Finite Element Modeling of a Membrane Sector of a Satellite Reflector Made of Triaxial Composites

Abstract

Single layers of triaxial woven fabric composites have been used to make communication satellite reflectors due to their extremely light weight with good stiffness and strength property. Special superfinite elements have been developed for the analysis of these lightweight materials. These superfinite elements are used for the deflection and stress analysis of a membrane sector of the satellite reflector subjected to lateral pressure. Due to the significant difference in the size of the satellite structure (order of meters) and the size of the superfinite elements (order of millimeters) it is not possible to model the satellite structure using the superfinite elements and computer facilities available in most labs (personal computers). In the process of finding a solution to this problem, a special similitude behavior for the deflection of the curved panels made of triaxial fabrics was discovered. Using this behavior, the deflection of a large-size reflector panel (order of meters) can be analyzed using models in the millimeters size range. Stresses in the triax reflector model were also calculated. However, no special similitude behavior was obtained for the stresses.