Normal and failure operation mode of resistojet thruster – experimental research on the laboratory model
DOI:
https://doi.org/10.24425/ather.2025.154180Abstract
Rocket thrusters of various types are used in space to change orbits, maneuver, and position control. The progressive trend in miniaturization of satellites also entails changes in propulsion systems. In recent years, electric rocket thrusters have become increasingly important. Resistojets are one of the simplest types offering thrust ranging from several to hundreds of millinewtons and use two types of energy: potential (pressure) and electrical. Electrical energy added by a resistive element a heater allows a significant increase in the temperature and specific impulse of the working medium. The paper considers the case of damage or lack of electrical power to the heater, which changes the engine operating mode from resistojet to coldgas. Experimental tests were carried out on a model of resistojet thruster operating in atmospheric conditions, both with the heater on and off. For the resistojet mode (heater on), three different variants of the flow delay to the heater activation time were considered. The analysis of results showed how the key propulsion parameters of the thruster change: specific impulse, total impulse, thrust and mass flow rate. For the tested model engine, wherein the resistojet mode the temperature was higher by approximately 120°C compared to coldgas, and approximately a 30% increase in specific impulse was observed. This demonstrates the advantages of the resistojet, where a heater failure "only" causes a reduction in the propulsion potential and not its complete loss. The spaceship or a satellite with resistojet thruster onboard has still the opportunity to accomplish mission goals.References
[1] Sutton, G.P., & Biblarz, O. (2010). Rocket propulsion elements (9th ed.). Wiley.
[2] Tajmar, M. (2012). Advanced space propulsion systems. Springer.
[3] Tummala, A.R., & Dutta, A. (2017). An overview of Cube‑Satellite propulsion technologies and trends. Aerospace, 4(4), 58. https://doi.org/10.3390/aerospace4040058
[4] Cervone, A., Mancaus, A., & Zandbergen, B. (2015). Conceptual design of a low‑pressure micro‑resistojet based on a sublimating solid propellant. Acta Astronautica, 108, 30–39. https://doi.org/10.1016/j.actaastro.2014.12.003
[5] Zakirov, V., Sweeting, M., Lawrence, T., & Sellers, J. (2001). Nitrous oxide as a rocket propellant. Acta Astronautica, 48(5–12), 353–362. https://doi.org/10.1016/S0094-5765(01)00047-9
[6] Lemmer, K. (2017). Propulsion for CubeSats. Acta Astronautica, 134, 231–243. https://doi.org/10.1016/j.actaastro.2017.01.048
[7] Leomanni, M., Garulli, A., Giannitrapani, A., & Scortecci, F. (2016). Propulsion options for very low Earth orbit microsatellites. Acta Astronautica, 133, 444–454. https://doi.org/10.1016/j.actaastro.2016.11.001
[8] Cifali, G., Gregucci, S., Andreussi, T., & Andrenucci, M. (2017). Resistojet thrusters for auxiliary propulsion of full electric platforms. 35th International Electric Propulsion Conference, 8–12 October, Atlanta, GA, USA. http://electricrocket.org/IEPC/IEPC_2017_371.pdf (accessed 22 Nov. 2024).
[9] Hejmanowski, N., Woodruff, C.A., Burton, R.L., Carroll, D.L., & Cardin, J.M. (2015). CubeSat High Impulse Propulsion System (CHIPS). 62nd JANNAF Propulsion Meeting (7th Spacecraft Propulsion), 1–5 June, Nashville, TN, USA.
[10] Schmuland, D., Carpenter, C., & Masse, R. (2012). Mission applications of the MRS‑142 CubeSat high‑impulse adaptable monopropellant propulsion system (CHAMPS). 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 30 July–1 August, Atlanta, GA, USA. https://doi.org/10.2514/6.2012-4269
[11] Kindracki, J., Paszkiewicz, P., & Mężyk, Ł. (2019). Resistojet thruster with supercapacitor power source – design and experimental research. Aerospace Science and Technology, 92, 847–857. https://doi.org/10.1016/j.ast.2019.07.010
