基于结构网格有限体积法和动网格技术,发展了一种通过双时间步LU-SGS方法耦合求解流动控制方程和强迫运动形式刚体动力学方程计算飞行器动态特性的CFD方法。通过探究积分法、T-F方法和最小二乘法等典型动导数辨识方法在实际应用的某些场合辨识结果不稳定、不同方法的辨识结果散布度大或过度依赖人工处理等问题的成因,提出了改进的措施。通过Finner导弹和HBS弹道外形等典型算例确认计算,表明文中方法是有效的。
On the basis of structured mesh finite volume method and dynamic mesh technique, a CFD method for calculating the dynamic performance of aircraft was developed by using flow control equation and rigid body dynamic equation of enforced oscillation form solved by dual-time stepping LU-SGS approach. Through exploring the origins of unstable identification result, large dispersion of the identification result of different methods, over reliance on manual processing and other problems existed in some occasions of practical application using integration method, T-F method, least square method and other typical dynamic derivative identification method, the improvement measures were put forward. The effectiveness of the method was proved by the confirmation of the Finner missile and HBS trajectory contour and other typical examples.
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