Multi-scale Analysis of Pyrolytic Graphite Sheet Laminates for Space Radiator Applications Using NASMAT

In space the only available method of heat transfer is radiation. This makes it difficult to design satellites and human spacecraft as these systems must maintain their internal temperatures within working parameters by dissipating more heat than is absorbed through solar and terrestrial radiation. This is done through external deployable radiator panels with closed loop radiator systems pumping heat to the panels. The heat dissipation performance of the radiator panels is largely dependent on their internal thermal conductivity due to the heat traveling further along the length of the panel before it is radiated. A new form of advanced satellites or spacecraft radiator panels in development is constructed from pyrolytic graphite sheet (PGS) laminates due their extremely high in-plane thermal conductivity. The current state-of-art thermal analysis of these novel satellite radiator systems has only focused on simulating heat transfer of the full radiator system. Using the NASA Multiscale Analysis Tool (NASMAT), the proposed research will expand on the development of this system by simulating the thermo-mechanical response of the PGS laminates subjected to space radiation and micrometeoroids and orbital debris (MMOD) impacts. NASMAT will allow increased accuracy to the prediction of temperature-dependent properties, interfaces, internal thermal stresses, and damage prediction within a multiscale recursive framework. The present work will focus on in-depth understanding of heat transfer and associated thermal stresses induced on the PGS laminate, resulting from the conduction heat transfer from the working fluid through the panel, to the vacuum of space by the medium of radiation. The viability of the radiator panels is confirmed by simulating MMOD impacts on the PGS laminate's surface to ensure their withstanding in harsh space environments. Accurately simulating the thermo-mechanical behavior in the PGS laminate radiator panel through multiscale analysis requires two steps. First, NASMAT simulates the PGS laminate. Second, the NASMAT model is integrated as the material model in an ABAQUS explicit simulation of the full spacecraft radiator panel. This work will provide an accurate simulation of thermal and mechanical loading on PGS laminate radiator panels and improve the technology readiness level of this lightweight, high performance thermal management system, so it can be effectively implemented in future space missions with a high degree of reliability.

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