Thermal Analysis Of Deployable Planar Antenna Support Structure

Truss support mechanism is widely used in deployable planar antenna.It plays animportant role in supporting antenna panel and ensuring the accuracy of the antenna.Soimproving the stiffness and thermal stability of the antenna is of great significance todevelop an antenna with high performance.By taking deployable planar antenna support mechanism as research object,theauthor first established the3D model with PROE,and imported to PATRAN finiteelement software for thermal deformation analysis and modal analysis consideringthermal effection.according to thermal deformation and modal analysis,autor establishedfinite element mode.in thermal deformation analysis,the autor established the hingeswith RBE2,a kind of Multiple Point Constraint；in modal analysis used rod element tosim--ulate the stiffness of the hinges.The support mechanism studied in this thesis has many joints and this joints allhave complex slapes. As the effecion of thermal deformation of joint to the supportmechanism can not be ignored,the joint can not be simplified too much.the materials ofjoint is aluminum alloy.even though all the thermal expansion coefficients of the barsare zero,the truss still has a large thermal deformation.to make the thermal deformationminimization,it is important to allocation thermal expansion coefficients of the bars.As for the problem of the stimulation of the hinges’ stiffness in the supportmechanism modal analysis,the author firstly infers the relation between the hinge’sstiffness to pull and press,the host curved stiffness as well as the axial stiffness and eachsimulation pole unit’ elasticity coefficient, providing a theoretical basis for theevaluation of the hinge pole unit elasticity coefficient,then obtaining the more accuratenatural frequency and the promotion result of the support mechanism.Besides the modalanalysis,this article has also analyzed the change trend of the support mechanism naturalfrequency along with the temperature field change and has given a reasonableexplanation to this tendency.Since the members of Plane aerial support mechanism are of great number andcomplexity and a large number of variables exist in the optimization process ofoutrigger thermal-expansion coefficient,it’s not easy to restrain. The author uses themulti-objective optimization software ISIGHT that MSC Corporation explores totransfer finite element model to analyze and optimize the hot sensitivity to themember’s thermal-expansion coefficient. Before analysis,the author first establishes thedocument of the finite element’s parametrization and optimization,then integrates thisdocument into ISIGHT,finally chooses separately the Latin square parameter parsingalgorithm to analyze the sensitivity of overall thermal deformation to thermal-expansion coefficient of various poles group,and Chooses the multi-island genetic algorithm tooptimize the outrigger thermal-expansion coefficient. This optimized value will becomethe basis to instruct the layer design of the support mechanism compound materialspole’s thermal-expansion coefficient.