基于变弹翼方式的非结构动网格建模方法研究

Research on and Development of a New and Efficient Dynamic Unstructured Grid Method for Missiles with Morphing Wings Based on the Principle of Spring Shape Changing

针对变弹翼导弹包含运动边界的复杂非定常流场的求解问题,基于弹簧变形原理,即在网格变形时,网格点与静止边界和运动边界的相对位置关系均保持不变,分别推导了旋转弹翼运动边界上的网格点和受运动边界扰动流场子域上网格点的变形算法,从而发展了一种新的非结构动网格方法,该方法在不降低计算效率的前提下,大大提高了网格的变形能力,并解决了现有研究通常忽略弹翼运动受弹身影响而产生的非刚性变形问题,是基于非结构网格框架下,求解具有复杂运动边界且网格变形较大的非定常流场的一种简单有效的方法。

To solve the complex unsteady flow of a missile with morphing swept wings,we propose a new dynamic unstructured grid method according to the principle of spring shape changing,under which the grid points＇ relative positions between stationary boundary and moving boundary are fixed.Sections 1 through 3 of the full paper explain our research and development mentioned in the title,whose algorithm we believe is new and efficient and whose core consists of：（1） we establish the swept wing mesh deformation algorithm and the flow field internal mesh deformation algorithm respectively,thus developing our new dynamic unstructured grid method;（2） we use the finite volume method to solve the 3-D Navier-Stokes equations and apply our new dynamic unstructured grid method to the numerical analysis of the flow field of a certain missile with morphing swept wings.The simulation results,given in Figs 5 through 10,and their analysis show preliminarily that：（1） our new method can greatly improve the grid deformation ability and the quality of the grids;（2） our new method takes into consideration the non-rigid deformation caused by the effects of the missile body on the motion of the swept wings;（3） it is an effective and simple method for solving a complex unsteady flow field that contains complex motion boundary and large-scale mesh deformation.