Journal of Aeronautical Engineering

Journal of Aeronautical Engineering

Semi-empirical electromechanical model for pulsed plasma thrusters using two different approaches and comparison with experimental results

Document Type : Original Article

Authors
Mohsen Oloumi 1
Hadi Movahed Nejad 2
DARIUSH ROSTSAMIFARD 3
Hasan Hossein Khani 2
Amir Kiani 2
1 Plasma and fusion Nuclear, Nuclear Science and Technology Research Institute
2 Nuclear Science and Technology Research Institute
3 Plasma and fusion, Nuclear Science and Technology Research Institute
10.22034/joae.2021.306101.1056
Abstract
Space engines are used for missions such as altitude change, position control, position maintenance, landing, and orbit change. In recent decades, the use of plasma thrusters as a space propulsion system has been considered, one of which is the pulsed plasma thrusters. In this paper, a quasi-experimental electromechanical model for rectangular flat plate electrodes has been developed using two different approaches: slug and snowplow. By equating the whole physical process as a one-dimensional electrical circuit and in the next step, coupling it with the force equation as well as using some experimental parameters, the electromechanical model is obtained. The results of this semi-empirical model are compared and evaluated with the basic experimental parameters for pulsed plasma thrusters used in two satellites. According to the positive results of the evaluations, using this semi-empirical model, the basic parameters of a pulsed plasma thruster such as impulse bit and plasma exhaust velocity can be calculated and some geometric parameters and capacitor parameters of this thruster can be optimized and controlled. The two approaches of slug and snowplow in this model are also compared with experimental results.
Keywords
Pulsed Plasma Thrusters
Electromechanical model
Semi-empirical model
Slug model
Snowplow model
[1]www.nasa.gov/directorates/spacetech/niac/2020_Phase_I_Phase_II/Pulsed_Plasma_Rocket.
[2] Keidar, M., & Boyd, I. D., “Optimisation issues for a mico-pulsed plasma thruster”, Journal of propulsion and power, Vol. 22, No. 1, pp. 48–55, 2006.
 [3] Rhodes, R., Keefer, D., & Thomas, H., “A numerical study of a pulsed plasma thruster”, 37th Joint propulsion conference, AIAA, Salt Lake City, Utah, 2001.
 [4] Laperriere, D. D., Gatsonis, N. A., & Demetriou, M. A., “Electromechanical modeling of applied field micro pulsed plasma thrusters”, 41st Joint propulsion conference, AIAA, Tucson, Arizona, 2005.
[5] Ziemer, J. K., & Choueiri, E. Y., “Scaling laws for electromagnetic pulsed plasma thrusters”, Plasma Sources Sci. Technol., Vol. 10, pp. 395-405, 2001.
[6] Solbes, A., & Vondra, R. J., “Performance study of a solid fuel-pulsed electric microthruster”, Journal of Spacecraft, Vol. 10, No. 6: 406–410, 1973. 
[7] Waelbroeck, F. L., Fitzpatrick, R., & Hazeltine, R. D., “Introduction to plasma physics: A graduate course University of Texas at Austin”, 2006.
[8] Solbes, A., Vondra, R. J., “Performance study of a solid fuel-pulsed electric microthruster”, Journal of Spacecraft, Vol. 10, No. 6: 406–410, 1973. 
[9] Michels, C. J., Heighway, J. E., & Johansen, A. E., “Analytical and experimental performance of capacitor powered coaxial plasma guns,” AIAA Journal, Vol. 4, No., 5, May, 1966.
Journal of Aeronautical Engineering
Volume 23, Issue 2
December 2021
Pages 116-123

  • Receive Date 22 September 2021
  • Revise Date 29 November 2021
  • Accept Date 21 December 2021