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术文描述由休斯航空公司研制、试验和取得专利的低重力推进剂测量系统(PGS)。PGS 在通常卫星预定15年飞行寿命中预测卫星寿命终了(EOL)的准确度在±2月之内甚至更佳。该系统已用于休斯 HS601同步通信卫星。PGS 从初始设计就简化并尽力减少系统所要求的硬件。现有的挤压气体箱和推进剂箱中间装有高分辨率传感器和内接阀门。PGS 通过瞬间打开对应的高压挤压气箱与推进剂箱之间的互连阀对推进剂周期性地加压进行测量。根据加压前后压力的测量值,应用气体定律计算可以确定推进剂箱中气体的体积,进一步可以得到液体的体积,这样就计算出箱中推进剂的质量。应用气体定律时也需要测定温度。为精确测定温度,每个贮箱都安装了多个温度敏感器,为进一步提高精度,使用非常精确的高分辨率的压力传感器作为气体温度计。通过对所推荐的测量方案的原型机试验,建立了对系统精确预测由于推进剂耗尽而引起的卫星寿命终了的能力的信心。PGS 具有容错能力,不受推进剂分系统正常工作的干扰。加压能力为双元推进系统额外提供了精密地控制氧化剂-燃料混合比的好处,这样通过使伴随某种推进剂比另一种先耗尽时使推进剂的残留量降到最低来提高位置保持寿命。
The article describes a low gravity propellant measurement system (PGS) developed, piloted and patented by Hughes Airlines. The accuracy of PGS predicting end-of-life (EOL) over the 15-year flight life of normal satellites is even better within ± 2 months. This system has been used on Hughes HS601 synchronous communications satellite. PGS simplifies and minimizes the hardware required by the system from the initial design. The existing squeeze gas box and propellant box equipped with high-resolution sensors and internal valves. The PGS measures the propellant pressure periodically by instantly opening the interconnecting valve between the corresponding high pressure extrusion gas tank and the propellant tank. According to the pressure before and after the pressure measurement, the application of gas law calculation can determine the volume of gas in the propellant tank, the liquid volume can be further obtained, thus calculating the quality of the propellant box. It is also necessary to determine the temperature when applying the gas law. For precise temperature measurement, multiple temperature sensors are installed in each tank. To further improve accuracy, a very accurate high-resolution pressure sensor is used as the gas thermometer. Prototype testing of the proposed measurement scheme established confidence in the ability of the system to accurately predict the end of satellite life due to depletion of propellants. PGS is fault-tolerant and immune to the normal operation of the propellant subsystem. Pressurization capabilities additionally provide the dual propulsion system with the benefit of finely controlling the oxidant-fuel mixture ratio by raising the position by minimizing propellant residues as one propellant is depleted over the other, first Maintain life.