TY - GEN
T1 - Vibration isolation platform of CMGS application on satellites with the flexible appendages
AU - Zhang, Yao
AU - Zhang, Jingrui
PY - 2012
Y1 - 2012
N2 - In this paper, a vibration isolation platform is installed between the control moment gyroscopes (CMGs) and the satellite bus and its application on satellites is discussed The first step constructs the dynamic model of the integrated satellite with vibration isolation platform, CMGs and some number of flexible appendages by Nevvton- Euler method and Kane equations, while the analytical control moment gyroscopes disturbance model is derived. The transmissibility matrix of the vibration isolation platform is then obtained, and the influences of the flexible solar arrays on the performance of the vibration isolation platform and these on stability of the closed-loop control system are analyzed. Based on the above analysis, the constraint conditions of the modal frequencies and the damping coefficient of the flexible appendages are able to be obtained. The third part chooses the reasonable parameters of vibration isolation platform and these of flexible solar arrays, and predicts the attitude stabilization performance with vibration isolation system.
AB - In this paper, a vibration isolation platform is installed between the control moment gyroscopes (CMGs) and the satellite bus and its application on satellites is discussed The first step constructs the dynamic model of the integrated satellite with vibration isolation platform, CMGs and some number of flexible appendages by Nevvton- Euler method and Kane equations, while the analytical control moment gyroscopes disturbance model is derived. The transmissibility matrix of the vibration isolation platform is then obtained, and the influences of the flexible solar arrays on the performance of the vibration isolation platform and these on stability of the closed-loop control system are analyzed. Based on the above analysis, the constraint conditions of the modal frequencies and the damping coefficient of the flexible appendages are able to be obtained. The third part chooses the reasonable parameters of vibration isolation platform and these of flexible solar arrays, and predicts the attitude stabilization performance with vibration isolation system.
UR - http://www.scopus.com/inward/record.url?scp=84883517267&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84883517267
SN - 9781622769797
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 6372
EP - 6379
BT - 63rd International Astronautical Congress 2012, IAC 2012
T2 - 63rd International Astronautical Congress 2012, IAC 2012
Y2 - 1 October 2012 through 5 October 2012
ER -