导弹折叠翼展开过程的动力学仿真及试验研究  

Dynamic Simulation and Experimental Study of Deployment Process of Missile Folding-wing

作　　者：甄文强 姬永强[1] 石运国[1] 

机构地区：[1]中国工程物理研究院总体工程研究所,四川绵阳621000

出　　处：《兵工学报》2016年第8期1409-1414,共6页Acta Armamentarii

基　　金：中国工程物理研究院总体工程研究所创新与发展基金项目(15CXJ13)

摘　　要：对导弹中常用的横向折叠翼展开过程进行研究,考虑折叠翼展开过程中气动阻力和摩擦力的作用,建立了导弹发射及地面试验时折叠翼展开过程的数学模型,使用动力学仿真软件建立相应动力学仿真模型,设计并制作了折叠翼,使用高速摄影获取折叠翼展开过程图像,开展地面试验研究。研究结果表明,试验结果与数学模型及动力学仿真模型结果的一致性较好,验证了折叠翼展开过程数学及动力学仿真模型的正确性。根据试验结果给出摩擦力矩的具体取值范围,为折叠翼的工程设计和应用提供了参考。The deployment process of transverse folding-wings of missiles is studied. The mathematical model and dynamic simulation model of deployment process of folding-wing in missile launching and ground tests are both established,in which the influences of friction and aerodynamic force are considered. The folding-wing were designed and manufactured. The images of deployment process of foldingwings are obtained using the high speed photography during ground test. The research results show that the test results are in good agreement with those of mathematic and dynamic simulation models. A value range of friction moment is also provided from the test results,which can support the design and application of folding-wing.

关 键 词：兵器科学与技术 折叠翼 展开 动力学仿真 试验 

分 类 号：TJ760.13[兵器科学与技术—武器系统与运用工程]