一种计及静气动弹性变形影响的跨声速机翼气动优化设计方法研究  

An aerodynamic shape optimization of transonic wing design method for aeroelastic system

作　　者：熊俊涛[1] 乔志德[1] 杨旭东[1] 朱标[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《空气动力学学报》2009年第2期154-159,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(10402036)

摘　　要：耦合流场控制方程和结构静平衡方程求解得到大展弦比跨声速弹性机翼气动性能,分析研究了结构静弹性变形对气动载荷的影响。在此基础上以机翼典型剖面外形和机翼型架外形为设计变量进行了基于控制理论的跨声速弹性机翼气动优化设计方法研究,实现了在真实飞行条件下考虑静气动弹性变形影响的大展弦比跨声速弹性机翼一体化优化设计。优化设计算例结果表明所发展的方法是成功的,优化得到的弹性机翼在满足升力系数约束条件下提高了升阻比。A new approach using control theory for the aerodynamic optimization design of elastic wing where aeroelastic interactions are significant is implemented and tested. Aero-Structural analysis has been carried out by coupling flow control equations solver and finite-element structural solver in which high-fidelity models are used. In design process, we take into account of static aeroelastic effect, and choose the section and jig shape parameters as design variables. The gradient of cost function with respect to design variables are determined through solving adjoint equations. The design results indicate that the present method can be successfully applied to optimization design of transonic elastic wing. After design, the lift to drag ratio can be improved with the lift constraint.

关 键 词：弹性机翼 控制理论 优化设计 升阻比 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]