Development of arcjet and ion propulsion for spacecraft stationkeeping

Abstract Near term flight applications of arcjet and ion thruster satellite station-keeping systems as well as development activities in Europe, Japan, and the United States are reviewed. At least two arcjet and three ion propulsion flights are scheduled during the 1992–1995 period. Ground demonstration technology programs are focusing on the development of kW-class hydrazine and ammonia arcjets and xenon ion thrusters. Recent work at NASA Lewis Research Center on electric thruster and system integration technologies relating to satellite stationkeeping and repositioning will also be summarized.

[1]  Kyoichi Kuriki.  Electric propulsion research and development in Japan , 1990 .

[2]  David C. Byers.  Advanced onboard propulsion benefits and status , 1989 .

[3]  Vincent K. Rawlin,et al.  Mass comparisons of electric propulsion systems for NSSK of geosynchronous spacecraft , 1991 .

[4]  Francis M. Curran,et al.  Preliminary performance and life evaluation of a 2-kW arcjet , 1991 .

[5]  M. Kinnersley,et al.  Low power hydrazine arcjet thruster study , 1992 .

[6]  Francis M. Curran,et al.  An extended life and performance test of a low-power arcjet , 1988 .

[7]  Frank M. Curran,et al.  Arcjet starting reliability: A multistart test on hydrogen/nitrogen mixtures , 1987 .

[8]  C. Roberts,et al.  Development and demonstration of a 1.8 kW hydrazine arcjet thruster , 1990 .

[9]  S. Kitamura,et al.  Cyclic test of a 14-cm diameter ring-cusp xenon ion thruster , 1992 .

[10]  Lynnette M. Zana.  Langmuir probe surveys of an arcjet exhaust , 1987 .

[11]  H.-P. Berg,et al.  Recent results on qualification of the RITA components for the ARTEMIS satellite , 1992 .

[12]  R. Feconda,et al.  Satellite Reaction Control Subsystems with augmented catalytic thrusters , 1984 .

[13]  Roger M. Myers,et al.  Electric propulsion - An evolutionary technology , 1993 .

[14]  F. Mckevitt.  Design and development approach for the augmented catalytic thruster(ACT) , 1983 .

[15]  Timothy R. Sarver-Verhey.  Extended-testing of xenon ion thruster hollow cathodes , 1992 .

[16]  John M. Sankovic,et al.  Investigation of the arcjet plume near field using electrostatic probes , 1990 .

[17]  John A. Hamley,et al.  Power electronics for low power arcjets , 1991 .

[18]  H. Bassner,et al.  Status of the RITA - Experiment on EURECA , 1987 .

[19]  A. Bogorad,et al.  The effects of 1 kW class arcjet thruster plumes on spacecraft charging and spacecraft thermal control materials , 1992 .

[20]  Vincent K. Rawlin.  Characterization of ion accelerating systems on NASA LeRC's ion thrusters , 1992 .

[21]  Roger M. Myers,et al.  The evolutionary development of high specific impulse electric thruster technology , 1992 .

[22]  W. E. Morren,et al.  Low-power arcjet test facility impacts , 1992 .

[23]  Francis M. Curran,et al.  Low Power Arcjet Performance , 1990 .

[24]  Michael J. Patterson,et al.  Derated ion thruster design issues , 1991 .

[25]  Deepakraj M. Divan.  High power density dc-to-dc converters for aerospace applications , 1990 .

[26]  Hao Ling,et al.  Near field interaction of microwave signals with a bounded plasma plume , 1991 .

[27]  John M. Sankovic,et al.  The effects of arcjet thruster operating condition constrictor geometry on the plasma plume , 1989 .

[28]  Michael J. Patterson,et al.  Performance and optimization of a derated ion thruster for auxiliary propulsion , 1991 .

[29]  R. R. Robson,et al.  Status of xenon ion propulsion technology , 1987 .