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Implementation of Thermal Gauging Method for SpaceBus 3000A (ArabSat 2B)

机译：SpaceBus 3000A（ArabSat 2B）的热测量方法的实现

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The current paper discusses the Thermal Gauging Method (TGM) developed and employed for the propellant estimation of ARABSAT 2B sateUite. ARABSAT 2B is a commercial geostationary telecommunications satellite owned and operated by the ARABSAT organization based in Riyadh Saudi Arabia. The satellite was built by Thales Alenia Space (Cannes, France) and launched in November 1996. It employs a standard bi-propellant chemical propulsion system. ARABSAT 2B completed its design life of 12 years in 2008 with full functionality and is currently still in operation. The life limiting factor for this satellite is available propellant, hence the importance of a gauging method that determines propellant. It is shown that the TGM provides more accurate estimation of propellant remaining now than methods such as bookkeeping and PVT (Pressure-Volume-Temperature). The TGM (as other thermal methods) is based on a concept of measuring the thermal capacitance of a tank containing liquid fuel and pressurant gas by measuring the thermal response of the propellant tank to heating and comparing the observed temperature rise to simulation results. The current paper discusses the difference between different thermal methods, namely, TPGS, PGS and TGM. The TGM employs a very sophisticated thermal model of the propellant tank which takes into account fuel distribution in the tank, temperature gradients in the tank, etc. While the method consists of several steps, the current paper discusses problems related to finding load of a propellant tank, e.g., how to isolate tank temperature rise due to tank heaters from temperature change due to other heat sources: sun, 'equipment, etc. An accuracy analysis of propellant estimates is also discussed in the current paper. The paper discusses different ways of calculating the error of propellant estimation and shows the most precise approach for calculation. Advantages and weaknesses of TGM are discussed. Accuracy of different methods of propellant estimations is also compared and an area of applicability for each method is determined.
机译：本文讨论了热计量法（TGM），该方法被用于ARABSAT 2B卫星的推进剂估算。 ARABSAT 2B是由位于沙特阿拉伯利雅得的ARABSAT组织拥有和运营的商业对地静止电信卫星。该卫星由Thales Alenia Space公司（法国戛纳）建造，于1996年11月发射。它采用了标准的双推进剂化学推进系统。 ARABSAT 2B于2008年完成其具有完整功能的12年设计寿命，目前仍在运行。该卫星的寿命限制因素是可用的推进剂，因此，确定推进剂的测量方法的重要性。结果表明，与簿记和PVT（压力-体积-温度）等方法相比，TGM可以更准确地估算出目前剩余的推进剂。 TGM（与其他热方法一样）基于以下概念：通过测量推进剂罐对加热的热响应并将观测到的温度升高与仿真结果进行比较，来测量包含液体燃料和增压气体的罐的热容量。本文讨论了不同的热学方法，即TPGS，PGS和TGM之间的区别。 TGM采用了非常先进的推进剂箱热模型，该模型考虑了箱中的燃料分布，箱中的温度梯度等。虽然该方法包括多个步骤，但本文讨论了与寻找推进剂载荷有关的问题。储罐，例如，如何将储罐加热器引起的储罐温度升高与其他热源（太阳，设备等）引起的温度变化隔离开来。本文还讨论了推进剂估算值的准确性分析。本文讨论了计算推进剂估算误差的不同方法，并给出了最精确的计算方法。讨论了TGM的优缺点。还比较了不同的推进剂估算方法的准确性，并确定了每种方法的适用范围。

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