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Structural studies of two aerobrake heatshield panel conceptsStructural 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 deg 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.
Document ID
Document Type
Conference Paper
Dorsey, John T.
(NASA Langley Research Center Hampton, VA, United States)
Dyess, James W.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: Engineering, construction, and operations in space - III: Space '92; Proceedings of the 3rd International Conference, Denver, CO, May 31-June 4, 1992. Vol. 1 (A93-41976 17-12)
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
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