Determining parameters of sandwich composite panels for earth remote sensing satellite bus

Abstract

The paper discusses the feasibility of replacing conventional sandwich panel with carbon fiber skins and aluminum honeycomb core in the structure of an Earth remote sensing satellite bus. Thermal loading conditions for sun-synchronous orbit were considered and math simulations were run for stress-strain behavior of a satellite bus element built of the proposed versions of sandwich composite panels. Simulations results might be of interest for design of ultra-lightweight structures of the satellite bus, solar arrays and antenna reflector. Key words: Earth remote sensing spacecraft, Sun-synchronous orbit, math simulations, polymer composite materials.