Structural Studies of Two Aerobrake Heatshield Panel Conceptsby John T. Dorsey, NASA Langley Research Cent, Hampton, United States,
James W. Dyess, NASA Langley Research Cent, Hampton, United States,
Document Type: Proceeding Paper
Part of: Engineering, Construction, and Operations in Space III
Abstract: Structural sizing and performance data are presented for two different aerobrake hexagonal heatshield panel structural concepts. One concept features a sandwich construction with an aluminum honeycomb core and thin quasi-isotropic graphite-epoxy face sheets. The other concept features a skin-rib isogrid construction with thin quasi-isotropic graphite-epoxy skins, and graphite-epoxy ribs oriented at 0°, +60°, and -60° along the panel. Linear static, linear bifurcation buckling, and nonlinear static analyses were performed to compare the structural performance of the two panel concepts and assess their feasibility for a Lunar Transfer Vehicle aerobrake application.
Subject Headings: Panels (structural) | Epoxy | Construction materials | Construction management | Isotropy | Linear analysis | Bifurcations
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