Failure Mechanism Analysis And Solution Research Of A New Satellite Deployable Mechanism

The solar panel is the main source of energy when the satellite is in orbit,which is of great significance to the satellite's life and the successful completion of the mission.Due to the overall quality constraints of a satellite and the constraint of the carrier rocket,a certain improvement has been made to the mechanism of the panel,so that it is in line with the characteristics of the microsatellite itself.At the initial stage of development,the windshield can be launched smoothly before the vibration test.After the end of the vibration test,the windshield failed to expand,and it could expand after human touch,but the deployment time increased significantly.Aiming at the failure of a new type of windshield deployment mechanism at the initial stage of development,the main contents of the paper are as follows:First,the characteristics of a satellite structure,the satellite vibration test and the surface expansion experiment of the board are introduced,and the traditional model of the plate launching dynamics is improved,and the failure mechanism of the satellite sailing board is analyzed.The advantages and disadvantages of the traditional sailing mechanism and the unfolding mechanism of the constant force moment hinges are introduced,and the vibration test of a satellite and the failure of the experimental panel are described.The traditional model of windshield deployment dynamics is introduced,and the relationship between the angle and time of the expansion mechanism of the constant moment hinge hinges before and after the vibration test is analyzed.In view of the shortcomings of the traditional model of the dynamic sailing of the panel,the traditional model of the plate expansion dynamics is improved.On the basis of this,this paper analyzes the failure mechanism of a satellite sailing board,and compares the simulation results and the experimental results to verify the accuracy of the improved model.Secondly,the impact force and wear of hinged joints in vibration test are quantitatively analyzed,and the influence of different parameters on contact impact force is studied.The Hertz model,the K-V linear spring damping model,the H-C contact force model and the L-N contact collision force model are compared and analyzed respectively.The contact impact force of a satellite hinges in the vibration test process is quantitatively analyzed by using the L-N contact impact force model.Then,combined with the Archard wear model,the parameters related to the wear amount of hinges in vibration tests are explored.Subsequently,the 3D model of the joint bearing is established by using Solid Works,and the contact force and the wear relationship of the joint bearing are discussed in detail by using the Simulation module.Finally,different initial collision speeds and different recovery coefficients are selected to study their impact on the contact impact force of the hinges,so as to provide an important reference for solving the failure of a satellite panel.Finally,based on the structural characteristics of a satellite,a solution for the failure of a satellite sailing board is proposed,and the effectiveness of the solution is verified by comparison and analysis of the dynamic improvement model,ADAMS model and experimental results.A satellite adopts two measures of adding auxiliary separation spring and improving the stiffness of hinges to solve the failure of the panel.Then,the dynamic model of the sailing board is used to analyze the improved model.Then the accuracy of the improved model is verified by a dynamic model of a satellite sailing board based on ADAMS,and then the ground experiment.The results verify the accuracy of the improved model and the effectiveness of the solution.