Synthesis of controls for a spacecraft that optimize the pole placement of the closed-loop control system

For a linear time-independent model of spacecraft motion, a method for the optimal pole placement of the spacecraft model transition matrix closed by a feedback is proposed. The method is based on the relationship between the modal and optimization approaches to the synthesis of the feedback ensuring the prescribed quality of the attitude stabilization and stability of the time response of the spacecraft determined by the Kalman-Letov performance index. This relationship is established in the paper. An example of applying the proposed method for controlling the motion of the center of mass and about the center of mass in the stabilization of the program rendezvous trajectory of spacecrafts in the orbital frame of reference is discussed.