Numerical Simulation Analysis Of Temperature Field In Space Capture Device

In this paper,the on-orbit temperature field of the space grabber is taken as the research object,and two conditions of whether there is no insulated material are considered respectively.The necessity of the heat-insulating material for the space grabber is clarified and the thermal design scheme is proposed,Temperature field in space to maintain the allowable temperature range,safe operation.This paper summarizes the research status of space orbital thermal analysis,introduces the research status of space manipulator and capture mechanism,summarizes the domestic and international space thermal design programs,and on this basis,clarifies the research contents and research objects of this paper.The main work of this paper is as follows:First of all,the components of the space catcher were analyzed to determine the safe operating temperature range of the catcher.The size of the heat flux outside the track is calculated,and the boundary conditions of the simulation analysis are determined according to the orbit parameters of the arrestor.The model of arresting device was simplified,the model which accords with thermal analysis was established,and the finite element model was established by using I-Deas/TMG module.The in-orbit temperature simulation was carried out for the grasper without the insulation material wrapped.The change of surface temperature distribution,the change of temperature field in the whole year and the change of temperature field in different periods make it clear the necessity of heat insulation material,which has a realistic guiding significance for the thermal control design of space grabber.Secondly,according to the basic principles of multi-layer insulation materials and insulation properties of the characterization method,calculate the thermal properties of multi-layer insulation materials.The motion interference analysis and temperature field analysis of the space grabber with the surface insulation material are carried out.The UG/Motion module was used to analyze the motion interference of the catcher with the largest thickness of heat insulation material to ensure that the operation of the catcher would not be affected after the heat insulation material was wrapped.Finally,by simulating the temperature field under the same boundary conditions and the temperature field at the same thermal control requirements of the three different thermal insulation materials,the thermal insulation material most suitable for the space arrestor is selected according to the temperature field results and economical comparison,Gives the thermal design suitable for the catcher.The I-Deas/TMG module was used to analyze the annual temperature change and the change of temperature distribution on the inner and outer surfaces of the heat arrestor wrapped in heat insulation material.Through the on-orbit temperature simulation in this paper,and taking into account the economic conditions,the thermal design of the space grabber is finally determined to ensure that the arrestor can operate safely on the track.