固体火箭发动机延伸喷管折转片接触分析  

Bnding Linkage Contact Analysis for Extendible Exit Cone Nozzle of Solid Rocket Motor

作　　者：王锟[1] 蔡体敏[1] 

机构地区：[1]西北工业大学航天学院

出　　处：《弹箭与制导学报》2010年第4期119-122,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：研究固体火箭发动机延伸喷管的动力学性能可为改进固体火箭发动机设计水平提供理论依据。仿真是多快好省实现延伸喷管动力学研究的有效方法。利用机械系统动力学仿真分析软件ADAMS进行延伸喷管展开动力学仿真，计算出延伸喷管展开过程中折转片支耳处的受力情况，利用其结果将动力接触计算问题简化为静力接触计算问题．并利用MARC计算了折转片展开到位时的强度和刚度，为延伸喷管展开机构的改进提供了重要的理论依据。Dynamics character of extendible exit cone nozzle is very important for character of solid rocket motor. Expansion dynamics simulations of extendible exit cone nozzle are carry out by ADAMS. And force conditions are calculate of follower pin of bending linkage. In order to further study, practical dynamic contact is simplifying to static contacted by analysis the results of force condition, Then the intensity and the rigidity can be calculated by MARC when bending linkage is all expansion. The results may be an important theoretical basis for improving design of extendible exit cone nozzle expansion device.

关 键 词：延伸喷管 数值仿真 折转片 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]