Dynamic Modeling and Adaptive Fast Nonsingular Terminal Sliding Mode Control for Satellite with Double Rotary Payloads  

作　　者：Xu Chen Lu Yuping Yao Keming Liu Yanbin Xiao Dibo 

机构地区：[1]College of Astronautics,Nanjing University of Aeronautics and Astronautics [2]College of Electric and Information Engineering,Jiangsu University of Technology

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2016年第3期310-318,共9页南京航空航天大学学报（英文版）

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)

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.

关 键 词：satellite with double rotary payloads multi-rigid-body system sliding mode control disturbance observers attitude control 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]