Flutter analysis of body-wing-rudder configurations at hypersonic velocities and variable attack-angles

The local piston theory of two-dimensional lifting surface is developed and a new method of flutter analysis is proposed for the configurations of body-wing-rudder at hypersonic velocity. In this method the aerodynamic force is calculated by the combined method of CFD (Computational Fluid Dynamics) simulation and engineering algorithm. The structural motion equation is solved by the state space method in time domain. The computational result of a missile in body-wing-ruder configuration shows that the critical dynamic pressure firstly increases then decreases as the Mach number and the attack-angle increase. The phenomenon of the increasing critical dynamic pressure at a small attack-angle is different from the monotonously decreasing in the traditional literatures, which indicates that the aeroelasticity stability of a configuration at high velocity is affected by multiple factors and the flutter characteristic becomes more complicated. The computational result also demonstrates that the above method is effective and efficient for aerocrafts in complicated shape at hypersonic velocity.