卫星液体推进剂剩余量测量的热力学模型及其应用

THERMODYNAMIC MODELS OF PSGI AND THEIR USAGE FOR LIQUID PROPELLANT REMAINING MEASUREMENT ON SATELLITE

通过对气体注入压力激励法测量卫星液体推进剂剩余量装置系统的详细热力学过程分析，建立了能满足实际测量需求的等温和绝热两种热力学模型，对具体测量模型的选用及相关问题进行了分析讨论，并在此基础上给出了两种模型在实际测量中的应用模式。

This paper is theoretical studies about the method of the pressure stimula ted by gas injecting(PSGI),which was nominated for the most suitable candidate applicable to the chinese telecommunication satellite to measure liquid propellant remaining.Two main thermodynamical models,the isothermal model and the adiabatic model,were established and the dominant equations corresponding to the models were derived for practical measurement usage.Lastly,some problems associated with actual operations were discussed in details.