【摘要】 利用直接激励法 ,对火箭发射过程中考虑星箭动力耦合作用的卫星结构瞬态响应问题进行了求解。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。该方法克服了大质量法和惯性载荷法瞬态响应计算中的载荷处理困难和数据回归困难。文中给出了大质量法、直接激励法和惯性载荷法的动力学方程 ,指出各种方法的应用条件。计算结果表明 ,直接激励法简捷实用 ,优于惯性载荷法和大质量法更多还原

【Abstract】 Structural transient response considering satellite rocket dynamic coupling effect was computed by the direct excitation method.The acceleration time response graphs at desired positions were presented under three load conditions:the maximum dynamic pressure,before separation,after separation.The enforced motion equations of three methods were presented and the application conditions were pointed out.It showed that all these methods were satisfied the engineering applications,whereas the direct excitation method is more preferable.更多还原