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跨声速副翼效率一直是静弹分析领域的热点和难点问题之一。目前,基于计算流体力学(CFD)/计算结构动力学(CSD)耦合的高精度静弹分析方法用于此类问题时还存在网格变形鲁棒性以及分析结果缺乏有效验证等问题。针对上述问题,提出了基于虚拟网格及虚拟位移的网格变形方法,对于迭代中出现的非物理振荡、非一致收敛问题,采用了松弛迭代以及部件载荷综合残差收敛方法。基于上述方法,分析了某型战斗机的跨声速(Ma=0.95)副翼效率,给出了静弹变形对翼面激波位置、激波强度、压力分布的影响以及副翼效率的弹性修正系数。为验证分析结果,开展了静弹试飞辨识,两者吻合良好,表明本文所提方法可以满足复杂构型跨声速副翼效率高精度静弹分析的需求,对于提高静弹工程设计能力具有重要意义。
Transonic ailerons efficiency has been one of the hot and difficult issues in the field of projectile analysis. At present, the problems of mesh deformation robustness and the lack of effective verification of the results of the analysis are based on computational fluid dynamics (CFD) / computational structural dynamics (CSD) coupling of high-precision projectile analysis methods. In order to solve the above problems, a mesh deformation method based on virtual grid and virtual displacements is proposed. For non-physical oscillation and non-uniform convergence problems in iteration, relaxation iteration and component residuals convergence method are used. Based on the above method, the transonic speed (Ma = 0.95) aileron efficiency of a fighter is analyzed. The influence of the detonation on the shock position, shock intensity and pressure distribution of the airfoil and the elastic correction coefficient of aileron efficiency . In order to validate the analysis results, the static projectile flight test was carried out, and the two agree well with each other, which shows that the proposed method can meet the needs of transonic aileron efficiency high precision projectile analysis with complex configurations and is of great significance for improving the design capability of projectile engineering .