Dissertation
Dissertation > Aviation, aerospace > Aerospace ( Astronauts ) > Space instrument,spacecraft devices,spacecraft guidance and control > Guidance and Control > Spacecraft guidance and control

Solar wing vibration motor drive control theory and simulation

Author LiuQiang
Tutor TangGuoAn
School Fudan University
Course Engineering Mechanics
Keywords Satellite Solar cell wing Vibration damping Active Control Transfer function Eigenvalue Modal
CLC V448.2
Type Master's thesis
Year 2011
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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 .

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