Aeroelastic characteristics of plane-symmetry vehicle main wing trailing edge rudder at high angle of attack

The plane-symmetry shuttle vehicle experiences a long period of supersonic high angle of attack flight stage during its reentry. It is hard for the aerospace-vehicles structure to sustain long-time supersonic flight at high angle of attack. Therefore, the aeroelastic response characteristics of the trailing edge rudder surface of the typical plane-symmetric shuttle configuration require in-depth analysis. In this paper, the analysis and calculation of the trailing-edge rudder of at the high angle of attack is carried out in high speed. The numerical CFD/CSD coupling method is employed in the analysis. The calculation results show that the symmetrical and antisymmetric deflection modes of the trailing-edge rudder are unstable, and the aerodynamic damping identified by the ARMA method is less than 0, which indicates the aeroelastic instability. Therefore, the dynamic stability of the structure during the reentry period needs to be considered in the design of the plane-symmetric aircraft.