卫星推进剂剩余量测量技术地面试验研究

SIMULATIVE TEST STUDY ABOUT THE TECHNOLOGY FOR GAUGING LIQUID PROPELLANT RESIDUAL ON SATELLITE

根据气体注入压力激励测量方法 ,研制了动态、高精度测量卫星液体推进剂剩余量原理样机 ,该样机以通信卫星双组元推进系统为测量对象。详细给出了利用该样机进行的地面试验情况 ,特别是测量数据平滑处理技术和液体蒸汽压误差修正技术。试验结果表明 ,当推进系统工作状态正常时 ,剩余液体体积量的测量误差小于贮箱总体积的 1 .0 % ,而当推进系统有小泄漏时 ,则小于 2 .0 %。

A principle simulative equipment applicable to gauge liquid propellant residual on satellite is introduced briefly. This equipment is developed by a dynamic accurate measurement method named pressure stimulated by gas injection (PSGI) to simulate the propulsion subsystem of DFH 3 satellite. The simulative measurement tests, in particular a smoothness technique for data treatment and a modification technique for uncertainty resulted from the liquid vapor pressure, are presented in details. The test results have indicated that the measurement uncertainties are smaller than one percent of the total tank volume when the propulsion system is normal, and than two percents when the propulsion system is abnormal with small liquid leakage.