This report is a summary of the work performed in the design, fabrication, and test of resistance jet microthruster systems for East-West station keeping and station changing duties on the Dodge-II Satellite. The thrusters were electrically heated and ammonia gas was used as fuel. For the station keeping function, thrust values of 3, 6, and 9 micropounds were supplied. For station keeping, 100 micropounds of thrust were provided, with a catalyst being used to assist in decomposition of the ammonia. Included in this work was the design and fabrication of a torsion-wire device that was used for measuring thrust in the required low range. Parabolic flights of KC-135 aircraft carrying plastic models of the microthruster system's fuel tank proved its suitability for delivering gas to the propulsion system under zero-g conditions. These experiments, showing equilibrium positions of the propellant, were recorded in slow motion on a 900 foot reel of color film. Electrical designs were completed for a power and signal conditioner to convert satellite electrical power into the forms required by the microthruster system. A portion of this conditioner contained circuitry to condition the various instrumentation signals into a form acceptable to the vehicle telemetry system for earth transmission. (Author)
Resistance Jet Microthruster System Development
1969
323 pages
Report
No indication
English
Rocket Engines & Motors , Manned Spacecraft , Scientific satellites , Attitude control systems , Design , Heating elements , Nozzles , Orifices , Gaseous rocket propellants , Ammonia , Propellant tanks , Pressure regulators , Valves , Power supplies , Thrust , Measurement , Manufacturing , Test methods , Dodge satellites , Microthrusters , Station keeping
Colloid microthruster system development
AIAA | 1968
|AIAA | 1969
|Problems of microthruster development
Springer Verlag | 2010
|AIAA | 2010
|Problems of microthruster development
Online Contents | 2010
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