基于卫星推进剂剩余量测量的热容法数值仿真  

Numerical Simulation of Thermal Propellant Gauging System for Satellite

作　　者：郭蕾 李永[1] 焦焱[1] 靳忠涛 李代伟 GUO Lei;LI Yong;JIAO Yan;JIN Zhong-tao;LI Dai-wei(Beijing Institute of Control Engineering,Beijing 100190;State Key Laboratory of Astronautic Dynamics,Xi'an 710043)

机构地区：[1]北京控制工程研究所,北京100190 [2]宇航动力学国家重点实验室,西安710043

出　　处：《导航与控制》2018年第6期102-107,共6页Navigation and Control

摘　　要：由于具有主动热源的输入,与传统PVT方法相比,热容法在卫星寿命末期具有较高的推进剂剩余量测量精度。为了获得地面条件下准确的热分析模型,对某型号1407L网式表面张力贮箱在地面条件下应用热容法进行数值仿真。通过数据分析,并与地面试验结果进行比对,验证了热分析模型的有效性,获得了地面环境下准确的热分析模型,为热容法的后续深入研究和在轨应用提供了参考。Comparing with PVT method,thermal propellant gauging system (PGS) method has more precision at end-of-life (EOL) of satellite toward propellant gauging because of the input of the active heat source. In order to obtain the accurate thermal analysis model on ground,the thermal propellant gauging system method used on a type of 1407L filling tank on ground are numerically simulated. According to the analysis and comparison with the ground test,the availability of the thermal analysis model is verified,and the accurate thermal analysis model is obtained. The profile is of reference value in the subsequent research and application of theramal propellant gauging system method.

关 键 词：热容法 推进剂剩余量 表面张力贮箱 数值分析 

分 类 号：V432[航空宇航科学与技术—航空宇航推进理论与工程]