摘要
从工程数学求解和有限元分析角度对复合材料结构的稳定性分析方法进行研究,基于这两个方面分别建立了同时考虑壁板稳定性约束和气动弹性约束的气动弹性优化技术,并以大展弦比复合材料机翼为对象,进行气动弹性综合优化设计。研究表明,机翼气动弹性优化中若不考虑稳定性约束条件,虽然可以获得较小结构重量,但往往不满足稳定性要求;相比从有限元角度考虑结构失稳特征的气动弹性综合优化设计方法,通过工程数学方法对机翼结构进行分区失稳分析优化可以更加精准地控制变量,在满足各项性能指标,特别是稳定性约束的同时,进一步减轻了结构重量,提高了结构失稳因子。
Based on engineering mathematical solution and finite element analysis, the aeroelastic optimization technology is developed with consideration of both the wall stability constraints and the aeroelastic constraints.The aeroelastic comprehensive optimization design is carried out for a large aspect ratio composite wing. It is shown that if the stability constraints are not considered in the aeroelastic optimization of the wing, although a smaller structural weight can be achieved, the stability requirements are often not satisfied. Compared with the aeroelastic comprehensive optimization design method with consideration of the structural instability characteristics by the finite element, the optimization with the partition instability analysis of the wing structure by engineering mathematical solutions can control the variables more accurately, further reduce the structural weight and improve the structural instability factor while satisfying various performance requirements, especially,the stability constraints.
作者
刘晓晨
LIU Xiaochen(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)
出处
《力学与实践》
北大核心
2020年第5期571-575,共5页
Mechanics in Engineering
关键词
气动弹性
结构优化
失稳分析
复合材料
aeroelastic
structural optimization
instability analysis
composite
