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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。
Transonic acoustic munition analysis has been a difficult problem in engineering design. Based on the linear static elastic equation in modal coordinate system, an efficient method of transonic acoustic munition based on high-precision modal aerodynamic force is proposed. This method still needs However, for the elastic aerodynamic increment caused by the key modal deformation, Computational Fluid Dynamics (CFD) / Computational Dynamics (Computational Fluid Dynamics) Structural Dynamics (CSD) coupling method to achieve efficient fusion of high-efficiency linear method and high-precision CFD / CSD coupling method. Taking a small aspect ratio wing basic state, the partial state of rudder and the transonic aileron efficiency of a certain type of fighter as an example, the results of this method, the classical linear method and the CFD / CSD coupling method are compared and analyzed. Aircraft flight test results. The analysis results show that the proposed method has comprehensive advantages in computational efficiency, accuracy and robustness, and has high engineering application value.