Integration planning of gimbal angle and attitude motion for zero propellant maneuver under attitude and control moment gyroscope constraints. (July 2020)

• Record Type: Journal Article
• Authors: Wang, Zhuo; Xu, Rui; Zhu, Shengying; Jiang, Huiping; Li, Zhaoyu; Liang, Zixuan; Luo, Da
• Is Part Of: Acta astronautica. Volume 172(2020)
• Page Start: 123
• Page End: 133
• Publication Date: 2020-07
• Subjects: Zero propellant maneuver -- Singularity and saturation -- Local control -- Attitude maneuver planning; ZPM Zero propellant maneuver -- LCDE Local Control Differential Evolution -- SGCMGs Single gimbal control moment gyroscopes -- CSS China Space Station; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2020.03.040
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: Zero propellant maneuver is an advanced concept of large spacecraft attitude control that has recently been applied to International Space Station. The objective of this paper is the zero propellant maneuver path planning of space station under attitude and control moment gyroscope constraints. First, a multi-constraint model of zero propellant maneuver with single gimbal control moment gyroscopes is established. Then, an integrated planning algorithm of gimbal angle and attitude motion is proposed: Local Control Differential Evolution. The algorithm can simultaneously handle attitude constraints and control moment gyroscope constraints to obtain an attitude path that satisfies the attitude constraints and a gimbal angle path that is far from singularity and saturation. In addition, the algorithm combines the local control algorithm with the global differential evolution algorithm. The local control algorithm based on the potential function idea can better deal with local attitude obstacle constraints, and the global optimization algorithm based on the improved differential evolution algorithm can perform global gimbal angle optimization. Finally, simulation results show that the method is effective in dealing with both attitude and control moment gyroscope constraints. Highlights: ZPM planning reduces fuel consumption and brings huge economic benefits to space station. LCDE method handles both attitude constraints and SGCMGs constraints. LCDE method effectively handles global gimbal angle optimization and local attitude constraints. The local control algorithm based on the potential function idea. The SGCMGs model of CSS performs well in various simulation situations.