Thermostructural analysis of three structural concepts for reusable space vehiclesThree structural concepts are studied: (1) a state-of-the-art insulated aluminum skin-stringer structure; (2) a near-art insulated evacuated aluminum-alloy honeycomb structure; and (3) an advanced evacuated Rene 41 honeycomb hot structure. Each is evaluated for its thermostructural performance for each of the flight profiles (ascent, entry, and a recall or abort). Results indicate that (1) the state-of-the-art structure encounters negligible thermal stress; (2) the near-art structure has acceptable thermal stresses; and (3) the advanced structure will have thermal stress levels above the material allowables.
Document ID
19790050698
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Taylor, A. H. (Kentron International, Inc. Hampton, Va., United States)
Jackson, L. R. (NASA Langley Research Center Hypersonic Aerodynamics Branch, Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 79-0874
Meeting Information
Meeting: Conference on Advanced Technology for Future Space Systems