基于高精度模态气动力的跨声速静弹高效分析方法

跨声速静弹分析一直是工程设计中的难点问题,以模态坐标系下的线性静弹方程为基础,提出了基于高精度模态气动力的跨声速静弹高效分析方法,该方法仍需求解线性静弹方程,但对于其中关键的模态变形引起的弹性气动力增量,采用由结构变形到气动力的单向计算流体动力学(Computational Fluid Dynamics,CFD)/计算结构动力学(Computational Structural Dynamics,CSD)耦合方法获得,实现了高效线性方法与高精度CFD/CSD耦合方法的有效融合。以某小展弦比机翼基本状态、舵偏状态以及某型战斗机跨声速副翼效率的静弹分析为例,对比分析了本文方法、经典线性方法、CFD/CSD耦合方法的计算结果以及某型机的试飞辨识结果。分析结果表明,所提出的方法在计算效率、精度和鲁棒性方面具备综合优势,具有较高的工程应用价值。

Efficient transonic static aeroelastic analysis method based on high accuracy modal aerodynamics

Transonic static aeroelastic analysis has always been a difficult problem in engineering design .In this paper , based on the linear static aeroelastic equation in the modal coordinate system ,a new efficient transonic static aeroelastic analysis method based on high precision modal aerodynamics is developed .The method still solves the linear equation ,but for the key aerodynamic increments caused by the modal deformation ,which can be obtained by the one-way CFD(Computa-tional Fluid Dynamics)/CSD(Computational Structural Dynamics) interaction .With the method ,effective fusion of high effi-ciency linear method and high accuracy CFD/CSD interaction method is realized .To validate the effects of the method ,stat-ic aeroelastic problems of a small aspect ratio wing with/without control surface and the aileron efficiency of a fighter aircraft are analyzed ,and the results of the classical linear method ,CFD/CSD interaction method and test flight identification are compared ,which show that the method developed has a comprehensive advantage in terms of efficiency , accuracy and robustness ,and has high engineering application value .