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One-dimensional model of a pulsed plasma thruster

Published online by Cambridge University Press:  27 January 2016

T. R. Nada
T. R. Nada*
Affiliation:
Emirates Aviation College, Dubai, UAE
*
tareknada@gmail.com
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Abstract

This paper presents a modified one dimensional model for the pulsed plasma thruster. The model takes into account the impact of thruster geometry and capacitor initial energy on plasma inductance and resistance, as well as the ablated mass per pulse. These three factors have significant impact on the performance of the thruster and have not been considered concurrently before. The model is verified by comparing the estimated specific impulse, impulse bit and thrust-to-power ratio with experimental measurements for space qualified thrusters. The maximum error is estimated to be about 8% when using the modified model, while the conventional snowplow model produces error up to about 70%. The modified model is then employed to generate design charts that would help in selecting the proper combination of thruster geometry and energy level in the preliminary design phase of a pulsed plasma thruster for different space missions.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1195 , September 2013 , pp. 929 - 942
Copyright
Copyright © Royal Aeronautical Society 2013 

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References

1. Burton, R.L and Turchi, P.J. Pulsed plasma thruster, J Propulsion and Power, September-October 1998, 14, (5), pp 716–735.Google Scholar
2. Jahn, R.G. Physics of Electric Propulsion, Dover Publications Inc, 2006.Google Scholar
3. Ziemer, J.K. Performance Scaling of Gas-Fed Pulsed Plasma Thrusters, PhD Thesis, Department of Mechanical and Aerospace Engineering, Princeton University, New Jersey, USA, June 2001.Google Scholar
4. Ziemer, J.K. and Choueiri, E.Y. Scaling laws for electromagnetic pulsed plasma thrusters, Plasma Sources Science and Technology, 2001, 10, pp 395–405.Google Scholar
5. Burton, R.L., Wilson, M.J. and Bushman, S. Energy balance and efficiency of the pulsed plasma thruster, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cleveland, OH, USA, 13-15 July 1998.Google Scholar
6. Laperrier, D.D. Electromechanical modelling and open-Loop control of parallel-plate pulsed plasma micro thruster with applied magnetic fields, MSc Thesis, Worcester Polytechnic Institute, Worchester, UK, 2005.Google Scholar
7.. Eckman, R.F. Langmuir Probe Measurements in the Plume of a Pulsed Plasma Thruster, MSc thesis, Worcester Polytechnic Institute, Worchester, UK, 1999 Google Scholar
8. Igarashi, M. et al Performance improvement of pulsed plasma thruster for micro satellite, IEPC-01-152, 27th International Electric Propulsion Conference, Pasadena, California, USA, October, 2001.Google Scholar
9. Marques, R.I. A Mechanism to Accelerate the Late Ablation in Pulsed Plasma Thruster, PhD Thesis, University of Southampton, Southampton, UK, 2009.Google Scholar
10. Schönherr, T., Nawaz, A., Herdrich, G., Röser, H-P and Auweter-Kurtz, M. Influence of electrode shape on performance of pulsed magnetoplasmadynamic thruster SIMP-LEX, J Propulsion and Power, March–April 2009, 25, (2), pp 380–386.Google Scholar
11. Arrington, L., Haag, T. Pencil, E. and Meckel, N. A performance comparison of pulsed plasma thruster electrode confgurations, NASA-TM 97-206305, also IEPC-97-127, 25th International Electric Propulsion Conference, Cleveland, Ohio, USA, August 1997.Google Scholar
12. Arrington, L. Evaluation of pulsed plasma thruster micropulsing, NASA/CR–2004-213209, also, AIAA–2004–3458, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Florida, USA, July 2004.Google Scholar
13. Nawaz, A. and Lau, M. Plasma sheet velocity measurement techniques for the pulsed plasma thruster SIMP-LEX, IEPC-2011-248, the 32nd International Electric Propulsion Conference, Wiesbaden, Germany, September 2011.Google Scholar
14. Gatsonis, N., Zwahlen, J., Wheelock, A., Pencil, E. and Kamhawi, H. Pulsed plasma thruster plume investigation using a current-mode quadruple probe method, J Propulsion and Power, March–April 2004, 20, (2), pp 243–254.Google Scholar
15. Rayburn, C.D., Campbell, M.E. and Mattick, A.T. Pulsed plasma thruster system for microsatellites, J Spacecraft and Rockets, January–February 2005, 42, (1), pp 161–170.Google Scholar
16. Laystrom, J.K., Burton, R.L. and Benavides, G.F. Geometric optimization of a coaxial pulsed plasma thruster, AIAA 2003-5025, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 2003.Google Scholar
17. Rayburn, C., Campbell, M., Hoskins, W.A. and Cassady, R.J. Development of a micro pulsed plasma thruster for the Dawgstar nanosatellite, AIAA-2000-3256.Google Scholar
18. Antonsen, E.L., Burton, R.L., Reed, G.A. and Spanjers, G.G. Effects of postpulse surface temperature on micropulsed plasma thruster operation, J Propulsion and Power, September–October 2005, 21, (5), pp 877–883.Google Scholar
19. Rysanek, F. and Burton, R. Performance and heat loss of a coaxial Teflon pulsed plasma thruster, IEPC-01-151, the 27th International Electric Propulsion Conference, Pasadena, California, USA, 15-19 October 2001.Google Scholar
20. Lin, G. and Karniadakis, G.E. A high-order discontinuous Galerkin method for modelling micro-pulsed plasma thrusters, IEPC-01-154, the 27th International Electric Propulsion Conference, Pasadena, California, USA, 15-19 October, 2001.Google Scholar