The Design Of Space Mechanical Performance Test System Of Deployment Mechanism On Large Solar Wing Panels

With the development of China’s aerospace industry,the solar wing panels commonly used in satellite and spacecraft to supply energy become the focus of study.The solar wing panels realize unfolding and folding process in space by space deployable mechanism.Through the failure case investigation of power system at home and abroad,it’s founded that deploying fault of solar wing panels has the highest frequency of occurrence among the on orbit fault.Therefore,it is very necessary to study deployment performance of deployment mechanism on earth,to test whether the deployment mechanism with load can be normal deployment or not in high-low temperature environment,and to test deployment ability with load of the deployment mechanism.Aiming at the flexible truss deployable mechanism,a set of testing system is designed to test deployment force and the deployment transmission efficiency of the deployable mechanism.Thus,deployable performance of large truss deployment mechanism in high-low temperature environment is evaluated.The deployment mechanism of solar wing panels is the special mechanism which can drive flexible solar wing panels from the folded to unfolded state on-orbit in space.In order to make sure the operation reliability of deployment mechanism in space environment,its mechanical properties should be tested on earth.Space mechanical properties testing system of deployment mechanism on large solar wings panels is to simulate the deployment process of deployment mechanism in high-low temperature and microgravity environment,and to test mechanical performance of deployment mechanism.The detailed structure design of the test system is completed in this thesis.It mainly includes the structure design of gravity balance unit and force loading unit.The test system is discussed mainly from the study on the gravity balance method,the study on a wide range of high-precision axial force loading,the study on deployment transmission efficiency test of the deployment mechanism,the study on the adaptability of high-low temperature environment,the detailed theoretical analysis and experimental verification are carried out.They also verify the correctness and reliability of the test system.In this thesis,the lift-type gravity balancing scheme is proposed to simulate micro-gravity environment.The lift-type gravity balancing device based on a plurality of elastic follow-up moving vehicle is designed to balance the gravity of deployment mechanism.Compared to the traditional gravity balancing scheme of hanging-type,the lift-type gravity balancing scheme overcome the shortcomings that the hanging-type are unable to hook and unhook in turn automatically and reliably.This scheme effectively improve the reliability and stability of gravity balance in the fully automatic unfolding process.In addition,a wide range of high-precision axial force loading device based on the wire rope transmission is proposed.The device solve the problem that the transmission mechanism have large deformation and can’t be accurate transmission and loading in high-low temperature environment.Besides,by co-simulation using Matlab Simulink and Adams software,the change curve of loading force and other related curves are output.The loading precision of the test system is predicted.The predicted results lay a good foundation for the mechanical bearing performance test in the deployment process of deployable mechanism,and verify the feasibility of the axial force loading pattern.In high-low temperature environment range from-110℃ to +110℃,the measures are taken from the mechanical part and the electrical part to overcome the high-low temperature in this thesis.Deformation analysis of the key parts are carried out by using Ansys and SolidWorks software.On the basis of the analysis results,reasonable guidance and advice on the structure design and assembly is given.Finally,The test system was tested.The test system is used to complete mechanical performance test on deployable mechanism.The test results show that the test system has satisfied the test requirements of deployment mechanism of large solar wings in high-low temperature and microgravity environment.The test results also verify the correctness of the design and loading mode of the test system.