Abstract: For the control design problems of spacecraft flight in the atmosphere, the aerodynamic angles are directly related to aerodynamic forces and aerodynamic moments, so the aerodynamic angle feedback is generally adopted. When studying the closed loop performance such as stability, it is necessary to use the aerodynamic angular kinematics formula. However, it is difficult to find the derivation method of aerodynamic angular kinematics, so there is a lack of flexibility in the definition of different coordinate systems in application. The kinematic forms of aerodynamic angles are complex, and their derivation is difficult. In this paper, the derivation method is put forward, the kinematic equations of aerodynamic angles are given, and their open loop performance is analyzed, providing the basis for control design. The derivation method and the equations of aerodynamic angular kinematics, and the methods and results of open loop performance analysis proposed in this paper can be applied to the control design and analysis of aerodynamic entry of target stars with atmosphere, thus providing theoretical support for them.

Key words: aerodynamic angle, kinematics, open loop performance, aerodynamic entry, stars with atmosphere