Solar wing vibration motor drive control theory and simulation
|Keywords||Satellite Solar cell wing Vibration damping Active Control Transfer function Eigenvalue Modal|
Dynamic incentive for satellite solar cell wing attitude adjustment after normal work affects spaceborne payload . Implementation of damping control technology means there are two categories, one is passive damping measures , and the other is the active control . The passive damping measures , subject to the constraints of the structural mass , material properties , and other factors , and is not easy to achieve the requirements of solar cell wing Vibration Control . By active control increases system vibration damping , fast and effective control the sun the wing attitude adjustment after the residual vibration damping In this thesis, the problem is mainly to do the following work : 1 ) on the basis of vibration theory to explore a speed feedback active control mode, to increase the vibration damping so as to achieve to accelerate the vibration damping purposes. 2 ) According to the existing literature eigenvalue allocation theory , try to be introduced to the 2nd order linear vibration system , try to achieve particular vibration mode damping coefficient of solar wing configuration control theory . 3) In order to verify before two active control the effectiveness of the method , the the solar wings simplified beam model by active feedback control integrated into the advanced dynamics finite element analysis , numerical simulation results to verify the effectiveness of the method . 4 ) on the basis of the above theoretical derivation of the simplified model validation results , the solar wing vibration control theory is extended to the two - dimensional plate model , combined with bending , torsion active control of the study , the actual working conditions to be more attuned to the solar wing .