Jose Gonzalez del Amo

Jose Gonzalez del Amo
European Space Agency | ESA · Department of Science, Applications and Future Technologies

MS in Applied Physics and ME in Space System Engineering

About

149
Publications
42,671
Reads
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636
Citations
Citations since 2016
58 Research Items
388 Citations
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Introduction
Jose Gonzalez del Amo currently works at the Department of Science, Applications and Future Technologies, European Space Agency (ESA). Jose does research in Aerospace Engineering, Spectroscopy and Astrochemistry. Their current project is 'Electric Propulsion Innovation and Competitivity.' José GONZALEZ DEL AMO is the Head of the Electric Propulsion Section at ESA since October 2003 and the ESA Propulsion Laboratory Manager since 2004. He was before Electric propulsion Engineer in the Electric Propulsion Section at ESA from 1991 to 2003.
Additional affiliations
October 2003 - April 2020
European Space Agency
Position
  • Head of Department
April 1991 - October 2003
European Space Agency
Position
  • Engineer
Description
  • Electric Propulsion Engineer
Education
September 1998 - September 1999
Delft University of Technology
Field of study
  • Space Systems Engineering
September 1983 - September 1988
Universidad Autónoma de Madrid
Field of study
  • Applied Physics

Publications

Publications (149)
Conference Paper
Full-text available
ArianeGroup GmbH has continued the development and test of a neutralizer with rf-ionization instead of thermionic electron emitters for their RIT-µX propulsion system. The proof of concept has been successfully completed. During a 2 x 2,500 hour endurance test the RIT-µX thrusters demonstrated their high reliability. Valuable data for erosion model...
Conference Paper
Full-text available
Space mission planners have always tried to reduce the amount of propellant required to bring the spacecraft to the final orbit and reach the required lifetime. Electric propulsion can help them to achieve this goal due to the high specific impulse and in many cases brings huge benefits as in the case of orbit raising manoeuvres for GEO telecommuni...
Conference Paper
Full-text available
Space propulsion systems undergo thorough ground testing before being deployed in space. We report the results of a functional verification and performance characterisation test campaign of an integrated electric propulsion system for cubesats and microsats with purely electric thrust vectoring capability and no moving parts. Visualisations of the...
Conference Paper
Propulsion of satellites and of spacecrafts near the giant planets and especially in the Neptune vicinity by using as propellant their atmospheres, composed mainly by molecular hydrogen and helium, is addressed. Modeling of such mixtures aiming to evaluate their properties and to support their use as propellant in ISRU technology is provided and di...
Conference Paper
Full-text available
The four component Detailed Global Model 4CDGM, used previously to characterize electric thrusters meant for propulsion in the LEO and VLEO regions, is used here in studying thrusters meant for ISRU propulsion in extremely low altitudes within 120 km and 160 km. Satellites in this region, following Extremely Low Earth Orbits (ELEO) are considered a...
Article
ESA’s Next Generation Gravity Mission (NGGM) is a candidate Mission of Opportunity for ESA-NASA cooperation in the frame of the MAss change and Geosciences International Constellation (MAGIC) . The mission aims at enabling long-term monitoring of the temporal variations of Earth’s gravity field at relatively high temporal (down to 3 days) and incre...
Conference Paper
Full-text available
2020/2021 orbit calculations (DLR Bremen + MAI Moscow): 3 Orbits for one non-human MARS/EUROPA-INPPS flagship 1. Orbit Earth (11 Oct 2026) => Mars (28 Jan 2028); 2. Orbit Mars (22 Sept 2028) => Earth (29 Jul 2029); 3. Orbit Earth (12 Oct 2031) => Jupiter / Europa (6 Dec 2035) 22 ETs (for the INPPS flagship CET): example - gridded CET plate with com...
Conference Paper
Full-text available
Test campaign of a Cubesat equipped with a helicon plasma thruster / Stesina, F.; Corpino, S.; Calvi, D.; Pavarin, D.; Trezzolani, F.; Bellomo, N.; Bosch Borras, E.; Gonzalez Del Amo, J..-(2020), pp. 1-8. ((Intervento presentato al convegno 71st International Astronautical Congress. Original
Preprint
The outer planets of the Solar System (SSys) have atmospheres composed essentially (about 80 %) of hydrogen plus less of 20 % of helium, with very small percentages of additional components. Consequently, modeling of H/He plasma is of paramount importance for the outer planets atmospheres studies. Moreover, if H/He mixtures collected from the outer...
Preprint
Full-text available
The Iodine Detailed Global Model (IDGM) developed by DEDALOS Ltd provides theoretical characterization and optimization of on ground iodine-fueled thruster prototypes, on the basis of Plasma Components Composition (PCC) diagrams and of Functioning Diagrams (FD) and also the background for their Optical Emission Spectroscopy (OES) diagnostics. PCCs...
Article
Full-text available
According to the Global Exploration Roadmap, a Getaway in the lunar vicinity will enable the human exploration of the Moon, paving the way toward Mars and further in the deep space. A reusable transportation system, the Lunar Space Tug (LST), can be a key support transportation system to achieve a continuous and sustainable connection between the E...
Preprint
In Situ Resource Utilization (ISRU) propulsion technology aiming to support missions in various regions of the Solar System, avoids or minimizes all of the difficulties related with the propellant transport. CO2, the main constituent of Mars ATMosphere (MATM) and of Venus ATMosphere (VATM) is considered here as Electric Thruster (ET) propellant for...
Presentation
Full-text available
CO2DGM is a Detailed Global Model (DGM) leading to characterization of CO2-fed Electric Thrusters (ET). Low pressure values from 1 mTorr to 10 mTorr are tackled, with a standard feed of 40 sccm. Disruptive In Situ Resource Utilization (ISRU) technology is addressed.-Besides an improved functioning insight, essentials of Optical Emission Spectroscop...
Conference Paper
Full-text available
The CO2DGM Detailed Global Model is used to characterize electric thrusters using in situ available CO2 as propellant. Low pressure values in the region of 1 mTorr to 10 mTorr with a feed of 40 sccm are addressed. Besides an improved functioning insight, the essentials of optical emission spectroscopy diagnostics and monitoring are provided by this...
Conference Paper
The EOP Directorate of the European Space Agency has contributed and supported the design of a variable specific impulse electrostatic thruster based on Field Emission Electric Propulsion (FEEP), in which a liquid propellant is electrostatically extracted and accelerated to high exhaust velocity. The core element of this propulsion technology is a...
Conference Paper
Full-text available
This paper discusses current test results of the coaxial breech-fed pulsed plasma thruster (PPT) PETRUS. Two major aspects are investigated. First, the influence of different anode geometries to thruster specific parameters like impulse bit, mass bit, and thrust efficiency. Second, a laboratory model of a CubeSat-size Power Processing Unit (PPU) is...
Conference Paper
Full-text available
Plasma diagnostics using Langmuir probes are relatively simple in application, but interpretation of the data is a complex process. The results are sensitive to the vacuum quality and facility effects. The European Space Agency (ESA) and the Institute of Space Systems (IRS) conducted a joint test campaign to identify these facility effects and to e...
Conference Paper
The Strategic Research Cluster (SRC) on Space Electric Propulsion (EP) is the new European Commission (EC) instrument into the European Union's Horizon 2020 research and innovation programme (H2020) to target mid-term and long-term objectives in the space electric propulsion field, considered strategic for Europe. The SRC is implemented through a P...
Conference Paper
Full-text available
The high specific impulse of Electric propulsion systems reduces the amount of propellant required to perform an operation in space. These savings will allow space projects to use smaller launches or increasing the payload. In the commercial arena (telecommunication and constellations space missions), the strong competition among satellite manufact...
Conference Paper
According to the Global Exploration Roadmap, a Getaway in the lunar vicinity will enable the human exploration of the Moon, Mars and the deep space. A reusable transportation system, the Lunar Space Tug (LST), can be the key support to achieve a continuous link between the Earth and the lunar outpost. The complexity of the preliminary design of the...
Conference Paper
Full-text available
Electric propulsion activity in horizon 2020 from European Community
Conference Paper
Full-text available
The new era of space exploration has begun with the intent of expanding the frontiers of knowledge, capability, and opportunities in space, to bring humans back to the Moon before sending them to Mars. One of the first milestones is represented by the settlement of the Deep Space Gateway by the mid 2020’s in the lunar proximity, thanks to the explo...
Conference Paper
Full-text available
To measure the impulse bit of Pulsed Plasma Thrusters developed at the Institute of Space Systems at the University of Stuttgart, an already well-proven high sensitive vertical impulse pendulum is used. Due to the almost frictionless pivot bearings and a high sensitive optical sensor it is possible to perform highly accurate impulse bit measurement...
Conference Paper
Full-text available
ESA activities in Electric propulsion as where envisaged in 2018.
Conference Paper
InDGM, a detailed global model for indium plasma, is used here to evaluate the plasma constitution of an In fed FEEP type electric thruster and to obtain its characterization and functioning description. Theoretical intensities of atomic lines belonging to the first three In spectra are also obtained by InDGM. This is an important property of the m...
Conference Paper
Full-text available
XeDGM, a detailed Xe plasma global model, is summarily described and used to evaluate the plasma components constitution of Helicon type electric thrusters fed by Xe. Characterization and functioning description of the thrusters on the basis of XeDGM are also addressed. One of the XeDGM assets is the calculation of the atomic lines intensities pert...
Conference Paper
Our iodine detailed global plasma model, IDGM, is used here to evaluate the plasma components composition of a Helicon type prototype fed by iodine. Characterization and functioning description of such a prototype on the basis of IDGM are also addressed. One of the IDGM assets is the calculation of spectral lines intensities of the first three spec...
Conference Paper
A four components detailed global model, with Earth atmosphere remnants (nitrogen and oxygen mixtures in atomic and molecular form) as initial components, is used to study the functioning of air-breathing electric thrusters. The latter are of interest to both low and high Earth orbit satellites and to space missions. Theoretical characterization of...
Poster
Full-text available
4CDGM, a four initial components (O, O2 , N, N2) volume averaged detailed global model developed by DEDALOS Ltd, is meant to analyze the functioning of Air-Breathing Electric Thrusters (ABET), to foresee the constitution of their plasma and diagnose it by Optical Emission Spectroscopy (OES). The four components addressed are the main atomic and mol...
Presentation
Full-text available
4CDGM, a four initial components (O, O 2 , N, N 2) volume averaged detailed global model used to analyze the functioning of Electric Thrusters (ET) of Air-Breathing Electric Thrusters (ABET) type, to foresee the plasma constitution and to diagnose it by Optical Emission Spectroscopy (OES) ♣ Plasma Component Composition (PCC) and Functioning Diagram...
Presentation
Full-text available
Paper presentation slides. InDGM, a detailed global model for indium plasma, is used here to evaluate the plasma constitution of an In fed FEEP type electric thruster and to obtain its characterization and functioning description. Theoretical intensities of atomic lines belonging to the first three In spectra are also obtained by InDGM. This is an...
Presentation
Full-text available
Paper presentation slides. The Iodine Detailed Global Model (IDGM) is used to evaluate the plasma components constitution of an Helicon type prototype fed by iodine. ♣ Characterization and functioning description of such a prototype on the basis of IDGM are addressed. ♣ One of the IDGM assets is the calculation of spectral lines intensities of the...
Conference Paper
Full-text available
The European Space Agency is devoting a large effort to meet standardisation of the on-ground diagnostic tools and procedures for the qualification of the future European electric thrusters. In 2006 a first programme aimed at developing Advanced Electric Propulsion Diagnostics (AEPD) for thruster characterisation was initiated. The results of that...
Conference Paper
Full-text available
The Strategic Research Cluster (SRC) on Space Electric Propulsion (EP) is the new European Commission (EC) instrument into the European Union’s Horizon 2020 research and innovation programme (H2020) to target mid-term and long-term objectives in the space electric propulsion field, considered strategic for Europe. The SRC is implemented through a P...
Conference Paper
Full-text available
Electric Propulsion (EP) is a class of space propulsion technologies that make use of electrical power to accelerate a propellant by means of electro-thermal, electro-static or electro-magnetic processes. There are many figures of merit to assess propulsion performances, but spacecraft engineers primarily use Thrust and Specific Impulse (Isp). Whi...
Conference Paper
Full-text available
Electric Propulsion is a very attractive way to save thousands of kilos in orbit transfer for telecommunication satellites, furthermore can bring hughe spacecrafts at different planets.
Article
Full-text available
Recently, we have set up an Advanced Electric Propulsion Diagnostic (AEPD) platform [1], which allows for the in-situ measurement of a comprehensive set of thruster performance parameters. The platform utilizes a five-axis-movement system for precise positioning of the thruster with respect to the diagnostic heads. In the first setup (AEPD1) an ene...
Article
Full-text available
A performance model of a radio frequency plasma bridge neutralizer was developed to calculate the electrical parameters and optimize the neutralizer design. Minimization of power losses and gas consumption, and a maximization of the neutralizer lifetime and the reliability of the system are requirements of all electric propulsion concepts and stron...
Article
Full-text available
CubeSats and nanosatellites represent an emerging opportunity to pursue a broad set of mission goals, including science, technology demonstration, communications, and Earth observation, at low cost and fast delivery. To fully exploit the potential of this class of spacecraft, there is a need for improvement of technology to enhance nanosatellites p...
Poster
Full-text available
Air-Breathing Electric Thrusters (ABET) diagnostics is addressed, with on-ground prototypes also in mind. It is based on detailed volume averaged Global Models (GM) and focuses on emission spectroscopy. Optical Emission Spectroscopy (OES) diagnostics tools give important information about the thruster propellant constitution including the ionizatio...
Conference Paper
Recently, we have set up an Advanced Electric Propulsion Diagnostic (AEPD) platform, which allows for the in-situ measurement of a comprehensive set of thruster performance parameters. The platform utilizes a five-axis-movement system for precise positioning of the thruster with respect to the diagnostic heads. In the first setup (AEPD1) an energy-...
Conference Paper
We have performed performance model calculations based on the energy balance equation (Lieberman model) and the transformer model. The influence of a geometrical parameter (orifice diameter), RF power and gas flow rate (with Xe gas) on the extractable electron current has been investigated. Furthermore, the plasma wall potential, the complex plasma...
Conference Paper
The European Space Agency is devoting a large effort for the development of standard on-ground diagnostics tools for Electric Propulsion thrusters. In 2006 a first program aimed at developing Advanced Electric Propulsion Diagnostics (AEPD) for thruster characterization was initiated. The results of that program lead to the development of a number o...
Article
Full-text available
Study of atmospheric remnants in the low Earth orbit region (~200 km altitude) using Global Models, with application to electric thrusters of in situ resources utilization type. Atmospheric Remnants in the Low Earth Orbit Region around 200 km Altitude. Available from: https://www.researchgate.net/publication/283345841_Atmospheric_Remnants_in_the_...
Article
Full-text available
Air-Breathing Electric Thrusters (ABET) diagnostics is addressed, with on-ground prototypes in mind. It is based on detailed volume averaged Global Models and focuses on emission spectroscopy. Notably, the obtained optical emission spectroscopy diagnostics tools give important information about the thruster propellant constitution and also the ioni...