复杂构型高精度静气动弹性分析方法及其应用研究  

A High-Fidelity Static Aeroelastic Analysis Method for Complex Configuration and Its Application

作　　者：刘艳[1] 白俊强[1] 华俊 刘南[1] 

机构地区：[1]1西北工业大学航空学院,陕西西安710072 [2]中国航空研究院,北京100012

出　　处：《西北工业大学学报》2015年第1期14-20,共7页Journal of Northwestern Polytechnical University

摘　　要：为了准确地预测增升装置的气动弹性变形,基于Navier-Stokes方程求解器和结构静力学方程,建立了一种静气动弹性分析方法。发展了一种全局/局部混合的数据交换方式,解决了复杂构型数据交换过程中相邻部件间数据干扰的问题。同时,建立了变形能力强、引入并行算法的基于RBF插值技术的动网格方法,很好地保证了复杂构型网格的变形能力。此外,为了提高静气弹分析效率,所建立方法根据收敛特点引入了加速收敛技术。通过F6翼身组合体和某大型客机着陆构型,验证文中发展的静气动弹性分析方法的可行性和鲁棒性。分析结果表明,弹性变形最终导致大型客机着陆构型8°迎角状态时的升力系数减小约1.0%。For a large transport aircraft with high aspect ratio wing, aeroelasticity is one of the most important fac- tors that affects the aerodynamic efficiency of a high-lift configuration. To analyze its static aeroelasticity accurately, we propose the high-fidelity static aeroelastic analysis method based on the solution of Navier-Stokes equations and structural equations. We develop a global-local mixed algorithm for exchanging data between computational fluid dy- namics results and computational structural dynamics results, which eliminates the data interference among adjacent parts of the complex configuration. We also work out the dynamic mesh method that uses the radial basis function interpolation technique that has good elastic deformation the mesh deformation capability of the complex configurati and introduces the parallel algorithm, thus guaranteeing on. In order to enhance the static aeroelastic analysis effi- ciency, we introduce the convergence acceleration technique based on the convergence characteristics. Finally, we use the DLR-F6 wing body configuration and the high-lift configuration of a large transport aircraft to verify the fea- sibility and robustness of the static aeroelastic analysis method. The verification results show that the elastic deform- ation decreases the lift coefficient of the high-lift configuration results by around 1.0% under the influence of aero- elasticity.

关 键 词：Navier—Stokes方程 静气动弹性力学 RBF插值技术 动网格 大型客机 

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] V214.32