Development of a MEMS based colloid thruster with sandwich structure

Abstract Design of a propulsion system with mini-size, high specific impulse and extremely low impulse bit is highly demanded by micro and nano spacecrafts. In this paper, a MEMS based micro colloid thruster has been developed by bulk silicon processing. The dimensions of the new thruster have been reduced considerably, which allows the micro thrusters to use a working voltage of 1–3 kV instead of 5–10 kV traditionally. The emitter of the thruster is designed to enable fine thrust control in the micro Newton range. A cantilever-based test facility is further developed to test the micro colloid thruster. Experimental results show that a thrust in the order of micro Newton can be produced by a single emitter, with a working threshold voltage as low as 1400 V.

[1]  Jeffrey Reichbach,et al.  MICROPROPULSION SYSTEM SELECTION FOR PRECISION FORMATION FLYING SATELLITES , 2001 .

[2]  J. Mora,et al.  The current emitted by highly conducting Taylor cones , 1994, Journal of Fluid Mechanics.

[3]  Juergen Mueller,et al.  Towards micropropulsion systems on-a-chip: initial results of component feasibility studies , 2000, 2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484).

[4]  Juergen Mueller,et al.  Thruster Optins for Microspacecraft: A Review and Evaluation of Existing Hardware and Emerging Technologies , 1997 .

[5]  Siegfried W. Janson,et al.  Microtechnology for space systems , 1998, 1998 IEEE Aerospace Conference Proceedings (Cat. No.98TH8339).

[6]  Zhaoying Zhou,et al.  A vaporizing water micro-thruster , 2000, Proceedings IEEE Thirteenth Annual International Conference on Micro Electro Mechanical Systems (Cat. No.00CH36308).

[7]  Scott D. Collins,et al.  Vaporizing liquid microthruster , 2000 .

[8]  Mark Campbell,et al.  A micro pulsed plasma thruster (PPT) for the "Dawgstar" spacecraft , 2000, 2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484).