Accession Number : ADA307926
Title : Transient Thermal Performance of Multilayer Insulation Systems During Simulated Ascent Pressure Decay.
Descriptive Note : Technical note,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Sumner, Irving E. ; Maloy, Joseph E.
PDF Url : ADA307926
Report Date : JUL 1971
Pagination or Media Count : 79
Abstract : Thermal tests were conducted to determine experimentally the transient heat flux and total integrated heat transferred to a liquid hydrogen tank during a simulated Saturn V ascent pressure decay. Three 30-layer helium purged multilayer insulations systems, comprised of (1) glass fiber paper or silk netting spacers between aluminized Mylar radiation shields and (2) fiber glass mat or sealed foam sublayers, were tested. All three insulation systems achieved space hold heat transfer conditions within 2 hours after initiation of pumpdown. The integrated heat transferred was approximately 25 percent greater than ideal, except for the system utilizing the foam sublayer which had not been optimized with regard to thickness.
Descriptors : *FUEL TANKS, *LAUNCH VEHICLES, *THERMAL INSULATION, *CRYOGENIC PROPELLANTS, THERMAL PROPERTIES, THICKNESS, FIBERGLASS, PERFORMANCE(ENGINEERING), LAYERS, ALUMINUM COATINGS, POLYMERIC FILMS, GLASS FIBERS, LIQUID HYDROGEN, HEAT FLUX, PAPER, FOAM, RADIATION SHIELDING, ASCENT TRAJECTORIES, POLYETHYLENE TEREPHTHALATE.
Subject Categories : Ground Support Sys & Facil For Space Vehicles
Air Condition, Heating, Lighting & Ventilating
Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE