摘要
研究大型发射装置的减重优化设计对其战斗效率提升具有重要意义,针对其实物实验周期长、成本高的问题,提出基于虚拟试验的方法开展研究.以某大型高超声速飞行器发射装置为研究对象,考虑高超声速飞行器、发射筒、起竖托架为柔性体、起竖机构为刚性体,通过模态分析获取了柔性体部件的模态信息,建立了发射装置的刚柔耦合模型,进行2种工况的起竖动力学仿真,并探究发射筒4个壁厚参数对于起竖承载能力的影响.结果表明:相比开环控制工况,带前馈PD控制工况下起竖过程高超声速飞行器的横向加速度过载降低了75.90%.以发射筒最大Mises应力作为承载指标,发射筒首部(Ⅳ)段厚度降低会使得承载其情况更优,前托座后部、起竖托架覆盖处(Ⅱ、Ⅲ)厚度对承载情况影响显著.基于RBF神经网络建立承载指标与2个影响较大(Ⅱ、Ⅲ)厚度参数的代理模型,利用NSGA-Ⅱ算法对发射筒质量和承载情况进行了多目标优化;保证了承载情况下,发射筒减重率达12.79%.
Weight reduction optimization of large-scale launch systems is crucial for enhancing combat efficiency.To address the challenges of prolonged cycles and high costs in physical experiments,a virtual testingbased approach was proposed.Taking a hypersonic vehicle launch system as research subject,a rigid-flexible coupling model was developed by treating the hypersonic vehicle,launch canister,and erection cradle as flexible bodies while modeling the erection mechanism as a rigid body.Modal characteristics of flexible components were obtained through modal analysis.Erection dynamics simulations under two control schemes were done and the influence of four wall thickness parameters on the erection load-bearing capacity was investigated.Results demonstrated that the feedforward-augmented PD control reduced lateral acceleration overload on the hypersonic vehicle by 75.90%compared to open-loop control.Using the maximum Mises stress of the launch canister as the load-bearing index,parametric studies on four wall thickness parameters revealed that reducing thickness in the forward section(zone IV)improved load-bearing capacity,while thickness variations in the rear area of the front support base(zone II)and the cradle interface(zone III)significantly affected structural performance.A radial basis function(RBF)neural network surrogate model was established based on the load-bearing index(maximum Mises stress)and two critical thickness parameters(zones II and III).Multi-objective optimization for canister mass and load-bearing capacity was implemented using the NSGA-II algorithm,achieving a 12.79%weight reduction while maintaining structural integrity.
作者
荣吉利
孙泽源
宗凯
陈子超
王圣龙
韦振乾
RONG Jili;SUN Zeyuan;ZONG Kai;CHEN Zichao;WANG Shenglong;WEI Zhenqian(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《北京理工大学学报》
北大核心
2025年第12期1247-1258,共12页
Transactions of Beijing Institute of Technology
关键词
大型发射装置
起竖过程
仿真分析
多目标优化
large-scale launch system
erection process
simulation analysis
multi-objective optimization
