Author(s)

M. Cioeta & M. Marchetti

Abstract

This paper presents the results of the design of an inflatable rigidizable space structure. The structure is a balloon of approximately 5 metres diameter, made of a composite material that rigidizes by curing of the epoxy resin of which it is made, under the action of the typical thermal loads of LEO orbit. The balloon is covered with a metallic layer that must be a continuum electric conductor. An analysis of mono-dimensional continuum will be presented to validate the hypothesis that the thermal gradient trough the thickness of the material is negligible so that it is possible to study a two-dimensional model. A model of the LEO orbit environment has been studied in order to define the thermal fluxes on the structure surface. The considered thermal loads are: sun ra

Keywords