High-Precision Composite Control of Driving Current for Non-Contact Annular Electromagnetic Stabilized Spacecraft Subject to Multiple Disturbances

• Published in: Aerospace Vol. 11; no. 8; p. 627
• Main Authors: Liao, He, Yuan, Haoxiang, Xie, Jinjin
• Format: Journal Article
• Language: English
• Published: Basel MDPI AG 01.08.2024
• Subjects: Accuracy; Actuators; Back electromotive force; Control algorithms; Control systems; Controllers; Design; Design and construction; Disturbances; driving current control; Dynamic response; Electromagnetism; Electromotive forces; feedforward compensation; Feedforward control; Fuzzy control; fuzzy rule; Gravitational waves; Methods; non-contact annular electromagnetic stabilized spacecraft; Numerical simulations; Parameter robustness; Payloads; Pulse duration modulation; Robust control; robust Smith predictor; Space ships; Space telescopes; Space vehicles; Spacecraft; Switching; variable switching frequency; China
• ISSN: 2226-4310; 2226-4310
• DOI: 10.3390/aerospace11080627

Based on the design concept of dynamic and static isolation, disturbance-free payload (DFP) satellites can isolate the effects of interference on sensitive payloads, and can realize the high-precision control of the payload better than a traditional spacecraft. Among these, non-contact annular electromagnetic stabilized spacecraft (NCAESS) can effectively alleviate control output problems such as the six-degree-of-freedom coupling and nonlinear effects found in traditional non-contact spacecraft. As a key actuator, the driving current control of the non-contact annular electromagnetic actuator (NCAEA) will have a direct impact on the attitude performance of NCAESS. However, there are multiple interference effects present in the actual driving current control. Therefore, this paper proposes a composite control scheme to improve the driving accuracy by suppressing these multiple disturbances. Firstly, the variable-switching-frequency pulse-width modulation is used to adjust the switching frequency adaptively to reduce switch ripple. Secondly, feedforward compensation is employed to mitigate the back electromotive force. Thirdly, the robust Smith predictor is utilized to compensate for the digital control delay. Finally, an internal model proportional–integral controller with fuzzy rule is applied to adjust the parameters adaptively. The numerical simulation results demonstrate that the proposed approach can be adopted to enhance the robustness and dynamic response of the driving current effectively, which leads to precise control of the non-contact annular electromagnetic stabilized spacecraft.