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

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.