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The Attitude Control System Design and Simulation of Three-axis Sabilization Micro-satellite

Author: WuHaiLiang
Tutor: WangHuiNan
School: Nanjing University of Aeronautics and Astronautics
Course: Precision instruments and machinery
Keywords: Micro-satellite Attitude determination Attitude control Particle filter EKF algorithm VxWorkx
CLC: V448.2
Type: Master's thesis
Year: 2008
Downloads: 407
Quote: 3
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Abstract


Micro-satellite, a kind of modern small satellite, has advantages of light weight, small size, low cost and so on. It plays a more and more important role in various space missions. The attitude control system is the precondition of fulfilling all kinds of tasks, is the key technology and emphasis of interrelated research.Attitude determination and control system of a satellite contains two parts, one is the attitude determination system and the other is the attitude control system. The determination of attitude is the process of getting attitude parameter of satellite by certain sense organ while the control of attitude is the research about attitude orientation to a target attitude.Based on the research of the attitude determination and control system, the author uses particle filter to deal with the attitude parameters and simulates the main control models with the detailed theory analyse.besides, this paper still studies the software design of the attitude determination system.This article established a model with magnetometers as well as sun sensors and used Particle Filter to complete the attitude estimate. The final result compared the filter capability in two different mumble of particles. Besides this, the article also compares Particle Filter to EKF algorithm, the estimate result validates that Particle Filter can fulfill the control desire of low precision Micro-satellite.After this, this paper simulate the main modes contained in attitude control process and analyses the simulation result of the unloading of momentum wheel by magnetic torque, however ,the simulation result of nutation and precession damping is also given. Meanwhile, this paper analyses the attitude maneuver of micro-satellite with a little angle and also gives the simulation result.Finally, the paper studies the software design of the attitude determination system and supplies two different actualize methods based on whether there exits a telecontrol come from ground.This article researches the attitude determination and control methods of micro-satellite and analyses the software design of the attitude control system. It can be used as reference in other micro-satellite.

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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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