作者：龚景松, 侯凌云, 赵文华

作者单位：清华大学航天航空学院, 北京 100084

关键词：测量装置; 微小卫星; 微小推力; 动态响应; 电磁加载力

摘要：

为满足微小卫星姿态和轨道控制发动机微小推力(几百毫牛量级)动态特性研究和测试的需要,在一种微小推力测量系统上(其推力范围为0~400 mN)开展了动态响应特性研究,分别采用小球加载和电磁加载技术给系统加力,对比了小球下落、负阶跃力响应和电磁加载的动态响应过程。实验结果表明:电磁加载标定方式简单实用,避免了运动部件和操作因素等随机干扰带来的误差;测量系统的响应时间达到了15 ms,并具有很好的测量稳定性和重复性,可以满足微小卫星用发动机的动态推力测量的需要,具有很好的应用前景。

Study on unsteady response characteristics of small thrust measurement system

GONG Jing-song, HOU Ling-yun, ZHAO Wen-hua

School of Aerospace, Tsinghua University, Beijing 100084, China

Abstract: The unsteady response characteristic of small thrust measurement was presented in this paper to satisfy the need of unsteady small thrust measurement of attitude and orbit control thrusters employed by the micro-satellite. Small ball and electromagnetic force adding method were used to be loaded on the system. The range of the thrust is from 0 mN to 400 mN. The experimental result shows that the electromagnetic method is simpler than that of the balls. The response-time can reach about 15 ms. Measurement stability and repeatability are good enough to meet the need of research on micro-satellite thrusters. It has a good prospect in applications.

Keywords: measuring device; small satellite; small thrust; unsteady response; electromagnetic force adding

2012, 38(2): 10-12  收稿日期: 2011-9-9;收到修改稿日期: 2011-11-21

基金项目: 

作者简介: 龚景松(1975-),男,天津市人,讲师,博士,主要从事航空宇航推进理论与技术的研究。

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