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Dynamic Performance of a Subliming Solid Reaction Jet
AEROSPACE CORP EL SEGUNDO CA LAB OPERATIONS
The pulsed propulsive performance of a low-thrust subliming-solid ammonium carbamate reaction jet is analyzed and compared with the results of laboratory experiments. Tests of the 15 millipound thruster were conducted at sea level using a 1.68 to 1 expansion ratio nozzle and at vacuum using a 48 to 1 expansion ratio nozzle. The transient processes, which dominate the short-pulse or limit-cycle mode of thruster operation, are formulated and show good correlation with the data. The apparatus, procedures, and techniques required to obtain accurate test results for a low-thrust dynamic mode of operation are described. Impulse bit size, gas consumption, and specific impulse are characterized in terms of thruster geometry, gas properties, and command pulse width to provide a systematic basis for design. Limitations and design criteria necessary for successful spacecraft installation are discussed. A comparison is made between the performance of the subliming solid reaction jet system and the performance of other propellants.
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