摘要
为解决大型运载火箭助推器舱体结构承受偏置集中力问题,开展舱体结构优化设计研究。首先围绕舱段结构多工况、多约束的设计需求,采用多目标折衷规划实现舱体结构整体传力路径拓扑优化,根据拓扑优化结果设计一种"梁式"舱体结构,对舱体结构开展强度仿真分析,计算结果表明,"梁式"舱体结构可以提高整体承载能力14.2%,最后通过地面静力试验验证了舱体结构优化设计的正确性。
In order to solve the problem that the cabin structure of the large launch vehicle booster bears the offset concentrated force.The cabin structure is studied by optimization.Firstly,based on designing demand of cabin structure with multiple load cases and constraints,topology optimization of overall force transfer path is realized by multi-objective compromise programming.Then,according to the results of topology optimization,a‘beam type’cabin structure is designed.The result of simulation shows that the bearing load capacity of the‘beam type’cabin structure could be increased by 14.2%.Finally,the result of static experiment verifies the correctness of the design of the cabin structure.
作者
王春林
张游
赵学成
黄帅
张欣耀
Wang Chun-lin;Zhang You;Zhao Xue-cheng;Huang Shuai;Zhang Xin-yao(Shanghai Aerospace Engineering Research Institute,Shanghai,201108;Shanghai Aerospace Equipments Manufacturer Co,Ltd,Shanghai,200245)
出处
《导弹与航天运载技术》
CSCD
北大核心
2021年第5期25-28,共4页
Missiles and Space Vehicles
关键词
偏置集中力
传力路径
拓扑优化
折衷规划
offset concentrated force
force transfer path
topology optimization
compromise programming method
