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文章总结了航天器系统级力限振动试验夹具设计思路,提出利用合力和合力矩进行力测量装置有效性校核的方法。并通过航天器系统级力限振动试验,对力测量误差原因进行分析,指出通过提高加速度和力信号信噪比的办法可使相对误差减小到±10%以内或更低,验证了力测量装置的有效性。
The paper summarizes the design idea of system-level force-limited vibration test fixture for spacecraft and proposes a method to check the validity of force measuring device by using resultant force and moment. And through the system-level force-limited vibration test of spacecraft, the reason of force measurement error is analyzed. It is pointed out that the relative error can be reduced to within ± 10% or lower by increasing the signal-noise ratio of acceleration and force signal. The effectiveness of the device.