The dynamic stability of the re-entry vehicle is a key factor in the success or failure of its mission. So it is necessary to conduct in-depth research on the dynamic characteristics of the new Starship-like spacecraft at high angles of attack. To evaluate the dynamic derivatives， numerical simulations of forced vibrations are performed using an unsteady N-S equation solver based on the partitioned spring approximation dynamic mesh technique. The finite volume discretization adopts Roe format and SST turbulence model， and the time direction adopts fully implicit GMRES method for iterative solution. Based on the verification of the hyper ballistic shape （HBS） standard model， the variation law of pitch dynamic characteristics of different flight Mach numbers， centers of gravity position， deflection angles of control surface， angles of attack， reduction frequencies under the typical high angle of attack state of Starship-like spacecraft is obtained. In the typical state， the pitch dynamic derivatives are negative at supersonic speed and positive at subsonic speed. With the change of different factors， the pitch dynamic characteristics of Ma=0.3 and Ma=5.0 are significantly different. At high speed， the deflection of the control surface can reduce the damping， and the influence of the rear wing is more significant. The calculation results show the application value of the method in the identification of the dynamic characteristics of the complex-shaped aircraft in wide speed and large airspace.