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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0～400mN)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15ms,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。
In order to meet the need of researching and testing the dynamic characteristics of micro-satellite attitude and orbital control micro-thrust (hundreds of milliohms), the dynamic response characteristics of a small thrust measurement system (the thrust range is 0 ~ 400mN) are studied , Respectively, using the ball loading and electromagnetic loading technology to force the system, compared the ball drop, negative step response and electromagnetic loading dynamic response process. The experimental results show that the electromagnetic load calibration method is simple and practical, which avoids the error caused by random disturbance such as moving parts and operating factors. The response time of the measurement system reaches 15ms and has good measurement stability and repeatability, The need for dynamic thrust measurement of satellite engines has good application prospects.