空间飞行器界面力限控制技术研究

目的 研究力限控制技术,解决过试验问题.方法 以空间飞行器模拟件为试验对象,搭建力限振动试验系统.通过低量级正弦扫频试验方法获取力限参数.采用半经验法、简单二自由度法、复杂二自由度法的极小包络建立力限控制方程.对比研究力限控制与加速度限制控制两种方法对控制效果的影响.结果 在力限控制作用下,振动曲线控制比较稳定,且在预期的共振频带处呈现倒三角窄带下凹现象.相较于加速度限制方法,力限控制方法对共振现象限制比较稳定、精准,对共振峰抑制比较明显.结论 力限控制技术对共振现象具有较好的控制效果,可以针对共振频带进行精准控制.

Research on Interface Force Limiting Control Technology of Space Vehicle

This paper aims to study the force limited control technology and solve the overtesting problem. In this study, a force-limited vibration test system was built using a space vehicle simulator as the test object. The force-limit parameters were obtained by low-level sinusoidal sweep test method. By the way of the semi-empirical method, the simple two-degree- of-freedom method and the complex two-degree-of-freedom method, the force-limit control equations were established with their minimum envelope. The influence of force limited control and acceleration limit control on the control effect was comparatively studied. By the force-limit control technique, the vibration control curve is more stable with a inverted triangular narrow-band concave at the resonance frequencies. Compared with the acceleration limit method, the force limit control method is more stable and accurate in limiting the resonance phenomenon, and the resonance peak suppression is more obvious. The force-limit control technique is better in controlling resonance, and has great significance to the assessment of environment space products in vibration test.