力限技术在航天器振动试验中的应用

Application of Force Limited Method in Vibration Test of Spacecraft

为了在正弦振动试验中模拟真实的飞行环境,防止因"过试验"而导致航天器结构发生不必要的破坏,需要对试验条件进行下凹控制。在以往的加速度下凹控制方法的基础上,引入力限控制方法可以提高航天器主频处下凹控制的精度和有效性。文章分析了传统加速度下凹控制方法的局限性,并以某结构星力限控制试验为基础,阐述了结构星力限试验条件的制定方法,介绍了力限双控试验平台设计,并分析了试验结果。经分析表明,力限控制具有较高的控制精度,在加速度控制的基础上引入力限控制的"双控"试验方法,能够有效解决航天器振动试验中的"过试验"和"欠试验"问题。

In order to simulate the real flight evrionment and avoid unnecessary structure destruc- tion by over-testing, the sinusoidal vibration test level needs to be notched down. The accuracy and effectivness of notch-down control at the resonance frequencies of spacecraft can be improved by introducing force limited method into traditional acceleration notch-down method. In this pa- per, the limitaions of traditional acceleration notch-down method are disscussed~ and then force limited control test on a satellite strucutal model, the test criteria, and the test platform for force limited test are introduced. The analysis shows that force limited test has high efficiency and ac- curacy, and the over-testing or insufficient-testing problems in spacecraft vibraiton tests can be solved by dual contral test method with force limitation.