HARDWARE-IN-THE-LOOP GROUND SIMULATION OF SPACECRAFT ATTITUDE CONTROL SUBSYSTEM

• Main Authors: YONG-LIN KUO, 郭永麟
• Other Authors: YIING-YUH LIN
• Format: Others
• Language: zh-TW
• Published: 1994
• Online Access: http://ndltd.ncl.edu.tw/handle/49571269478703166505

碩士 === 國立成功大學 === 航空太空工程學系 === 82 === This research prsents some analysis and comparison of the attitude stabilization control methods for a low-earth orbit satellite by using personal computer controlled simple equipment and hardware setup. In this paper, we presented the following studies: (1) Under the high accuracy pointing requirement, we selected the two attitude control methods, the momentum bias and the three-axis stabilization to discuss the satellite attitude motion in normal mode. (2) Besides performing the attitude stabilization, we used the magnetic coils to dump the excess angular momentum from the momentum wheels or the reaction wheels on the satellite simultaneously. (3) We considered the some main environmental torques for a low- earth orbit satellite, which included the gravity-gradient torque, the magnetic disturbance torque, and the aerodynamic torque. (4) On the attitude determination, we designed the estimator and tested its performance to computer the satellite attitude as the attitude feedback control signal. (5) We established a hardware-in-the-loop environment to simulate the satellite attitude motion and tested the feasibility of the attitude control design. At last, we made two examples. One is to simulate the attitude stabilization by the personal computer. The other is to simulate a large-angle attitude maneuver by the hardware-in-the-loop equipment.