卫星结构和控制的复杂性、独特性和诱发故障的多源性导致其故障诊断的困难。
The fault diagnosis of satellites is a difficult problem due to the complex and unique of structure and control of satellite and the presence of multi-excite sources.
用这种方法减缩之后的卫星结构和火箭模型结合后，可以进行载荷耦合计算工作。
Once the satellite structure, shrunk through this method, is connected with the rocket model, coupled loads computation can then be conducted.
给出了最大动压、一二级分离前和分离后三种工况下卫星结构的加速度响应历程。
The acceleration time response graphs at desired positions were presented under three load conditions: the maximum dynamic pressure, before separation, after separation.
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