 10.3844/ajeassp.2016.669.679
Comanescu, A., 2010. Bazele Modelarii Mecanismelor.
1st Edn., E. Politeh, Press, Bucureşti, pp: 274.
Darabi, A., S.A. Soleamani and A. Hassannia, 2008.
Fuzzy based digital automatic voltage regulator of a
synchronous generator with unbalanced loads. Am.
J. Eng. Applied Sci., 1: 280-286.
DOI: 10.3844/ajeassp.2008.280.286
Daud, H., N. Yahya, A.A. Aziz and M.F. Jusoh, 2008.
Development of wireless electric concept powering
electrical appliances. Am. J. Eng. Applied Sci., 1:
12-15. DOI: 10.3844/ajeassp.2008.12.15
Demetriou, D., N. Nikitas and K.D. Tsavdaridis, 2015.
Semi active tuned mass dampers of buildings: A
simple control option. Am. J. Eng. Applied Sci., 8:
620-632. DOI: 10.3844/ajeassp.2015.620.632
Dixit, S. and S. Pal, 2015. Synthesis and characterization
of ink (Carbon)-perovskite/polyaniline ternary
composite electrode for sodium chloride separation.
Am. J. Eng. Applied Sci., 8: 527-537.
DOI: 10.3844/ajeassp.2015.527.537
Djalel, D., M. Mourad and H. Labar, 2013. New
approach of electromagnetic fields of the lightning
discharge. Am. J. Eng. Applied Sci., 6: 369-383.
DOI: 10.3844/ajeassp.2013.369.383
Dong, H., N. Giakoumidis, N. Figueroa and N. Mavridis,
2013. Approaching behaviour monitor and vibration
indication in developing a General Moving Object
Alarm System (GMOAS). Int. J. Adv. Robotic Sys.
DOI: 10.5772/56586
Ebrahim, N.A., S. Ahmed, S.H.A. Rashid and Z. Taha,
2012. Technology use in the virtual R&D teams.
Am. J. Eng. Applied Sci., 5: 9-14.
DOI: 10.3844/ajeassp.2012.9.14
El-Labban, H.F., M. Abdelaziz and E.R.I. Mahmoud,
2013. Modification of carbon steel by laser surface
melting: Part I: Effect of laser beam travelling speed
on microstructural features and surface hardness.
Am. J. Eng. Applied Sci., 6: 352-359.
DOI: 10.3844/ajeassp.2013.352.359
Elliott, A., S. AlSalihi, A.L. Merriman and M.M. Basti,
2016. Infiltration of nanoparticles into porous binder
jet printed parts. Am. J. Eng. Applied Sci., 9: 128-
133. DOI: 10.3844/ajeassp.2016.128.133
Elmeddahi, Y., H. Mahmoudi, A. Issaadi, M.F.A.
Goosen and R. Ragab, 2016b. Evaluating the effects
of climate change and variability on water
resources: A case study of the cheliff Basin in
Algeria. Am. J. Eng. Applied Sci., 9: 835-845.
DOI: 10.3844/ajeassp.2016.835.845
El-Tous, Y., 2008. Pitch angle control of variable speed
wind turbine. Am. J. Eng. Applied Sci., 1: 118-120.
DOI: 10.3844/ajeassp.2008.118.120
Faizal, A., S. Mulyono, R. Yendra and A. Fudholi, 2016.
Design Maximum Power Point Tracking (MPPT) on
photovoltaic panels using fuzzy logic method. Am.
J. Eng. Applied Sci., 9: 789-797.
DOI: 10.3844/ajeassp.2016.789.797
Farahani, A.S., N.M. Adam and M.K.A. Ariffin, 2010.
Simulation of airflow and aerodynamic forces acting
on a rotating turbine ventilator. Am. J. Eng. Applied
Sci., 3: 159-170. DOI: 10.3844/ajeassp.2010.159.170
Farokhi, E. and M. Gordini, 2015. Investigating the
parameters influencing the behavior of knee braced
steel structures. Am. J. Eng. Applied Sci., 8: 567-
574. DOI: 10.3844/ajeassp.2015.567.574
Fathallah, A.Z.M. and R.A. Bakar, 2009. Prediction studies
for the performance of a single cylinder high speed
spark ignition linier engine with spring mechanism as
return cycle. Am. J. Eng. Applied Sci., 2: 713-720.
DOI: 10.3844/ajeassp.2009.713.720
Fawcett, G.F. and J.N. Fawcett, 1974. Comparison of
Polydyne and Non Polydyne Cams. In: Cams and
Cam Mechanisms, Rees Jones, J. (Ed.), MEP,
London and Birmingham, Alabama.
Fen, Y.W., W.M.M. Yunus, M.M. Moksin, Z.A. Talib and
N.A. Yusof, 2011. Optical properties of crosslinked
chitosan thin film with glutaraldehyde using surface
Plasmon resonance technique. Am. J. Eng. Applied
Sci., 4: 61-65. DOI: 10.3844/ajeassp.2011.61.65
Feraga, C.E., A. Moussaoui, A. Bouldjedri and A.
Yousfi, 2009. Robust position controller for a
permanent magnet synchronous actuator. Am. J.
Eng. Applied Sci., 2: 388-392.
DOI: 10.3844/ajeassp.2009.388.392

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
334
Franklin, D.J., 1930. Ingenious Mechanisms for
Designers and Inventors. 1st Edn., Industrial Press
Publisher.
Fu, Y.F., J. Gong, H. Huang, Y.J. Liu and D. Zhu et al.,
2015. Parameters optimization of adaptive cashew
shelling cutter based on BP neural network and
genetic algorithm. Am. J. Eng. Applied Sci., 8: 648-
658. DOI: 10.3844/ajeassp.2015.648.658
Gao, F., W.Z. Guo, Q.Y. Song and F.S. Du, 2010.
Current development of heavy-duty manufacturing
equipment. J. Mech. Eng., 46: 92-107.
Ge, H. and F. Gao, 2012. Type design for heavy-payload
forging manipulators. Chinese J. Mech. Eng., 25:
197-205.
Ge, L. and X. Xu, 2015. A scheme design of cloud + end
technology in demand side management. Am. J.
Eng. Applied Sci., 8: 736-747.
DOI: 10.3844/ajeassp.2015.736.747
Giordana, F., V. Rognoni and G. Ruggieri, 1979. On the
influence of measurement errors in the Kinematic
analysis of cam. Mechanism Mach. Theory, 14: 327-
340. DOI: 10.1016/0094-114X(79)90019-3
Gruener, J.E., 2006. Lunar exploration (Presentation to
ITEA Human Exploration Project Authors, November
2006, at Johnson Space Center). Houston, TX.
Gupta, P., A. Gupta and A. Asati, 2015. Ultra low power
MUX based compressors for Wallace and Dadda
multipliers in sub-threshold regime. Am. J. Eng.
Applied Sci., 8: 702-716.
DOI: 10.3844/ajeassp.2015.702.716
Gusti, A.P. and Semin, 2016. The effect of vessel speed
on fuel consumption and exhaust gas emissions.
Am. J. Eng. Applied Sci., 9: 1046-1053.
DOI: 10.3844/ajeassp.2016.1046.1053
Hain, K., 1971. Optimization of a cam mechanism to
give good transmissibility maximal output angle of
swing and minimal acceleration. J. Mechanisms, 6:
419-434. DOI: 10.1016/0022-2569(71)90044-9
Hassan, M., H. Mahjoub and M. Obed, 2012. Voice-
based control of a DC servo motor. Am. J. Eng.
Applied Sci., 5: 89-92.
DOI: 10.3844/ajeassp.2012.89.92
Hasan, S. and M.H. El-Naas, 2016. Optimization of a
combined approach for the treatment of carbide
slurry and capture of CO2. Am. J. Eng. Applied Sci.,
9: 449-457. DOI: 10.3844/ajeassp.2016.449.457
Helmy, A.K. and G.S. El-Taweel, 2010. Neural network
change detection model for satellite images using
textural and spectral characteristics. Am. J. Eng.
Applied Sci., 3: 604-610.
DOI: 10.3844/ajeassp.2010.604.610
Hirun, W., 2016. Evaluation of interregional freight
generation modelling methods by using nationwide
commodity flow survey data. Am. J. Eng. Applied
Sci., 9: 625-634.
DOI: 10.3844/ajeassp.2016.625.634
Ho, C.Y.F., B.W.K. Ling, S.G. Blasi, Z.W. Chi and
W.C. Siu, 2011. Single step optimal block matched
motion estimation with motion vectors having
arbitrary pixel precisions. Am. J. Eng. Applied Sci.,
4: 448-460. DOI: 10.3844/ajeassp.2011.448.460
Huang, B., S.H. Masood, M. Nikzad, P.R. Venugopal
and A. Arivazhagan, 2016. Dynamic mechanical
properties of fused deposition modelling processed
polyphenylsulfone material. Am. J. Eng. Applied
Sci., 9: 1-11. DOI: 10.3844/ajeassp.2016.1.11
He, B., Z. Wang, Q. Li, H. Xie and R. Shen, 2013. An
analytic method for the kinematics and dynamics of
a multiple-backbone continuum robot. IJARS.
DOI: 10.5772/54051
Idarwazeh, S., 2011. Inverse discrete Fourier transform-
discrete Fourier transform techniques for generating
and receiving spectrally efficient frequency division
multiplexing signals. Am. J. Eng. Applied Sci., 4:
598-606. DOI: 10.3844/ajeassp.2011.598.606
Iqbal, 2016. An overview of Energy Loss Reduction
(ELR) software used in Pakistan by WAPDA for
calculating transformer overloading, line losses and
energy losses. Am. J. Eng. Applied Sci., 9: 442-448.
DOI: 10.3844/ajeassp.2016.442.448
Ismail, M.I.S., Y. Okamoto, A. Okada and Y. Uno, 2011.
Experimental investigation on micro-welding of thin
stainless steel sheet by fiber laser. Am. J. Eng.
Applied Sci., 4: 314-320.
DOI: 10.3844/ajeassp.2011.314.320
Jaber, A.A. and R. Bicker, 2016. Industrial robot fault
detection based on statistical control chart. Am. J.
Eng. Applied Sci., 9: 251-263.
DOI: 10.3844/ajeassp.2016.251.263
Jafari, N., A. Alsadoon, C.P. Withana, A. Beg and A.
Elchouemi, 2016. Designing a comprehensive
security framework for smartphones and mobile
devices. Am. J. Eng. Applied Sci., 9: 724-734.
DOI: 10.3844/ajeassp.2016.724.734
Jalil, M.I.A. and J. Sampe, 2013. Experimental
investigation of thermoelectric generator modules
with different technique of cooling system. Am. J.
Eng. Applied Sci., 6: 1-7.
DOI: 10.3844/ajeassp.2013.1.7
Jaoude, A.A. and K. El-Tawil, 2013. Analytic and
nonlinear prognostic for vehicle suspension systems.
Am. J. Eng. Applied Sci., 6: 42-56.
DOI: 10.3844/ajeassp.2013.42.56
Jarahi, H., 2016. Probabilistic seismic hazard
deaggregation for Karaj City (Iran). Am. J. Eng.
Applied Sci., 9: 520-529.
DOI: 10.3844/ajeassp.2016.520.529
Jarahi, H. and S. Seifilaleh, 2016. Rock fall hazard
zonation in Haraz Highway. Am. J. Eng. Applied
Sci., 9: 371-379.
DOI: 10.3844/ajeassp.2016.371.379

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
335
Jauhari, K., A. Widodo and I. Haryanto, 2016.
Identification of a machine tool spindle critical
frequency through modal and imbalance response
analysis. Am. J. Eng. Applied Sci., 9: 213-221.
DOI: 10.3844/ajeassp.2016.213.221
Jiang, J., Q. Chen and S. Nimbalkar, 2016. Field data
based method for predicting long-term settlements.
Am. J. Eng. Applied Sci., 9: 466-476.
DOI: 10.3844/ajeassp.2016.466.476
Jones, J.R. and J.E. Reeve, 1974. Dynamic Response of
Cam Curves Based on Sinusoidal Segments. In:
Cams and cam Mechanisms, Rees Jones, J. (Ed.),
MEP, London and Birmingham, Alabama.
Kaewnai, S. and S. Wongwises, 2011. Improvement of
the runner design of francis turbine using
computational fluid dynamics. Am. J. Eng. Applied
Sci., 4: 540-547.
DOI: 10.3844/ajeassp.2011.540.547
Khalifa, A.H.N., A.H. Jabbar and J.A. Muhsin, 2015.
Effect of exhaust gas temperature on the
performance of automobile adsorption air-
conditioner. Am. J. Eng. Applied Sci., 8: 575-581.
DOI: 10.3844/ajeassp.2015.575.581
Khalil, R., 2015. Credibility of 3D volume computation
using GIS for pit excavation and roadway
constructions. Am. J. Eng. Applied Sci., 8: 434-442.
DOI: 10.3844/ajeassp.2015.434.442
Kamble, V.G. and N. Kumar, 2016. Fabrication and
tensile property analysis of polymer matrix
composites of graphite and silicon carbide as fillers.
Am. J. Eng. Applied Sci., 9: 17-30.
DOI: 10.3844/ajeassp.2016.17.30
Kazakov, V.V., V.I. Yusupov, V.N. Bagratashvili, A.I.
Pavlikov and V.A. Kamensky, 2016. Control of
bubble formation at the optical fiber tip by analyzing
ultrasound acoustic waves. Am. J. Eng. Applied
Sci., 9: 921-927.
DOI: 10.3844/ajeassp.2016.921.927
Kechiche, O.B.H.B., H.B.A. Sethom, H. Sammoud and
I.S. Belkhodja, 2011. Optimized high-frequency
signal injection based permanent magnet
synchronous motor rotor position estimation applied
to washing machines. Am. J. Eng. Applied Sci., 4:
390-399. DOI: 10.3844/ajeassp.2011.390.399
Koster, M.P., 1974. The Effects of Backlash and Shaft
Flexibility on the Dynamic Behavior of a Cam
Mechanism. In: Cams and Cam Mechanisms, Rees
Jones, J. (Ed.), MEP, London and Birmingham,
Alabama.
Kuli, I., T.M. Abu-Lebdeh, E.H. Fini and S.A. Hamoush,
2016. The use of nano-silica for improving
mechanical properties of hardened cement paste.
Am. J. Eng. Applied Sci., 9: 146-154.
DOI: 10.3844/ajeassp.2016.146.154
Kumar, N.D., R.D. Ravali and PR. Srirekha, 2015.
Design and realization of pre-amplifier and filters
for on-board radar system. Am. J. Eng. Applied Sci.,
8: 689-701. DOI: 10.3844/ajeassp.2015.689.701
Kunanoppadon, J., 2010. Thermal efficiency of a
combined turbocharger set with gasoline engine.
Am. J. Eng. Applied Sci., 3: 342-349.
DOI: 10.3844/ajeassp.2010.342.349
Kwon, S., Y. Tani, H. Okubo and T. Shimomura, 2010.
Fixed-star tracking attitude control of spacecraft
using single-gimbal control moment gyros. Am. J.
Eng. Applied Sci., 3: 49-55.
DOI: 10.3844/ajeassp.2010.49.55
Lamarre, A., E.H. Fini and T.M. Abu-Lebdeh, 2016.
Investigating effects of water conditioning on the
adhesion properties of crack sealant. Am. J. Eng.
Applied Sci., 9: 178-186.
DOI: 10.3844/ajeassp.2016.178.186
Lee, B.J., 2013. Geometrical derivation of differential
kinematics to calibrate model parameters of flexible
manipulator. Int. J. Adv. Robotic Syst.
DOI: 10.5772/55592
Li, G. and D.S. Liu, 2010. Dynamic behavior of the
forging manipulator under large amplitude
compliance motion. J. Mech. Eng., 46: 21-28.
Li, R., B. Zhang, S. Xiu, H. Wang and L. Wang et al.,
2015. Characterization of solid residues obtained
from supercritical ethanol liquefaction of swine
manure. Am. J. Eng. Applied Sci., 8: 465-470.
DOI: 10.3844/ajeassp.2015.465.470
Lin, W., B. Li, X. Yang and D. Zhang, 2013. Modelling
and control of inverse dynamics for a 5-DOF
parallel kinematic polishing machine. Int. J. Adv.
Robotic Sys. DOI: 10.5772/54966
Liu, H., W. Zhou, X. Lai and S. Zhu, 2013. An efficient
inverse kinematic algorithm for a PUMA560-
structured robot manipulator. IJARS.
DOI: 10.5772/56403
Lubis, Z., A.N. Abdalla, Mortaza and R. Ghon, 2009.
Mathematical modeling of the three phase induction
motor couple to DC motor in hybrid electric vehicle.
Am. J. Eng. Applied Sci., 2: 708-712.
DOI: 10.3844/ajeassp.2009.708.712
Madani, D.A. and A. Dababneh, 2016. Rapid entire body
assessment: A literature review. Am. J. Eng. Applied
Sci., 9: 107-118. DOI: 10.3844/ajeassp.2016.107.118
Malomar, G.E.B., A. Gueye, C. Mbow, V.B. Traore and
A.C. Beye, 2016. Numerical study of natural
convection in a square porous cavity thermally
modulated on both side walls. Am. J. Eng. Applied
Sci., 9: 591-598. DOI: 10.3844/ajeassp.2016.591.598
Mansour, M.A.A., 2016. Developing an anthropometric
database for Saudi students and comparing Saudi
dimensions relative to Turkish and Iranian peoples.
Am. J. Eng. Applied Sci., 9: 547-557.
DOI: 10.3844/ajeassp.2016.547.557

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
336
Maraveas, C., Z.C. Fasoulakis and K.D. Tsavdaridis,
2015. A review of human induced vibrations on
footbridges. Am. J. Eng. Applied Sci., 8: 422-433.
DOI: 10.3844/ajeassp.2015.422.433
Marghany, M. and M. Hashim, 2009. Robust of doppler
centroid for mapping sea surface current by using
radar satellite data. Am. J. Eng. Applied Sci., 2:
781-788. DOI: 10.3844/ajeassp.2009.781.788
Martins, F.R., A.R. Gonçalves and E.B. Pereira, 2016.
Observational study of wind shear in northeastern
Brazil. Am. J. Eng. Applied Sci., 9: 484-504.
DOI: 10.3844/ajeassp.2016.484.504
Marzuki, M.A.L.B., M.H. Abd Halim and A.R.N.
Mohamed, 2015. Determination of natural
frequencies through modal and harmonic analysis of
space frame race car chassis based on ANSYS. Am.
J. Eng. Applied Sci., 8: 538-548.
DOI: 10.3844/ajeassp.2015.538.548
Mavukkandy, M.O., S. Chakraborty, T. Abbasi and S.A.
Abbasi, 2016. A clean-green synthesis of platinum
nanoparticles utilizing a pernicious weed lantana
(Lantana Camara). Am. J. Eng. Applied Sci., 9: 84-
90. DOI: 10.3844/ajeassp.2016.84.90
Minghini, F., N. Tullini and F. Ascione, 2016. Updating
Italian design guide CNR DT-205/2007 in view of
recent research findings: Requirements for pultruded
FRP profiles. Am. J. Eng. Applied Sci., 9: 702-712.
DOI: 10.3844/ajeassp.2016.702.712
Moezi, N., D. Dideban and A. Ketabi, 2008. A novel
integrated SET based inverter for nano power
electronic applications. Am. J. Eng. Applied Sci., 1:
219-222. DOI: 10.3844/ajeassp.2008.219.222
Mohamed, M.A., A.Y. Tuama, M. Makhtar, M.K.
Awang and M. Mamat, 2016. The effect of RSA
exponential key growth on the multi-core
computational resource. Am. J. Eng. Applied Sci., 9:
1054-1061. DOI: 10.3844/ajeassp.2016.1054.1061
Mohan, K.S.R., P. Jayabalan and A. Rajaraman, 2012.
Properties of fly ash based coconut fiber composite.
Am. J. Eng. Applied Sci., 5: 29-34.
DOI: 10.3844/ajeassp.2012.29.34
Mohseni, E. and K.D. Tsavdaridis, 2016. Effect of nano-
alumina on pore structure and durability of class f fly
ash self-compacting mortar. Am. J. Eng. Applied Sci.,
9: 323-333. DOI: 10.3844/ajeassp.2016.323.333
Momani, M.A., T.A. Al Smadi, FM. Al Taweel and K.A.
Ghaidan, 2011. GPS ionospheric total electron content
and scintillation measurements during the October
2003 magnetic storm. Am. J. Eng. Applied Sci., 4:
301-306. DOI: 10.3844/ajeassp.2011.301.306
Momta, P.S., J.O. Omoboh and M.I. Odigi, 2015.
Sedimentology and depositional environment of D2
sand in part of greater ughelli depobelt, onshore
Niger Delta, Nigeria. Am. J. Eng. Applied Sci., 8:
556-566. DOI: 10.3844/ajeassp.2015.556.566
Mondal, R., S. Sahoo and C.S. Rout, 2016. Mixed nickel
cobalt manganese oxide nanorods for supercapacitor
application. Am. J. Eng. Applied Sci., 9: 540-546.
DOI: 10.3844/ajeassp.2016.540.546
Montgomery, J., T.M. Abu-Lebdeh, S.A. Hamoush and
M. Picornell, 2016. Effect of nano-silica on the
compressive strength of harden cement paste at
different stages of hydration. Am. J. Eng. Applied
Sci., 9: 166-177.
DOI: 10.3844/ajeassp.2016.166.177
Moretti, M.L., 2015. Seismic design of masonry and
reinforced concrete infilled frames: A
comprehensive overview. Am. J. Eng. Applied Sci.,
8: 748-766. DOI: 10.3844/ajeassp.2015.748.766
Morse, A., M.M. Mansfield, R.M. Alley, H.A. Kerr and
R.B. Bucinell, 2016b. Traction enhancing products
affect maximum torque at the shoe-floor interface:
A potential increased risk of ACL injury. Am. J.
Eng. Applied Sci., 9: 889-893.
DOI: 10.3844/ajeassp.2016.889.893
Moubarek, T. and A. Gharsallah, 2016. A six-port
reflectometer calibration using Wilkinson power
divider. Am. J. Eng. Applied Sci., 9: 274-280.
DOI: 10.3844/ajeassp.2016.274.280
Nabilou, A., 2016a. Effect of parameters of selection and
replacement drilling bits based on geo-mechanical
factors: (Case study: Gas and oil reservoir in the
Southwest of Iran). Am. J. Eng. Applied Sci., 9:
380-395. DOI: 10.3844/ajeassp.2016.380.395
Nabilou, A., 2016b. Study of the parameters of Steam
Assisted Gravity Drainage (SAGD) method for
enhanced oil recovery in a heavy oil fractured
carbonate reservoir. Am. J. Eng. Applied Sci., 9:
647-658. DOI: 10.3844/ajeassp.2016.647.658
Nachiengtai, T., W. Chim-Oye, S. Teachavorasinskun
and W. Sa-Ngiamvibool, 2008. Identification of
shear band using elastic shear wave propagation.
Am. J. Eng. Applied Sci., 1: 188-191.
DOI: 10.3844/ajeassp.2008.188.191
Nahas, R. and S.P. Kozaitis, 2014. Metric for the fusion
of synthetic and real imagery from multimodal
sensors. Am. J. Eng. Applied Sci., 7: 355-362.
DOI: 10.3844/ajeassp.2014.355.362
Nandhakumar, S., V. Selladurai and S. Sekar, 2009.
Numerical investigation of an industrial robot arm
control problem using haar wavelet series. Am. J.
Eng. Applied Sci., 2: 584-589.
DOI: 10.3844/ajeassp.2009.584.589
Ng, K.C., M.Z. Yusoff, K. Munisamy, H. Hasini and
N.H. Shuaib, 2008. Time-marching method for
computations of high-speed compressible flow on
structured and unstructured grid. Am. J. Eng.
Applied Sci., 1: 89-94.
DOI: 10.3844/ajeassp.2008.89.94

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
337
Obaiys, S.J., Z. Abbas, N.M.A. Nik Long, A.F. Ahmad
and A. Ahmedov et al., 2016. On the general
solution of first-kind hypersingular integral
equations. Am. J. Eng. Applied Sci., 9: 195-201.
DOI: 10.3844/ajeassp.2016.195.201
Odeh, S., R. Faqeh, L. Abu Eid and N. Shamasneh, 2009.
Vision-based obstacle avoidance of mobile robot using
quantized spatial model. Am. J. Eng. Applied Sci., 2:
611-619. DOI: 10.3844/ajeassp.2009.611.619
Ong, A.T., A. Mustapha, Z.B. Ibrahim, S. Ramli and
B.C. Eong, 2015. Real-time automatic inspection
system for the classification of PCB flux defects.
Am. J. Eng. Applied Sci., 8: 504-518.
DOI: 10.3844/ajeassp.2015.504.518
Opafunso, Z.O., I.I. Ozigis and I.A. Adetunde, 2009.
Pneumatic and hydraulic systems in coal fluidized
bed combustor. Am. J. Eng. Applied Sci., 2: 88-95.
DOI: 10.3844/ajeassp.2009.88.95
Orlando, N. and E. Benvenuti, 2016. Advanced XFEM
simulation of pull-out and debonding of steel bars
and FRP-reinforcements in concrete beams. Am. J.
Eng. Applied Sci., 9: 746-754.
DOI: 10.3844/ajeassp.2016.746.754
Pannirselvam, N., P.N. Raghunath and K. Suguna, 2008.
Neural network for performance of glass fibre
reinforced polymer plated RC beams. Am. J. Eng.
Applied Sci., 1: 82-88.
DOI: 10.3844/ajeassp.2008.82.88
Pattanasethanon, S., 2010. The solar tracking system by
using digital solar position sensor. Am. J. Eng. Applied
Sci., 3: 678-682. DOI: 10.3844/ajeassp.2010.678.682
Pérez-de León, G., V.E. Lamberti, R.D. Seals, T.M.
Abu-Lebdeh and S.A. Hamoush, 2016. Gas
atomization of molten metal: Part I. Numerical
modeling conception. Am. J. Eng. Applied Sci., 9:
303-322. DOI: 10.3844/ajeassp.2016.303.322
Padula, F. and V. Perdereau, 2013. An on-line path
planner for industrial manipulators. Int. J. Adv.
Robotic Sys. DOI: 10.5772/55063
Perumaal, S. and N. Jawahar, 2013. Automated
trajectory planner of industrial robot for pick-and-
place task. IJARS. DOI: 10.5772/53940
Petrescu, F. and R. Petrescu, 1995a. Contributions to
optimization of the polynomial motion laws of the
stick from the internal combustion engine
distribution mechanism. Bucharest, 1: 249-256.
Petrescu, F. and R. Petrescu, 1995b. Contributions to the
synthesis of internal combustion engine distribution
mechanisms. Bucharest, 1: 257-264.
Petrescu, F. and R. Petrescu, 1997a. Dynamics of cam
mechanisms (exemplified on the classic distribution
mechanism). Bucharest, 3: 353-358.
Petrescu, F. and R. Petrescu, 1997b. Contributions to the
synthesis of the distribution mechanisms of internal
combustion engines with a Cartesian coordinate
method. Bucharest, 3: 359-364.
Petrescu, F. and R. Petrescu, 1997c. Contributions to
maximizing polynomial laws for the active stroke of
the distribution mechanism from internal
combustion engines. Bucharest, 3: 365-370.
Petrescu, F. and R. Petrescu, 2000a. Synthesis of
distribution mechanisms by the rectangular
(Cartesian) coordinate method. Proceedings of the 8th
National Conference on International Participation,
(CIP' 00), Craiova, Romania, pp: 297-302.
Petrescu, F. and R. Petrescu, 2000b. The design
(synthesis) of cams using the polar coordinate
method (triangle method). Proceedings of the 8th
National Conference on International Participation,
(CIP' 00), Craiova, Romania, pp: 291-296.
Petrescu, F. and R. Petrescu, 2002a. Motion laws for
cams. Proceedings of the International Computer
Assisted Design, National Symposium with
Participation, (SNP' 02), Braşov, pp: 321-326.
Petrescu, F. and R. Petrescu, 2002b. Camshaft dynamics
elements. Proceedings of the International Computer
Assisted Design, National Participation Symposium,
(SNP' 02), Braşov, pp: 327-332.
Petrescu, F. and R. Petrescu, 2003. Some elements
regarding the improvement of the engine design.
Proceedings of the National Symposium,
Descriptive Geometry, Technical Graphics and
Design, (GTD' 03), Braşov, pp: 353-358.
Petrescu, F. and R. Petrescu, 2005a. The cam design for
a better efficiency. Proceedings of the International
Conference on Engineering Graphics and Design,
(EGD’ 05), Bucharest, pp: 245-248.
Petrescu, F. and R. Petrescu, 2005b. Contributions at the
dynamics of cams. Proceedings of the 9th IFToMM
International Symposium on Theory of Machines
and Mechanisms, (TMM’ 05), Bucharest, Romania,
pp: 123-128.
Petrescu, F. and R. Petrescu, 2005c. Determining the
dynamic efficiency of cams. Proceedings of the 9th
IFToMM International Symposium on Theory of
Machines and Mechanisms, (TMM’ 05), Bucharest,
Romania, pp: 129-134.
Petrescu, F. and R. Petrescu, 2005d. An original internal
combustion engine. Proceedings of the 9th IFToMM
International Symposium on Theory of Machines
and Mechanisms, (TMM’ 05), Bucharest, Romania,
pp: 135-140.
Petrescu, F. and R. Petrescu, 2005e. Determining the
mechanical efficiency of Otto engine’s mechanism.
Proceedings of the 9th IFToMM International
Symposium on Theory of Machines and Mechanisms,
(TMM 05), Bucharest, Romania, pp: 141-146.
Petrescu, F.I. and R.V. Petrescu, 2011a. Mechanical
Systems, Serial and Parallel (Romanian). 1st Edn.,
LULU Publisher, London, UK, pp: 124.
Petrescu, FIT. and RV. Petrescu, 2011b. Trenuri
Planetare. 1st Edn., Createspace Independent Pub.,
ISBN-13: 978-1468030419, pp: 104.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
338
Petrescu, F.I. and R.V. Petrescu, 2012a. Kinematics of
the planar quadrilateral mechanism. ENGEVISTA,
14: 345-348.
Petrescu, F.I. and R.V. Petrescu, 2012b. Mecatronica-
Sisteme Seriale si Paralele. 1st Edn., Create Space
Publisher, USA, pp: 128.
Petrescu, F.I. and R.V. Petrescu, 2013a. Cinematics of
the 3R dyad. ENGEVISTA, 15: 118-124.
Petrescu, F.I.T. and R.V. Petrescu, 2013b. Forces and
efficiency of cams. Int. Rev. Mech. Eng., 7: 507-511.
Petrescu, F.I.T. and R.V. Petrescu, 2013c. Cams with
high efficiency. Int. Rev. Mech. Eng., 7: 599-606.
Petrescu, F.I.T. and R.V. Petrescu, 2013d. An algorithm
for setting the dynamic parameters of the classic
distribution mechanism. Int. Rev. Modell. Simulat.,
6: 1637-1641.
Petrescu, F.I.T. and R.V. Petrescu, 2013e. Dynamic
synthesis of the rotary cam and translated tappet
with roll. Int. Rev. Modell. Simulat., 6: 600-607.
Petrescu, F.I.T. and R.V. Petrescu, 2014a. Parallel
moving mechanical systems. Independent J.
Manage. Product., 5: 564-580.
Petrescu, F.I.T. and R.V. Petrescu, 2014b. Cam gears
dynamics in the classic distribution. Independent J.
Manage. Product., 5: 166-185.
Petrescu, F.I.T. and R.V. Petrescu, 2014c. High-
efficiency gears synthesis by avoid the interferences.
Independent J. Manage. Product., 5: 275-298.
Petrescu, F.I.T. and R.V. Petrescu, 2014d. Gear design.
J. ENGEVISTA, 16: 313-328.
Petrescu, F.I.T. and R.V. Petrescu, 2014e. Kinetostatic
of the 3R dyad (or 2R module). J. ENGEVISTA, 16:
314-321.
Petrescu, F.I.T. and R.V. Petrescu, 2014f. Balancing
Otto engines. Int. Rev. Mech. Eng., 8: 473-480.
Petrescu, F.I.T. and R.V. Petrescu, 2014g. Machine
equations to the classical distribution. Int. Rev.
Mech. Eng., 8: 309-316.
Petrescu, F.I.T. and R.V. Petrescu, 2014h. Forces of
internal combustion heat engines. Int. Rev. Modell.
Simulat., 7: 206-212.
Petrescu, F.I.T. and R.V. Petrescu, 2014i. Determination
of the yield of internal combustion thermal engines.
Int. Rev. Mech. Eng., 8: 62-67.
Petrescu, F.I.T. and R.V. Petrescu, 2015a. Forces at the
main mechanism of a railbound forging
manipulator. Independent J. Manage. Product., 6:
904-921.
Petrescu, F.I.T. and R.V. Petrescu, 2015b. Kinematics at
the main mechanism of a railbound forging
manipulator. Independent J. Manage. Product., 6:
711-729.
Petrescu, F.I.T. and R.V. Petrescu, 2015c. Machine
motion equations. Independent J. Manage. Product.,
6: 773-802.
Petrescu F.I.T. and R.V. Petrescu, 2015d. Presenting a
railbound forging manipulator. Applied Mech.
Mater., 762: 219-224.
Petrescu, F.I.T. and R.V. Petrescu, 2015e. About the
anthropomorphic robots. J. ENGEVISTA, 17: 1-15.
Petrescu, F.I. and R.V. Petrescu, 2016a. Parallel moving
mechanical systems kinematics. ENGEVISTA, 18:
455-491.
Petrescu, F.I. and R.V. Petrescu, 2016b. Direct and
inverse kinematics to the anthropomorphic robots.
ENGEVISTA, 18: 109-124.
Petrescu, F.I. and R.V. Petrescu, 2016c. Dynamic
cinematic to a structure 2R. Revista Geintec-Gestao
Inovacao E Tecnol., 6: 3143-3154.
Petrescu, FIT. and R.V. Petrescu, 2016d. An Otto engine
dynamic model. Independent J. Manage. Product., 7:
038-048.
Petrescu, R.V., R. Aversa, A. Apicella and F.I. Petrescu,
2016. Future medicine services robotics. Am. J.
Eng. Applied Sci., 9: 1062-1087.
DOI: 10.3844/ajeassp.2016.1062.1087
Petrescu, F.I., B. Grecu, A. Comanescu and R.V.
Petrescu, 2009. Some mechanical design elements.
Proceeding of the International Conference on
Computational Mechanics and Virtual Engineering,
(MVE’ 09), Braşov, pp: 520-525.
Petrescu, F.I.T., 2008. Theoretical and applied
contributions about the dynamic of planar
mechanisms with superior linkages. Ph.D. Thesis,
Bucharest Polytechnic University.
Petrescu, F.I.T., 2011. Teoria Mecanismelor si a
Masinilor: Curs Si Aplicatii. 1st Edn., CreateSpace
Independent Publishing Platform. ISBN-10:
1468015826. pp: 432.
Petrescu, F.I.T., 2015a. Geometrical synthesis of the
distribution mechanisms. Am. J. Eng. Applied Sci.,
8: 63-81. DOI: 10.3844/ajeassp.2015.63.81
Petrescu, F.I.T., 2015b. Machine motion equations at the
internal combustion heat engines. Am. J. Eng.
Applied Sci., 8: 127-137.
DOI: 10.3844/ajeassp.2015.127.137
Petrescu, F.I.T., A. Apicella, A. Raffaella, RV. Petrescu
and J.K. Calautit et al., 2016. Something about the
mechanical moment of inertia. Am. J. Applied Sci.,
13: 1085-1090.
DOI: 10.3844/ajassp.2016.1085.1090
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017a. Yield at thermal engines
internal combustion. Am. J. Eng. Applied Sci., 10:
243-251. DOI: 10.3844/ajeassp.2017.243.251
Petrescu, R.V., R. Aversa, B. Akash, B. Ronald and J.
Corchado et al., 2017b. Velocities and accelerations
at the 3R mechatronic systems. Am. J. Eng. Applied
Sci., 10: 252-263.
DOI: 10.3844/ajeassp.2017.252.263

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
339
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017c. Anthropomorphic solid
structures n-r kinematics. Am. J. Eng. Applied Sci.,
10: 279-291. DOI: 10.3844/ajeassp.2017.279.291
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017d. Inverse kinematics at the
anthropomorphic robots, by a trigonometric method.
Am. J. Eng. Applied Sci., 10: 394-411.
DOI: 10.3844/ajeassp.2017.394.411
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017e. Forces at internal
combustion engines. Am. J. Eng. Applied Sci., 10:
382-393. DOI: 10.3844/ajeassp.2017.382.393
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017f. Gears-Part I. Am. J. Eng.
Applied Sci., 10: 457-472.
DOI: 10.3844/ajeassp.2017.457.472
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017g. Gears-part II. Am. J. Eng.
Applied Sci., 10: 473-483.
DOI: 10.3844/ajeassp.2017.473.483
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017h. Cam-gears forces,
velocities, powers and efficiency. Am. J. Eng.
Applied Sci., 10: 491-505.
DOI: 10.3844/ajeassp.2017.491.505
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017i. Dynamics of mechanisms
with cams illustrated in the classical distribution.
Am. J. Eng. Applied Sci., 10: 551-567.
DOI: 10.3844/ajeassp.2017.551.567
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017j. Testing by non-destructive
control. Am. J. Eng. Applied Sci., 10: 568-583.
DOI: 10.3844/ajeassp.2017.568.583
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2017k. Transportation engineering. Am. J.
Eng. Applied Sci., 10: 685-702.
DOI: 10.3844/ajeassp.2017.685.702
Petrescu, R.V., R. Aversa, S. Kozaitis, A. Apicella and
F.I.T. Petrescu, 2017l. The quality of transport and
environmental protection, part I. Am. J. Eng.
Applied Sci., 10: 738-755.
DOI: 10.3844/ajeassp.2017.738.755
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017m. Modern propulsions for
aerospace-a review. J. Aircraft Spacecraft Technol.,
1: 1-8. DOI: 10.3844/jastsp.2017.1.8
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017n. Modern propulsions for
aerospace-part II. J. Aircraft Spacecraft Technol., 1:
9-17. DOI: 10.3844/jastsp.2017.9.17
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017o. History of aviation-a short
review. J. Aircraft Spacecraft Technol., 1: 30-49.
DOI: 10.3844/jastsp.2017.30.49
Petrescu, R.V., R. Aversa, B. Akash, R. Bucinell and J.
Corchado et al., 2017p. Lockheed martin-a short
review. J. Aircraft Spacecraft Technol., 1: 50-68.
DOI: 10.3844/jastsp.2017.50.68
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017q. Our universe. J. Aircraft Spacecraft
Technol., 1: 69-79. DOI: 10.3844/jastsp.2017.69.79
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017r. What is a UFO? J. Aircraft
Spacecraft Technol., 1: 80-90.
DOI: 10.3844/jastsp.2017.80.90
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017s. About bell helicopter FCX-001
concept aircraft-a short review. J. Aircraft
Spacecraft Technol., 1: 91-96.
DOI: 10.3844/jastsp.2017.91.96
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017t. Home at airbus. J. Aircraft
Spacecraft Technol., 1: 97-118.
DOI: 10.3844/jastsp.2017.97.118
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017u. Airlander. J. Aircraft Spacecraft
Technol., 1: 119-148.
DOI: 10.3844/jastsp.2017.119.148
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017v. When boeing is dreaming-a
review. J. Aircraft Spacecraft Technol., 1: 149-161.
DOI: 10.3844/jastsp.2017.149.161
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017w. About Northrop Grumman. J.
Aircraft Spacecraft Technol., 1: 162-185.
DOI: 10.3844/jastsp.2017.162.185
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017x. Some special aircraft. J. Aircraft
Spacecraft Technol., 1: 186-203.
DOI: 10.3844/jastsp.2017.186.203
Petrescu, R.V., R. Aversa, B. Akash, J. Corchado and F.
Berto et al., 2017y. About helicopters. J. Aircraft
Spacecraft Technol., 1: 204-223.
DOI: 10.3844/jastsp.2017.204.223
Petrescu, R.V., R. Aversa, B. Akash, F. Berto and A.
Apicella et al., 2017z. The modern flight. J. Aircraft
Spacecraft Technol., 1: 224-233.
DOI: 10.3844/jastsp.2017.224.233
Petrescu, R.V., R. Aversa, B. Akash, F. Berto and A.
Apicella et al., 2017aa. Sustainable energy for
aerospace vessels. J. Aircraft Spacecraft Technol., 1:
234-240. DOI: 10.3844/jastsp.2017.234.240
Petrescu, R.V., R. Aversa, B. Akash, F. Berto and A.
Apicella et al., 2017ab. Unmanned helicopters. J.
Aircraft Spacecraft Technol., 1: 241-248.
DOI: 10.3844/jastsp.2017.241.248
Petrescu, R.V., R. Aversa, B. Akash, F. Berto and A.
Apicella et al., 2017ac. Project HARP. J. Aircraft
Spacecraft Technol., 1: 249-257.
DOI: 10.3844/jastsp.2017.249.257

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
340
Petrescu, R.V., R. Aversa, B. Akash, F. Berto and A.
Apicella et al., 2017ad. Presentation of Romanian
engineers who contributed to the development of
global aeronautics-part I. J. Aircraft Spacecraft
Technol., 1: 258-271.
DOI: 10.3844/jastsp.2017.258.271
Petrescu, R.V., R. Aversa, B. Akash, F. Berto and A.
Apicella et al., 2017ae. A first-class ticket to the
planet mars, please. J. Aircraft Spacecraft
Technol., 1: 272-281.
DOI: 10.3844/jastsp.2017.272.281
Petrescu, R.V., R. Aversa, A. Apicella, M.M. Mirsayar
and S. Kozaitis et al., 2018a. NASA started a
propeller set on board voyager 1 after 37 years of
break. Am. J. Eng. Applied Sci., 11: 66-77.
DOI: 10.3844/ajeassp.2018.66.77
Petrescu, R.V., R. Aversa, A. Apicella, M.M. Mirsayar
and S. Kozaitis et al., 2018b. There is life on mars?
Am. J. Eng. Applied Sci., 11: 78-91.
DOI: 10.3844/ajeassp.2018.78.91
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2018c. Friendly environmental transport.
Am. J. Eng. Applied Sci., 11: 154-165.
DOI: 10.3844/ajeassp.2018.154.165
Petrescu, R.V., R. Aversa, B. Akash, T.M. Abu-Lebdeh
and A. Apicella et al., 2018d. Buses running on gas.
Am. J. Eng. Applied Sci., 11: 186-201.
DOI: 10.3844/ajeassp.2018.186.201
Petrescu, R.V., R. Aversa, B. Akash, T.M. Abu-Lebdeh
and A. Apicella et al., 2018e. Some aspects of the
structure of planar mechanisms. Am. J. Eng.
Applied Sci., 11: 245-259.
DOI: 10.3844/ajeassp.2018.245.259
Petrescu, RV., R. Aversa, T.M. Abu-Lebdeh, A.
Apicella and F.I.T. Petrescu, 2018f. The forces of
a simple carrier manipulator. Am. J. Eng. Applied
Sci., 11: 260-272.
DOI: 10.3844/ajeassp.2018.260.272
Petrescu, RV., R. Aversa, T.M. Abu-Lebdeh, A. Apicella
and F.I.T. Petrescu, 2018g. The dynamics of the otto
engine. Am. J. Eng. Applied Sci., 11: 273-287.
DOI: 10.3844/ajeassp.2018.273.287
Petrescu, RV., R. Aversa, T.M. Abu-Lebdeh, A. Apicella
and F.I.T. Petrescu, 2018h. NASA satellites help us
to quickly detect forest fires. Am. J. Eng. Applied
Sci., 11: 288-296.
DOI: 10.3844/ajeassp.2018.288.296
Petrescu, RV., R. Aversa, T.M. Abu-Lebdeh, A. Apicella
and F.I.T. Petrescu, 2018i. Kinematics of a
mechanism with a triad. Am. J. Eng. Applied Sci.,
11: 297-308. DOI: 10.3844/ajeassp.2018.297.308
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2018j. Romanian engineering "on the
wings of the wind". J. Aircraft Spacecraft Technol.,
2: 1-18. DOI: 10.3844/jastsp.2018.1.18
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2018k. NASA Data used to discover
eighth planet circling distant star. J. Aircraft
Spacecraft Technol., 2: 19-30.
DOI: 10.3844/jastsp.2018.19.30
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2018l. NASA has found the most distant
black hole. J. Aircraft Spacecraft Technol., 2: 31-39.
DOI: 10.3844/jastsp.2018.31.39
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2018m. Nasa selects concepts for a new
mission to titan, the moon of saturn. J. Aircraft
Spacecraft Technol., 2: 40-52.
DOI: 10.3844/jastsp.2018.40.52
Petrescu, R.V., R. Aversa, A. Apicella and F.I.T.
Petrescu, 2018n. NASA sees first in 2018 the direct
proof of ozone hole recovery. J. Aircraft Spacecraft
Technol., 2: 53-64. DOI: 10.3844/jastsp.2018.53.64
Pisello, A.L., G. Pignatta, C. Piselli, V.L. Castaldo and
F. Cotana, 2016. Investigating the dynamic thermal
behavior of building envelope in summer conditions
by means of in-field continuous monitoring. Am. J.
Eng. Applied Sci., 9: 505-519.
DOI: 10.3844/ajeassp.2016.505.519
Pourmahmoud, N., 2008. Rarefied gas flow modeling
inside rotating circular cylinder. Am. J. Eng.
Applied Sci., 1: 62-65.
DOI: 10.3844/ajeassp.2008.62.65
Pravettoni, M., C.S.P. Lòpez and R.P. Kenny, 2016.
Impact of the edges of a backside diffusive reflector
on the external quantum efficiency of luminescent
solar concentrators: Experimental and computational
approach. Am. J. Eng. Applied Sci., 9: 53-63.
DOI: 10.3844/ajeassp.2016.53.63
Qutbodin, K., 2010. Merging autopilot/flight control and
navigation-flight management systems. Am. J. Eng.
Applied Sci., 3: 629-630.
DOI: 10.3844/ajeassp.2010.629.630
Rajbhandari, S., Z. Ghassemlooy and M. Angelova,
2011. The performance of a dual header pulse
interval modulation in the presence of artificial light
interferences in an indoor optical wireless
communications channel with wavelet denoising.
Am. J. Eng. Applied Sci., 4: 513-519.
DOI: 10.3844/ajeassp.2011.513.519
Rajput, R.S., S. Pandey and S. Bhadauria, 2016.
Correlation of biodiversity of algal genera with
special reference to the waste water effluents from
industries. Am. J. Eng. Applied Sci., 9: 1127-1133.
DOI: 10.3844/ajeassp.2016.1127.1133
Rajupillai, K., S. Palaniammal and K. Bommuraju, 2015.
Computational intelligence and application of frame
theory in communication systems. Am. J. Eng.
Applied Sci., 8: 633-637.
DOI: 10.3844/ajeassp.2015.633.637

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
341
Raptis, K.G., G.A. Papadopoulos, T.N. Costopoulos and
A.D. Tsolakis, 2011. Experimental study of load
sharing in roller-bearing contact by caustics and
photoelasticity. Am. J. Eng. Applied Sci., 4: 294-
300. DOI: 10.3844/ajeassp.2011.294.300
Rama, G., D. Marinkovic and M. Zehn, 2016. Efficient
co-rotational 3-node shell element. Am. J. Eng.
Applied Sci., 9: 420-431.
DOI: 10.3844/ajeassp.2016.420.431
Rea, P. and E. Ottaviano, 2016. Analysis and mechanical
design solutions for sit-to-stand assisting devices.
Am. J. Eng. Applied Sci., 9: 1134-1143.
DOI: 10.3844/ajeassp.2016.1134.1143
Rhode-Barbarigos, L., V. Charpentier, S. Adriaenssens
and O. Baverel, 2015. Dialectic form finding of
structurally integrated adaptive structures. Am. J.
Eng. Applied Sci., 8: 443-454.
DOI: 10.3844/ajeassp.2015.443.454
Riccio, A., U. Caruso, A. Raimondo and A. Sellitto,
2016a. Robustness of XFEM method for the
simulation of cracks propagation in fracture
mechanics problems. Am. J. Eng. Applied Sci., 9:
599-610. DOI: 10.3844/ajeassp.2016.599.610
Riccio, A., R. Cristiano and S. Saputo, 2016b. A brief
introduction to the bird strike numerical simulation.
Am. J. Eng. Applied Sci., 9: 946-950.
DOI: 10.3844/ajeassp.2016.946.950
Rich, F. and M.A. Badar, 2016. Statistical analysis of
auto dilution Vs manual dilution process in
inductively coupled plasma spectrometer tests. Am.
J. Eng. Applied Sci., 9: 611-624.
DOI: 10.3844/ajeassp.2016.611.624
Rohit, K. and S. Dixit, 2016. Mechanical properties of
waste Biaxially Oriented Polypropylene metallized
films (BOPP), LLDPE: LDPE films with sisal
fibres. Am. J. Eng. Applied Sci., 9: 913-920.
DOI: 10.3844/ajeassp.2016.913.920
Rulkov, N.F., A.M. Hunt, P.N. Rulkov and A.G.
Maksimov, 2016. Quantization of map-based
neuronal model for embedded simulations of
neurobiological networks in real-time. Am. J. Eng.
Applied Sci., 9: 973-984.
DOI: 10.3844/ajeassp.2016.973.984
Saikia, A. and N. Karak, 2016. Castor oil based
epoxy/clay nanocomposite for advanced
applications. Am. J. Eng. Applied Sci., 9: 31-40.
DOI: 10.3844/ajeassp.2016.31.40
Sallami, A., N. Zanzouri and M. Ksouri, 2016. Robust
diagnosis of a DC motor by bond graph approach.
Am. J. Eng. Applied Sci., 9: 432-438.
DOI: 10.3844/ajeassp.2016.432.438
Samantaray, K.S., S. Sahoo and C.S. Rout, 2016.
Hydrothermal synthesis of CuWO4-reduced
graphene oxide hybrids and supercapacitor
application. Am. J. Eng. Applied Sci., 9: 584-590.
DOI: 10.3844/ajeassp.2016.584.590
Santos, F.A. and C. Bedon, 2016. Preliminary
experimental and finite-element numerical
assessment of the structural performance of SMA-
reinforced GFRP systems. Am. J. Eng. Applied Sci.,
9: 692-701. DOI: 10.3844/ajeassp.2016.692.701
Sava, I., 1970. Contributions to dynamics and
optimization of income mechanism synthesis. Ph.D.
Thesis, I.P.B.
Semin, A.R. Ismail and R.A. Bakar, 2009a. Combustion
temperature effect of diesel engine convert to
compressed natural gas engine. Am. J. Eng. Applied
Sci., 2: 212-216.
DOI: 10.3844/ajeassp.2009.212.216
Semin, A.R. Ismail and R.A. Bakar, 2009b. Effect of
diesel engine converted to sequential port injection
compressed natural gas engine on the cylinder
pressure Vs crank angle in variation engine speeds.
Am. J. Eng. Applied Sci., 2: 154-159.
DOI: 10.3844/ajeassp.2009.154.159
Semin S., A.R. Ismail and R.A. Bakar, 2009c. Diesel
engine convert to port injection CNG engine using
gaseous injector nozzle multi holes geometries
improvement: A review. Am. J. Eng. Applied Sci.,
2: 268-278. DOI: 10.3844/ajeassp.2009.268.278
Semin and R.A. Bakar, 2008. A technical review of
compressed natural gas as an alternative fuel for
internal combustion engines. Am. J. Eng. Applied
Sci., 1: 302-311.
DOI: 10.3844/ajeassp.2008.302.311
Sepúlveda, J.A.M., 2016. Outlook of municipal solid
waste in Bogota (Colombia). Am. J. Eng. Applied
Sci., 9: 477-483.
DOI: 10.3844/ajeassp.2016.477.483
Serebrennikov, A., D. Serebrennikov and Z. Hakimov,
2016. Polyethylene pipeline bending stresses at an
installation. Am. J. Eng. Applied Sci., 9: 350-355.
DOI: 10.3844/ajeassp.2016.350.355
Shanmugam, K., 2016. Flow dynamic behavior of fish
oil/silver nitrate solution in mini-channel, effect of
alkane addition on flow pattern and interfacial
tension. Am. J. Eng. Applied Sci., 9: 236-250.
DOI: 10.3844/ajeassp.2016.236.250
Shruti, 2016. Comparison in cover media under
stegnography: Digital media by hide and seek
approach. Am. J. Eng. Applied Sci., 9: 297-302.
DOI: 10.3844/ajeassp.2016.297.302
Stavridou, N., E. Efthymiou and C.C. Baniotopoulos,
2015a. Welded connections of wind turbine towers
under fatigue loading: Finite element analysis and
comparative study. Am. J. Eng. Applied Sci., 8:
489-503. DOI: 10.3844/ajeassp.2015.489.503
Stavridou, N., E. Efthymiou and C.C. Baniotopoulos,
2015b. Verification of anchoring in foundations of
wind turbine towers. Am. J. Eng. Applied Sci., 8:
717-729. DOI: 10.3844/ajeassp.2015.717.729

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
342
Suarez, L., T.M. Abu-Lebdeh, M. Picornell and S.A.
Hamoush, 2016. Investigating the role of fly ash and
silica fume in the cement hydration process. Am. J.
Eng. Applied Sci., 9: 134-145.
DOI: 10.3844/ajeassp.2016.134.145
Syahrullah, O.I. and N. Sinaga, 2016. Optimization and
prediction of motorcycle injection system performance
with feed-forward back-propagation method Artificial
Neural Network (ANN). Am. J. Eng. Applied Sci., 9:
222-235. DOI: 10.3844/ajeassp.2016.222.235
Sylvester, O., I. Bibobra and O.N. Ogbon, 2015a. Well
test and PTA for reservoir characterization of key
properties. Am. J. Eng. Applied Sci., 8: 638-647.
DOI: 10.3844/ajeassp.2015.638.647
Sylvester, O., I. Bibobra and O. Augustina, 2015b.
Report on the evaluation of Ugua J2 and J3 reservoir
performance. Am. J. Eng. Applied Sci., 8: 678-688.
DOI: 10.3844/ajeassp.2015.678.688
Taher, S.A., R. Hematti and M. Nemati, 2008.
Comparison of different control strategies in GA-
based optimized UPFC controller in electric power
systems. Am. J. Eng. Applied Sci., 1: 45-52.
DOI: 10.3844/ajeassp.2008.45.52
Takeuchi, T., Y. Kinouchi, R. Matsui and T. Ogawa,
2015. Optimal arrangement of energy-dissipating
members for seismic retrofitting of truss structures.
Am. J. Eng. Applied Sci., 8: 455-464.
DOI: 10.3844/ajeassp.2015.455.464
Taraza, D., N.A. Henein and W. Bryzik, 2001. The
frequency analysis of the crankshaft's speed
variation: A reliable tool for diesel engine diagnosis.
J. Eng. Gas Turbines Power, 123: 428-432.
DOI: 10.1115/1.1359479
Tesar, D. and G.K. Matthew, 1974. The Design of
Modeled Cam Systems. In: Cams and Cam
Mechanisms, Rees Jones, J. (Ed.), MEP, London
and Birmingham, Alabama.
Theansuwan, W. and K. Triratanasirichai, 2011. The
biodiesel production from roast Thai sausage oil by
transesterification reaction. Am. J. Eng. Applied
Sci., 4: 130-132.
DOI: 10.3844/ajeassp.2011.130.132
Thongwan, T., A. Kangrang and S. Homwuttiwong,
2011. An estimation of rainfall using fuzzy set-
genetic algorithms model. Am. J. Eng. Applied Sci.,
4: 77-81. DOI: 10.3844/ajeassp.2011.77.81
Tourab, W., A. Babouri and M. Nemamcha, 2011.
Experimental study of electromagnetic environment
in the vicinity of high voltage lines. Am. J. Eng.
Applied Sci., 4: 209-213.
DOI: 10.3844/ajeassp.2011.209.213
Tsolakis, A.D. and K.G. Raptis, 2011. Comparison of
maximum gear-tooth operating bending stresses
derived from niemann's analytical procedure and the
finite element method. Am. J. Eng. Applied Sci., 4:
350-354. DOI: 10.3844/ajeassp.2011.350.354
Vernardos, S.M. and C.J. Gantes, 2015. Cross-section
optimization of sandwich-type cylindrical wind
turbine towers. Am. J. Eng. Applied Sci., 8: 471-
480. DOI: 10.3844/ajeassp.2015.471.480
Wang, L., T. Liu, Y. Zhang and X. Yuan, 2016. A
methodology for continuous evaluation of cloud
resiliency. Am. J. Eng. Applied Sci., 9: 264-273.
DOI: 10.3844/ajeassp.2016.264.273
Wang, L., G. Wang and C.A. Alexander, 2015.
Confluences among big data, finite element analysis
and high-performance computing. Am. J. Eng. Applied
Sci., 8: 767-774. DOI: 10.3844/ajeassp.2015.767.774
Wang, J. and Y. Yagi, 2016. Fragment-based visual
tracking with multiple representations. Am. J. Eng.
Applied Sci., 9: 187-194.
DOI: 10.3844/ajeassp.2016.187.194
Waters, C., S. Ajinola and M. Salih, 2016. Dissolution
sintering technique to create porous copper with
sodium chloride using polyvinyl alcohol solution
through powder metallurgy. Am. J. Eng. Applied
Sci. 9: 155-165. DOI: 10.3844/ajeassp.2016.155.165
Wessels, L. and H. Raad, 2016. Recent advances in point
of care diagnostic tools: A review. Am. J. Eng.
Applied Sci., 9: 1088-1095.
DOI: 10.3844/ajeassp.2016.1088.1095
Wiederrich, J.L. and B. Roth, 1974. Design of Low
Vibration Cam Profiles. In: Cams and Cam
Mechanisms, Rees Jones, J. (Ed.), MEP, London
and Birmingham, Alabama.
Yan, C., F. Gao and W. Guo, 2009. Coordinated
kinematic modeling for motion planning of heavy-
duty manipulators in an integrated open-die forging
center. J. Eng. Manufacture, 223: 1299-1313.
Yang, M.F. and Y. Lin, 2015. Process is unreliable and
quantity discounts supply chain integration
inventory model. Am. J. Eng. Applied Sci., 8: 602-
610. DOI: 10.3844/ajeassp.2015.602.610
Yeargin, R., R. Ramey and C. Waters, 2016. Porosity
analysis in porous brass using dual approaches. Am.
J. Eng. Applied Sci., 9: 91-97.
DOI: 10.3844/ajeassp.2016.91.97
You, M., X. Huang, M. Lin, Q. Tong and X. Li et al.,
2016. Preparation of LiCoMnO4 assisted by
hydrothermal approach and its electrochemical
performance. Am. J. Eng. Applied Sci., 9: 396-405.
DOI: 10.3844/ajeassp.2016.396.405
Zeferino, R.S., J.A.R. Ramón, E. de Anda Reyes, R.S.
González and U. Pal, 2016. Large scale synthesis of
ZnO nanostructures of different morphologies
through solvent-free mechanochemical synthesis
and their application in photocatalytic dye
degradation. Am. J. Eng. Applied Sci., 9: 41-52.
DOI: 10.3844/ajeassp.2016.41.52
Zhao, K., H. Wang, G.L. Chen, Z.Q. Lin and Y.B. He,
2010. Compliance process analysis for forging
manipulator. J. Mech. Eng., 46: 27-34.

Relly Victoria Vir gil Petrescu / Journa l of Mechatronics and Robot ics 2019, Volume 3: 301.343
10.3844/jmrsp.2019.301.343
343
Zhao, B., 2013. Identification of multi-cracks in the gate
rotor shaft based on the wavelet finite element
method. Am. J. Eng. Applied Sci., 6: 309-319.
DOI: 10.3844/ajeassp.2013.309.319
Zheng, H. and S. Li, 2016. Fast and robust maximum
power point tracking for solar photovoltaic systems.
Am. J. Eng. Applied Sci., 9: 755-769.
DOI: 10.3844/ajeassp.2016.755.769
Zotos, I.S. and T.N. Costopoulos, 2009. On the use of
rolling element bearings' models in Precision
maintenance. Am. J. Eng. Applied Sci., 2: 344-352.
DOI: 10.3844/ajeassp.2009.344.352
Zulkifli, R., K. Sopian, S. Abdullah and M.S. Takriff,
2008. Effect of pulsating circular hot air jet
frequencies on local and average nusselt number.
Am. J. Eng. Applied Sci., 1: 57-61.
DOI: 10.3844/ajeassp.2008.57.61
Zulkifli, R., K. Sopian, S. Abdullah and M.S. Takriff,
2009. Experimental study of flow structures of
circular pulsating air jet. Am. J. Eng. Applied Sci.,
2: 171-175. DOI: 10.3844/ajeassp.2009.171.175
Zurfi, A. and J. Zhang, 2016a. Model identification and
wall-plug efficiency measurement of white LED
modules. Am. J. Eng. Applied Sci., 9: 412-419.
DOI: 10.3844/ajeassp.2016.412.419
Zurfi, A. and J. Zhang, 2016b. Exploitation of battery
energy storage in load frequency control-a literature
survey. Am. J. Eng. Applied Sci., 9: 1173-1188.
DOI: 10.3844/ajeassp.2016.1173.1188
Source of Figures
Figure 1:
https://upload.wikimedia.org/wikipedia/commons/thumb
/7/70/Viking_Lander_Model.jpg/1024px-
Viking_Lander_Model.jpg
Figure 2:
https://upload.wikimedia.org/wikipedia/commons/b/bc/
Mariner_3_and_4.jpg
Figure 3:
https://en.wikipedia.org/wiki/New_Horizons#/media/File
:New_Horizons_Transparent.png
Figure 4:
https://voyager.jpl.nasa.gov/mission/spacecraft/instrume
nts/
Figure 5:
https://upload.wikimedia.org/wikipedia/commons/thumb
/b/b2/Cassini_Saturn_Orbit_Insertion.jpg/1024px-
Cassini_Saturn_Orbit_Insertion.jpg
Figure 6:
https://upload.wikimedia.org/wikipedia/commons/thumb
/1/1f/Saturn%27s_rings_in_visible_light_and_radio.jpg/
1920px-
Saturn%27s_rings_in_visible_light_and_radio.jpg