| With the development of China’s aerospace industry,some solar wing space deployable mechanisms will be used in more and more aerospace engineering.The traditional solar wing would not meet the needs of multi-task because of the limitation of power and in order to achieve greater power-to-mass ratio and folding ratio requirements,the fan-shaped space deployable mechanism that can be applied to a spacecraft solar wing is designed in this paper.The main works includes:1.Based on the folding fan idea,the wraparound strategy of the designed space deployable mechanism is determined,and the whole mechanism are designed,including the design of synchronizing mechanism,the design of center hinge,the design of self-locking hinges and the design of driving mechanism.2.In this paper,the kinematics and multi-body dynamics simulations of the driving mechanism and the four-unit fan-shaped space deployable mechanism are performed respectively with two kinds of multi-body system dynamics software which include Adams and RecurDyn.Multi-stage expansion and the reliability and controllability of the space deployable mechanism can be realized.The two-wing model is simulated by the whole star with satellite.The results show that the deployment of the solar wing has a certain influence on the position and attitude of the spacecraft.3.Using the finite element software Ansys Workbench,the static analysis of the two self-locking hinges and the solar wing with the launching load in the collapsed state is carried out.The two self-locking hinges and the solar wing subjected to the space load in the unfolded state are statically analyzed.The modal analysis of the self-locking hinges and the solar wing in free is carried out,and the relevant parameters are obtained and the rationality of the design is proved. |
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