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Combined Attitude Control of Small Satellite by Using Reaction Wheels and Magnetorquers

Author: DuanChenYang
Tutor: TangGuoJian
School: National University of Defense Science and Technology
Course: Aeronautical and Astronautical Science and Engineering
Keywords: Small satellites Attitude control Reaction Flywheel Magnetorquer Joint control
CLC: V448.2
Type: Master's thesis
Year: 2007
Downloads: 379
Quote: 1
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Abstract


This thesis is three-axis stabilized high-performance small satellite attitude control system for the study of small satellite attitude control system based on the counterproductive flywheel Magnetorquer joint control study. Focused on solving three-axis stabilized satellite of reaction flywheel and Magnetorquer joint control, as well as the flywheel failure mode of small satellite attitude control programs and algorithms, and achieved the following innovations: First, there are three-axis orthogonal reaction flywheel installed and triaxial magnetic moment of small satellite, the joint program of the magnetron and wheel control, in order to take full advantage of the star on the performance of hardware resources, to improve the functional density of small satellites. Design a joint control by the control algorithm and control distribution, in order to reduce the difficulty of control system design; derived large angle maneuver Hierarchical saturation control algorithm, and a the maximum magnetron torque and energy optimal two control allocation strategy, numerical simulation results show the effectiveness of the algorithm and control of joint control scheme presented in this chapter. Secondly, for the the uniaxial reaction flywheel failure situation, it is designed to use the remaining two-axis reaction flywheel and three-axis magnetic torquer joint control Troubleshooting program derivation the joint posture failure mode control algorithm, and proposed the direct control of distribution and optimal control performance of two control allocation strategy, numerical simulation results show the effectiveness of this chapter, the feasibility of the proposed method and algorithm. Finally, for the two-axis reaction flywheel failure, first verify the control performance of the program using the of reaction flywheel and three-axis magnetic torquer control of joint control, stability control results show that the program can not achieve the high precision of small satellite mission. Special circumstances of reaction flywheel work properly for the remaining pitch axis, the proposed use of the shaft from the reaction flywheel spin a momentum wheel, and then in combination with three-axis magnetic torquer Troubleshooting control system to improve the control precision, and were designed the use of the magnetic moment of the flywheel from the spin control strategy and controller parameter design method based on genetic algorithms. Simulation results show that the program can achieve high control precision, to further extend the life of the small satellite mission. In this thesis reaction flywheel Magnetorquer, joint control technology, as well as the flywheel failure mode of small satellite attitude control programs and algorithms useful discussions, to provide some effective for the Design and Development of China's small satellite techniques.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Space instrument,spacecraft devices,spacecraft guidance and control > Guidance and Control > Spacecraft guidance and control
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