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美国政府科技报告
>Pulsed Plasma Solid Propellant Microthruster for the Synchronous Meteorological Satellite. Task 4 Engineering Model Fabrication and Test Report
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Pulsed Plasma Solid Propellant Microthruster for the Synchronous Meteorological Satellite. Task 4 Engineering Model Fabrication and Test Report
Two flight prototype solid propellant pulsed plasma microthruster propulsion systems for the SMS satellite were fabricated, assembled and tested. The propulsion system is a completely self contained system requiring only three electrical inputs to operate: a 29.4 volt power source, a 28 volt enable signal and a 50 millsec long command fire signal that can be applied at any rate from 50 ppm to 110 ppm. The thrust level can be varied over a range 2.2 to 1 at constant impulse bit amplitude. By controlling the duration of the 28 volt enable either steady state thrust or a series of discrete impulse bits can be generated. A new technique of capacitor charging was implemented to reduce high voltage stress on energy storage capacitors. (Author)
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