力限半经验系数研究

Research of force-limited vibration for semi-empirical coefficient

利用力限技术可以缓解由于星箭界面机械阻抗的差异所造成的过实验现象,半经验法是获取耦合界面力限的重要方法,如何确定半经验系数是关键。基于固定界面子结构模态综合法,推导了半经验系数的理论表达式,分析了半经验常数与星箭耦合系统参数之间的关系。基于此方法,以某工程型号卫星为例计算了其半经验系数并制定了正弦实验的力限条件,通过实验数据进行验证,结果表明:该方法所得力限条件能够较好的反映出耦合界面在共振峰处的真实受力。可以为后续力限半经验法的工程应用提供一定的参考。

Using force-limited technology can ease overtesting which caused by the difference of impedance of the interface between satellite and rocket.Semi-empirical method is a significant technology to acquire interface force.It is critical to identify the parameter of semi-empirical.This paper,based on fixed interface substructure modal synthesis method,deduce the theory expression of semi-empirical coefficient and analyze the relationship of the parameter between semi-empirical and satellite-spacecraft systems.Using the method,we calculate semi-empirical coefficient of a certain engineer satellite model and formulate sine testing force-limited condition,and verified by testing data.Experimental results indicate that the force limited condition,acquiring from this method,can preferably reflect the real stress between the satellite-rocket coupling system in resonance peak.It can provide some reference for the engineering application of the semi-empirical method.