Georg Herdrich

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To extend the lifetime of commercial and scientific satellites in low Earth orbit (LEO) and below (100-250 km of altitude) recent years showed an increased activity in the field of air-breathing electric propulsion as well as beamed-energy propulsion systems. However, preliminary studies showed that the propellant flow necessary for electrostatic propulsion(More)
As part of the partnership between the Center for Astrophysics, Space Physics and Engineering Research (CASPER) at Baylor University and the Institute of Space Systems (IRS) at the University of Stuttgart, a new design for a modular inductively driven plasma generator (IPG) is being developed and tested within CASPER and the IRS. The current IPG design is(More)
On January 15th 2006, the STARDUST capsule re-entered Earth’s atmosphere after its almost seven year journey with a re-entry speed of 12.8 km/s. Due to the nature of the mission, no diagnostics for the re-entry phase were installed on the capsule. Nevertheless, this was the fastest re-entry of a human made space vehicle ever and data on heat shield erosion(More)
An overview of the IRS payload development for ESA’s EXPERT mission is given. The final design and performance parameters of the payloads PYREX, PHLUX and RESPECT are described. PYREX is a sensor system measuring the thermal protection system (TPS) rear side temperature. PHLUX is a catalysis based experiment to determine the dissociation degree of the(More)
An assessment of a decentralized inductively heated plasma waste treatment system for energy recovery has been done. The modular miniaturized high enthalpy plasma source IPG6 is a reference for the system and has been qualified for inert but also chemically aggressive gas compositions. An identification and review of applications were undertaken. Niches of(More)
In order to develop inductive electric propulsion systems towards flight-ready status, an investigation into the influence of the dielectric separation between plasma and inductive coil has been conducted. This was completed by varying the wall thickness of the thruster discharge tube. The investigation assessed discharges of argon and an argon-nitrogen(More)
As one kind of electric space propulsion systems, pulsed plasma thrusters transform electrical energy into kinetic energy of an exhaust medium by means of a pulsed discharge. Due to the short discharge time, the nature of the discharge remained unraveled for long time. In recent years, indications from experimental work pointed to a strong similarity with(More)
The performance and the plasma created by a pulsed magnetoplasmadynamic thruster for small satellite application is studied to understand better the ablation and plasma propagation processes occurring during the short-time discharge. The results can be applied to improve the quality of the thruster in terms of efficiency, and to tune the propulsion system(More)
Estimation of the local dissociation degree and the local mass-specific enthalpy of a pure oxygen plasma flow determined mainly from laser-induced fluorescence measurements are reported. Measurements have been conducted for several generator parameters in an inductively heated plasma wind tunnel. Additional probe measurements of total pressure together with(More)