A hybrid cold gas microthruster system for spacecraft

• Published in: Sensors and actuators. A, Physical Physical, 2002-04, Vol.97, p.587-598
• Main Authors: Köhler, Johan, Bejhed, Johan, Kratz, Henrik, Bruhn, Fredrik, Lindberg, Ulf, Hjort, Klas, Stenmark, Lars
• Format: Article
• Language: English
• Subjects: Applied sciences; Cold gas micropropulsion; Electronics; Exact sciences and technology; Micro- and nanoelectromechanical devices (mems/nems); Micronozzle; Piezoelectric valve; Semiconductor electronics. Microelectronics. Optoelectronics. Solid state devices
• ISSN: 0924-4247; 1873-3069; 1873-3069
• DOI: 10.1016/S0924-4247(01)00805-6

A hybrid cold gas microthruster system suitable for low Δ v applications on spacecraft have been developed. Microelectromechanical system (MEMS) components together with fine-mechanics form the microthruster units, intergrating four independent thrusters. These are designed to deliver maximum thrusts in the range of 0.1–10 mN. The system includes three different micromachined subsystems: a nozzle unit comprising four nozzles generating supersonic gas velocity, i.e. 455 m/s, four independent piezoelectric proportional valves with leak rates at 10 −6 scc/s He, and two particle filters. The performances of all these MEMS subsystems have been evaluated. The total system performance has been estimated in two parameters, the system-specific impulse and the mass ratio of the propulsion system to the spacecraft mass. These figures provide input for spacecraft design and manufacture.