Thermal Deformation Analysis On Deployable Space Structure

With the continuous development of aerospace technology，the manufacturingerror and deformation of deployable antenna should be less，so thermal deformation ofantenna must be analysed more accurately. The in-orbit thermal deformation simulationanalysis of a new deployable antenna named spaceborne folded hoop-rib scheme iscarried out in this paper.Based on extensive referring to relative literatures，research background anddeveloping status on the thermal analysis of the space deployable antenna areintroduced，and its significance is also elaborated. It introduces the related analyticalworkflow of the satellite antenna by means of thermal analysis software I-DEAS andANSYS. In order to select the right materials for the hoop-rib antenna reflector,different orbits and different reflector materials are analysed by using I-DEAS TMGmodule.An expanded overall model of a folded hoop-rib scheme with a30m aperture isconstructed with I-DEAS. With the TMG module, the temperature field of the antenna’seight cycles are obtained when the spaceborne folded hoop-rib scheme is running on asun-synchronous orbit and the sun is in Vernal Equinox,Summer Solstice, AutumnalEquinox and Winter Solstice respectively. Then the deformation field of the spacebornefolded hoop-rib scheme is calculated by loading the temperature field and using finiteelement analysis software of ANSYS. Compared with the existing hoop-column antenna,the strengths and weakness of this antenna are found with the purpose of providing areference for the thermal design of the antenna.In the solar system，the sun is the biggest outside heat source of the antennain-orbit flight. It directs to the antenna and produce pressure in the form of radiationpressure, and thus affects the temperature field and the deformation field of thedeployable antenna. This paper takes primary analysis of the solar radiation pressure onthe hoop-rib deployable structure.The simulation analyses of in-orbit thermal deformation of the folded hoop-ribscheme validate the feasibility of the new structure, predicts thermal deformation scopeduring its in-orbit movement, and provides a valuable reference for the further research.