考虑星-箭动力耦合作用结构瞬态响应分析  

Structural transient response analysis considering satellite-rocket dynamic coupling effect

作　　者：杨德庆[1] 王德禹[1] 汪庠宝[1] 

机构地区：[1]上海交通大学船舶与海洋工程学院结构力学研究所,上海200030

出　　处：《宇航学报》2003年第2期213-216,共4页Journal of Astronautics

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 。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.

关 键 词：火箭发射 直接激励法 瞬态响应 动力耦合作用 星箭结构 

分 类 号：V525[航空宇航科学与技术—人机与环境工程]