Aerogel insulation systems for space launch applications

• Published in: Cryogenics (Guildford) Vol. 46; no. 2; pp. 111 - 117
• Main Author: Fesmire, J.E.
• Format: Journal Article Conference Proceeding
• Language: English
• Published: Oxford Elsevier Ltd 01.02.2006; Elsevier
• Subjects: Applied sciences; Cryogenics; Cryostats; Energy; Energy. Thermal use of fuels; Exact sciences and technology; Polymers; Refrigerating engineering. Cryogenics. Food conservation; Space cryogenics; Thermal conductivity; Transport properties; Thermal conductivity; Transport properties; Space cryogenics; Polymers; Cryostats; Space application; Cold; Thermal insulation; Aerodynamics; Polymer; Nitrogen; Cryopump; Cryogenics; Cryostat; Development
• ISSN: 0011-2275; 1879-2235
• DOI: 10.1016/j.cryogenics.2005.11.007

New developments in materials science in the areas of solution gelation processes and nanotechnology have led to the recent commercial production of aerogels. Concurrent with these advancements has been the development of new approaches to cryogenic thermal insulation systems. For example, thermal and physical characterizations of aerogel beads under cryogenic-vacuum conditions have been performed at the Cryogenics Test Laboratory of the NASA Kennedy Space Center. Aerogel-based insulation system demonstrations have also been conducted to improve performance for space launch applications. Subscale cryopumping experiments show the thermal insulating ability of these fully breathable nanoporous materials. For a properly executed thermal insulation system, these breathable aerogel systems are shown to not cryopump beyond the initial cooldown and thermal stabilization phase. New applications are being developed to augment the thermal protection systems of space launch vehicles, including the Space Shuttle External Tank. These applications include a cold-boundary temperature of 90 K with an ambient air environment in which both weather and flight aerodynamics are important considerations. Another application is a nitrogen-purged environment with a cold-boundary temperature of 20 K where both initial cooldown and launch ascent profiles must be considered. Experimental results and considerations for these flight system applications are discussed.