Angelo Cervone

Delft University of Technology | TU · Department of Space Engineering (SpE)

The aerospace industry is recently expressing a growing interest in green, safe and non-toxic propellants for the propulsion systems of the new generation of space vehicles, which is especially true in the case of Cubesat micro-propulsion systems. Demanding requirements are associated to the future missions and challenges offered by this class of s...

Green monopropellants play a crucial role in advancing propulsion systems for micro and nanosatellites, offering enhanced performance and safety compared to hydrazine. The development of feed and pressurization systems, particularly for CubeSats, poses a contemporary challenge impacting propulsion system efficiency, onboard power consumption, and s...

Recent trends in research and development on in-space propulsion have advanced the use of the “green propellants” on an ample scale, mainly eyeing environmental sustainability and especially addressing the handling safety concerns. Small satellites, in particular micro and nanosatellites, have advanced from passive orbiting to having the ability to...

This research evaluates Laser Powder Directed Energy Deposition (LP-DED) for producing fine feature internal microchannels. This study is focused on enhancing and characterising the surfaces of microchannels produced using techniques such as abrasive flow machining, chemical milling, chemical mechanical polishing, electrochemical machining, and the...

Modern spacecraft systems and launch vehicle design is more oriented towards reducing system-level design and assembly complexities. In order to maintain high overall system performance while reducing these complexities, the use of smart materials and smart structural components is becoming of more interest to space systems' designers. The paper wi...

Spacecraft systems monitoring is crucial for early fault detection and troubleshooting of various subsystems and components. To detect unexpected performance degradation or anomalies during the mission lifetime, multiple spacecraft subsystems require in-situ real-time monitoring and delicate acquisition of the operations' data. Subsystems on a sate...

This manuscript aims to present and evaluate the applicability of combining optical line-of-sight (LoS) navigation with crosslink radiometric navigation for deep-space cruising distributed space systems. To do so, a set of four distributed space systems architectures is presented, and for each of those, the applicability of the combination is evalu...

This paper aims to investigate the capabilities of exploiting optical line-of-sight navigation using star trackers. First, a synthetic image simulator is developed to generate realistic images, which is later exploited to test the star tracker’s performance. Then, generic considerations regarding attitude estimation are drawn, highlighting how the...

The paper presents the initial outcomes of a project, currently ongoing under the supervision of the European Space Agency, having the main objective to specify and design a Fault Detection Isolation and Recovery (FDIR) system by making use of relevant RAMS (Reliability, Availability, Maintainability, Safety) analyses for missions in non-determinis...

The propellant storage compartments (propellant tanks) have undergone noted evolution in the design nature (mainly the shape and the structural properties) as well as the development process. To achieve high system performance for a given propulsion system, inert mass reduction as well as efficient volume utilization can be considered as the main a...

Line-of-Sight (LoS) navigation is an optical navigation technique that exploits the direction to visible celestial bodies, obtained from an onboard imaging system, to estimate the position and velocity of a spacecraft. The directions are fed to an estimation filter, where they are matched with the actual position of the observed bodies, retrieved f...

Heat exchangers for use in propulsion applications are very critical components because they must be efficient, compact and light and often operate with working fluids at extreme temperatures or pressures or both. Various components and systems use heat exchangers such as combustion chambers of gas turbines and internal combustion engines, fuel cel...

The requirements of small satellite missions, especially interplanetary and deep-space ones, often generate a need for a reaction control system (RCS) thruster. This happens in the Lunar Meteoroid Impact Observer (LUMIO), an upcoming CubeSat mission designed to observe, quantify, and characterize meteoroid impacts on the lunar far-side, in which De...

The Lunar Meteoroid Impacts Observer (LUMIO) is a CubeSat mission to observe, quantify, and characterize the meteoroid impacts on the lunar farside by detecting their flashes. This complements the knowledge gathered by Earth-based observations of the lunar nearside, thus synthesizing global information on the lunar meteoroid environment and contrib...

In order for off-Earth top surface structures built from regolith to protect astronauts from radiation, they need to be several metres thick. With support from European Space Agency (ESA) and Vertico, the Technical University Delft (TUD) advanced research into constructing habitats in empty lava tubes on Mars in order to create subsurface habitats....

The propellant storage compartments (propellant tanks) are one of the parts that have undergone noted evolution in the design nature (mainly the shape and the structural properties) as well as the development process. To achieve high system performance for a given propulsion system, inert mass reduction as well as efficient volume utilization can b...

Additive Manufacturing (AM) offers new design and manufacturing opportunities of thin-wall microchannel heat exchangers for aerospace and industrial applications. Laser Powder Directed Energy Deposition (LP-DED) is an AM process providing large scale manufacturing of thin-wall microchannel heat exchangers. Successful industrialization of the LP-DED...

The Earth-Moon system is constantly bombarded by meteoroids of different size and impact speed. Observation of the impacts on the Moon can enable thorough characterization of the Lunar meteoroid flux, which is similar to that of the Earth. While Earth-based Lunar observations are restricted by weather, geometric and illumination conditions, a Lunar...

Electrothermal propulsion can be seen as an intermediate concept between electrical and chemical propulsion. Propellant heating typically happens by means of a resistance (resistojet) or an electrical discharge (arcjet). For the extremely miniaturized applications that will be discussed in this chapter, resistojets are by far the most commonly used...

This chapter covers the development of cold gas microthruster, which is widely regarded as the simplest way of generating thrust in space, for nanosatellites. A brief background and principles of operation were given, followed by the introduction of nozzle theory that could be used in the preliminary estimation of microthruster performance and cons...

The Lunar Meteoroid Impact Observer (LUMIO) is a mission designed to observe, quantify, and characterize the impacts of meteoroids on the lunar far side and, therefore, complement in both space and time the observations currently taken from Earth. While Earth-based lunar observations are restricted by weather, geometric and illumination conditions,...

Green propellants are currently considered as enabling technology that is revolutionizing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft, and to o...

Vast amounts of meteoroids and micrometeoroids continuously enter the Earth–Moon system and consequently become a potential threat. Lunar meteoroid impacts have caused a substantial change in the lunar surface and its properties. The Moon having no atmospheric blanket to protect itself, it is subjected to impacts from meteoroids ranging from a few...

Green monopropellants play a significant role in miniaturization and rapid development of propul-sion systems for micro and nanosatellite due to their superior performance and safety over hydra-zine. Feed and pressurization systems develop-ment for such monopropellant systems especially in CubeSats is a modern-day challenge since it would impact th...

Propulsion systems for small-sized spacecraft are trending toward miniaturization and system modu-larity. Moreover, green propulsion is becoming the norm in space propulsion, particularly in CubeSats, due to the high performance and favorable physi-cal properties of green propellants, as well as the global efforts toward greener environment. These...

Small satellites with increased capabilities in terms of power and propulsion are being demanded for future missions. This paper addresses an alternative bi-modal solution which consists of a solar thermal propulsion system coupled with a micro-Organic Rankine Cycle system, to co-generate thrust and electrical power. Current literature on bi-modal...

The purpose of this work is to present a novel CubeSat architecture, aimed to explore Near Earth Asteroids. The fast growth in small satellite commercial-off-the-shelf technologies, which characterized the last decade of space industry, is exploited to design a 3U CubeSat able to provide a basic scientific return sufficient to improve the target as...

The LUnar Meteoroid Impacts Observer (LUMIO) is a CubeSat mission to a halo orbit at Earth–Moon L2 that shall observe, quantify, and characterize meteoroid impacts on the Lunar farside, by detecting their flashes. In this way, LUMIO is expected to significantly contribute to Lunar Situational Awareness and to the current knowledge on the evolution...

Small satellites are receiving increased recognition in the space domain due to their reduced associated launch costs and shorter lead time when compared to larger satellites. However, this advantage is often at the expense of mission capabilities, such as available electrical power and propulsion. A possible solution is to shift from the conventio...

Small satellites with increased capabilities in terms of power and propulsion are being demanded for future missions. This paper proposes a possible solution which is the design of a novel integrated solar thermal system that co-generates propulsion and power on-board mini satellites. The system consists of a solar thermal propulsion system (STP) c...

Mars Atmospheric Radiation Imaging Orbiter (MARIO) is a 16U stand-alone CubeSat mission that shall escape Earth, perform autonomous deep-space cruise, achieve ballistic capture, and enter an operational orbit at Mars to perform thermal radiation imaging. This work focuses on the systems design of MARIO. The design of combined chemical-electric prop...

Stand-alone CubeSat missions to Mars that escape Earth and experience a deep-space cruise require robust primary propulsion systems for orbit manoeuvring and precise trajectory control. Combined chemical-electric propulsion systems enable a hybrid high-thrust-low-thrust transfer from a high energy Earth orbit to Mars. High-thrust chemical propulsio...

Delft University of Technology is currently developing the pico-satellite platform Delfi-PQ, based on the PocketQube standard, in pursuit of a new generation of satellites with lower cost, flexibility and short development time. A technology demonstration payload expected to fly in one of the first Delfi-PQ satellites is a dual thruster micro-propu...

Small satellites are receiving increased recognition in the space domain due to their reduced associated launch costs and their shorter lead time when compared to larger satellites. However, this advantage is often at the expense of mission capability, such as available electrical power. A possible solution is to change from the conventional solar...

The Lunar Meteoroid Impact Observer (LUMIO) is a CubeSat mission to observe, quantify, and characterise the meteoroid impacts by detecting their flashes on the lunar far-side. This complements the knowledge gathered by Earth-based observations of the lunar nearside, thus synthesising a global information on the lunar meteoroid environment. LUMIO en...

Stand-alone interplanetary CubeSats require primary propulsion systems for orbit ma- neuvering and precise trajectory control. The current work focuses on the design and perfor- mance characterization of the combined chemical–electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust–low-thrust trajector...

This papers gives an insight on different sub topics related to a micro-propulsion subsystem for a PocketQube. First, PocketQubes will be introduced and then Delfi-PQ will be presented, providing an overview of the mission for which this micro-propulsion system will be used. Step by step, the paper will explain the subsystem, its challenges, mechan...

The Lunar Meteoroid Impact Observer (LUMIO) is one of the four projects selected within ESA’s SysNova competition to develop a small satellite for scientific and technology demonstration purposes to be deployed by a mothership around the Moon. The mission utilizes a 12U form-factor CubeSat which carries the LUMIO-Cam, an optical instrument capable...

This paper presents an innovative approach combining a fuzzy controller and a control allocation method applied to the control problem of allocating actuators’ efforts in an over-actuated system. The controller is applied to a space debris removal mission using a deployable net on-board a 3U CubeSat. The controller calculates the necessary effort o...

In recent years, satellite design has extended towards miniaturisation to reduce associated cost with launching and conducting space missions. Small satellites provide low-cost platforms for space missions. However, this lower cost comes at the expense of the removal of key sub-systems, such as the propulsion system, due to the small available onbo...

Stand-alone interplanetary CubeSats to Mars require primary propulsion systems for orbit manoeuvring and trajectory control. The context is a 30 kg 16U Interplanetary CubeSat mission on a hybrid high-thrust & low-thrust trajectory utilising a Dual Chemical-Electric Propulsion System to achieve Earth escape (high-thrust) and perform autonomous deep-...

Delft University of Technology is currently developing the pico-satellite platform Delfi-PQ, based on the PocketQube standard, in pursuit of a new generation of satellites with lower cost, flexibility and short development time. A technology demonstration payload expected to fly in one of the first Delfi-PQ satellites is a dual thruster micro-propu...

This brief presents a comprehensive approach for the modeling of micropropulsion systems based on the vaporization of a liquid. The model combines the analytical and empirical relations derived from extensive experimental analysis and fundamental physical laws. This allows modeling of key parameters, such as mass flow rate, for the entire system co...

There is a clear trend towards the developments of micro-propulsion system to enhance the capabilities of nano- and pico-satellites. A promising propulsion option to meet the strict requirements of these small satellites is the Low-Pressure Micro-Resistojet (LPM) which works under rarefied gas dynamic regime. To simplify the engineering design of t...

Vaporizing Liquid Microthrusters (VLM) have recently received attention as promising propulsion technology for highly miniaturized spacecraft due to its high thrust levels and low power consumption. This paper presents the results of numerical optimization of the parameters for the design of the heating chamber of VLMs that use water as the propell...

As a further step in the research towards miniaturization of satellite components and sub-systems, the Department of Space Systems Engineering at the Delft University of Technology has recently embarked in the end-to-end engineering of the Delfi-PQ picosatellite platform, designed according to the PocketQube size standard. This new satellite platfo...

A Low-Pressure Micro-Resistojet (LPM) is under development at TU Delft with the intention to provide future nano- and pico-satellites with the necessary capability to execute formation flying maneuvers, orbit change maneuvers, and station keeping. In this particular type of electro-thermal thruster, water is a green propellant of excellent performa...

Interplanetary CubeSats enable universities and small-spacecraft-consortia to pursue low-cost, high-risk and high-gain Solar System Exploration missions, especially Mars; for which cost-effective, reliable, and flexible space systems need to be developed. Missions to Mars can be achieved through a) in-situ deployment by a mothership and b) highly f...

CubeSats have been extensively used in the past decade as scientific tools, technology demonstrators and for education. Recently, PocketQubes have emerged as an interesting and even smaller alternative to CubeSats. However, both satellite types often lack some key capabilities, such as micropropulsion, in order to further extend the range of applic...

Plasma engines for space propulsion generate plasma jets (also denominated plasma plumes) having supersonic ion groups with typical speeds in the order of tens of kilometers per second, which lies between electron and ion thermal speeds. Studies of the stationary plasma expansion process using a four-grid retarding field energy analyzer (RFEA), an...

Three Low Pressure Micro-resistojets (LPM) with integrated heater and temperature measurement were designed, manufactured and characterized at Delft University of Technology. The devices were manufactured using Silicon-based Micro Electro Mechanical Systems (MEMS) technology including a heater made of Molybdenum for better operations at high temper...

This Challenge Analysis proposes a Lunar Meteoroid Impact Observer (LUMIO) to observe, quantify, and characterise the meteoroid impacts by detecting the impact flashes on the lunar farside. This will complement the knowledge gathered by Earth-based observations of the lunar nearside, thus synthesising a global information on the lunar meteoroid env...

This paper presents the results of design, manufacturing and characterization of Vaporizing Liquid Microthrusters (VLM) with integrated molybdenum heaters and temperature sensing. The thrusters use water as the propellant and are designed for use in CubeSats and PocketQubes. The devices are manufactured using silicon based MEMS (Micro Electro Mecha...

Pulsed fusion propulsion might finally revolutionise manned space exploration by providing an affordable and relatively fast access to interplanetary destinations. However, such systems are still in an early development phase and one of the key areas requiring further investigations is the operation of the magnetic nozzle, the device meant to explo...

The number of launches of nano- and pico-satellites have significantly increased over the past decade. Miniaturized subsystems, such as micro-propulsion, for these classes of spacecraft are rapidly evolving and, in particular, microresistojets have shown great potential of applicability. One of the key points to address in the development of such d...

A reduced-order model for the preliminary design and performance prediction of radial turbopumps is illustrated. The model expresses the 3D, incompressible, inviscid, irrotational flow through helical blades with slow axial variations of their pitch and backsweep angles by superposing a 2D axial vorticity correction to a fully guided forced vortex...