摘要
A robust attitude control methodology is proposed for satellite system with double rotary payloads. The dynamic model is built by the Newton-Euler method and then the dynamic interconneetion between satellite＇s main body and payloads is described precisely. A nonlinear disturbance observer is designed for satellite＇s main body to estimate disturbance torque acted by motion of payloads. Meanwhile, the adaptive fast nonsingular terminal sliding-mode attitude stabilization controller is proposed for satellite＇s main body to quicken convergence speed of state variables. Similarly, the adaptive fast nonsingular terminal sliding-mode attitude maneuver controller is designed for each payload to weaken the disturbance effect of motion of satellite＇s main body. Simulation results verify the effectiveness of the proposed method.
A robust attitude control methodology is proposed for satellite system with double rotary payloads.The dynamic model is built by the Newton-Euler method and then the dynamic interconnection between satellite′s main body and payloads is described precisely.A nonlinear disturbance observer is designed for satellite′s main body to estimate disturbance torque acted by motion of payloads.Meanwhile,the adaptive fast nonsingular terminal sliding-mode attitude stabilization controller is proposed for satellite′s main body to quicken convergence speed of state variables.Similarly,the adaptive fast nonsingular terminal sliding-mode attitude maneuver controller is designed for each payload to weaken the disturbance effect of motion of satellite′s main body.Simulation results verify the effectiveness of the proposed method.
基金
supported by the National Natural Science Foundation of China(No.91016017)
the Funding of Jiangsu Innovation Program for Graduate Education (No. CXZZ12_0160)
the Natural Science Foundation of Jiangsu Province of China(No.BK20130234)
the Changzhou Sci.& Tech.Program (CE20145056)
