Scheduled Development of the TIHTUS System: Geometric Optimisation and Alternative Propellant Operation (original) (raw)

Current Numerical and Experimental Investigations of the Hybrid DC-RF Thruster TIHTUS

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2010

Electric space propulsion delivers high exhaust velocities usually in combination with relatively low thrust levels. Raising the thrust level at a constant high exhaust velocity, fuel consumption for a specific mission is reduced and payload mass is increased. Also, an increase in mission flexibility and a reduction of duration can be achieved. Promising thrusters are hybrid concepts like TIHTUS. This thruster combines an arcjet and an ICP in series. The proof of concept already shows promising results. After a description of the thruster system actual experimental and theoretical optimizations of the standalone ICP are summarized. For a decrease of wall thickness from 2.3 mm to 1.25 mm the thermal plasma power is increased by 40 % and the thinner quartz tube can resist higher heat loads, too. These results show the potential for large improvements of the overall thruster parameters and motivate a research program for further optimization of the already promising TIHTUS engine. In this program, theoretical and experimental investigation will be accompanied by numerical simulations for a detailed understanding of the relevant processes and the identification of the prospects of success for further optimization. The current status of development of the numerical tool is also described.

Activities In Electric Propulsion Development at IRS

Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan, 2009

More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme=IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. Among the described electric propulsion systems are recent developments in the field of applied field MPD but also from high power hybrid thrusters. In addition, new concepts such as the hybrid systems Thermal-Inductively heated Hybrid-Thruster of the University of Stuttgart (TIHTUS) and the so-called Coupled Tether/Ion Engine Propulsion (CETEP) are analysed.

Overview on Electric Propulsion Development at IRS

More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme = IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. In addition, several advanced plasma propulsion designs have been developed and characterized at IRS in the past 10 years. Among them are the hybrid thruster TIHTUS, steady state...

Arcjet Stage Investigation and Inductive Hydrogen Heating in the TIHTUS Engine

The water-cooled laboratory model of the two-stage hybrid thruster TIHTUS is briey explained and results of investigations of each stage are presented. Thrust measurements of the arcjet stage yield a maximum thrust of 3.3 N and a maximum specic impulse of 1430 s with the curves showing no sign of saturation. Hydrogen operation at the induc- tively coupled stage is presented showing an eciency of plasma heating of 32% and a thrust of over 2.3 N is estimated at a specic impulse of lower than 400 s. Theoretical investigations of magnetohydrodynamic (MHD) eects within the inductive stage are pre- sented. From the obtained terms for magnetic pressure and Lorentz force an optimization tool for inductively heated plasma sources was derived.

Overview on Electric Propulsion Developments at IRS

2011

More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme = IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. In addition, several advanced plasma propulsion designs have been developed and characterized at IRS in the past 10 years. Among them are the hybrid thruster TIHTUS, steady state applied field thrusters and the iMPD IMAX. These concepts have been experimentally and numerically characterized and show promising potential for future missions. The paper will discuss the design and the operational features of the devices. In addition, more advanced systems are under investigation. Here, a focus is in the field of fusion driven systems and M2P2 (magnetic sail systems).

Advanced plasma (propulsion) concepts at IRS

Vacuum, 2013

Several advanced plasma propulsion designs have been developed and characterized at IRS in the past years. Among them are the hybrid thruster TIHTUS, the steady state applied field thrusters AF MPD ZT1 and ZT2 and advanced iMPD designs. These concepts show promising potential for future missions. The paper will discuss the designs and their operational features.

Presented at the 31st International Electric Propulsion Conference

2009

K.Katsonis9 CNRS-LPGP Abstract: This paper describes the experimental layout under development to test a helicon plasma thruster for a small satellite. The thruster class is 50 W 1mN. This work is done within the research project Helicon Plasma Hydrazine Combined Micro (HPH.com) in the frame of the 7th Framework Programme of the EU by a European consortium. Experimental tests are foreseen to validate codes, to support thruster design and to verify thruster performances. Two different test beds will be designed, an engineering model and a