Michael Boss's research while affiliated with ASTRIUM and other places

Publications (17)

Conference Paper
Many of ESA’s and NASA’s future missions are based on Formation flying, Fine attitude control and (fine) Drag compensation. As prominent examples one could mention LISA, DARWIN, PROBA-III, etc. For all these applications there is a need for propulsion system with: - High thrust accuracy and - High thrust controllability Taking into account, that...
Article
Electronic equipments for electric propulsion systems have been built by Astrium over many years. Main contributions have been made to the programs EURECA, GOCE, and AlphaBus. This has formed the basis for the development of "Generic High Voltage Power Supply - Next Generation" (HVPS-NG) providing a "tool box" of functional blocks and modules - wit...
Conference Paper
RIT-µX is a radio frequency ion engine for micro propulsion applications. The ionization of the propellant by electro magnetic fields offers inherently highest thrust control, -stability and resolution. The function principle of the engine and the specific advantages are explained and the layout of a propulsion system is presented. Potential missio...
Conference Paper
Different requirements of Electric Propulsion Systems, like ion thrusters for the European Space Mission GOCE and AlphaBus Platform or the new High Efficiency Multistage Plasma (HEMP) thruster for future telecom missions, have triggered the development of a Generic High Voltage Power Supply referred as "HVPS - Next Generation". Focusing on a generi...
Conference Paper
High Voltage Power Modules for Electrical Propulsion have been developed for the European Space Agency's GOCE and ALPHABUS missions, featuring Kaufmann-Type Ion Tiirusters with power levels between 520W and 4.8 kW and output voltages from 1200V to 2000V. Based on these developments a new concept lias been established for modular generic power modul...
Conference Paper
Full-text available
ARC-sr together with EADS Astrium and EADS Space Transportation is jointly developing a flight design for an Indium FEEP Microthruster suitable for LISA Pathfinder. The paper reviews all basic design elements and performance parameters and shows that the Indium FEEP thruster is capable of meeting all key requirements for ultra-precise attitude and...
Conference Paper
The coming generation of scientific and earth observation missions demands for fast ultra-precise attitude and orbit controlled platforms. A promising approach for the necessary fine controllable micro-Newton thrusters is the use of Field Emission Electric Propulsion or μ-Newton-RITs. For the European Missions LISA Pathfinder and Proba-3 concepts h...
Article
Full-text available
A promising concept for μ-Propulsion is currently under development: the μN-RIT (Radio Frequency Ion Thruster), a μ-Newton engine, which has been subject of intensive research by the University of Giessen in the past years. In order to accompany the thruster development activities, the European Space Agency and the German Space Agency DLR are suppo...
Article
High Voltage Power Modules for Electrical Propulsion have been developed for the European SpaceAgencs GOCE and ALPHABUS missions, featuring Kaufmann-Type Ion Thrusters with power levels between 520W and 4.8 kW and output voltages from 1200V to 2000V. Based on these developments a new concept has been established for modular generic power modules be...
Article
Full-text available
RIT-µX is a radio frequency ion engine for micro propulsion applications. The ionization of the propellant by electro magnetic fields offers inherently highest thrust control, -stability and resolution. The function principle of the engine and the specific advantages are explained and the layout of a propulsion system is presented. Challenges for s...
Article
Full-text available
Electric Propulsion development in Germany goes back to the early sixties, when Prof. Dr. Horst Loeb at 1 st Physical Institute of Justus-Liebig-University Giessen de-signed the first Radiofrequency Ion Thruster – RIT. Ten years later, a fruitful cooperation was initiated with the aerospace company MBB based in Ottobrunn. In the early seventies Pro...

Citations

... Electric space engines have evolved out of their shadowy existence due to the abovementioned strong points. [97][98][99][100][101] There are a large number of different types of EP systems, some still at a conceptual level, others already at a very high technological maturity level, and a few already in use in space (cf. Fig. 4). ...
... RIT-2 can realize thrust range from 7 μN to 18 μN adjusted by grid voltage at 0.08 sccm and work stably at 60 μN for 10 h after improving flow rate. It shows RF ion thruster is potential for space GWs detection [52]. RIT-μX developed by German Airbus under the support of ESA can realize thrust range from 10 μN to 120 μN with 0.1 μN resolution and thrust noise lower than 0.1 μN/Hz 1/2 [53]. ...
... This action is provided by means of FEEP thrusters, modeled here as a first-order system with a characteristic time constant of 0.1303 s (corresponding to approximately 0.3 s rise time). The selected time constant takes into account the delays introduced by the electronic devices driving the thrusting actuators [16,17]. In this paper the FEEP thrusters are considered as a baseline actuator system because they have been identified as a key technology for future drag-free missions [17]. ...
... Miniaturization of a durable cathode for electron supply presents a challenge with respect to miniaturization, in addition to the ability to manufacture flat grids out of materials that show high resistivity to ion erosion while space charge between the accelerating grids limits the achievable emission current density and therefore thrust. Recent developments in miniaturized ion engines make use of RF ioniziation, obviating the need for an internal electron emitter [36]- [38]. Ion engines have been employed in notable missions such as Deep Space-1 [10], Dawn [39], and GOCE [40], and typically achieve specific impulse between I sp = 2000-3000 s. ...
... The field emission electric propulsion system operates by flowing a liquid metal, typically cesium or indium, through a small channel or over the surface of a high aspect ratio tip. 19,20,21,22 A high strength electric field is generated at the surface of the liquid metal by applying a large electric potential difference between the liquid and a downstream electrode grid. Note that the field strength at the emitter tip is intensified due to the field-focusing that occurs at sharp points. ...
... Unlike as is in chemical propulsion systems, EP systems require a very little mass of propellant to accelerate a spacecraft. Generally, propellant is ejected up to twenty times faster than from a conventional chemical thruster which makes the overall system many times more mass efficient which is measured by the term Specific Impulse (Isp) [3]. When compared to the EP systems which generally have the values of Isp in thousands of seconds, conventional chemical propulsion systems have Isp values in the mere range of 250-450 seconds. ...
... The ultra-high voltage power supplies are widely used in various industrial and aerospace applications, such as the high-voltage power supplies for electrostatic accelerator [1,2], particle accelerator in nuclear physics [3], electron microscope [4], X-Rays [5,6], electric propulsion (EP) thruster [7][8][9][10] etc. Nowadays, the research on the high voltage power supply mainly focuses on the topology [11][12][13][14], high voltage conversion ratio [15][16][17], closedloop control stability [18,19], output voltage accuracy and low ripple [20][21][22] etc. However, when designing this kind of power supply, the high-voltage insulation protection should be of prior consideration. ...
... The 4 cm ion thruster RIT-4, shown in Fig. 1 is a miniaturized radio-frequency ion thruster (μN-RIT) built by Giessen University especially for the test. It is a 37-hole thruster able to produce a thrust up to 500 μN within its nominal range 7 . The unique feature of this type of engine is the electrodeless ionization of the Xenon propellant by electromagnetic waves. ...
... A DC/DC step-up converter generally transforms a high current with low-level input DC voltage to a low current with high-level output DC voltage. The high DC voltage output is used in many applications like large off-shore wind farms [4,5] grid-connected photovoltaic power systems [6], satellite ion thrusters [7], power generators of X-ray in power electronics of medical science [8], and many other fields, such as a pulsed electric field. There are a lot of limitations of conventional step-up converters regarding the achievement Fig. (1). ...