Simulation Research And Design On Repeated Fold-unfold And Lock-unlock Mechanism Of Solar Wing

The foldable way of solar wing is taken as the main power equipment for spacecraft worked in-orbit to act the indispensable function. The fold-unfold and lock-unlock mechanism of the solar wing is the key component, whose structure will influence deploying and working condition of solar wing in-orbit. The repeated fold-unfold and lock-unlock mechanism of the solar wing is developed to realize folding when the spacecraft is orbital transfer or posture regulating control. After the orbital transfer being finished or the attitude adjustment being ended, the solar wing is deployed repeatly. All of above is significant to guarantee that the work of solar wing is normal and reliable, the attitude of spacecraft is stability and the flight of spacecraft is safety.This article takes the foldaway solar wing as the object of study to give a design and reseach to the hinge joint which is of repeated fold-unfold and lock-unlock function, the main research is shown as follows:Based on the comprehensive analysis of present research situation and tendency for fold-unfold and lock-unlock mechanism of solar wing at home and abroad and combined with its application background and design principle, the design schemes of repeated fold-unfold and lock-unlock mechanism are proposed. Two-stage fuzzy comprehensive evaluation is made on various schemes By using multi-level fuzzy comprehensive evaluation method of fuzzy mathematics, then the two-stage helical repeated fold-unfold and lock-unlock mechanism by fixed self-locking and self-balancing for solar arrays is comfirmed as the optimal design scheme.Based on aspects of drive type, lock-unlock way, transmission characteristic, implementing mechanism, the driving system design of the two-stage helical solar wing, the calculation on structure dimension and strength of its key components are made to satisfy the synchronization requirement of fold-unfold and lock-unlock. Through the solar wing assembly analyzing, the foundation is provided for the physical prototype manufacture.According to the transmission order of repeated fold-unfold and lock-unlock hinge joint to simplify its structure relations, kinematics analysis on deployment of two-stage helical repeated fold-unfold and lock-unlock mechanism for solar wing is carried out. Used the Kane dynamic equation, the dynamics model of solar array deployment is established. And then the plane degree, synchronization degree and the hing joint torque are gained. Based on the Pro/E three-dimensional model and ADAMS, the dynamics simulation model of virtual prototype on fold-unfold and lock-unlock mechanismsolar wing is established. Then the simulation value of fold-unfold speed, acceleration, axial displacement and the joint torque for the solar wing are tested to verify the theory modelling is correct, which are compared with the theoretical calculation results to verify the structure design is rationality.