TY - JOUR
T1 - Physical simulation experiment for flexible satellite control with vibration information feedback
AU - Zhou, Jun
AU - Liu, Yingying
PY - 2008/3
Y1 - 2008/3
N2 - The attitude control for large flexible spacecrafts is a key issue in space technology. Satellites with large flexible solar panels are taken as practical background. A physical simulation system for flexible satellite is used as an experiment test-bed. Vibration suppression control with flexible vibration acceleration feedback is promoted. A small accelerometer is placed at the end of the flexible penal, the measurement model of this accelerometer is established and an adaptive filter is designed for its data procession. Feedback control using the vibration information from the acceleration signal is designed. Large angle maneuver experiment is carried out. The centre body maneuvers about 25° smoothly and the precision of the attitude after maneuver is within 0.01°. The acceleration at the end point of the flexible panel during the experiment is within 0.15 m/s2, and the altitude of the first mode is 0.015 m/s2. Compared with classical PD control, physical simulation experiments verify that the control scheme with vibration information feedback can suppress flexible vibration more effectively. Only a small accelerometer is placed on the flexible panel, the control system is simple and the control scheme can be carried out in real time system.
AB - The attitude control for large flexible spacecrafts is a key issue in space technology. Satellites with large flexible solar panels are taken as practical background. A physical simulation system for flexible satellite is used as an experiment test-bed. Vibration suppression control with flexible vibration acceleration feedback is promoted. A small accelerometer is placed at the end of the flexible penal, the measurement model of this accelerometer is established and an adaptive filter is designed for its data procession. Feedback control using the vibration information from the acceleration signal is designed. Large angle maneuver experiment is carried out. The centre body maneuvers about 25° smoothly and the precision of the attitude after maneuver is within 0.01°. The acceleration at the end point of the flexible panel during the experiment is within 0.15 m/s2, and the altitude of the first mode is 0.015 m/s2. Compared with classical PD control, physical simulation experiments verify that the control scheme with vibration information feedback can suppress flexible vibration more effectively. Only a small accelerometer is placed on the flexible panel, the control system is simple and the control scheme can be carried out in real time system.
KW - Flexible satellite
KW - Physical simulation experiment
KW - Vibration feedback control
KW - Vibration suppression
UR - http://www.scopus.com/inward/record.url?scp=43249099155&partnerID=8YFLogxK
M3 - 文章
AN - SCOPUS:43249099155
SN - 1004-6801
VL - 28
SP - 50
EP - 54
JO - Zhendong Ceshi Yu Zhenduan/Journal of Vibration, Measurement and Diagnosis
JF - Zhendong Ceshi Yu Zhenduan/Journal of Vibration, Measurement and Diagnosis
IS - 1
ER -