Open AccessAn implementation of optimal control methods (LQI, LQG, LTR) for geostationary satellite attitude control
Author(s) -
Farid Djaballah,
M. A. Si Mohammed,
Nabil Boughanmi
Publication year - 2019
Publication title -
international journal of electrical and computer engineering
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.277
H-Index - 22
ISSN - 2088-8708
DOI - 10.11591/ijece.v9i6.pp4728-4737
Subject(s) - linear quadratic gaussian control , control theory (sociology) , geostationary orbit , attitude control , controller (irrigation) , satellite , overshoot (microwave communication) , optimal projection equations , computer science , linearization , mathematics , optimal control , engineering , control engineering , control (management) , physics , mathematical optimization , aerospace engineering , nonlinear system , telecommunications , agronomy , artificial intelligence , quantum mechanics , biology
This paper investigates a new strategy for geostationary satellite attitude control using Linear Quadratic Gaussian (LQG), Loop Transfer Recovery (LTR), and Linear Quadratic Integral (LQI) control techniques. The sub-system satellite attitude determination and control of a geostationary satellite in the presence of external disturbances, the dynamic model of sub-satellite motion is firstly established by Euler equations. During the flight mission at 35000 Km attitude, the stability characteristics of attitude motion are analyzed with a large margin error of pointing, then a height performance-order LQI, LQG and LTR attitude controller are proposed to achieve stable control of the sub-satellite attitude, which dynamic model is linearized by using feedback linearization method. Finally, validity of the LTR order controller and the advantages over an integer order controller are examined by numerical simulation. Comparing with the corresponding integer order controller (LQI, LQG), numerical simulation results indicate that the proposed sub-satellite attitude controller based on LTR order can not only stabilize the sub-satellite attitude, but also respond faster with smaller overshoot.