Patent ID: 6293496
Filing Date: 2001-09-25
Classification: B64G,F16B

Abstract:
A strain compatible attachment arrangement for securing a plurality of metallic thermal protection system panels to a space vehicle substructure, which arrangement comprises:a plurality of attachment means for attaching a plurality of said panels in a edge abutting relationship to a portion of a substructure of a space vehicle to provide a coterminous outer panel surface spaced from said substructure portion of the vehicle to support aerodynamic loading of said outer panel surface while isolating said outer panel surface from strains in said substructure and to isolate said vehicle substructure from direct thermal energy conductance through said outer panel surface of the space vehicle,wherein each panel is shaped to have at least three corners, each of said plurality of attachment means comprises at least one stand-off leg member that is secured at a first end to said attachment means and is releasably secured at a second end to one corner of one panel, and said plurality of attachment means are secured to the substructure of the space vehicle to space the outer panel surface from the space vehicle substructure to isolate said outer panel surface from thermal expansion differences with said space vehicle substructure during vehicle tanking and during ascent and re-entry flight maneuvers.