Attitude Tracking Control Based on Adaptive Sliding Mode Technique with Double Closed Loop for Spacecraft Near Small Body

2014 ◽  
Author(s):  
Chunhui Liang ◽  
Yuanchun Li
Keyword(s):  
Tracking Control ◽  
Closed Loop ◽  
Sliding Mode ◽  
Small Body ◽  
Adaptive Sliding Mode ◽  
Attitude Tracking ◽  
Attitude Tracking Control ◽  
Mode Technique ◽  
Sliding Mode Technique

Spacecraft Adaptive Sliding Mode Attitude Tracking Control Using DGCMG

2011 ◽  
Vol 110-116 ◽  
pp. 5283-5291
Author(s):  
Lei Wang ◽  
Yu Shan Zhao ◽  
Peng Shi
Keyword(s):  
Tracking Control ◽  
Sliding Mode ◽  
Major Elements ◽  
Wheel Speed ◽  
External Torque ◽  
Adaptive Sliding Mode ◽  
Adaptive Sliding Mode Controller ◽  
Attitude Tracking ◽  
Steering Law ◽  
Attitude Tracking Control

This investigation is concerned with the non-linear multi-in-multi-out tracking control of a spacecraft with Double-gimbaled control moment gyros as actuators. An attitude dynamic model of rigid spacecraft with DGCMG and a kinematics model in terms of Modified Rodriguez parameters are given for the controller development. Then the control objective and system uncertainties in tracking problem are analyzed considering the major elements which work on the control performance such as moment of inertia change, wheel speed drift and external torque. A adaptive sliding mode controller is designed and is proved stable later in which the sliding mode control are used to compensate external torque and un-modeled dynamics while the adaptive parameters are used to estimate inertia and wheel speed on line. And a steering law of parallel mounted DGCMG is illuminated. Finally Monte Carlo simulation is carried out to prove the effectiveness of the controller.

Adaptive attitude-tracking control of spacecraft considering on-orbit refuelling

2020 ◽  
pp. 014233122097313
Author(s):  
Yiqi Xu
Keyword(s):  
Tracking Control ◽  
Closed Loop ◽  
Closed Loop System ◽  
Tracking Errors ◽  
Attitude Tracking ◽  
Control Scheme ◽  
Inertia Model ◽  
And Performance ◽  
Attitude Tracking Control ◽  
The Stability

This paper studies the attitude-tracking control problem of spacecraft considering on-orbit refuelling. A time-varying inertia model is developed for spacecraft on-orbit refuelling, which actually includes two processes: fuel in the transfer pipe and fuel in the tank. Based upon the inertia model, an adaptive attitude-tracking controller is derived to guarantee the stability of the resulted closed-loop system, as well as asymptotic convergence of the attitude-tracking errors, despite performing refuelling operations. Finally, numerical simulations illustrate the effectiveness and performance of the proposed control scheme.

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