运动导弹激励下柔性导轨振动的多体动力学分析法  

Multi-body Dynamics Analysis Method for Vibration of Flexible Guide Activated by Moving Missile

作　　者：王林鹏[1] 王汉平[1] 杨鸣[1] 毕世华[1] 王绍助[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空学报》2014年第3期756-763,共8页Acta Aeronautica et Astronautica Sinica

基　　金：部级项目~~

摘　　要：针对导弹轨式发射采用柔性接触进行动力学建模后计算稳定性差、结构复杂时计算规模大的问题,提出了一种用能随柔性导轨变形的柔性点线约束来替代导弹定向钮与导轨之间接触关系的建模方法;基于有限元模型、单段导轨多体动力学模型和多段拼接导轨多体动力学模型的模态和静态对比分析,验证并消除了应力刚化效应的影响;在考虑导轨应力刚化效应的前提下构建了运动导弹激励下柔性导轨振动的多体动力学模型。仿真结果表明,该方法不仅可以有效解决柔性体接触算法计算量大、计算稳定性差等问题,而且也具有较好的仿真精度。该方法可为复杂导弹发射系统发射过程的多柔体动力学建模提供可行的简化途径。For a launching dynamics model of a guide-type missile launcher system based on the flexible contact method, the stability is unsatisfactory, and the calculation scale is also too large when the guide shape is complex. To solve this prob- lem, a modeling method is proposed which substitutes the flexible point-curve joint following the flexible guide for the contact relationship between the missile directional supports and the guide. By comparing the modal and static analysis results of the finite element model, the single segment guide dynamics model and the multi-segment guide dynamics model, the stress stiff- ening effect is verified and eliminated. Taking the stress stiffening effect of the flexible guide into consideration, a multi-body dynamics model is established which describes the vibration of the flexible guide activated by a moving missile. The simula- tion results show that the method not only effectively resolves the low efficiency of the flexible body contact algorithm, signif- icantly improves the calculation stability, but also demonstrates good simulation accuracy. This method may provide a new way for modeling flexible multi-body dynamics of complex missile launcher systems.

关 键 词：发射动力学 柔性导轨 柔性线 多体动力学 应力刚化 形函数 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程] TJ768.2[兵器科学与技术—武器系统与运用工程]