Session: 01-12-02: Spacecraft Structures 2

Paper Number: 159954

159954 - Thermo-Mechanical Modeling of Pyrolytic Graphite Sheet Laminates for Space Radiator Applications 

Satellites are designed to maintain their internal temperatures within working parameters by dissipating more heat to their environment than is absorbed through incoming solar and terrestrial radiation. Space radiator panels with embedded closed-loop heat pipe systems are employed to efficiently transfer heat from the satellite’s interior components to the space environment. The heat dissipation performance of the radiator panels is largely dependent on their internal in-plane thermal conductivity. The present work simulates a developing spacecraft radiator panel material system composed of carbon fiber reinforced polymer (CFRP) and pyrolytic graphite sheet (PGS) composite laminates  due to their extremely high specific in-plane thermal conductivity. Analyzing the thermo-mechanical behavior of the laminate under realistic low earth orbit conditions using ABAQUS is essential for the development of PGS laminate-based space radiation shielding panels. The three most significant thermal loads applied to the external surfaces of the radiator panel were considered: direct solar radiation, planetary infrared (IR) radiation, and solar albedo radiation. This work will provide an accurate simulation of thermal and mechanical responses of PGS laminate radiator panels under realistic space thermal loading and improve the technology readiness level of this lightweight, high performance thermal management system for reliable implementation in future space missions.

Presenting Author: Devin Nielsen Utah State University

Presenting Author Biography: Devin Nielsen is currently a master's student in his second year at Utah Stat University. He is currently a recipient of the NASA space technology graduate research opportunities grant. His research interests primarily concern multiscale and finite element models of composite structures.