摘要
对于大长细比的旋转火箭，研究发射过程中火箭弹和发射装置的耦合振动，分析火箭、发射管和定心部的结构柔性对其运动姿态的影响，并讨论了当前定心部滑离轨道时的系统撞击动力响应，为火箭姿态控制和新型发射装置的设计提供了有益的参考。
In this paper, the coupled vibrating behavior between a spinning rocket with large slenderness ratio and the launcher is studied. Effects of flexibility of rocket and launcher and supporting shoes on the rocket's motion attitude are analyzed. The impact transient response is obtained using a hybrid method when some supporting shoes separate out of the launcher. The approach will provide a useful reference to the design for the new type of rocket-launcher system.
出处
《工程力学》
EI
CSCD
北大核心
1998年第1期133-139,共7页
Engineering Mechanics
基金
国防科技预研基金
上海市科技发展基金
