Performance Evaluation of Two Nonlinear Controllers on an Attitude System Using SGCMG

2015 ◽  
Author(s):  
Juan Sebastian Nuñez Gamboa ◽  
Juan David López
Keyword(s):  
Control System ◽  
Power Systems ◽  
Dynamic Model ◽  
Attitude Control ◽  
Sliding Mode ◽  
Attitude Control System ◽  
Unknown Parameters ◽  
Control Moment ◽  
Nonlinear Controllers ◽  
New States

This paper deals with the modeling and simulation of an attitude control system composed of three Single Gimbal Control Moment Gyroscopes (SGCMG) in a pyramidal configuration using two nonlinear controllers. The first controller is a first-order sliding mode which is robust to bounded uncertainties such as modeling simplifications, sensor noise and external disturbances, but it causes high frequency input, which can exceed the limit of the power systems. To overcome the drawback of the sliding mode, an I&I adaptive control is proposed. This controller estimates unknown parameters by introducing new states, resulting in smaller input gains and frequencies. At first, the dynamic model of SGCMG and the dynamic model of the attitude system were constructed. Based on this model, the steering laws of the SGCMG’s for the two nonlinear controllers were designed. The simulation of the attitude control system is implemented in MATLAB. The simulation results show the effectiveness and the advantages of the proposed controllers.

scholarly journals Fault Reconstruction Approach for Distributed Coordinated Spacecraft Attitude Control System

2015 ◽  
Vol 2015 ◽  
pp. 1-9
Author(s):  
Mingyi Huo ◽  
Yanning Guo ◽  
Xing Huo
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Large Scale ◽  
Sliding Mode ◽  
Reconstruction Error ◽  
Spacecraft Attitude ◽  
Alignment Error ◽  
Spacecraft Attitude Control ◽  
Attitude Control System ◽  
Fault Reconstruction

This work presents a novel fault reconstruction approach for a large-scale system, that is, a distributed coordinated spacecraft attitude control system. The attitude of all the spacecrafts in this distributed system is controlled by using thrusters. All possible faults of thruster including thrust magnitude error and alignment error are investigated. As a stepping stone, the mathematical model of thruster is firstly established based on the thruster configuration. On the basis of this, a sliding mode observer is then proposed to reconstruct faults in each agent of the coordinated control system. A Lyapunov-based analysis shows that the observer asymptotically converges to the actual faults. The key feature of this fault reconstruction approach is that it can achieve a faster reconstruction of the fault in comparison with the conventional fault reconstruction schemes. It can globally reconstruct thruster faults with zero reconstruction error, and this is accomplished within finite time. The effectiveness of the proposed approach is analytically authenticated via simulation study.

A Global Fast Integral Operator Terminal Adaptive Sliding-Mode Controller

2012 ◽  
Vol 190-191 ◽  
pp. 880-885
Author(s):  
Lu Cao ◽  
Xiao Qian Chen ◽  
Yong Zhao
Keyword(s):  
Control System ◽  
Integral Operator ◽  
Attitude Control ◽  
High Performance ◽  
Sliding Mode ◽  
High Reliability ◽  
Sliding Mode Controller ◽  
Limited Time ◽  
Attitude Control System ◽  
Adaptive Sliding Mode Controller

Attitude Control System(ACS); Terminal; Adaptive; Integral operator Abstract: Attitude Control System (ACS) with high performance, high precision, and high reliability is the kernel technology of the research of spacecraft, which directly affects the whole performance of spacecraft. Hence, a global fast integral operator Terminal adaptive sliding-mode controller is proposed to come true the high performance control. The theory of this controller is to introduce the limited time mechanics—Terminal mode to the sliding-mode control and introduce the integral operator to the sliding-mode plane, which can realize the convergence of spacecraft attitude in “limited time” in the condition of serious disturbance , in order to enhance the performance of fast response. At last, the simulation results demonstrate the high reliability and advantages of the control approach.

Development experience of the attitude control system using single-axis control moment gyros for long-term orbiting space stations

1988 ◽  
Vol 18 ◽  
pp. 91-98 ◽  
Author(s):  
V.N. Branets ◽  
D.M. Weinberg ◽  
V.P. Verestchagin ◽  
N.N. Danilov-Nitusov ◽  
V.P. Legostayev ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Control Moment ◽  
Development Experience
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