无人机零长发射分离安全性分析
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摘要
论述了零长发射闭锁力、释放机构剪切销尺寸、剪切力计算方法。利用虚拟样机技术(VPT)建立了无人机零长发射分离过程动力学仿真模型,对发射分离各种工况进行仿真分析,得到了无人机离轨运动规律、安全距离等参数,并对靶试工况进行仿真,仿真结果与靶试结果对比基本一致,验证了某型无人机零长发射的可行性和安全性。
This paper presents the calculation method of zero length launch locking force, shear pin dimension of release mechanism and shearing force. The dynamic simulation model of UAV zero length launch separation process is established by means of VPT to carry out the simulation analysis for various operation conditions of launch separation, to obtain the parameters such as off-track law of motion, safety distance, etc. are obtained. The target test operation conditions are simulated, and the simulation result is compared with the target test result, which are basically identical, so as to validate the feasibility and safety of the UAV zero length launch.
This paper presents the calculation method of zero length launch locking force, shear pin dimension of release mechanism and shearing force. The dynamic simulation model of UAV zero length launch separation process is established by means of VPT to carry out the simulation analysis for various operation conditions of launch separation, to obtain the parameters such as off-track law of motion, safety distance, etc. are obtained. The target test operation conditions are simulated, and the simulation result is compared with the target test result, which are basically identical, so as to validate the feasibility and safety of the UAV zero length launch.
引文
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[6]郭卫东.虚拟样机技术与ADAMS应用实例教程[M].北京:北京航空航天大学出版社,2008.
[2]田新锋,薛鹏,李红泉.某无人机火箭助推发射研究[J].宇航计测技术,2012.32(2):30-32.
[3]导弹结构强度计算手册编写组.导弹结构强度计算手册[M].北京:国防工业出版社,1978.
[4]李军.火箭发射系统设计[M].北京:国防工业出版社,2008.
[5]张有济.战术导弹飞行力学设计[M].北京:宇航出版社,1996.
[6]郭卫东.虚拟样机技术与ADAMS应用实例教程[M].北京:北京航空航天大学出版社,2008.