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建立卫星性能的数学模型通常可用来决定部件尺寸并预示工作参数。这些模型中有的可用地面试验验证其有效性,但其精度必须等到飞行卫星发射后才能最终确认。这些模型是由英国航天航空公司(BAe)为了预示其EUROSTAR平台统一推进分系统的性能而发展的,在1990年10月成功发射的第一个INMARSAT第二代卫星上,这些模型首次接受了飞行验证。液体远地点发动机的挤压系统和推进剂供给模型已用于飞行任务的转移轨道阶段。定点阶段感兴趣的主要参数是反作用控制推力器的进口压力,这些参数用另一程序模拟。本文比较了由计算机模型得到的结果和从卫星遥测接收到的数据。发现模型和遥测结果在一般情况下十分一致。因而通过这次飞行试验可以认为这些模型是正确的。
Mathematical models that establish the performance of satellites are often used to determine the size of components and to predict operating parameters. Some of these models can be validated by ground tests, but their accuracy has to wait until the flying satellites launch to finalize. These models were developed by BAe in anticipation of the unified performance of the subsystems of its EUROSTAR platform. The models were first flown on the first INMARSAT Gen 2 satellite successfully launched in October 1990 verification. Fluid apogee The engine’s extrusion system and propellant supply models have been used in the mission orbit transfer orbit phase. The main parameter of interest during the fixed-point phase is the reaction-controlled inlet pressure of the thrusters, which are modeled by another procedure. This article compares the results obtained from computer models with the data received from satellite telemetry. The results of the model and telemetry are found to be very consistent under normal circumstances. Therefore, the flight test can be considered these models are correct.