Conceptual design and control method for a noncontact annular electromagnetic stabilized satellite platform  

作　　者：He LIAO Daixin WANG Yuan REN Weijie WANG 

机构地区：[1]Institute of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China [2]Department of Basic Course,Space Engineering University,Huairou District,Beijing 101416,China

出　　处：《Chinese Journal of Aeronautics》2024年第1期256-270,共15页中国航空学报（英文版）

基　　金：co-supported by the National Natural Science Foundation of China(No.12172168)。

摘　　要：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.

关 键 词：Disturbance-free payload Robust model matching Dual quaternion Sliding mode control Collision avoidance 

分 类 号：V474[航空宇航科学与技术—飞行器设计] V448.2