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针对导弹虚拟飞行数值模拟问题,发展了空气动力学/飞行力学数值计算方法和软件。控制方程为非定常雷诺时均Navier-Stoker(RANS)方程和刚体六自由度运动方程;流场求解器为有限体积法结构网格求解器,时间推进采用双时间步法,湍流模型为Spalart-Allmaras一方程模型;采用Adams预估校正法实现飞行力学方程与流场控制方程的耦合计算;使用嵌套网格方法模拟多体运动。首先模拟了美国国家航空航天局(NASA)窄条翼导弹模型纵向虚拟飞行,研究耦合方式和时间步长的影响。仿真结果表明,双时间步三阶Adams耦合方法,同等精度下可以显著增大时间步长,缩短仿真时间。最后,采用该方法模拟了导弹自由摇滚特性和纵向虚拟飞行,模拟结果与试验值吻合较好。
Aimed at the numerical simulation of missile virtual flight, numerical and aerodynamic / aeromechanical calculation methods and software are developed. The governing equations are the unsteady Reynolds-averaged Navier-Stoker (RANS) equation and rigid body six-degree-of-freedom equations of motion. The flow solver is a finite-volume structured grid solver with two time steps for time propulsion. The turbulence model is Spalart- Allmaras an equation model; using Adams predictive correction method to achieve the flight mechanics equations and flow field governing equations coupling calculation; using nested grid method to simulate multi-body motion. First, a longitudinal virtual flight of a narrow-wing missile model of NASA was simulated to study the influence of the coupling method and the time step. The simulation results show that the double time step third-order Adams coupling method can significantly increase the time step and reduce the simulation time under the same precision. Finally, this method is used to simulate the missile’s free-rock characteristics and longitudinal virtual flight. The simulation results are in good agreement with the experimental values.