A hybrid cold gas microthruster system for spacecraft

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A hybrid cold gas microthruster system for spacecraft

Köhler, J. / Simu, U. / Bejhed, J. / Kratz, H. / Jonsson, K. / Nguyen, H. / Bruhn, F. / Hedlund, C. / Lindberg, U. / Hjort, K. / ... [more]

Abstract

MEMS components forming a complete hybrid cold gas microthruster system for spacecraft, designed to deliver maximurn thrusts in the range of 0.1 mN to 10 mN, have been demonstrated. The systern includes three different micromachined subsystems: a nozzle unit comprising four nozzies generating supersonic flows, four independent piezoelectric proportional valves with leak rates below 10^-5 sccm He, and two particle filters. The perforrnances of all these MEMS subsystems liave been evaluated.

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Document information

Title :

A hybrid cold gas microthruster system for spacecraft

Additional title:

Hybride Mikroantriebe mit kalten Druckgasen für die Raumfahrttechnik

Contributors:

Köhler, J. (author) / Simu, U. (author) / Bejhed, J. (author) / Kratz, H. (author) / Jonsson, K. (author) / Nguyen, H. (author) / Bruhn, F. (author) / Hedlund, C. (author) / Lindberg, U. (author) / Hjort, K. (author)

Published in:

Transducers, International Conference on Solid State Sensors and Actuators, 11, Eurosensors, 15 ; 886-889

Publication date :

2001

Size :

4 Seiten, 3 Bilder, 1 Tabelle, 9 Quellen

ISBN :

3-540-42150-5

Type of media :

Conference paper

Type of material :

Language :