At the end of a test satellite, oxidant of the propulsion system was exhausted ahead of fuel. Long-term monopropellant working condition without combustion, cool gas flow working condition and interim working condition were experienced, which trouble the de-orbit control of the satellite. In order to evaluate the performance of the propulsion system on the special working conditions during the satellite de-orbit, theoretic analysis of the specific thrusters is introduced. And effective calculation method is built. Based on the method and obtained remote data, the thrust and specific impulse of the propulsion system on monopropellant working condition and cool gas flow working condition are calculated. It is indicated that, on monopropellant working condition, the thrust of 10N thruster declines 83%, the specific impulse declines about 82%. On cool gas flow working condition, the thrust of the 10N thrusters is less than 0.12N, and declines with the decrease of the tank pressure. The specific impulse is less than 146s. These results can be consulted by other satellites confronting similar conditions.


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    Title :

    Performance Analysis of Bipropellant Propulsion System on Special Working Conditions


    Contributors:

    Published in:

    Publication date :

    2013-08-30


    Size :

    5 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English