A Cascade Saturation Attitude Control Method for Spacecraft Stealth Under Input Constraints

In the detection range of the ground radar station, under the conditions of saturation input and rate constraints, a cascade saturation PID control law is designed based on the error quaternion. By limiting the error quaternion of the spacecraft, the attitude error between the satellite-ground vector and the stealth axis is gradually eliminated, so as to realize the attitude tracking of the desired attitude and achieve the purpose of stealth. The mathematical simulation results demonstrate that the control algorithm designed in this paper can enable the spacecraft to achieve large-angle attitude maneuver within the detection range of the ground station under the constraints of input saturation and rate limitation. This verifies the stealth effectiveness of the spacecraft and the robustness of the control algorithm.