摘要
针对火箭、导弹储运发射箱前盖快速开启、可靠分离的设计需求,提出一种利用弹簧储能的低冲击弹射式发射箱前盖方案。在此基础上,结合设计方案各部件在分离过程中的受力特性,建立前盖分离和抛落的理论模型,对箱盖分离轨迹进行计算分析。为优化设计参数,利用实验设计方法(DOE)和响应面法(RSM)对影响前盖抛落距离的储能弹簧刚度、有效作用距离以及活动冲击部件的斜板倾角等进行优化分析,获得满足可靠分离判据的优化结果。最后利用基于多体动力学模型的虚拟样机试验对优化模型进行了校验分析,验证了设计方案的可行性和理论模型的合理性。
The reliability of unlocking and separation during missile launching is a design challenge for canister front cover. An ejection cover with low impact, which contains a spring to store impact energies and an inclined plate to change the direction of separation force, is proposed to solve this problem. Considering the separation process of this cover, a dynamic model is built to predict the cover separation trajectory, and two criterions are put forward to judge the reliability of separation. Then some typical design parameters influencing separation characteristics, including the angle of inclined plate, the stiffness and the compression length of the spring, are investigated in detail based on experimental design method and response surface method to achieve optimization results that satisfy the reliable separation criterions. Moreover, the virtual prototype experiment based on the multi-body dynamics model is utilized to verify the cover separation process. The result shows that the front cover with optimized parameters could separate reliably for missile launching, and the dynamic model predicting the separating trajectory is reasonable.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2016年第4期488-493,共6页
Journal of Astronautics
基金
国家自然科学基金(51306019)
关键词
发射箱盖
分离特性
响应面法(RSM)
虚拟样机
Canister cover
Separation characteristics
Response surface method （RSM）
Virtual prototype
