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Cryogenic Foam Insukhn - Abstracted Publications Loan COPY: RETURN ~0 AFN- TECHNICAL LIBRARY Kirtf-AND AFB, N NASA Reference Publication 1002 Cryogenic Foam Insukhn - Abstracted Publications LoAN COPY: RETURN ~0 AFN- TECHNICAL LIBRARY KIRTf-AND AFB, N. Ma Frank R. Williamson SEPTEMBER 1977 TECH LIBRARY KAFB, NM llwwslllllllMsll~lpl Clllb297b NASA Reference Publication 1002 Cryogenic Foam Insulation - Abstracted Publications Frank R. Williamson Cryogenics Division, Institute for Basic Standards National Bureau of Standards, Boulder, Colorado Prepared for The Aerospace Safety Research and Data Institute, NASA Lewis Research Center NASA National Aeronautics and Space Administration Scientific and Technical Information Office 1977 PREFACE This Reference Publication-is part of a cryogenic fluids safety review performed by the NASA-Lewis Research Center. Major emphasis has been on oxygen safety. The objectives of the review include: ‘1: Recommendations to improve NASA cryogenic and oxygen handling practices by comparing NASA and contractor systems including the design, inspection, operation, maintenance, and emergency procedures. 2. Assessment of the vulnerability to failure of cryogenic and oxygen equipment from a variety of sources so that hazards may be defined and remedial measures formulated. 3. Formulation of criteria and standards on all aspects of handling, storage, and disposal of oxygen and cryogenic fluids. This Reference Publication is composed of information from the available reports and publications on Cryogenic Foam Insulation. The documents abstracted and listed contain information on the properties of foam materials and on the use of foams as thermal insulation at cryogenic temperatures. The properties include thermal properties, mechanical properties, and compatibility properties with oxygen and other cryogenic fluids. Uses of foams include applications as thermal insulation for spacecraft propellant tanks, and for liquefied natural gas storage tanks and pipelines. iii CONTENTS Page PREFACE............................. iii INTRODUCTION . vii . ABSTRACTED DOCUMENTS . 1 OTHERDOCUMENTS . 113 AUTHORINDEX . 137 SUBJECT INDEX . 157 V INTRODUCTION This survey is composed of information from the reports and publications available in January, 1976, on Cryogenic Foam Insulation. One group of documents, listed alphabetically by first author, was chosen to include the most important or most informative papers on the properties and applications of foams. An abstract has been prepared for each document in this group, and the most important references are listed as found in the document. Another group of documents, also listed alphabetically by author, generally includes less important papers than those in the first group. Some important papers are in the second group because information from them has been reviewed or repeated in documents included in the first group. An author index and a subject index are provided. The indexes cover the authors and subjects of both groups of documents. Paul M. Ordin of the NASA-Lewis Research Center was the Project Manager for NASA. Identification of a manufacturer's product in this publication in no way implies a recommendation or endorsement by the National Bureau of Standards or by the National Aeronautics and Space Administration. Vii ABSTRACTED DOCUMENTS PLASTIC AND ELASTOMERIC FOAM MATERIALS Arden, B. Northrop Corp., Calif., Nortronics Div., Rept. National Aeronautics and Space Administration Rept. No. NASA CR-100463, Contract NAS 7-430 (1966) 186 pp The purpose of this report is to review contributions to the technology of plastic and elastomeric foam materials derived from NASA research and development programs. The emphasis is on actual or proposed use of foam materials in space vehicles. One chapter of the review is on foam systems for cryogenic insulation, mostly for liquid hydrogen tankage. It is noted that foams have much higher thermal conductivities than do evacuated multilayer insulations, but that advantages of weight, cost, producibility, and reliability have made foams the insulation of choice for short-term missions with liquid hydrogen. Several foam insulations are described extensively. The first of these is the internal insulation developed for the S-IV-B third stage of the Saturn V. This was the "3-D foam," a polyurethane foam reinforced with glass threads oriented in three mutually-perpendicular directions, bonded to the inside of the tank with an epoxy adhesive, lined with a glass cloth reinforced polyurethane resin layer, and sealed with a coat of polyurethane resin. The second system is the external insulation developed for the S-II stage of the Saturn V vehicle. This was the polyurethane foam-filled phenolic honeycomb bonded to the outside of the tank, purged with helium to prevent condensation of air. A third insulation system is the external insulation developed for the Centaur vehicle. This was a polyurethane foam, sealed with an aluminized mylar vapor barrier, and held to the tank by a constrictive wrapping of glass filament. This final insulation was under development, and the development program is discussed quite extensively. The report is an excellent review of the foam insulations developed for space vehicle liquid hydrogen tanks before 1966. It is limited by its age, and does not cover several later developments. Fifteen references are given for more comprehensive information on the foam insulations discussed. Important references: 1. Perkins, P. J., Jr. and Esgar, J. B., AIAA Fifth Annual Structures and Materials Conf. (Palm Springs, Calif., Apr 1-3, 1964), NASA LERC Publication CP-8. 2. Sealed-Foam, Constrictive-Wrapped External Insulation System for Liquid Hydrogen Tanks of Boost Vehicles, NASA TN D-2685 (1965). 3. PlcGrew, J. L., Advances in Cryogenic Engineering 8, 387-392 (1963). Important references (continued): 4. Dearing, D. L., Advances in Cryogenic Engineering 11, 89-97 (1966). 5. Shriver, C. B., Goodyear Aerospace Corp., Final Rept. GER-12249, NASA Contract NAS 3-5646 (Jun 25, 1965). 6. Burkley, R. A. and Shriver, C. B., Goodyear Aerospace Corp., Final Report GER-11193, NASA Contract NAS 3-3238 (Nov 1, 1963). 7. Knoll, R. H. and Oglebay, J. C., Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks, NASA, paper 746C, Presented International Automotive Eng. Congress (Detroit, Mich., Jan 11-15, 1965). 3 COMPRESSIVE PROPERTIES OF POLYURETHANEAND POLYSTYRENEFOAMS FROM 76 TO 300 K Arvidson, J. M., Durcholz, R. L., and Reed, R. P. (National Bureau of Standards, Boulder, Colo. Cryogenics Div.) Advances in Cryogenic Engineering 18, Proc. Cryogenic Engineering Conf. (Colorado Univ., Boulder, Aug 9-11, 1972), K. D. Timmerhaus, Editor. Plenum Press, New York, 194-201 (1973) For many applications of foam insulation in cryogenic environments, compressive properties are more important than tensile properties. The ultimate strength (in the compressive mode) is not well defined for most foams, in that the foam does not reach an ultimate strength, but the rigid foam begins to crumble allowing higher and higher loads to be sustained as the cell structure collapses. This paper complements another paper abstracted on page 89 giving tensile properties for foam insulation. The compressive properties, measured in transverse and longitudinal directions, were modulus of elasticity, proportional limit, yield strength, compressive strength and elongation. The materials were four densities of polyurethane (95.64 kg/m3 to 31.72 kg/m3) and two densities of polystyrene (99.48 kg/m3 to 51.26 kg/m3. Three of the polyurethane foams were rigid and one was flexible while both polystyrenes were rigid. The paper gives tabular results for the compressive properties, but stress-strain curves are also presented. These results showed a strong dependence on density for compressive behavior. As with the tensile results reported in a previous paper the modulus of elasticity, yield strength and compressive strength increased with decreasing temperature while the elongation increased. An approximate linear dependence 3n density was found for the modulus and proportional limit. Longitudinal specimens were usually stronger than transverse specimens. The results of the compression tests were compared to companion tensile results. Both the modulus of elasticity and yield strength were about twice as great in tension as in compression and this difference held for all temperatures. In ultimate strength the differences diminished at the lowest temperatures. Important references: 1. Doherty, D. J., Hurd, R. and Lester, G. R., Chemistry and Industry (London) p. 1340 (Jul 1962). 2. Reed, R. P., Arvidson, J. M. and Durcholz, R. L., Advances in Cryogenic Engineering -18 (1972). INTERNAL INSULATION SYSTEMS FOR LH2 TANKS - GAS LAYER AND REINFORCED FOAM Barker, H. H., Jr., McGrew, J. L., Buskirk, D. L., and Gille, J. P. (McDonnell-Douglas Astronautics Co., Huntington Beach, Calif., and Martin Marietta Corp., Denver, Colo.) Space Transportation Systems Propulsion Technology, Proc. Conf. (George C. Marshall Space Flight Center, Huntsville, Ala., Apr 6-7, 1971) - Vol 4 - Cryogens. National Aeronautics and Space Administration, Rept. No. NASA TM-X-67348, 1453-80 (Apr 1971) Three forms of internal insulation for the liquid hydrogen tanks of the Space Shuttle were being developed: gas layer or capillary insulation, reinforced foam, and polyphenylene oxide foam. The polyphenylene oxide foam is described in the paper abstracted on page 108. This paper describes the other two concepts. The reinforced foam, identified as 3-D foam insulation, was developed for use as internal insulation for the
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