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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 %。
According to the measurement method of gas injection pressure excitation, a prototype of the principle of dynamic and high precision measurement of the residual liquid propellant of satellite was developed. The prototype is based on the communication satellite dual component propulsion system. The ground tests conducted by the prototype are given in detail. In particular, the measurement data smoothing technology and liquid vapor pressure error correction technology are given. The test results show that when the working condition of the propulsion system is normal, the measurement error of the remaining liquid volume is less than 1.0% of the total volume of the tank, and less than 2.0% when the propulsion system has a small leakage.