Design and Simulation of a Picosatellite Attitude Control Subsystem

• Main Authors: Yu-Ming Suen, 孫煜明
• Other Authors: Jyh-Ching Juang
• Format: Others
• Language: zh-TW
• Published: 2003
• Online Access: http://ndltd.ncl.edu.tw/handle/60817138147574330244

碩士 === 國立成功大學 === 電機工程學系碩博士班 === 91 === PACE satellite is the first indigenous Picosat that attempts to achieve 3-axis stabilization. In this thesis, the design and simulation of the attitude control subsystem of the PACE satellite are presented. The requirement is to achieve 5 degree earth pointing accuracy at 600 km altitude, 98 degree inclination orbit. A momentum-biased control system is employed to control the pitch angle and stabilize the roll/yaw dynamics. In addition, three orthogonal magnetic coils are used to damp the angular rate after separation, eliminate nutation and precession phenomena, and prevent the momentum wheel from saturation. Through analysis and simulation, it is shown that a 5° attitude control requirement can be achieved.