In response to the urgent demand for high-precision and high-stability pointing control technology of satellite platforms for complex space missions such as space laser communication, research has been conducted on the configuration design and control method of a spherical magnetically suspended universally stabilized platform (MSUSP). Firstly, the omnidirectional stable suspension characteristics of the MSUSP were analyzed, and a space structure with a right-angled equilateral triangular pyramid configuration was designed. Coordinate transformation was used to decouple the magnetic bearing rotor translation, and a three-degree-of-freedom dynamic model of the spherical magnetic bearing was created. Based on this, in order to achieve stable control of the magnetic bearing rotor under external disturbance conditions, a three-channel self-disturbance rejection controller based on coordinate transformation was designed, which treated the unmodeled dynamics and external disturbances between each channel as merged disturbances for tracking and compensation, thereby improving the speed and stability of the controller under disturbance conditions. The effectiveness and superiority of the suggested method were demonstrated by the analysis of simulation results, which revealed that this method significantly improved the anti-interference performance of the magnetic bearing rotor under various frequency sinusoidal disturbances and reduced the step response time for translational motion by 42.86% when compared to traditional methods.

Disturbance-Free Payload (DFP) spacecraft can meet the requirements of ultra-high attitude pointing accuracy and stability for future space missions. However, as the main control actuators of DFP spacecraft, Linear Non-Contact Lorentz Actuators (LNCLAs) have control output problems with six-degree-of-freedom coupling and nonlinear effects, which will affect the attitude control performance of DFP spacecraft. To solve this problem, a novel concept for Non-Contact Annular Electromagnetic Stabilized Satellite Platform (NCAESSP) is proposed in this study. The concept is centered on replacing the LNCLAs with a non-contact annular electromagnetic actuator to solve the two problems mentioned above. Furthermore, for the different control requirements of the payload module and the support module of the NCAESSP, a high-precision attitude controller based on the robust model matching method and a dual quaternion-based adaptive sliding mode controller are proposed. Additionally, the simulation results verify the feasibility and effectiveness of the proposed approach.