Dynamic Characteristics And Deployment Reliability Analysis Of Lunar Rover With Clearance Joints Under Extreme Temperature

Due to the extreme temperature of the space environment,the deployable panel mechanism of the spacecraft,such as the Harbert telescope,has been invalidation.Therefore,it is of great engineering value to study the influence of extreme temperature on the expansion process of the deployable panel.This paper is based on the study of the independent R & D reduplicated Solar array of the lunar rover.Through the analysis of the influence of the lunar surface temperature on the dynamic performance and the reliability of te unfolding process,it provides a theoretical basis for the optimal design of the deployable mechanism and the optimal temperature range.The main contents of this paper are as follows:First of all,that the lunar extreme temperature effects on the exhibition panels materials and hinge structure is analyzed.Considering the influence of the extreme temperature of the moon on the modulus of elasticity and the Poisson’s ratio of the plate material,the influence of the monthly temperature on the coach clearance is calculated by using the finite element theory and the elastic thin wall circle theory.The two types of hinge structures containing sliding bearing and rolling bearing are calculated respectively.Secondly,a dynamic model of the lunar exhibition panels under extreme temperature is established.Two types of hinge structure clearance model with rolling bearing and sliding bearing are constructed.Based on the kinematic elastodynamic modeling method,combined with the influence factors of extreme temperature on the plate material and hinges structure,the flexible coupling dynamic model of the two types of hinges under the extreme temperature of the lunar surface is established.Third,the numerical method to analyze the influence of surface temperature extremes on the dynamic characteristics of the deployable panels is used.The four order variable step length lomo Kutta method and newmark-β method are used to calculate the dynamic characteristics of the adjustable lunar surface with two types of hinge structures,and the dynamic characteristics of the hinges are found.Use the quasi-static method to establish the finite element model of vibration,and analysis the influence of surface temper-ature on the natural frequency of the deployable panel.Finally,the reliability model is established,and the influence of extreme temperature on reliability is analyzed by using the end displacement error as an index.The geometric parameters and physical parameters of the material are taken as random variables.The reliability model of the deployable panel is established by combining the BP neural network algorithm with the two order moment method.By comparing the reliability indexes at different extreme temperatures,the optimal temperature range of the reliable expansion of the board is found.