摘要
针对传统的安全因数法考虑载荷和强度不确定性因素对飞机安全性的影响太笼统,无法从根本上减轻飞机结构质量的问题,提出一种飞机结构可靠性优化设计方法.根据应力-强度干涉模型计算结构单元的可靠度,建立以单元满可靠度为准则的优化模型,实现包含可靠性约束的结构尺寸优化.该功能已经加入到COMPASS中.算例结果表明该方法能够减轻结构质量,改善结构可靠度.该方法为开展飞机结构不确定性设计提供技术手段.
As to the problem that the structure mass can not be lightened fundamentally by traditional safety factor method that considers the safety influence caused by load and intensity nondeterminacy factor too indistinctly,a reliability optimization design method for aircraft structure is proposed.According to the stress-intensity interference model,the structure unit reliability is calculated,then a optimization model is built taking unit full-reliability as criterion and the structure size optimization including reliability restriction is realized.The function is added into COMPASS.The calculation case results show that the method can lighten structure mass and improve structure reliability.The method can provide technique means on aircraft structural uncertainty design.
出处
《计算机辅助工程》
2013年第3期29-33,共5页
Computer Aided Engineering
基金
中航工业集团公司航空支撑项目(61901050202)
关键词
飞机
薄壁结构
准则法
可靠性
优化设计
关键元
COMPASS
aircraft
thin-wall structure
criterion method
reliability
optimization design
key element
COMPASS
