ABLATIVE COMPOSITES FOR SUPERORBITAL GLIDE RE-ENTRY.
Rept. for Apr 63-Apr 64,
MARTIN CO BALTIMORE MD
Pagination or Media Count:
An investigation of the construction and attachment of composite ablative-radiative heat shields for superorbital glide re-entry was conducted. Major areas of investigation included heat shield chemical compatibility, ablator attachment techniques, thermal stresses, effects of local loss of ablator, and cyclic re-entry heating. This effort employed geometry, trajectories, and environments of the RTD superorbital lifting re-entry vehicle, SORTIE, focusing on the windward lifting surface panels. An extra environment added to those of the SORTIE for completeness was a low temperature soak at -80 F. The radiative heat shield designated for ablator protection was a metallic honeycombreinforced alumina foam composite developed by the Aeronca Manufacturing Company. Author