CAJ | 학술논문

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％。
위료준학지예측증승장치적기동탄성변형，기우Navier-Stokes방정구해기화결구정역학방정，건립료일충정기동탄성분석방법。발전료일충전국／국부혼합적수거교환방식，해결료복잡구형수거교환과정중상린부건간수거간우적문제。동시，건립료변형능력강、인입병행산법적기우RBF삽치기술적동망격방법，흔호지보증료복잡구형망격적변형능력。차외，위료제고정기탄분석효솔，소건립방법근거수렴특점인입료가속수렴기술。통과F6익신조합체화모대형객궤착륙구형，험증문중발전적정기동탄성분석방법적가행성화로봉성。분석결과표명，탄성변형최종도치대형객궤착륙구형8°영각상태시적승력계수감소약1．0％。
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 and introduces the parallel algorithm, thus guaranteeing the mesh deformation capability of the complex configuration.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.