推进剂加注后卫星封闭管路内压力爬升特性研究

Study on pressure climbout characteristic in liquid-locked pipeline of satellite after filling propellant

为有效评估推进剂加注后卫星封闭管路的压力爬升特性,提出了一种综合考虑推进剂液体体积膨胀效应和管路残余气体压缩效应的改进算法,定量分析了初始液体温度、初始气体温度、初始加注压力和初始真空度等加注参数对管路压力爬升的影响。结果表明,相对于传统的理想气体状态方程法和液体膨胀法,本文提出的改进算法与实测值最为接近;初始气体温度对管路压力爬升影响较小,初始液体温度越低、初始加注压力取值越高、初始真空度取值越低则管路压力爬升效果越明显;设置初始加注压力0.30MPa、初始真空度2.00kPa,在全工况范围内管路压力升高比不超过4.5,即管路压力不超过1.35MPa,满足推进系统压力警戒值不超过2 MPa的设计要求。

In order to effectively evaluate the pressure climbout characteristics of the liquid-locked pipeline on the satellite after filling propellant,an improved algorithm that integrated the liquid volume expansion effect of propellant and the compression effect of residual gas in the pipeline was proposed.The influence of the filling parameters such as initial liquid temperature,initial gas temperature,initial filling pressure and initial vacuum degree on the pressure climbout of the pipeline was quantitatively analyzed.The results show that compared with the traditional ideal gas state equation method and liquid expansion method,the obtained results from the improved algorithm proposed in this paper are the closest to the measured values.The initial gas temperature has less effect on the pressure climbout of the pipeline.With the decrease of initial liquid temperature,the increase of initial filling pressure value and the decrease of initial vacuum degree,the pressure climbout effect of the pipeline becomes obvious.Setting the initial filling pressure at 0.30MPa,the initial vacuum degree at 2.00kPa,the pipeline pressure rise ratio does not exceed 4.5 in the full range of working conditions,i.e.,the pipeline pressure does not exceed 1.35MPa,which meets the design requirement of the propulsion system pressure alert value not exceeding2MPa.