Performance and lifetime testing of a pulsed plasma thruster for Cubesat applications

• Published in: Aerospace science and technology Vol. 47; pp. 291 - 298
• Main Authors: Ciaralli, S., Coletti, M., Gabriel, S.B.
• Format: Journal Article
• Language: English
• Published: Elsevier Masson SAS 01.12.2015
• Subjects: Compensation; Cubesat; Drag; Electrical propulsion; Mathematical models; Pulsed plasma thruster; Pulsed plasma thrusters; Safety factors; Shot; Thrusters; Cubesat; Pulsed plasma thruster; Electrical propulsion
• ISSN: 1270-9638; 1626-3219
• DOI: 10.1016/j.ast.2015.09.031

This paper describes the design and testing of the engineering model of a pulsed plasma thruster for Cubesat applications (PPTCUP-EM). It has been developed by Mars Space Ltd, Clyde Space Ltd and the University of Southampton with the main aim of increasing the in-orbit lifetime of Cubesats by providing drag compensation. Nevertheless, this thruster can be also utilized to perform formation flying, small orbit changes and Cubesat end of life deorbiting. A test campaign has been carried out to prove that the thruster and the conditioning electronics lifetimes are long enough to utilize all the propellant stored on-board. From the results of the test, the PPTCUP-EM can deliver a total impulse of 42.9±3.9 N s in about 1,125,000 shots. Moreover during the test campaign, a total of more than 1,800,000 shots have been achieved providing a safety factor of about 60% with respect to the number of required shots. The results gathered, including a preliminary characterization of the electromagnetic noise generated by the unit, are presented and show that the overall thruster performance is not influenced by the thruster aging.