Matthias Gollor's research while affiliated with Universität Konstanz and other places

Publications (16)

Conference Paper
The accommodation of Electric Propulsion and the associated Power Processing Units (PPU) within a Spacecraft must lead to an integrated system providing full function and performance. An important aspect is the grounding of the electric propulsion system. It affects not only the performance of the electric propulsion (EP) system, moreover it affect...
Conference Paper
The accommodation of Electric Propulsion and the associated Power Processing Units within a Spacecraft must lead to an integrated system providing full function and performance. This process starts with a proper specification of the electrical interface between thrusters and electronics, the handling of high voltages in a distributed harness, the i...
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...
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
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
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
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
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...

Citations

... In this model, the satellite is placed in the Sun-Earth Lagrangian point. The force and torque acting on the spacecraft due to drag-free control is provided by means of micro-thrusters (Gollor and Franke 2016), which are modeled as a first order system. The time constant takes into account the delays introduced by the electronic devices which driving the thrusting actuators. ...
... 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). ...
... Because a thruster-generated plasma is a relatively dense and electrically active entity involved in complex surface interactions with the spacecraft, the operation of a plasma thruster is an important driver of the spacecraft electrostatic charging process. Unexpectedly high levels of charging leading to potentially damaging electrostatic parasitic discharges can compromise the nominal operation of a Solar Electric Propulsion System (SEPS) and the lifetime of its subsystems (Gollor, 2011). Therefore, design phases and test campaigns heavily rely on numerical simulations of both ground and flight operations of any EP system (Sarrailh et al., 2019). ...
... 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]. ...
... 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). ...