Virtual flight numerical simulation of the basic finner projectile with closed loop

Through the solution by coupling of the unsteady Navier-Stokes equations, the rigid-body six degree-of-freedom (6DOF) motion equations and the rudder deflection control law, a set of platforms is developed and the virtual flight simulation of a basic finner projectile is investigated. The flow solver is a finite-volume solver based on a structure grid with dual time stepping, the chimera method is used to simulate relative motions, the fourth-order Runger-Kutta method is used to solve the motion equations, and the rudder control law using feedback control is based on proportional integral and differential (PID). Simulation results show that the virtual flight simulation platform is capable of solving the complicated unsteady flows with moving boundaries, andproviding data for unsteady aerodynamic modeling, which indicates the stability of the aircraft and test flight control law, and promises a strong prospect for engineering application.