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 

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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: 

2. 

3. 

Recommendations to improve NASA cryogenic and oxygen 

handling practices by comparing NASA and contractor 

systems including the design, inspection, operation, 

maintenance, and emergency procedures. 

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. 

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 POLYURETHANE AND POLYSTYRENE FOAMS 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 liquid hydrogen tanks 

of the Saturn-IV and S-IVB stages. It consisted of a polyurethane 

foam reinforced with glass threads in three mutually perpendicular 

directions. The foam was bonded to the tank wall with an epoxy 

adhesive, and sealed against hydrogen permeation with a layer of glass 

cloth impregnated with polyurethane resin. The insulation on each of 

two battleship vehicles survived over 100 cryogenic loadings, on 

an all-systems vehicle 300 loadings, and on each flight stage between 

2 and 6 loadings. After initial modifications on the first battleship 

vehicle, no significant degradation was observed. Thermal conductivity 

of the foam approached that of helium gas. For the Space Shuttle, the 

maximum service temperature was increased to 450 K. The paper shows 

some results of weight-loss tests at high temperatures on various 

candidate materials, including a polyurethane foam which, after heat 

conditioning, was more stable than the previously-used foam, and 

seemed usable at 450 K. A total weight reduction by 20 or 25% seemed 

feasible. 

The gas layer insulation consists of a honeycomb structure 

bonded to the tank wall and covered with a punctured membrane. 

Capillary forces at the membrane holes support a stable liquid/gas 

interface, separating liquid in the tank from the gaseous hydrogen 

within the honeycomb cells. This concept is similar to an open-cell 

foam with large cell size. The insulation appeared usable at 

temperatures up to 616 K to 644 K with available materials. 

The authors conclude that both the reinforced foam and the gas 

layer insulation are feasible for use on the Space Shuttle. 

5 
A STRUCTURAL PUSTIC FOAM THERMAL INSULATION FOR CRYOGENIC SERVICE 

Bennett, R. B. (Amspec, Inc., Columbus, Ohio) 

Advances in Cryogenic Engineering 19, Proc. Cryogenic Engineering Conf. 

(Georgia Inst. of Tech., Atlanta, Aug 8-10, 1973), K. D. Timmerhaus, 

Editor. Plenum Press, New York, 393-9 (1974) 

This paper describes a commercial rigid polystyrene foam developed 

as a load bearing insulation for the bases or bottoms of liquefied 

natural gas tanks. The material is a high density (52.8 kg/m3) extruded 

foam. 

Compressive stress-strain curves at 111 K and 296 K show that 

compressive strength increased gradually with decreasing temperature. 

Yield points at both temperatures were at about 4% strain. Long-term 

compressive creep was estimated at less than 2% after 20 years at 

maximum design ioad at 296 K, and was even lower at lower temperatures. 

Cyclic loading and freeze-thaw cycling had little effect on the foam. 

Thermal conductivity had an s-shaped curve with a maximum near 185 K 

and a minimum near 250 K. Measured thermal conductivities were 0.022 

W/m*K at a mean temperature of 200 K and 0.030 W/m*K at 297 K. Complete 

replacement by diffusion of the freon blowing agent with methane would 

substantially increase the thermal conductivity, but over a period of 

10 to several hundred years. Long term immersion tests in liquid 

methane, liquid ethane, liquid propane, and LNG showed complete 

compatibility. The foam contained a fire retardant. In actual 

applications to LNG tanks, the polystyrene foam performed well within 

design expectations. 
ANALYSIS AND MEASUREMENT OF THE HEAT TRANSMISSION OF MULTI-COMPONENT 

INSULATION ON PANELS FOR TRERMAL PROTECTION OF CRYOGENIC LIQUID 

STORAGE VESSELS 

Bourne, J. G., and Tye, R. P. (Dynatech R/D Co., Cambridge, Mass.) 

Heat Transmission Measurements in Thermal Insulations, Proc. Symp. 

Thermal and Cryogenic Insulating Materials (Philadelphia, Pa., Apr 

16-7, 1973), American Sot. for Testing and Materials, Philadelphia, 

Pa., Special Tech. Publ. No. STP-544, 297-305 (Jun 1974) 

The usual insulation for the liquefied natural gas tanks on ocean 

tanker vessels is external insulation, which provides structural load 

bearing as well as thermal insulation. Insulation systems combining 

foam insulation with balsa wood were developed, and this paper reports 

on thermal conductivity measurements of the insulation components and 

of scale models of the composite insulation systems. These measurements 

aided the development of an analytical model to predict the,thermal 

performance of full-scale insulation systems. 

The components tested were a commercial polyurethane foam, a 

commercial polystyrene foam, balsa wood with two grain orientations, and 

commercial foamed glass. A layer of the composite insulation consisted 

of alternating strips of balsa wood and foam insulation. Scaled samples 

consisted of three layers of the composite, with or without adhesive 

bonding, with or without plywood facings, and with varying angular 

displacement of strip orientation between layers. Thermal conductivities 

were measured between a cold face at 82 K and a hot face at 395 K. 

Results are tabulated for the five component materials and for six 

composite insulations. The analytical model used the properties of the 

components to predict the thermal conductivities of the composite 

insulations, with errors ranging from 0 to 7%. The authors conclude 

that the analytical approach is valid and useful. 

Important references: 

1. Tye, R. P., Proc. XIII International Congress of Refrigeration 1 

(Washington, D.C.), Institute International de Froid, Paris (1971). 

7 
METHODS OF INSULATING PIPE WITH POLYURETHANE FOAMS 

Brochhagen, F. K., and Schmidt, W. (Farbenfabriken Bayer A. A., 

Leverkusen, West Germany) 

Plastics Inst. (London) Trans. J. 35, No. 117, 499-503 (1967) 

Polyurethane foams have found increasing use in insulating pipelines. 

This paper reviews the methods of applying the foam to the pipe, and 

describes some of the limitations in using polyurethane foams as 

pipeline insulation. Service temperature limits are given as 73 K to 

403 K for rigid foam and 233 K to 383 K for flexible foams. 

The methods of application are foaming in place, installing 

prefabricated half-pipe sections, or pre-insulating the pipe in sections 

at the factory. In foaming in place, the reactive mixture is injected 

between the pipe and a sheet-metal jacket. This method is limited by 

temperature requirements for proper production of foam. Prefabricated 

half-pipe sections can be molded to shape or cut from rectangular shapes, 

and applied to the pipe as other solid insulations are. Flexible foams 

can be made as tubing to slip over the pipe, or as sheet to wrap around 

the pipe. Pre-insulated pipe is foamed in place under controlled 

conditions in the factory. 

A problem with polyurethane foam insulation is its permeability to 

water vapor. This property makes it necessary to seal the foam in a 

vapor barrier for low-temperature applications. 
PPO FOAM FOR CRYOGENIC APPLICATIONS 

Burkinshaw, L. D. (General Electric Company, Bridgeport, Connecticut) 

Proceedings of the International Conference on LNG lst, Chicago, Ill. 

(Apr 7-12, 1968) (J. W. White and A. E. S. Neumann, Eds.) Institute of 

Gas Technology, Chicago, Ill. (1968) 12 pp 

Polyphenylene oxide (PPO) foam was described in this paper as a 

potential component for cryogenic insulations. The foam is an 

anisotropic open cell foam produced in flat sheets. The open cells 

extend through the entire thickness of the sheet, all aligned in the 

same direction. 

Foam densities ranged from 24 to 59 kg/m3. Thermal conductivity 

of a foam of unspecified density was 0.025 W/m-K at 208 K and 0.058 

W/m-K at 316 K. Compressive strength of the foam with load applied 

perpendicular to the plane of the sheet was greater than that of 

polyurethane foam of similar density over the temperature range from 

220 K to 480 K. Compressive strength was strongly dependent on density 

and weakly dependent on temperature. 

In a test as insulation, the PPO foam was sealed on one side and 

exposed directly to liquid nitrogen or liquid natural gas on the other 

side. The liquid cryogens penetrated less than 5 mm into the foam. 

Pressure increases caused only temporary increases in the penetration 

depth of the liquid. The reason for the limited penetration was not 

known, but it was suggested that liquid entering the pores boiled and 

produced a back pressure which prevented further penetration by the 

liquid. A proposed container would consist of a PPO foam liner within 

an outer metal housing. 
DEVELOPMENT OF METHODS FOR APPLICATION OF POLYURETHANE SPRAY FOAM 

INSULATION SYSTEMS TO LIQUID HYDROGEN TANKS 

Carter, J. M. 

National Aeronautics and Space Administration, Huntsville, Ala., 

George C. Marshall Space Flight Center, Tech. Memo No. NASA TM-X-53897, 

62 pp (Sep 1969) 

Polyurethane foams had been used for insulating liquid hydrogen 

tanks for several years when, in 1967, two proposals were made to apply 

spray polyurethane foam as insulation for liquid hydrogen tanks on 

large flight type structures. These structures were the Nuclear Ground 

Test Module and the S-II vehicle. This report reviews the available 

spray foam application equipment, describes the modified commercial 

spray foam formulator developed for use, describes the methods of 

surface preparation, foam application, and surface finishing, and 

reports on the results of several test items insulated with the 

polyurethane spray foam. 

The foam is sprayed onto a cleaned and etched aluminum tank 

exterior surface. Specific instructions are given for applying the 

spray. The exterior surface of the foam is sealed with a sprayed-on 

coating of polyurethane adhesive or with a fiberglass reinforced 

polyurethane adhesive coating. Spray foam insulation was applied to a 

1.8 m diameter tank which was then subjected to a liquid hydrogen 

fill-drain cycle. Foam failures led to modification of the procedure. 

Spray foam was applied to a 76 cm rectangular dewar, which withstood 

liquid nitrogen and liquid hydrogen fill-drain cycles and exposure to 

radiation without visible damage. Some debonding was noted after 

further liquid hydrogen fill-drain cycles. Spray foam applied to a 

S-IC/S-II test container showed split and debonded areas after a 

cryogenic tanking procedure, but all defective areas were removed and 

repairs made. 

The author concludes that a capability has been developed to 

satisfactorily apply polyurethane spray foam insulation to cryogenic 

propellant tanks, and that the foam insulation applied to test tanks 

satisfactorily withstood cryogenic cycling. 

10 
AN INVESTIGATION OF THE USE OF INTERNAL INSULATION FOR LIQUID 

HYDROGEN FUELED MISSILES 

Coxe, E. R., Lowrey, R. O., Hunt, R. T., and Freeman, S. M. 

(Lockheed-Georgia Co., Marietta) 

Advances in Cryogenic Engineering 8, Proc. Cryogenic Engineering Conf. 

(Los Angeles, Calif., Aug 14-16, 1962), K. D. Timmerhaus, Editor. 

Plenum Press, New York, 404-10 (1963) 

An experimental study was conducted to determine the suitability 

of several commercial plastic foams for use in composite internal 

insulation for liquid hydrogen tanks. The insulation considered was 

plastic foam adhesively bonded to the inside of the tank wall and 

covered by a vapor barrier bonded to the foam. 

The first part of the program obtained the mechanical properties 

of three adhesives, six foams, and two vapor barriers. In the second 

part of the program, twelve composite insulation configurations were 

installed in 30-cm diameter tanks and tested by thermal cycling in 

liquid nitrogen and then in liquid hydrogen. In general, flexible 

foams resulted in the vapor barrier failing in tension under tank 

pressure, while the rigid foams failed under high thermal stresses. 

The best foams from these tests were a flexible polyurethane foam and 

a rigid epoxy foam. Composite insulations with these foams were 

subjected to pressure and vibration in liquid hydrogen. The polyurethane 

foam failed in compression and its vapor barrier failed in tension under 

pressure. The epoxy foam did not fail, but separated from the tank wall. 

The two systems were then applied to a 1 m diameter, 2.5 m long tank, 

and tested under pressure in liquid hydrogen. The polyurethane sample 

showed vapor barrier penetrations, and a thermal conductivity no better 

than that of hydrogen. The epoxy foam did not fail, and the vapor 

barrier did not rupture where it covered the epoxy foam, but there was 

considerable detachment of vapor barrier from foam and of foam from the 

tank wall. 

The tests showed that the main problem with foam internal insulation 

is maintaining an intact vapor barrier. Local penetrations of the 

vapor barrier only resulted in contamination of the insulation with 

hydrogen gas, so that insulation performance is at least as good as 

that of gaseous hydrogen even with local failures of the vaporbarrier. 

11 
LOW TEMPERATURE INSTJLATIONS-FOAMS AND COMPOSITES 

Cryogenic Engineering News 

Cryogenic Eng. News A, No. 5, 20-5 (May 1969) 

This review covers the subjects of foam insulation and composite 

insulation with the aid of data taken from a number of sources. The 

rather brief discussion of foams stresses the polyurethanes. Graphical 

data show the temperature dependence of thermal conductivity of freonblown polyurethane foam, of polystyrene foams, and of teflon and a 

composite of teflon foam with teflon. Thermal conductivity versus 

pumping time is shown for polystyrene, epoxy, and isocyanate foams. 

Thermal conductivities are tabulated for polystyrene, epoxy, polyurethane, 

rubber, and silica foams. Thermal and mechanical properties of several 

densities of polyurethane foam are tabulated. Graphs and a table show 

the tensile, shear, and compressive strengths and the linear thermal 

expansions of polyester polyurethane, epoxy, polyurethane, and polyether 

foams. Composite insulations containing foams are very briefly discussed. 

The review concludes with an extensive bibliography of 29 references, 

most of which deal with foam insulation. The primary application of this 

review would be as an introduction to the subject, with the bibliography 

providing sources of more detailed information. 

Important references: 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

Development of Low-Density Rigid, Polyurethane Foam for Use on 

S-1C Flight Vehicle, Final Report, NASA CR-62110 (1964). 

Barringer, C. M., Refrigerating Engineering New York 65, No. 4, 

53-6 and 108-12 (1957). 

Haskins, J. R. and Hertz, J., Advances in Cryogenic Engineering 1, 

Plenum Press, New York, 353-9 (1962). 

Lewis Research Center Staff: Sealed-Foam, Constrictive-Wrapped, 

External Insulation System for Liquid-Hydrogen Tanks of Boost 

Vehicles, NASA TN D-2685 (1965). 

McClintock, R. M., Advances in Cryogenic Engineering 4, 132 (1958). 

Miller, R. N., Bailey, C. D., Beall, R. T. and Freeman, S. M., 

Advances in Cryogenic Engineering 8, Plenum Press, New York, Paper 

C-6 (1963). 

Miller, R. N., Bailey, C. D., Beall, R. T., Freeman, S. M. and 

Coxe, E. F., Ind. Eng. Chem. 1, No. 4, 257-61 (Dee 1962). 

Stoecker, L. R., Advances in Cryogenic Engineering 2, Plenum Press, 

New York, 273-81. 

12 
MATERIALS OF CONSTRUCTION FOR USE IN AN LNG PIPELINE 

Dainora, J., Duffy, A. R., and Atterbury, T. J. (Battelle Memorial 

Inst., Columbus, Ohio) 

American Gas Association, Arlington, Va., Rept. No. L40000, 127 pp 

(Apr 1968) 

This report contains a 13-page section reviewing cellular 

insulation, including plastic foams, foam glass, cork, and balsa wood. 

The review is based on data taken from the literature. The major types 

of material discussed are urethane foams, polystyrene foams, epoxy 

foams, silicone foams , phenolic foams, syntactic foams, cellular glass, 

and cork and balsa wood. Nine data sources are cited in the discussion. 

Much of the information included in this review is on properties 

at room temperature. Tables summarize the room temperature properties 

of the urethane, polystyrene, epoxy, silicone, syntactic, and glass 

foams. Mechanical properties and thermal conductivity of urethane 

foams, thermal conductivity of polystyrene foams, compressive strength 

of epoxy foams, and mechanical properties and thermal conductivity of 

phenolic foams are all presented graphically as functions of foam 

density at room temperature. Data of more direct interest for cryogenic 

insulation are graphs of thermal conductivities from 200 K to 400 K of 

cellular glass, cork, polystyrene foam, phenolic foam, and urethane 

foam; mechanical properties of urethane foams from 77 K to 297 K; thermal 

conductivities of polystyrene foams from 30 K to 310 K; mechanical 

properties of epoxy foam from 77 K to 310 K; and thermal conductivity of 

corkboard from 77 K to 300 K. 

The review should serve as an introduction to and comparison 

between cellular insulation, rather than as a source of specific data. 

Important references: 

1. 

2. 

3. 

4. 

5. 

6. 

Gerstin, H., Product Engineering, 59-68 (Jun 1965). 

Miller, R. N., et al., Advances in Cryogenic Engineering 8, Edited 

by K. D. Timmerhaus, Plenum Press, Inc.; New York, 417-24 (1963). 

Campbell, M. D., Haskins, J. R., Hertz, J., Jones, H., and Percy, 

J. L., MRG-312, Contract No. A!F 33(616)-7984 (Compilation of 

Materials Research Data (Apr 1962)). 

Haskins, J. F. and Hertz, J., Advances in Cryogenic Engineering 8, 

Edited by K. Il. Timmerhaus, Plenum Press, Inc.., New York, 353-9 

(1963). 

Fabian, R. J., 'Mater. Design Eng. (Mar 1958). 

Gray, V. H., Gelder, T. F., Cochran, R. P., and Goodykoontz, J. H., 

NASA TN D476, Washtngton, DC (1960). 

13 
Important references (continued): 

7. Jacobs, R. B., Technology and Uses of Liquid Hydrogen, Edited by 

.R. B. Scott, W. H. Denton, and C. M. Nicholls, .Macmillan Co., New 

York, 106-48 (1964). 

14 
EXPANDED POLYSTYRENE MOULDING TECHNIQUES APPLIED TO A LIQUID NITROGEN 

DEWAR 

Dickson, E. M-9 and Sheffield, T. B. (Warwick Univ., Coventry, England) 

J. Sci. Xnstrum. 3, No. 6, 466-8 (Jun 1970) 

A method is described in detail for fabricating various shaped 

vessels by expanding polystyrene in a mold. The technique requires 

the construction of a mold in which pre-expanded polystyrene beads 

are expanded to form the vessel. The authors provide sufficiently 

detailed instructions so that either leak-proof (liquid) or nonleakproof vessels can be fabricated. 

The authors have applied these molding techniques to the 

fabrication of a rather large (615 mm long and 230 mm in diameter) 

vessel intended as the liquid nitrogen shield surrounding a conventional 

glass finger Dewar holding liquid helium. 

Included in the paper are detailed suggestions concerning such 

things as the Styrofoam density needed for minimum thermal conductivity, 

the age of the polystyrene beads, etc. 

Important references: 

1. Dillon, J. F., Geschwind, S., Jaccarino, V., and Machalett, A., 

Rev. Sci. Instrum. 30, 559-61 (1959). 

15 
THE DEVELOPMENT OF INSULATION SYSTEMS FOR LARGE CAPACITY DOUBLE 

WALLED METALLIC LNG STORAGE TANKS 

Dodd, P., and Todd, G. (Whessoe, Ltd., Darlington, England) 

Proc. Fourth International Conf. Liquefied Natural Gas (Algiers, 

Algeria, Jun 24-7, 1974), Inst. Gas Technology, Chicago, Ill., 

Session-VI-Paper-8 (1974) 27 pp 

This paper presents the design basis and results of development 

work on the insulation for a 50000 m3 capacity liquefied natural gas 

storage tank. The design used foamed glass as the base insulation 

under the tank. Foamed glass had been used successfully as base 

insulation for smaller tanks, but the base insulation carries the 

weight of the tank and its contents, and a larger tank imposes larger 

loads. An experimental program of strength testing on foamed glass 

was carried out. 

Compressive strength of foamed glass is highly dependent on the 

capping material, used on and between blocks of foamed glass to distribute the load and prevent stress concentrations. Initial ambient 

temperature tests were made with.some 40 capping materials, including 

paper and cardboard, rubber, roofing materials, and fabric-reinforced 

asphalt materials. Ultimate compressive strengths varied widely, over 

a range of nearly 14 to 1, between capping materials. The four best 

capping materials were asphalts, two not reinforced, one reinforced 

with paper, and one with hessian. These materials were used in further 

tests, for ambient temperature creep, large-scale ambient compressive 

strength with eight layers of 100~mm thick blocks, and compressive 

strength of four layers of the blocks when one face was cooled to 77 K. 

The hessian-reinforced material was the only capping material that 

allowed the foamed glass to pass all of the tests. 

The base insulation under the periphery of the tank is loaded with 

the weight of the tank shell and part of the sidewall insulation. For 

this area, a low density aerated concrete was substituted for the foamed 

glass. This concrete had a density of 600 kg/m3, and a thermal 

conductivity of 0.09 W/m-K at a mean temperature of 200 K. Both the 

concrete and the foamed glass had additional advantages of being 

non-combustible and chemically inert in LNG. 

An outline for design of a 100000 m3 tank also considers foamed 

glass for the base insulation, but the authors conclude that the 

strength limits of foamed glass have been utilized and that future 

efforts will be directed toward other systems. 

Important references: 

1. Furber, B. N. and Davidson, J., The Thermal Performance of Porous 

Insulants in a High Pressure Gas Environment, 2nd Conf. Prestressed 

Concrete Reactor and their Thermal Insulation (Brussels, Nov 

18-20, 1969). 

16 
INVESTIGATION OF THE VAPOR PERMEABILITY OF THERMAL INSDLATION 

MATERIALS 

Dudnik, D. M. 

Foreign Technology Div., Wright-Patterson AFB, Ohio, Transl. No. 

FTD-HT-23-541-68, Ott 1969. Transl. of Kholod. Tekh. Tekhnol. No. 4, 

45-9 (1967) 

Water vapor permeabilities of several foamed plastics and thermal 

insulation materials are reported in this Russian paper. The 

measurements were intended as an aid to the refrigeration industry. 

Of the materials tested by one method, 12 are various polyurethane 

foams and 11 are identified by code designations only. A variation of 

this method was used with two polyurethanes, two polystyrene foams, 

foam glass, mineral wool, a foamed urea-formaldehyde resin, and some 

13 unidentified materials. The tests measured loss of water through a 

sample over a period of 5 to 7 months. Temperature was held constant 

at 293 - 303 K. Results are in terms of water vapor penetrating a 

1 m2 area of sample in 1 h, through a 1 m thickness, under a pressure 

of 1 N/m2, reported by the author in units of g=m/N*h. 

The author concludes that all of the foam plastics investigated, 

with the exception of the foamed urea-formaldehyde and an elastic 

polyurethane foam, are good vapor insulators. In general, from the 

tabulated results, all of the polyurethane foams have higher 

permeabilities than the other plastic foams. 

17 
COOL-DOWN OF FOAM INSULATED CRYOGENIC TRANSFER LINES 

Durga Prasad, K. A., Srinivasan, K. and Krishna Murthy, M. V. (Indian 

Inst. of Tech., Madras. Refrigeration and Airconditioning Lab.) 

Cryogenics 14, No. 11, 615-7 (Nov 1974) 

An experimental program was carried out to test the validity of 

an analytical method of estimating cooldown of foam-insulated transfer 

lines. The experiments were conducted with liquid nitrogen flowing 

into a copper tube insulated with polystyrene foam. The commercial 

foam was bonded to the copper with glue and sealed with a film of bitumen 

as moisture barrier. Temperatures at various locations were monitored 

during cooldown and compared to analytical predictions. The experimental 

and analytical results agreed well enough to validate the analytical 

method. 

The authors report a "crashing" noise in the insulation near the 

end of cooldown. They attribute the noise to cell destruction caused 

by the differential thermal contraction of the foam and the metal tube. 

The authors recommend leaving sufficient gap between insulation and tube 

to accommodate the differential thermal contraction, and prevent 

degradation of the foam insulation. 

Important references: 

1. Srinivasan, K., Seshagiri Rao, V. and Krishna Murthy, M. V., Paper 

s-5. ICEC5 (Kyoto, 1974). 

2. Durgaprasad, K. A., M Tech Dissertation, Indian Institute of 

Technology, Madras (1974). 

18 
RIGID OPEN CELL POLYURETHANE FOAM AS A CRYOGENIC MDLTI-LAYER INSULATION 

COMPONENT 

Faddoul, J. R., and Lindquist, C. R. (National Aeronautics and Space 

Administration, Cleveland, Ohio, and Union Carbide Corp., Tonawanda, 

N.Y.) 

Annual Technical Conf. of the Society of the Plastics Industry, 12th 

(Washington, D. C., Ott 16-18, 1967), Paper. National Aeronautics and 

Space Administration, Cleveland, Ohio, Lewis Research Center, Tech. 

Memo. No. NASA TM-X-52332, 32 pp (1967). J. Cellular Plastics 4, No. 3, 

l-10 (Mar 1968) 

This paper describes the application of a rigid open cell urethane 

foam in a self-evacuating multilayer insulation panel concept. The 

insulation consists of aluminized mylar radiation shields separated by 

sheets of the foam, with the multilayer structure sealed inside a 

gas-tight vacuum jacket filled with carbon dioxide. In use, the 

insulation evacuates itself when the carbon dioxide condenses at the 

cold side of the insulation. 

The open cell foam was first selected for development because it 

showed greater compressive strength than closed cell foam, it was easier 

to evacuate, and it had a better surface quality than closed cell foam 

when sliced to the 0.5 mm thickness of the foam spacers in the multilayer 

insulation. The paper shows compressive strengths of bulk samples of 

both open and closed cell foams at RT. Pressure-deflection curves of 

both types of foam at RT and 77 K show a permanent set after the first 

compressive cycle, but no further set in subsequent cycles. Offgassing 

tests show that the open cell foam has a much lower offgassing rate 

than the closed cell foam. A preliminary large scale thermal test used 

panels with 6 radiation shields and 7 foam spacers, applied to a 

calorimeter tank in a shingled configuration to give a total of 18 

radiation shields. After filling the tank with liquid hydrogen, the net 

equilibrium heat flux was 2.5 W/m2, 

W/m2. 

better than the initial goal of 3.2 

Several configurations of foam spacers, with punched holes or 

crisscrossed strips of foam used to reduce contact area, were tested for 

thermal performance. A small reduction in heat flux was achieved, along 

with a secondary advantage of improved gas conductance which allows more 

rapid self-evacuation of the insulation. 

The authors conclude that the open cell foam shows promise, with 

further development to improve spacer configuration and cryopumping 

performance, of achieving the overall program goal of a net heat flux of 

0.9 W/m2 into a liquid hydrogen tank. 

Important references: 

1. Little (Arthur D.) Inc., Rept. No. ADL-67180-00-04, and NASA Rept. 

No. NASA CR-54929 (Jun 1966). 

19 
LOW-TEMPERATURE THERMAL AND MECHANICAL PROPERTIES OF POLYSTYRENE 

AND POLYETHYLENE FOAMS 

Foley, R. J., and Jelinek, F. 3. (Lawrence Livermore Lab., California 

Univ., Livermore, and Battelle Columbus Labs., Ohio) 

International Cryogenic Engineering Conf., Proc. 5th (Kyoto, Japan, 

May 7-10, 1974), K. Mendelssohn, Editor. IPC Science and Technology 

Press, Sussex, England, 439-42 (1974) 

An experimental program was conducted to determine the low 

temperature properties of several polystyrene and polyethylene foams 

of varying densities. These foams were candidate materials to improve 

insulation systems for storage of cryogenic materials. 

Polystyrene foams were fabricated at densities of 50 and 100 kg/m3. 

Thermal contractions and thermal conductivities were measured from 4 K 

to 300 K, and ultimate tensile and compressive strengths were measured 

at 20 K, 77 K, and 300 K. Thermal contractions were independent of 

density. Thermal conductivities showed a density dependence, with the 

denser material results 40% higher at 300 K and 80% higher at 4 K than 

the results on the less dense material. Strengths showed a density and 

temperature dependence, with higher densities and lower temperatures 

leading to greater tensile and compressive strengths. 

Polyethylene foam was chilled and compressed to a density of 

220 kg/m3. The compression at low temperature ruptured previously-closed 

cells, resulting in an open-cell structure. It also resulted in 

anisotropic behavior. Thermal contractions and thermal conductivities 

were measured from 4 K to 300 K, with orientations parallel and 

perpendicular to the direction of compression. Both thermal contraction 

and thermal conductivity were considerably higher in the parallel 

orientation. 

20 
FOAM INSULATION FOR TANKS AND VESSELS 

Foster, C. S. (Upjohn Co., Torrance, Calif.) 

Chem. Eng. Progr. z, No. 8, 55-6 (Aug 1974) 

This rather short article describes the applications and advantages 

of a spray type polyurethane foam insulation material for application to 

large tanks and the like. Prior forms of polyurethane were blocks or 

blankets which resulted in high installation costs ($38 to $48/m2>. The 

use of mechanized, revolving scaffolds permits fast application and 

results in installed costs of $11 to $16/m2. Examples are given of the 

use of spray type polyurethane for heated tanks as well as ammonia 

tanks and LNG tanks. 

Included with the article is a comparison of the K-factor (thermal 

conductivity per unit thickness) of polyurethane with styrene foam, 

glass fiber, cork, asbestos fiber and glass foam. Comparative K-factors 

are given at four temperatures: 116 K, 239 K, 311 K and 367 K. At all 

temperatures polyurethane was a more efficient thermal insulation than 

the other materials. 

21 
RECENT EXPERIMENTAL DATA CONCERNING THE THERMAL CONDUCTIVITY OF 

FIBERGLASS AND POLYSTYRENE FOAM INSULANTS AT LOW TEMPERATURE 

Fournier, D,, and Klarsfeld, S. (Centre de Recherches Industrielles, 

St-Gobain Ind., Rantigny, France) 

Some Thermophysical Properties of Refrigerants and Insulants, Proc. 

International Inst. of Refrigeration Commission Bl (Zurich, Switzerland, 

Sep 27-9, 19731, Bull. Inst. Int. Froid, Annexe 1973-4, 183-8 (1973) 

Thermal conductivity measurements were made on several insulation 

materials, including polystyrene foams of three densities. The foam 

densities were 18.2, 21.3, and 33 kg/m3, and measurements covered mean 

temperatures from 130 K to 300 K. At temperatures below about 230 K, 

the thermal conductivities were practically the same for all three 

densities. Above 230 K, a density effect appeared, with the higher 

density material having a lower thermal conductivity. 

Thermal conductivity curves for polyurethane foam and polyvinyl 

chloride foam, taken from a paper by R. P. Tye, are shown for comparison 

with the polystyrene foams. At cryogenic temperatures, the polystyrene 

had the lowest and the polyurethane had the highest thermal conductivity. 

Important references: 

1. Tye, R. P., Proc. XIII International Congress on Refrigeration I 

(Washington, D.C.), 371-378 (1971). 

22 
NONMONOTONICITY IN SENSITIVITY TEST DATA 

Gayle, J. B. (National Aeronautics and Space Administration, Buntsville, 

Ala., George C. Marshall Space Flight Center) 

Mater. Res. Stand. 5, No. 3, 147-8 (Mar 1966) 

This paper reports an apparently anomalous response in liquid 

oxygen impact sensitivity tests on an insulation system. The insulation 

consists of a mylar-aluminum-mylar laminate adhesively bonded to a 

polyester foam. The results of the tests show a rapid rise in the 

frequency of visible or audible reactions with liquid oxygen as the 

impact energy is increased, to a peak at an impact energy of 2 kg*m. 

As the impact energy is increased further, the reaction frequency 

drops to a minimum at 7 to 8 kg*m, then increases slowly. 

Such anomalous behavior had been reported previously, but was often 

attributed to experimental error. Sufficient tests were made on the 

insulation material to confirm the existence of the irregular response, 

and further tests on the constituents of the insulation showed that the 

behavior was a characteristic of the polyester foam. Tests on other 

foams were planned. 

The mechanism of the anomalous behavior was not known, but the fact 

that such behavior exists in a foam material emphasizes the need for 

caution in interpreting and extrapolating test results. 

23 
EVALUATION OF CRYOGENIC INSULATION MATERIALS AND COMPOSITES FOR USE IN 

NUCLEAR RADIATION ENVIRONMENTS 

General Dynamics/Fort Worth 

General Dynamics/Fort Worth, Tex., Rept. National Aeronautics and Space 

Administration, Rept. No. NASA CR-2162, Contract No. NAS 8-18024, 179 pp 

(Dee 1972) 

The radiation effects tests described in this report are part of a 

long-term evaluation of materials subjected to high levels of nuclear 

radiation at cryogenic temperatures. The materials tests reported here 

include several composite structures, liquid level sensors, fission 

couples, valve-seal materials, explosives, bifuels and thermal insulation. 

The thermal insulation tests were conducted on a 20.4 m3 tank insulated 

with polyurethane foam and complete with vapor barrier. In effect, this 

was a test of the complete assembly. The reactor facility was not 

adequate to irradiate the insulated tank so that the various materials 

were irradiated separately and the tank assembly was thermally cycled. 

The tank was subjected to five fill, drain and warmup cycles, using 

liquid nitrogen. Temperature, boiloff and strain measurements were used 

to aid in the evaluation. 

Test results revealed considerable wrinkling and puckering of the 

outer glass cloth covering of the foam during filling, however, there 

was no evidence, visually or from temperature data that the insulation 

was damaged or that its effectiveness was impaired. The measured boiloff 

rate was 0.08 m3/hr and the effective thermal conductivity was 0.00795 

W/m-K. Data from strain gages mounted internally on the tank wall 

indicated that strains were within expectations during the pressure 

cycles (to 0.186 MPa). Data from the gages mounted on the outer surface 

of the insulation tended to have large variability, generally going from 

large positive values to large negative values during the cycles. This 

is probably a reflection of the considerable movement that obviously 

occurred due to the lowering of the pressure and partial condensation 

of the freon gas in the foam. After completion of the tests, the outer 

coating retained slight creases at the locations of the deeper wrinkles. 

However, there was no visual indication of insulation separation from 

the tank or other deterioration. 

Important references: 

1. General Dynamics/Fort Worth, Tex. Rept. No. FZK-348 (Jun 1968). 

2. General Dynamics/Convair, Fort Worth, Tex. Rept. No. FZK-378 

(Jun 1971). 

24 
FOAMGLAS INSULATION SYSTEMS FOR LOAD-BEARING APPLICATIONS IN THE 

STORAGE OF CRYOGENIC LIQUIDS 

Gerrish, R. W. (Pittsburgh Corning Corp., Pittsburgh, Pa.) 

Cryogenic Engineering Conference and International Cryogenic Materials 

Conference, Joint Meeting (Queens Univ., Kingston, Ontario, Canada, 

Jul 22-5, 1975) 10 pp 

Blocks of foamed glass have been used as load-bearing thermal 

insulation in the base of cryogenic storage tanks for liquid natural gas, 

oxygen, nitrogen, and ethylene. Base insulations use capping or interleaving materials, such as asphalt, felts with asphalt, or asbestos paper, 

between layers of blocks to reduce stress concentrations. Some concern 

was expressed that differential thermal contraction could cause shear 

stresses at the interfaces, and reduce the compressive strength of the 

base insulation at low operating temperatures. This paper presents 

information on strength characteristics of foamed glass blocks at 

ambient and cryogenic temperatures, with standard and experimental capping 

or interleaving materials. 

The foamed glass had a density of about 136 kg/m3. The capping 

materials tested were a hot-melt asphalt, a hessian-reinforced asphalt, 

an asphalt-saturated roofing felt, asbestos paper, and a vermiculite 

aggregate. Compressive strengths were measured on a single layer with 

hot asphalt capping at ambient temperature as control, on a single 

layer with the test capping material at ambient temperature, on a twolayer stack at ambient temperature, and on a two-layer stack with one 

face at 77 K and the other face at ambient temperature. Compressive 

strengths were "yield" strengths for initial failure of some of the 

cells. Generally, ultimate compressive strengths were considerably 

higher. 

The asphalt capping materials produced compressive strengths nearly 

twice as high as those with the felts and asbestos paper, apparently 

because the asphalts filled the top layer of cells and distributed the 

load better. Compressive strength with the asphalts dropped off slightly 

at cryogenic temperatures, as an effect of differential thermal contractions. With the vermiculite experimental capping, the average 

compressive strength was higher at cryogenic temperatures, showing that 

decreasing temperature increases the strength of the glass itself. 

Important references: 

1. Reyntjens, G. P., Univ. of Leuven Report,-PV: R/I 3287/73, Leuven, 

Belgium (1973). 

25 
THERMAL INSULATION SYSTEMS, A SURVEY 

Glaser, P. E., Black, I. A., Lindstrom, R. S., Ruccia, F. E., and 

Wechsler, A. E. 

Little (Arthur D.), Inc., Cambridge, Mass., Rept. National Aeronautics 

and Space Administration, Washington, D. C., Office of Technology 

Utilization, Rept. No. NASA SP-5027, 154 pp (1967) 

This review of thermal insulation includes a chapter on cryogenic 

insulation systems, which contains a section on foam insulation. After 

a discussion of the types, materials, and some advantages and 

disadvantages of foam insulation, some problems in application of foams 

to cryogenic tanks are described. Polyurethane foams on metal tanks 

cracked because of differential thermal expansion, until the problem 

was solved by using glass fibers as reinforcement. Cryopumping of air 

and oxygen enrichment of the condensed liquid presented the possibility 

of fire and explosion hazards. Extensive tests showed that catastrophic 

failure is possible but improbable with well-designed foam insulation. 

The specific foam insulation systems used with the Centaur and Saturn 

S-1C are described briefly. 

The properties of foams are described with the aid of data taken 

from a paper by Miller, et al. (see abstract on page 73) These data 

include tensile and shear strengths of urethane, epoxy, polyurethane 

and polyether foams from 20 K to 394 K; load-compression strengths of 

the same foams at 20 K; snd linear thermal expansions of six urethane 

and epoxy foams from 77 K to 300 K. Other data on thermal conductivity 

and on effects of radiation combined with cryogenic temperatures are in 

references mentioned in the review. 

Another section of the same chapter, on composite insulations, 

describes the use of foams in honeycomb-foam insulations, such as the 

Saturn S-II insulation system, and in constrictive-wrap external 

insulation, such as a system designed for the Centaur. Exterior surface 

bonded foam insulation and an internally insulated fiberglass cryogenic 

storage tank using foam insulation are also described. 

Important references: 

1. Haskins, J. F., and Hertz, J., Advances in Cryogenic Engineering L, 

353-9 (1962). 

2. Black, I. A., et al, NASA Rept. No. NASA CR-54191 (1964). 

3. Heidelberg, L. J., NASA Tech. Note No. NASA TN-D-3068 (1965). 

4. Key, C. F., and Gayle, J. B., NASA Tech. Memo. No. NASA TM-X-53144 

(1964). 

5. North American Aviation, Inc., Rept. NO. SID-63-600-2, NASA Contract 

No. NAS 7-200 (Jul 1964). 

26 
Important references (continued): 

6. Islamoff, I., 

kept. (1965). 

NASA-Marshall Flight Center, Huntsville, Ala.., 

7. ' NASA Rept. No. NASA CR-62110 (1964). 

8. Isenberg, L., National SAMPE Symp. on Materials for Space Vehicle 

Use, 6th. Society of Aerospace Materials and Process Engineers 

(Nov 1962). 

9. Kerlin, E. E., and Smith, E. T., NASA Rept. No. NASA CR-51140 

(1962). 

10. Lockheed Missiles and Space Co., Palo Alto, Calif., Rept. NASA 

Contract No. NAS 8-9500 (Ott 1964). 

11. NASA Tech. Note No. NASA TN-D-2685 (1965). 

27 
EVALUATION OF URETHANE FOAM PANELS 

Glemser, N. N. 

General Dynamics/Astronautics, San Diego, Calif., Rept. No. 

GDA-AN62AMR4087 (Apr 1962) 15 pp 

Rigid polyurethane foams, bonded to tanks as cryogenic external 

insulation, showed a tendency to grow or change dimension over a period 

of time. The growth caused cracking in-the foam and failures in bonds 

to the tank, and loss of insulation effectiveness when atmospheric 

moisture and air could reach the metal tank surface. A test program 

was conducted to measure dimensional changes in foam samples subjected 

to various treatments. 

Twelve freon-blown polyurethane foams were each treated to six 

test conditions, trimmed to standard size panels, and carefully measured 

in all three dimensions. The size measurements were repeated after 

storage at ambient conditions, every week for five to eight weeks. The 

test conditions included unstabilized foam, stabilized foam, stabilized 

foam formed at about 355 K, stabilized foam formed at about 380 K, 

stabilized foam vacuum-formed at about 380 K, and stabilized foam 

vacuum-formed at about 380 K and coated. All of the foams were 

dimensionally unstable and showed erratic but progressive growth with 

storage time. The growth was accelerated by heat and humidity. The 

foams with the lowest average growth rates were also least affected by 

the forming cycles. The author notes that polyurethane foams subjected 

to 100% humidity at 350 K can grow as much as 12% in 4 h. 

The author recommends using foams with the highest heat distortion 

point and the lowest permeability and moisture absorption rate for best 

stability, coating or ,sealing cut surfaces of foam to retard'moisture 

absorptfon, and 'investigating foams other than polyurethanes for use as 

insulation. 

28 
BONDED AND SEALED EXTERNAL INSULATIONS FOR LIQUID-HYDROGEN-FUELED 

ROCKET TANKS DURING ATMOSPHERIC FLIGHT 

Gray, V. H., Gelder, T. F., Cochran, R. P., and Goodykoontz, J. H. 

National Aeronautics and Space Administration, Cleveland, Ohio, Lewis 

Research Center, Tech. Note No. NASA TN-D-476, 51 pp (Ott 1960) 

Several nonmetallic insulation materials capable of being bonded 

onto liquid-hydrogen tanks and sealed against air penetration into the 

insulation, were investigated for use on rockets and spacecraft. 

Emphasis was placed on the problems of insulating high-acceleration rocket 

vehicles which attain high velocities while in the atmosphere. 

Requirements for this application include resistance to aerodynamic loads 

and heat fluxes, and unreinforced plastic foams were excluded from the 

investigation because of their lack of strength at high velocity and 

temperature. However, one of the tested insulation systems used 

polyurethane foam as filler material in the cells of a phenolic 

honeycomb sandwich. 

The insulation materials considered were two composition corkboards, 

foamed corkboard, balsa wood, a phenolic-glass cloth laminate, a 

waterglass laminate, an epoxy mastic with glass spheres and fibers, and 

phenolic honeycomb core with air, potassium titanate-epoxy mastic, dry 

potassium titanate, and two commercial low-density fillers, as well as 

the polyurethane foam filler. Several facing materials, seal materials, 

and bonding materials were also evaluated. Experimental data were 

taken on thermal conductivity, sealability, strength and high-temperature 

resistance. The overall temperature range was from 20 K to 730 K. 

Thermal conductivity of the foam-filled honeycomb was greater than 

that of the foamed corkboard, balsa wood, composition corkboards, and 

the honeycomb filled with the lighter of the two commercial fillers, 

over the temperature range from 90 K to 200 K. The importance of 

sealing against air was shown, by measurements of boiloff from an 

insulated liquid-hydrogen container. The seal over the foam-filled 

honeycomb insulation developed leaks in an early test, and subsequent 

tests showed thermal conductivities rising to 230% of the original 

value as air condensed in the insulation. At high temperatures, 

composition corkboard failed gradually by charring between 600 K and 

730 K, phenolic honeycomb failed at 600 K, but the polyurethane foam 

in the cells melted away at lower temperatures. 

For the intended purpose, the composition corkboards were the best 

insulation. The balsa wood and foam-filled honeycomb might be suitable 

except for marginal strengths at the temperature extremes. Filling the 

cells of the honeycomb with low-density fillers, including polyurethane 

foam, was considered worthwhile, because the increase in weight was 

more than offset by the reduction in thermal conductivity. 

29 
Important references: 

1. National Bureau of Standards Rept. No. 58229 (Feb 1956). 

2. Eppinger, C. E., and Love, W.: J., Advances In Cryogenic Engineering 

4, 123-31 (1959). 

3. Wilkes, G. B., Refrig. Eng. 52, No. 1, 37-42 (Jul 1946). 

4. Rowley, F. B., Jordan, R. C., and Lander, R. M., Refrig. Eng. 50, 

No. 6, 541-4 (Dee 1945). 

30 
AN ANALYTICAL MODEL FOR DETERMINING THE THERMAL CONDUCTIVITY OF 

CLOSED-CELL FOAM INSULATION 

Hammond, M. B., Jr. (North American Rockwell, Downey, Calif. Space 

Div.) 

Advances in Cryogenic Engineering 15, Proc. Cryogenic Engineering Conf. 

(California Univ., Los Angeles, Jun 16-18, 1969), K. D. Timmerhaus, 

Editor. Plenum Press, New York, 332-42 (1970) 

An analytical model of a closed-cell polyurethane foam insulation 

is presented in this paper. The insulation was developed for spray-on 

application to the liquid hydrogen tanks of the Saturn V second stage 

(S-II). The model assumes parallel heat-flow contributions from solid 

conduction in the resin of the cell walls, gas conduction within the 

cells, and radiation from cell to cell. The cells are originally full 

of fluorotrichloromethane blowing agent, but air rapidly diffuses 

through the cell walls. The analytical model predicts the mole fraction 

of air in the cells. 

In the insulation nearest the liquid hydrogen tank, in the cells 

below 50 K, the air is condensed and the dominant heat-flow is by solid 

conduction. Between 50 K and 250 K, gaseous air in the cells is 

dominant, while above 250 K the presence of freon mixed with the air 

reduces the conductivity. At higher temperatures, radiation becomes 

significant. 

This model was one of several described in the paper abstracted 

on page 32. 

Important references: 

1. Hammond, M. B., Advances in Cryogenic Engineering 14 (1969). - 

2. Tye, R. P., Dynatech Report No. 798 (Ref. NASA-23) (22 Jul 1968). 

31 
ANALYTICAL MODELS FOR AIRBORNE-CRYOGENIC-INSULATION THERMAL PERFORMANCE 

Hammond, M. B., Jr. (North American Rockwell Corp., Downey, Calif. 

Space Div.) 

Advances in Cryogenic Engineering 14, Proc. Cryogenic Engineering Conf. 

(Cleveland, Ohio, Aug 19-21, 1968), K. D. Timmerhaus, Editor. Plenum 

Press, New York, 205-12 (1969) 

In the process of designing thermal insulation systems for liquid 

hydrogen tanks of spacecraft, one requirement is to determine the thermal 

conductivity of the system and to establish the influences that might 

change the thermal conductivity in service. This paper summarizes three 

insulation designs, presents analytical predictions of thermal performance, and correlates the predictions with test results. Two of the 

three insulation designs involve foam insulation: a helium-purged 

foam-filled honeycomb external insulation, and a closed-cell foam 

external insulation. 

The helium-purged foam-filled honeycomb used polyurethane foam 

pressed into a glass-phenolic honeycomb core, bonded to the outside of 

the liquid hydrogen tank wall and sealed with a vapor barrier film. 

The insulation was pressurized with helium to prevent air from penetrating into the insulation. The analysis showed that the helium purge 

gas was the predominant contributor to thermal conductivity of this 

system, which was the basic insulation designed for the Saturn-V second 

stage. 

The helium-purged insulation was later replaced on the Saturn-V 

second stage with a closed-cell polyurethane foam sprayed on the tank. 

Analysis of this insulation showed that diffusion of air into the cells 

had great influence on the thermal conductivity. At temperatures below 

255 K, the freon blowing agent was condensed and air in the cells was 

the primary contributor to heat conduction. At higher temperatures, the 

presence of freon mixed with the air tended to reduce gas conduction. 

This mechanism explains the S-shaped character of the thermal conductivity 

versus temperature curve of closed cell polyurethane foam. 

Important references: 

1. Hammond, M. B., Chem. Eng. Progr. Symp. Ser. 62, No. 61, 213 (1966). 

2. Key, C. F. and Gayle, J. B., NASA TM S-43144 (1964). 

3. Glaser, F. E., Black, I. A., Lindstrom, R. S., Ruccia, F. E. and 

Wechsler, A. E., NASA SP-5027, NASA Office of Technological 

Utilization, Washington, D.C. (1967). 

4. Liquid-Hydrogen Tank Insulation Test Report, Space Div. of North 

American Rockwell Corp., SID 64-1157 (Jun 1964). 

5. Hammond, M. B., Paper 68-766, AIM Thermophysics Specialists 

Meeting (Jun 1968). 

32 
THERMAL CONDUCTIVITY OF PLASTIC FOAMS FROM -423 DEGREES TO 75 DEGREES F 

Haskins, J. F., and Hertz, J. (General Dynamics/Astronautics, San 

Diego, Calif.) 

Advances in Cryogenic Engineering 1, Proc. Cryogenic Engineering Conf. 

(Michigan Univ., Ann Arbor, Aug 15-17, 1961), K. D. Timmerhaus, Editor. 

Plenum Press, New York, 353-9 (1962) 

This paper presents a method of measuring thermal conductivities 

of plastic foams from 20 K to room temperature, and gives results of 

measurements on polystyrene foam, polyurethane foam, a polyurethane 

foam-filled honeycomb composite, and a composite of polytetrafluoroethylene sheet and foam. A total of 13 foam materials was tested. 

Of the two polystyrene foams tested, the fire-retardant material 

was the poorer insulator. Among the several polyurethane foams tested, 

thermal conductivities were about the same at 90 K and below, while the 

carbon dioxide-blown (high-temperature resistant) foams had thermal 

conductivities 50% higher than those of the freon-blown foams at 285 K. 

The foam-filled honeycomb was similar to the carbon dioxide-blown foam. 

Two fire-retardant polyurethane foams had nearly identical thermal 

conductivities at 90 K, but thermal conductivity of the molded 

formulation was 25% higher than that of the spray formulation at 285 K, 

with this result attributed to the finer cell structure usually 

obtained with spray foams. 

The authors conclude that base resin and blowing agent have more 

effect on thermal conductivity at RT than at 90 K and below. At 

cryogenic temperatures, gases within the celis are condensed, and cell 

size and uniformity is the major factor contributing to good insulation 

properties. 

Important references: 

1. Stoecker, L. R., Advances in Cryogenic Engineering 2, 273 (1960). 

2. Gray, V. H., and Gelder, T. F., Advances in Cryogenic Engineering 

2, 131 (1960). 

3. Waite, H. J., Advances in Cryogenic Engineering 5, 230 (1960). 

33 
CELLULAR PLASTICS FOR CRYOGENIC INSULATION 

Hayes, R. G. (Upjohn Co., Torrance, Calif. CPR Div.) 

Cryogen. Technol. 8, No. 4, 127-8 (Jul-Aug 1972) 

This paper describes the application of polyurethane foam 

insulation to the piping of a major liquefied natural gas project. The 

Brunei project produces LNG for transport by ship to Japan. The project 

involves nearly 10 km of stainless steel pipe, factory preinsulated with 

a fire-retardant fluorocarbon-blown rigid polyurethane spray foam. Foam 

insulation was chosen rather than vacuum jacketing because of its ease 

of maintenance in the field. 

The foam was applied in the factory to a length of pipe rotating 

at a controlled speed, from the spray equipment moving along the pipe 

length at a controlled speed. A 57cm thickness of foam was applied and 

wrapped with glass fiber reinforced tape, a second 5-cm layer was applied 

and reinforced similarly, then a third foam layer was applied and 

wrapped with a glass reinforced epoxy vapor barrier 3 mm thick. 

Polyurethane foam is seen by the author to be a potential insulation 

of choice for'other LNG projects, including piping and LNG tankers, 

because of its insulating efficiency and its ease of maintenance in 

remote locations. 

34 
DEVELOPMENT OF URETHANE FOAMS FOR LNG INSULATION 

Hayes, R. G. (Upjohn Co., Torrance, Calif. CPR Div.) 

Advances in Cryogenic Engineering 20 (Presented at National Technical 

Meetings during 1973 and 1974), K.D. Timmerhaus, Editor. Plenum 

Press, New York, 338-42 (1975) 

The purpose of the testing program was to find a polyurethane 

foam suitable for use as insulation for liquefied natural gas storage 

or transport containers. Eight polyurethane foam formulations were 

screened by measuring volume change and absorption after immersion in 

LNG. The four formulations least affected were used to make samples 

for mechanical strength testing at 296 K and 111 K. The two best 

formulations were selected for full-scale testing. Immersion in LNG 

for 1000 h caused no apparent loss in physical properties. Thermal 

conductivities were measured between surfaces at 111 K and ambient 

temperature, and thermal expansions between 77 K and 296 K were 

determined. In a test simulating service conditions as external 

insulation, the foams were attached to aluminum plate and cycled between 

77 K and 289 K. One formulation warped, but the other remained nearly 

unchanged through 20 cycles. 

The author concludes that the one best formulation of polyurethane 

foam will be a useful insulation for cryogenic systems down to 77 K, 

and is completely compatible with LNG. 

35 
EVALUATION OF A SUBSCALE INTERNALLY INSULATED FIBER-GLASS PROPELLANT 

TANK FOR LIQUID HYDROGEN 

Heidelberg, L. J. 

National Aeronautics and Space Administration, Cleveland, Ohio, Lewis 

Research Center, Tech. Note No. NASA TN-D-3068, 31 pp (Ott 1965) 

The use of glass fiber reinforced plastics as structural materials 

for liquid hydrogen propellant tanks was investigated. The research 

program had the objective of designing, fabricating, and evaluating the 

thermal and structural performance of a subscale tank. The tank consisted 

of a structural shell of filament-wound fiber-glass, an internal 

insulation system of polyurethane foam enclosed in an aluminum-mylaraluminum laminate vacuum jacket, and an impermeable liner of the same 

laminate. Thermal performance was evaluated by liquid hydrogen boiloff 

tests, and structural performance by pressure-cycling tests with liquid 

hydrogen in the tank. 

Initial leak tests showed that the aluminum-mylar-aluminum laminate 

with adhesive-bonded seams produced leakproof vacuum jackets and liner. 

Thermal shocks with liquid nitrogen and liquid hydrogen did not cause 

leaks. The insulation performed satisfactorily. A large heat leak 

occurred where the laminated vacuum jackets were bonded together and 

provided an aluminum heat path through the insulation. Pressure cycling 

caused a liner failure at a pressure below the design goal. It was felt 

that changes in construction, to allow the liner to expand more, would 

bring the failure pressure closer to the ultimate strength of the 

filament-wound tank structure. 

Important references: 

1. Hanson, M. P., Richards, H. T., and Hickel, R. O., NASA Tech. Note 

No. NASA TN-D-2741 (1965). 

2. Shriver, C. B., NASA Rept. No. NASA CR-127 (1964). 

36 
THE EFFECT OF HEAT FORMING ON THE THERMAL CONDUCTIVITY OF POLYURRTHANE 

FOAMS 

Hertz, J., and Haskins, J. 

General Dynamics/Astronautics, San Diego, Calif., Quarterly Progress 

Rept. No. MRG-303, Contract No. AF33 616 7984, 8 pp (May 1963) 

The insulation for the Centaur forward bulkhead was manufactured 

by heat-forming of polyurethane foam panels. This heat-forming process 

in vacuum at 372 K had the potential of removing the freon 11 blowing 

agent from the foam cells, and allowing air to replace it. This would 

result in an increased thermal conductivity and would introduce a 

source of error in determining heat transfer‘across the forward 

bulkhead. A test program was conducted to evaluate these possibilities. 

Three polyurethane foams were supplied for test in the form of 

panels. The thermal conductivities were measured between 91 K and 296 K, 

the panels were subjected to the heat-forming process, and thermal 

conductivities were measured again. Thermal conductivities after 

heat-forming were 8% lower, 5% lower, and 5% higher than those before 

heat-forming for the three foams. Since experimental error could 

amount to 6%, and the expected changes were toward increases of thermal 

conductivity, it was concluded that the heat-forming caused no 

significant changes. 

37 
GETTING THE MOST FROM RIGID POLYURETHANE FOAMS 

Hilado, C, J, (Union Carbide Chemical Co,, South Charleston, W. Va.) 

Chem. Eng, 74. No. 20, 190+192+194+196 (Sep 1967) 

This article is a brief but thorough review of the application of 

rigid polyurethane foams as insulation over the entire temperature range 

from 5 K to 560 K. Graphs of generalized properties show thermal 

conductivity, tensile, compressive, flexural, and shear strength and 

modulus, and water vapor permeability, as functions of density at 297 K. 

Other graphs show generalized thermal conductivity and tensile and 

compressive strength as functions of temperature for isotropic closed-cell 

foams of 32 kg/m3 density. 

The total temperature range of application is divided into several 

parts. Below about 89 K, the thermal conductivity is very low, and the 

major problem is air condensation and liquid oxygen accumulation, with 

some danger of detonation on impact. Between 89 K and 211 K, the thermal 

conductivity is that of an air-filled foam, and moisture accumulation is 

the major problem. Between 211 K and 395 K, polyurethane foam is more 

effective than most other insulations, but suffers from dimensional 

changes and increased conductivity caused by air and water permeation. 

Low strength and thermal degradation are the major problems at 

temperatures above 395 K. 

The review cites 23 references as sources of more detailed information. 

Important references: 

1. Hilado, C. J., J. Cell. Plast. 3, No. 4, 161-7 (Apr 1967). 

2. Key, C. F., and Riehl, W. A., Repts No. MTP-P and VE-M-63-14 (Dee 

1963). 

3. Key, C, F., NASA Tech. Memo. No. NASA TM-X-53052 (May 1964). 

4. Levy, M. M., J. Cell. Plast. 2 (Jan 1966). 

38 
A METHOD FOR DETERMINING THE EFFECTIVENESS OF THERMAL INSULATION 

SYSTEMS AT LOW TEMPERATURES 

Hilado, C. J. (Union Carbide Corp., South Charleston, W. Va.) 

J. Cell. Plast. 2, No. 2, 110-l (Mar-Apr 1968) 

A method of comparing piping thermal insulation systems is 

presented. The method is specifically designed to compare complete 

systems in an operational configuration rather than comparisons based 

on the thermal conductivity of the insulation alone. The configuration 

uses a one meter length of aluminum tube 7.6 cm in diameter, and 

closed at both ends. The insulation systems are installed complete 

with adhesive and vapor barrier. A test consisted of filling the tube, 

sealing the fill end and measuring, continuously, the weight loss 

from vaporization. This allowed the calculation of average heat 

transfer rates over a three hour period. 

The paper presents results of a comparison of 2.5 cm thickness of 

cellular urethane and 10.1 and 15.2 cm thicknesses of cellular glass 

using both liquid nitrogen and solid carbon dioxide. In all cases the 

urethane performed much better than the cellular glass. 

The heat transfer rates per unit length of pipe differed 

significantly from the values predicted on the basis of available 

thermal conductivity data for the insulation material. The actual 

values were lower than predicted for cellular polyurethane, and higher 

for cellular glass. 

The total time required for a test is 1.5 hour which makes this 

a quick way to arrive at system comparisons. 

Important references: 

1. American Society for Testing and Materials, ASTM Std. 14, 172-9 

(Nov 1967). 

2. Haskins, J. F., ASTM Spec. Tech. Publ. No. 411, 3-12 (Feb 1966). 

3. Karp, G. S., and Lankton, C. S., ASTM Spec. Tech. Publ. No. 411, 

13-24 (Feb 1966). 

4. Black, I. A., Wechsler, A. E., Glaser, P. E., and Fountain, J. A., 

ASTM Spec. Tech. Publ. No. 411, 74-94 (Feb 1966). 

5. Black, I. A., Glaser, P. E., and Perkins, P., ASTM Spec. Tech. 

Publ. No. 411, 52-60 (Feb 1966). 

6. Hollingsworth, M., ASTM Spec. Tech. Publ. No. 411, 43-51 (Feb 1966). 

39 
Important references (continued): 

7. Kinzer, G. R., and Pelanne, C. M., ASTM Spec. Tech. Publ. No. 411, 

110-8 (Feb .1966). 

8. Gibbon, N. C., Matsch, L.'C., and Wang, D. I. J., ASTM Spec. Tech. 

Publ. No. 411, 61-73 (Feb 1966). 

40 
A THERMAL PROTECTION SYSTEM FOR LIQUID HYDROGEN FUEL TANKAGE IN 

HYPERSONIC VEHICLES 

Johnson, C. L. (Lockheed-California Co., Burbank) 

AIAA Thermophysics Specialist Conf. (New Orleans, La., Apr 17-20, 1967), 

Paper No. AIAA-67-297 (1967) 

A composite insulation system for the liquid hydrogen tanks of a 

hypersonic vehicle was designed and tested. In the design concept, the 

liquid hydrogen tank was the primary vehicle structure. A polyurethane 

foam was sprayed onto the outside of the tank and sealed with a glass 

cloth reinforced epoxy layer. Layers of silica fiber batting were wrapped 

over the foam and held in place with a stainless steel screen. Thin-walled 

inconel 718 tubing standoff posts were attached to the tank wall, and 

extended through the insulation to support inconel 718 heat shield shingles. 

The polyurethane foam provided cryogenic insulation, while the silica 

fiber insulation kept the high temperatures generated by aerodynamic 

heating from reaching the surface of the foam. 

The insulation was applied to a calorimeter, and tested with liquid 

nitrogen or liquid hydrogen in the calorimeter and heat lamps at the outer 

surface. Heat flux values were satisfactory in the liquid nitrogen tests, 

but doubled with liquid hydrogen in the calorimeter. Calculations showed 

that the difference could be attributed to a relatively small amount of 

air condensing on the tank surface. Disassembly of the insulation 

revealed extensive thermal stress cracking of the polyurethane foam and 

its vapor barrier, which allowed air penetration and condensation. 

Modifications to improve the insulation system included changing from 

spray-on foam to panels of the glass fiber reinforced polyurethane foam 

developed for the Saturn S-IV stage. The reinforcement was to strengthen 

the foam while application in panels left space for thermal stress relief. 

The vapor barrier was changed to a more flexible polyester cloth 

reinforced epoxy layer. The report states that the initial results 

demonstrated the practicability of the insulation system, and that the 

modifications should produce a system with acceptably low thermal 

conductivity. 

41 
INSULATION SYSTEMS FOR CRYOGENIC STAGES 

Jonke, R. J. 

Rev. Sci. Tech. CECLES/CERS 3, No. 1, 17-48 (1971) 

This paper is a review of experimental work on thermal 

insulation systems for cryogenic propellant tanks, summarizing those 

systems which were candidates for the ELDO Europa III upper stage but 

were not finally selected for use. The systems covered are polyphenylene 

oxide (PPO) foam (described here as "polypropylene oxide foam"), 

polyvinyl chloride (PVC) foam, polyurethane foam, and polymethacrylimide 

foam. Another PVC foam was selected for the application, and is 

described elsewhere (see the paper abstracted on page 74). 

The PPO foam is an anisotropic open-cell foam, with the cells 

oriented in a single direction. It was proposed as an external 

insulation, with the cells closed at one end by bonding to the tank 

wall, and at the other by a vapor barrier film and a protective glass 

cloth reinforced epoxy coating. Linear thermal expansion of the foam, 

both parallel and perpendicular to fiber orientation, is shown from 

20 K to 300 K; tensile properties in both orientations are shown from 

20 K to 400 K. Thermal conductivity is given as 0.024 W/m-K at a mean 

temperature of 166 K, and 0.009 W/m*K at 138 K. The foam was applied 

to a test tank, and during cooldown with liquid nitrogen, the vapor 

barrier delaminated from the foam. A prestressed constrictive wrap 

solved the problem, but a better bond might make prestressing 

unnecessary. 

The polyurethane and PVC foams were studied in another program. 

Data are shown on thermal conductivities of the foams at temperatures 

from 20 K to 320 K. For the same density, the polyurethane shows 

slightly lower thermal conductivity than the PVC. The typical 

S-shaped curves of freon-blown foams are evident in the data. Thermal 

contractions, tensile strengths, and ultimate elongations of the foams 

are compared from 20 K or lower to 300 K or higher. A polyurethane 

foam reinforced with glass fibers was included in the comparisons. 

Small scale tests on tanks with liquid hydrogen also provided data. 

It was concluded that thermal performance of the foams was approximately 

equal, but higher elasticity at low temperature made the polyurethane 

a better choice than the PVC, and the fiber-reinforced polyurethane 

better than the plain foam. 

In another program, a polymethacrylimide foam was evaluated, 

and thermoforming was investigated as a means of shaping this foam 

along with polyurethane and PVC foams. The polymethacrylimide required 

closely controlled high temperature for thermoforming, and was highly 

permeable to gas, making it unsuitable for insulation. Thermoforming 

was highly successful with PVC, while polyurethane foam tended to crack. 

42 
THERMAL INSULATION IN CRYOGENIC ENGINEERING 

Kaganer, M. G. 

Israel Program for Scientific Translations, Jerusalem, 1969. Transl. of 

Teplovaya Izolyatsiya v Tekhnike Nizkikh Temperatur, Izdatelstvo 

Mashinostroenie, Moscow, 226 pp (1966) 

This Russian book on thermal insulation only briefly considers 

foam insulation. Evacuated powder, evacuated fiber, high-vacuum, and 

evacuated multilayer insulations receive much greater coverage. 

The cellular materials considered are cork, expanded ebonite, a 

urea-formaldehyde foam, polystyrene foam, polyurethane foam, and foam 

glass. The properties of these materials are presented as general 

graphs or tabulations of thermal conductivity, specific heat, linear 

thermal expansion, and moisture permeability, in a general temperature 

range from 175 K to 300 or 325 K. The data are taken from the 

literature, and the literature should provide better sources of 

information on these properties. 

Important references: 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

Dudnik, D. M., and Meltser, L. Z., Trudy OTIPKhP, lo, 75-86, 

Odessa (1961). 

Cammerer, W. F., Kaeltetechnik 12, No. 4, 107-10 (1960). 

Cooper, A., International Congress of Refrigeration, Proc. X, L, 

251-60 (1961). 

Haskins, J. F., and Hertz, J., Advances in Cryogenic Engineering 1, 

353-9 (1962). 

Battle, B., and Laine, P., Suppl. Bull. Inst. Intern. du Froid, 

No. 4, 267-73, Annexe (1958). 

Miller, R. N., Bailey, C. D., Beall, R. T., and Freeman, S. M., 

Advances in Cryogenic Engineering 8, 417-24 (1963). 

Vahl, L., International Congress of Refrigeration, Proc. X, &, 

267-73 (1961). 

43 
MEASURED EFFECTS OF THE VARIOUS COMBINATIONS OF NUCLEAR RADIATION, 

VACUUM AND CRYOTEMPERATURES ON ENGINEERING MATERIALS 

Kerlin, E. E., and Smith, E. T. 

General Dynamics/Fort Worth, Tex., Nuclear Aerospace Research Facility, 

Rept. No. FZK-290. National Aeronautics and Space Administration, Rept. 

No. NASA CR-77772, Contract No. NAS 8-2450, 520 pp (Jul 1966) 

This report summarizes the work done during the last two years of 

a five year contract with NASA to measure the effects (singly and in 

combination) of nuclear radiation, vacuum and cryogenic temperatures on 

structural adhesives, structural laminates, potting compounds, electrical 

insulation, thermal insulation, dielectrics, thermal control coatings, 

seals, sealants and lubricants. The testing was done for the purpose of 

establishing guidelines in the selection of materials for the Space 

Nuclear Propulsion System (NERVA). Tests were conducted in air at 

ambient temperature, in liquid nitrogen, at 77 K and in liquid hydrogen 

at 20 K. The tests included mechanical and tensile properties 

(measured at test temperature and in test environment), lubricating 

properties, electrical properties and thermal conductivity for the foam 

insulation. 

The foam thermal insulations tested are: polyurethane (polyetherpolyester rigid foam), polyurethane (carbon dioxide blown rigid foam), 

urethane (polyester flexible foam), epoxy (rigid, spray foamed), 

polyurethane (polyether, rigid, halocarbon blown) and polystyrene. 

Measurements were made in the radiation environment in vacuum and air 

at ambient temperature and in liquid nitrogen and liquid hydrogen. The 

results indicate that radiation levels to 5 x lo6 J/kg had no or 

insignificant effects on the thermal conductivity of all specimens 

tested. With regard to the compression test, not all of the foam 

materials have data reported because experimental difficulties resulted 

in a small number of reliable results. Because of these factors, the 

data presented are considered to be of marginal reliability. The 

authors did conclude, however, that for most foams the exposure to both 

vacuum and radiation reduced significantly the compressive strength. 

Important references: 

1. Kerlin, E. E., General Dynamics/Fort Worth, Tex. Rept. No. FZK-161-1 

(Jan 1963). 

2. Kerlin, E. E., and Smith, E. T., General Dynamics/Fort Worth, Tex. 

Rept. No. FZK-188-2 (May 1964). 

44 
COMPATIBILITY OF MATERIALS WITH LIQUID OXYGEN, III. 

Key, C. F. 

National Aeronautics and Space Administration, Huntsville, Ala., George 

C. Marshall Space Flight Center, Tech. Memo. No. TM-X-53533, 54 pp 

(Nov 1966) 

This report summarizes in tabular form the results of the 

compatibility testing of a large number of materials with liquid oxygen. 

The classes of materials included are lubricants, sealants and threading 

compounds, thermal and electrical insulation, plastics, elastomers, 

adhesives, gaskets and packings, metals and alloys, solders, chemicals, 

solvents, paints and leak check compounds. The tests were conducted 

with the Army Ballistic Missile Agency (ABMA), LOX impact tester used 

according to MSFC-SPEC-106B. Two ratings 'are given, one for the 

individual sample or lot evaluated and the other for the material in 

general. The ratings are Satisfactory (S), Satisfactory, if each jar 

of sample is individually tested and found acceptable (J), Satisfactory 

if each batch is tested and found acceptable (BT), Insufficient test 

experience to rate sample adequately (I) and Unsatisfactory (U). 

The foam insulation tested and the results are: H-Foam (batch 

rating - S, material rating - I), RL Foam (batch and material rating - 

(U), Styrofoam (batch and material rating - U). As would be expected 

foam insulations are not particularly compatible with liquid oxygen. 

No results are given for polyurethane foam. 

Important references: 

1. Lucas, W. R., and Riehl, W. A., ASTM Bulletin No. 244, 29-34 (Feb 

1960). 

2. Key, C. F., and Riehl, W. A., NASA Tech Memo. No. NASA TM-X-985 

(Aug 1964). 

3. Key, C. F., NASA Tech Memo. No. NASA TM-X-53052 (May 1964). 

45 
EFFECT OF LIQUID NITROGEN DILUTION ON LOX IMPACT SENSITIVITY 

Key, C.-F,., and Gayle, J. B. (National Aeronautics and Space 

Administration, Huntsville, Ala., George C. Marshall Space Flight 

Center) 

J. Spacecraft Rockets 3, No. 2, 274-6 (Feb 1966) 

This paper-summarizes an experimental investigation on the impact 

sensitivities of a number of materials in liquid nitrogen-oxygen mixtures. 

Earlier work had shown that organic materials were impact-sensitive in 

liquid oxygen, and that there was a chance of a catastrophic reaction if 

damaged insulation on a liquid hydrogen tank was impacted during ground 

hold, because air could condense in the insulation and become enriched in 

oxygen by fractionation processes. The liquid nitrogen-oxygen mixtures 

in this work represented liquid air and oxygen-enriched liquid air, 

ranging from 20% to 100% oxygen. 

The materials tested included a polyurethane foam insulation, an 

epoxy foam, a foam of 132 kg/m3 density identified by its commercial 

designation, and a foam-filled 4 henolic honeycomb. All of the foams were 

completely insensitive in 50% oxygen mixtures at impact energies up to 

10 kg-m. Threshold impact energies dropped to 1 to 2 kg-m in 100% liquid 

oxygen. The foam-filled honeycomb was insensitive in 20% oxygen mixture 

(liquid air) up to 10 kg-m, but the threshold impact energy was only 3 

kg-m in 30% oxygen mixture, and less than 1 kg-m in 100% liquid oxygen. 

While none of the materials reacted in liquid air, and the foams remained 

insensitive with considerable oxygen enrichment, the foam-filled honeycomb 

became impact sensitive in only slightly oxygen-enriched liquid air. 

This paper summarizes the work reported in an earlier Technical 

Memorandum (below and in Secondary Documents). This summary contains the 

experimental results, but not all of the details on test methods. 

Important references: 

1. Key, C. F., and Gayle, 3. Bt, NASA Tech. Memo. No. NASA TM-X-53144 

(Ott 1964). 

2. Key, C. F., and Gayle, J. Bt, NASA Tech. Memo. No. NASA TM-X-53208 

(Feb 1965). 

46 
PRELIMINARY INVESTIGATION OF FIRE AND EXPLOSION HAZARDS ASSOCIATED 

WITH S-II INSULATION 

Key, C. F., and Gayle, J. B. 

National Aeronautics and Space Administration, Huntsville, Ala., George 

C. Marshall Space Flight Center, Tech. Memo. No. NASA TM-X-53144 (Ott 1974) 

Insulation developed for the S-II vehicle was polyurethane foam 

bonded to the aluminum tank surface with an epoxy adhesive, reinforced 

with a phenolic-fiberglass honeycomb, and covered with an essentially 

impermeable vapor barrier. With the tank wall at liquid hydrogen 

temperature, any leakage in the vapor barrier was expected to allow air 

to condense inside the insulation. The condensate could contain 

appreciably more than 20% liquid oxygen, and could create a fire or 

explosion hazard in the event of an impact. A series of tests was 

conducted to evaluate this hazard. 

Standard LOX impact tests on the composite insulation and its 

constituents showed a high sensitivity. Since condensate in the 

insulation would not be pure LOX, the tests were repeated in LOX/LN2 

mixtures. Decreased oxygen concentration resulted in decreased sensitivity, 

down to zero sensitivity in 20% LOX mixture. 

In a more realistic test configuration, the insulation was applied 

to flat aluminum plates and the vapor barrier was removed or punctured. 

Samples were immersed in LOX/LN2 mixtures for about 15 min, removed and 

allowed to stand for varying lengths of time, and impacted by about 125 

0.013 g lead shot fired from a .22 calibre rifle. With the rifle located 

less than 1.3 m from the sample, reactions occurred consistently when LOX 

concentration in the mixture exceeded about 20%. Reaction frequency 

increased with increasing warm-up time after immersion in mixtures 

containing 20 to 30% LOX, consistent with the expectation that condensate 

becomes enriched with LOX during warm-up. Similar results were obtained 

with .177 calibre copper coated pellets fired from an air gun and with 

insulation applied to the curved surface of a test tank. 

To achieve a more realistic simulation by eliminating direct 

immersion in LOX/LN2 mixtures, the insulation was applied to liquid 

hydrogen tanks and the vapor barrier was punctured to allow natural 

cryopumping. After maintaining the liquid hydrogen for 4 to 12 h, the 

hydrogen supply was cut off and the test tank impacted with bird shot 

fired from a 22 calibre rifle from a distance of 45 to 70 cm from the 

tank. Sustained burning occurred 10 min and 8 min after liquid hydrogen 

shutoff in two of the tests. The reaction after 10 min warm-up was more 

violent than that after 8 min warm-up, indicating either a larger quantity 

or more oxygen-richness of the condensate. 

47 
The authors conclude that there is a small but finite probability 

of catastrophic reaction if damaged S-II insulation is subjected to 

impact, shock, fire, or other stimuli during or after liquid hydrogen 

hold. The danger is greater during warm-up. This small hazard must 

be baianced against other factors to determine whether modification 

is required. 

48 
HEAT TRANSFER IN EXPANDED MATERIALS (uBER DEN WARMETRANSPORT IN 

SCHAUMSTOFFEN) 

Koglin, B. (ERNO Raumfahrttechnik GmbH, Bremen, West Germany) 

Kaltetechnik-Klimatisierung 21, No. 5, 122-5 (May 1969) 

An experimental program was conducted to measure heat transmission 

in plastic foam insulation materials, and to establish the effects of 

variations in foam properties on the heat transfer mechanisms. A 

polyurethane foam of 40 kg/m 3 density and a polystyrene foam of 15 kg/m3 

density were the materials measured, and thermal conductivities were 

determined in the temperature range between 20 K and 350 K. 

The polyurethane foam thermal conductivity showed characteristics 

typical of halocarbon-blown foams, with a maximum and a minimum in the 

curve between 230 K and 280 K, near the condensation temperature of the 

blowing agent, where variations in the vapor pressure cause the thermal 

conductivity to change. The thermal conductivity also showed an abrupt 

drop as the temperature decreased below about 50 K, a region where air 

in the cells of the foam has mostly condensed. 

The polystyrene foam was made with air as the blowing agent. Its 

thermal conductivity showed a continuous increase with increasing 

temperature from 110 K to 330 K. Other measurements at a temperature of 

308 K established the effects on thermal conductivity of air pressure 

in the cells, of temperature difference across the sample, of sample 

thickness, and of emissivity of the foam surface. These results along 

with simple models of heat transfer mechanisms were used to show the 

effects due to solid conduction, gas conduction, and radiation heat 

transfer. Convective heat transfer was negligible in the tests. The 

combined effects led to the conclusion that, for foam of a specific 

density, there is an optimum cell size for minimum thermal conductivity. 

Important references: 

1. DIN 52612, Beuth-Vertrieb, Berlin-KGln. 

2. Koglin, B., Diss. TU Berlin (1967). 

3. Haskins, J. F. and Hertz, J., Adv. Cryog. Eng. 1, 353 (1962). 

4. Tariel, H. M., Boissin, J. C. and Segel, M. P., Adv. Cryog. Eng. 

12, 274 (1967). 

5. Zehendner, H., Kgltetechn. 2, No. 1, 2 (1967). 

49 
MECHANICAL PROPERTIES OF FOAM MATERIALS IN THE TEMPERATURE RANGE OF 

300'K TO 20PK (MECHANISCHE EIGENSCHAFTEN VON SCHADMSTOFFEN IM 

TEMPERATURBEREICH VON 300°K BIS 20'K) 

Kreft, H., and Wagner, D, (ERNO-Raumfahrttechnik GmbH, Bremen, West 

Germany) 

Kaltetechnik-Klimatisierung 2.& No. 9, 258-65 (Sep 1969) 

An insulation consisting of foam bonded to the wall of a liquid 

hydrogen or liquid oxygen tank, and sealed with a vapor barrier bonded 

to the foam, was considered for upper rocket stages. Such insulation 

must withstand loads imposed by thermal contraction, external air 

pressure or vacuum, tank pressurization, and acceleration and air friction 

during launch. The mechanical properties of the materials must be known 

for des,ign of the insulation system. Two foams, a polyurethane and a 

polyvinyl chloride, were tested along with four adhesives and an 

aluminized mylar vapor barrier. 

Standard bar samples of both foams were tested for tensile strength 

at 20 K, 77 K, and 293 K, and for elongation and modulus at 77 K and 

293 K. Flatwise tensile strengths of samples adhesively bonded between 

metal blocks were measured at 77 K and 293 K. Compressive strengths at 

77 K and 293 K, tensile-shear strengths at 20 K, 77 K, and 293 K, and 

T-peel shear strengths at 77 K and 293 K were also measured for both 

foams. At all temperatures, the polyurethane foam had lower strengths 

and tensile modulus, and higher elongation, than the PVC foam. The PVC 

showed considerable sensitivity to temperature, with decreasing tensile 

and shear strengths and increasing compressive strength at lower 

temperatures. The polyurethane has the same general trends except that 

tensile strength of the bar samples increased at lower temperatures. 

The authors conclude that the polyurethane has good mechanical 

properties at all temperatures being considered. The polyvinyl chloride 

foam has relatively high strength at room temperature and is brittle at 

lower temperatures. 

Important references: 

1. Kreft, H., Technischer Bericht RT/P-l/1/66, ERNO-Raumfahrttechnik 

GmbH, Bremen (Jan 1966). 

2. Kreft, H., Abschlussbericht TB RT/Zj1/69, ERNO-Raumfahrttechnik 

GmbH, Bremen (Apr 1969). 

3. Hollstein, W., Technischer Bericht 1204, Hamburger Flugzeugbau 

GmbH, Hamburg (Mar 1968). 

4. Wagner, D., Technischer Bericht RT/S-86/68, ERNO-Raumfahrttechnik 

GmbH, Bremen (Jun 1968). 

5. Wagner, D., Technischer Bericht RT/S-148/68, ERNO-Raumfahrttechnik 

GmbH, Bremen (Ott 1968). 

50 
CRYOGENIC PROPERTIES 

Landrock, A. H. (Plastics Technical Evaluation Center, Picatinny 

Arsenal, Dover, N. J.) 

Encyclopedia of Polymer Science and Technology Vol 4. John Wiley and 

Sons, Inc., New York, 415-49 (1966) 

The article includes a summary of cryogenic foam insulation, 

reviewing some data from the literature. Data are taken from Miller, 

et al. (see the paper abstracted on page 73), on tensile, shear, and 

compressive strengths of rigid.polyester-polyurethane, epoxy, semirigid 

polyurethane, and flexible polyether foams, between 20 K and 298 K. 

Other data from Bailey (included in the paper abstracted on page 73) 

show linear thermal expansions of six foams between 78 K and 295 K. 

Tabulations from Kropschot's papers (listed under Secondary Documents) 

demonstrate the high thermal conductivities of foams as compared with 

evacuated powder and multilayer insulations. The discussion on 

cryogenic foam insulation cites 14 references. 

Important references: 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

General Dynamics/Astronautics, San Diego, Calif., Rept. No. MRG-162 

(Jun 1960). 

Hertz, J., and Haskins, J., General Dynamics/Astronautics, San 

Diego, Calif., Rept. No. MRG-202, 10 pp (Dee 1960). 

Haskins, J. F., and Hertz, J., General Dynamics/Astronautics, San 

Diego, Calif., Rept. No. MRG-242, 21 pp (Jul 1961). 

Hertz, J., and Haskins, J., General Dynamics/Astronautics, San 

Diego, Calif., Rept. No. MRG-303, 8 pp (Mar 1962). 

Isenberg, L., and Johnson, C. L., Materials Compatibility and 

Contamination Control Process, Proc. National Symp., 4th (Hollywood, 

Calif., Nov 13-15, 1962). Sot. Aerospace Mater. Process Engrs. 

(SAMPE), 445-79 (1962). 

Campbell, M. D., Haskins, J. F., Hertz, J., Jones, H., and Percy, 

J. L., General Dynamics/Astronautics, San Diego, Calif., Rept. No. 

MRG-312, 75 pp (Apr 1962). 

Doherty, D. J., Hurd, R., and Lester, G. R., Chem. Ind. (London), 

1340-53 (1962). 

Griffin, J. D., and Skochdopole, R. E., Chapter 15 in Engineering 

Design for Plastics, E. Baer, Editor. Reinhold Publishing Corp., 

New York (1964). 

51 
POLYURETHANE FOAMS. TECHNOLOGY, PROPERTIES AND APPLICATIONS 

Landrock, A. H. 

Plastics Technical Evaluation Center, Dover, N. J., PLASTEC Rept. 

No. 37, 256 pp (Jan 1969) 

This report discusses the state of the art of polyurethane foams as 

it existed in 1969. While much of the report is taken up with the 

chemistry and‘production of polyurethane foams, and with properties and 

applications outside the cryogenic temperature range, the chapter on 

Foam Properties includes sections on low-temperature effects, cryogenic 

effects, and liquid oxygen compatibility. The chapter on Military and 

Space Applications has a section on thermal insulation. 

The low-temperature effects are mostly concerned with temperatures 

between room temperature and about 200 K. The section on cryogenic 

effects cites some 17 papers and reports from the literature. Specific 

data used in the discussion include a table of compressive strength, 

modulus, and deflection of three densities of foams, taken from Buxton, 

Hanson, and Fernandez (cited under Secondary Documents); graphs of 

tensile, shear, and compressive strengths of rigid, semi-rigid, and 

flexible foams, taken from Miller, Bailey, Beall, and Freeman (abstracted 

on page 73); and graphs of linear thermal expansions of two foams, taken 

from Bailey (cited under Secondary Documents) and from Miller, Bailey, 

Freeman, Beall, and Coxe (cited under Secondary Documents). A section 

on radiation effects on polyurethane foams also discusses combinations 

of radiation with exposure to vacuum and cryogenic temperatures. The 

section on liquid oxygen compatibility states that most polyurethanes 

are not LOX compatible, but that halogenated polyurethanes and those 

prepared from hexafluoropentanediol are compatible with LOX. The section 

on the application of polyurethane foams as insulation cites 8 references 

which deal specifically with cryogenic temperatures. 

This report looks in depth at polyurethane foams and provides some 

comparisons with other foams as well. The bibliography of over 700 

references from the literature aids in finding more detailed information. 

Important references: 

1. Haskins, J. F., and Hertz, J., General Dynamics/Astronautics, San 

Diego, Calif;, Rept. No. MRG-242 (Jul 1961). 

2. Dearing, D. L., Advances in Cryogenic Engineering l& 89-97 (1966). 

3. Johnson, P. M., Lewis, J, H., and Self, M. R., General Dynamics/Fort 

Worth, Rept. No. FZK-195 (Dee 1964). 

4. Hauck, J. E., Mater. Des. Eng. 63, No. 5, 87-102 (May 1966). 

52 
Important references (continued): 

5. Kropschot, R. H., Applied Cryogenic Engineering, Chapter 6, edited 

by R. W. Vance and W. M. Duke. Wiley, New York (1962). 

6. Landrock, A. H., Encyclopedia of Polymer Science and Technology 5. 

Wiley-Interscience, New York, 415-99 (1966). 

53 
PROPERTIES OF PLASTICS AND RELATED MATERIALS AT CRYOGENIC TEMPERATURES 

Landrock, .A. H. 

Plastics Technical Evaluation Center, Picatinny Arsenal, Dover, N. J., 

Plastec Rept. No. 20, 253 pp (Jul 1965) 

This extensive compilation includes a section on foam cryogenic 

insulation, with a discussion summarizing data or conclusions from 22 

references. The index lists over 64 references under the "foam" 

categories. 

Graphical and tabulated data used in the discussion include data on 

the tensile, shear, and load-compression strengths of five foams at 

temperatures between 20 K and 395 K, taken from a paper by R. N. Miller, 

et al. (see abstract on page 73). Data on load-compression strengths 

of six foams at 20 K, 77 K, and 296 K were taken from another paper by 

R. N. Miller, et al. (cited under Secondary Documents). Linear thermal 

expansion of six foams between 78 K and 300 K were taken from a report 

by C. D. Bailey (cited under Secondary Documents). Thermal conductivities 

of polystyrene and polyurethane foams came from a 1961 report by J. F. 

Haskins and J. Hertz (cited under Secondary Documents). Other data on 

compressive strengths of polyurethane and polystyrene foams between 20 K 

and 300 K were taken from a report by M. D. Campbell, et al., and a 

journal article by D. J. Doherty, et al. (both cited under Secondary 

Documents). Tensile and shear moduli and anisotropy of the moduli, 

between 20 K and 300 K were taken from a book chapter by J. D. Griffin 

and R. E. Skochdopole (cited under Secondary Documents). Thermal 

conductivities of several foam materials at temperatures from 20 K to 

300 K, and comparisons with vacuum powder and multilayer insulations, 

came from a chapter on Low-Temperature Insulation, by R. H. Kropschot, in 

the book Applied Cryogenic Engineering (cited under Secondary Documents). 

This report on plastics at cryogenic temperatures is very 

comprehensive in the area of properties of materials. It represents 

the state of the art at the time of its publication, in 1965. Applications 

of materials were not covered in the report. Despite its age, the report 

remains a valuable source of information. 

Important references: 

1. Allen, R. J., and Van Paassen, H. L. L., Advances in Cryogenic 

Engineering 5, 548-54 (1961). 

2. Hertz, J., and Haskins, J., General Dynamics/Astronautics, San Diego, 

Calif., Rept. No. MRG-303, Contract No. AF 33(616)-7984, 8 pp (Mar 

1962). 

3. Isenberg, L., and Johnson, C. L., Proc. National SAMPE Symp., 4th 

(Hollywood, Calif., Nov 13-15, 1962), 445-79 (1962). 

54 
Important references (continued): 

4. Stoeker, L. R., Advances in Cryogenic Engineering 5, 273-81 (1960). 

5. Vahl, L., Progress in Refrigeration Science and Technology, Vol. 1, 

Proc. International Congress of Refrigeration, 10th (Copenhagen, 

Denmark, 1959). Pergamon Press, New York, 267-73 (1960). 

6. Eyles, A. G., Advances in Cryogenic Engineering 10, 224-32 (1965). 

55 
DEVELOPMENT OF ADVANCED MATERIALS COMPOSITES FOR USE AS INSULATION 

FOR LH2 TANKS 

Lemons, C. R., and Salmassy, 0. K. 

McDonnell-Douglas Astronautics Co., Huntington Beach, Calif., Research 

and Engineering Dept., Rept. No. MIX-G4492. National Aeronautics and 

Space Administration Rept. No. NASA CR-124388, Contract No. NAS 8-25973 

(Apr 1973) 101 pp 

This report is on a continuation of the work described in the 

report abstracted on page 58. The earlier work had developed and 

optimized an internal insulation system, consisting of 3D foam (a 

polyurethane foam reinforced with glass fibers oriented in three mutually 

perpendicular directions) bonded to the tank wall with epoxy adhesive 

and lined with a glass-cloth-reinforced epoxy layer. This system was 

applied to a one-meter dome and subjected to seven simulated mission 

cycles consisting of liquid hydrogen tanking, pressurization, and 

reentry heating to 450 K. The insulation withstood the simulated 

mission cycles with no apparent damage or degradation. 

Another one-meter dome was insulated with a similar composite 

system, but using simpler butt joints between 3D foam panels. A 

syntactic foam material, epoxy resin filled with phenolic microballoons 

and glass fibers, was used as a gap filler in the butt joints. Only 

about half as much adhesive was used in bonding the foam to the dome. 

This modified insulation also withstood seven simulated mission cycles 

without significant damage or degradation, while reducing insulation 

weight and cost. 

The authors conclude that the original structural and thermal 

objectives of the program were achieved, and that weight and cost 

reduction objectives were exceeded. 

An appendix contains material and process specifications for the 

polyurethane foam, for the yarn-reinforced polyurethane foam, for the 

epoxy adhesive, and for installation of the internal insulation system. 

Important references: 

1. Salmassy, O., et al., MDAC Quarterly Summary Report MDC-G2525, 

Contract NAS 8-25973 (Sep 1971). 

2. Lemons, C. R., Watts, C. R. and Salmassy, 0. K., Summary Report 

Phase II MDC-G3677, Contract NAS 8-25973 (Jun 1972). 

56 
ADVANCES IN CRYOGENIC FOAM INSULATION 

Lemons, C. R., Salmassy, 0. K., and Watts, C. R. 

McDonnell Douglas Astronautics Co., Huntington Beach, Calif., Paper No. 

MDAC WD 1756, Presented at Society of Aerospace Material and Process 

Engineers National Tech. Conf. on Space Shuttle Materials (Huntsville, 

Ala., Ott 5-7, 1971), Contract No. NAS 8-25973 (Sep 1971) 12 pp 

An internal insulation was required for the liquid hydrogen tanks 

of both the booster and orbiter of the Space Shuttle. Prime considerations 

were reusability and heat resistance to survive reentry with wall 

temperatures up to 450 K. A thread-reinforced polyurethane foam internal 

insulation had proven reliable in the Saturn S-IV and S-IVB stages, and 

a program was conducted to modify this insulation to satisfy the 

requirements for the Space Shuttle. 

The insulation was a polyurethane foam reinforced with glass fiber 

threads oriented in three mutually perpendicular directions. This 3D 

foam underwent expansion followed by shrinking when exposed to a 

temperature of 450 K. It could be stabilized by preheating to take care 

of the dimensional changes before applying the foam to the tank. A new 

formulation of poiyurethane proved superior in having better stability 

after heating, lower density, and no cracking problem. Thermal 

conductivities of the new foam were measured in vacuum and helium 

environments at temperatures from 134 K to 325 K and found equivalent 

to the older foam. The insulation was applied to an aluminum dome by 

bonding with an epoxy adhesive, then sealed with a liner of glass-cloth 

reinforced polyurethane. The dome was subjected to simulated Space 

Shuttle service by cooling with liquid hydrogen, then heating to 450 K. 

The insulation survived testing with no apparent serious degradation. 

The authors concluded that the insulation system was shown to be ready 

for scale-up to large tank insulation. 

57 
DEVELOPMENT OF ADVANCED MATERIALS FOR USE AS INSULATIDNS FOR LH2 

TANKS 

Lemons, C. R., Watts, C. R., and Salmassy, 0. K. 

McDonnell-Douglas Astronautics Co., Huntington Beach, Calif., 

Summary Rept. No. MDC-G3677, Jul 1971 - Apr 1972. National 

Aeronautics and Space Administration Rept. No. NASA CR-123928, 

Contract No. NAS 8-25973, 176 pp (Jun 1972) 

The experimental program had the objective of developing reliable 

composite materials for a--minimum weight internal insulation for the 

Space Shuttle liquid hydrogen tanks. The approach was to modify the 

reinforced foam insulation which had been developed for the Saturn 

S-IVB. This insulation, called 3D foam, consisted of a polyurethane 

foam reinforced with glass fibers oriented in three mutually 

perpendicular directions, bonded to the tank wall with epoxy adhesive 

and lined with a glass cloth reinforced epoxy coating. 

A polyurethane foam formulated to withstand 450 K, as required 

for the Space Shuttle, was used, and foam fabrication was optimized 

to produce the lightest composite with the greatest strength possible. 

Some results of tensile, compressive, shear, and bond strengths at 

77 K and 298 K are given. Adhesive bonding to the tank wall was 

optimized, vibration and acoustic fatigue tests were devised, various 

panel joints were evaluated, and methods of repairing the insulation 

were developed and tested. 

The program succeeded in developing a satisfactory material and 

methods for manufacturing, applying, testing, and repairing the 

internal insulation. Detailed material and process specifications 

were to be prepared using the data from this experimental program. 

Earlier work in this program was reported in the paper abstracted 

on page 57. A report of later work is abstracted on page 56. 

Important references: 

1. Salmassy, et al., MDAC Quarterly Summary Rept. No. MDC G2525 

(Sep 1971). 

2. MDC Rept. No. G2525 (Sep 1971). 

3. MDC Rept. No. E0276 (Jun 1971). 

4. MDAC Quarterly Rept. No. MIX G2740 (Jan 1972). 

5. Dearing, D. L., MDAC Rept. No. SM-42545 (Nov 1962). 

58 
OPTIMIZATION ASPECTS AND TEST RESULTS OF A CRYOGENIC UPPER STAGE TANK 

INSULATION 

Leupold, M., and Mueller, E. 

Boelkow Entwicklungen GmbH, Munich, West Germany, Rept. No. U55-1, 

35 pp (1967) 

This paper describes a compound insulation for the upper stage of a 

space vehicle, combining foam insulation with superinsulation. The 

vehicle stage has both liquid hydrogen and liquid oxygen tanks to be 

insulated. The foam insulation is effective during ground hold and ascent 

while the superinsulation becomes most effective in space. The foam is 

bonded to the tank wall, superinsulation is applied over the foam, and 

the total insulation is enclosed in a vacuum bag and evacuated. 

The insulation system was analytically optimized to balance propellant 

boiloff loss against insulation weight. This analysis assumed a constant 

10 mm thickness of foam insulation, and varied the number of superinsulation layers according to mission length. Two foams were considered, 

a polyurethane foam and a polyvinyl chloride foam. In tests of tensile 

and shear strengths at 77 K and room temperature, the PVC foam was 

superior. Weight losses at elevated temperatures were measured because 

the insulation is exposed to aerodynamic heating. The PVC foam began to 

decompose at a temperature near 410 K, while the polyurethane remained 

stable at least up to 425 K. 

A program was started to measure the effectiveness of compound 

insulation by measuring boiloff from insulated liquid nitrogen tanks. 

Only initial results are reported, and tests with liquid hydrogen tanks 

were planned. 

59 
SEALED-FOAM, CONSTRICTIVE-WRAPPED, EXTERNAL INSULATION SYSTEM FOR 

LIQUID-HYDROGEN TANKS OF BOOST VEHICLES 

Lewis Research Center 

National Aeronautics and Space Administration, Cleveland, Ohio, Lewis 

Research Center, Tech. Note No. NASA TN-D-2685, 157 pp (Mar 1965) 

This report is a collection of nine chapters by various authors, 

describing the concept, design and testing of the external foam insulation 

system. The first chapter, by P. T. Hacker and J. B. Esgar, describes 

the insulation concept. The system consisted of 10 mm thick, 32 kg/m3 

density polyurethane foam panels, hermetically sealed within a mylaraluminum-mylar laminate covering, protected from aerodynamic erosion by a 

thin fiberglass cloth layer, adhesively bonded to the tank wall to prevent 

air penetration, and held in place by a prestressed constrictive wrap 

of fiberglass roving. Chapter 2, by W. H. Roudebush, presents the 

calculated thermal conditions during a boost trajectory, which the 

insulation was designed to withstand. 

Chapter 3, by L. J. Heidelberg, gives results of measurements of 

thermal conductivity of insulation panels. Panels were tested under 

compressive loads between surfaces at liquid hydrogen and ambient 

temperatures. The average thermal conductivity, 0.021 W/m-K at a mean 

temperature of 156 K, was considered a good indication of the thermal 

conductivity of the insulation held against a liquid hydrogen tank by 

constrictive wrapping. Changes in compressive load did not affect 

thermal conductivity, and addition of fiberglass separators produced 

small reduction of thermal conductivity while adding to weight and 

complexity of the insulation. 

The insulation system was sealed to prevent cryopumping of air, 

but any leaks in the seal would allow air to condense in the insulation, 

and the collection of liquid air or liquid oxygen might create a 

hazardous condition in case of accidental impact. Chapter 4, by R. P. 

Dengler, describes tests of the impact sensitivity of the insulation and 

its component materials in the presence of liquid oxygen. In 40 tests, 

10 produced some reaction and only 1 led to sustained combustion. These 

results, along with the effective hermetic sealing, the localized area 

of any leakage, the condensation of air rather than liquid oxygen, and 

the high impact magnitudes used in the test program, led to the 

conclusion that the probability of damage was very small. 

Chapter 5, by P. J. Perkins, Jr., M. Colaluca, F. P. Behning, and F. 

Devos, reports on the fabrication and tests of insulated ,subscale tanks. 

Tests included equivalent thermal conductivity during ground hold, 

structural effect of rapid pressure drop during launch, and effect of 

surface heating during launch. Chapter 6, by R. P. Cochrane, V. 0. 

Bazarko, and R. W. Cubbison, describes aerodynamic heating tests 

conducted in a jet engine exhaust and in a supersonic wind tunnel. 

60 
Chapter 7, by P. J. Perkins, Jr., C. B. Shriver, and R. A. Burkley, 

reports on application of the insulation to a full-scale centaur tank. 

Chapter 8, by H. F. Calvert, P. J. Perkins, Jr., W. C. Morgan, and M. A. 

Colaluca, describes ground-hold tests on the full-scale insulated tank. 

Chapter 9, by J. B. Esgar and P. T. Hacker, summarizes results of the 

program. 

The subscale tests showed thermal conductivities about the same as 

those determined in the thermal conductivity tests. Full-scale tests 

showed even lower thermal conductivities, near 0.014 W/m-K, partially 

because of lower mean temperature of 110 K. The insulation, protected 

by the constrictive wrap and fiberglass cloth layer, withstood the 

simulated aerodynamic heating and pressure of launching. Leaks were 

observed in the tests, but were limited to relatively small areas, and 

had no apparent effect on thermal performance of the insulation. The 

insulation withstood all tests, and was considered suitable for use on 

hydrogen-fueled boost vehicles. 

Important references: 

1. McGrew, J. L., Advances in Cryogenic Engineering 8, 387-92 (1963). 

2. Miller, R. N., Bailey, C. D., Beall, R. T., and Freeman, S. M., 

Advances in Cryogenic Engineering 8, 417-24 (1963). 

3. Perkins, P. J., Jr., and Esgar, J. B., AIAA Annual Structures and 

Materials Conf., 5th (Palm Springs, Calif., Apr 1-3, 1964), Publ. 

CP-8, 361-71 (1964). 

4. Gray, V. H., Gelder, T. F., Cochran, R. P., and Goodykoontz, J. H., 

NASA Tech. Note No. NASA TN-D-476 (1960). 

5. Perkins, P. J., Jr., NASA Tech. Note No. NASA TN-D-2679 (1964). 

6. Key, C. F., and Riehl, W. A., NASA Tech. Memo. No. NASA TM-X-54611 

(1963). 

7. Dengler, R. P., NASA Tech. Note No. NASA TN-D-1882 (1963). 

61 
MECHANICAL AND PHYSICAL PROPERTIES OF ORGANIC FOAMS 

Lormis, F. E. 

Bendix Corp., Kansas City, MO., Final Rept. No. BDX-613-562-REV. 

(Feb 1972) 60 pp 

A test program was conducted to establish the cryogenic properties 

of organic structural foams. Four foams were investigated, including a 

rigid polystyrene foam, two rigid polyurethane foams, and a flexible 

polyurethane foam. The tests were for thermal conductivity, thermal 

expansion, and torsional shear modulus and shear strength between 77 K 

and 298 K. 

In all of the shear tests, shear modulus and ultimate shear strength 

increased and ultimate angle of rotation decreased with decreasing 

temperature. Tests were run at 77 K, 195 K, and 298 K, except on the 

flexible polyurethane foam which was unable to support the test fixture 

at 298 K and only partially supported the fixture at 195 K. The author 

states that the polyurethanes showed orientation effects while the 

polystyrene did not. This statement is not confirmed by the data,,which 

show little or no orientation effect for any of the foams. The author 

also states that the polystyrene was by far the most flexible at 77 K. 

While this is true of the rigid foams, the flexible polyurethane is 

shown by the data to be more flexible than the polystyrene at 77 K. 

Thermal conductivity results are given for samples with a cold 

side between 75 K and 91 K and a hot side between 289 K and 303 K. 

Thermal expansion results are shown between 100 K and 298 K. In another 

test, tensile strengths of the polystyrene and a polyurethane were 

measured at room temperature using three different adhesive systems. 

It was concluded that there was little or no difference resulting from 

the type of adhesive. Conditioning times were determined in tests 

measuring the time required for the center of a polyurethane foam block 

to reach the testing temperature. The center of a cylindrical block 

76 mm long by 29 mm diameter reached 77 K in 10 min after immersion 

in liquid nitrogen. The center reached the gas temperature in 45 min 

after being placed in gaseous nitrogen at 78 K. Conditioning times 

were assigned as 15 min in liquid and 60 min in gaseous coolants. 

The shear modulus and shear strength of a polyurethane foam were measured 

after long conditioning in gaseous nitrogen and after rapid cooling in 

liquid nitrogen. Strength and modulus were the same or higher in the 

liquid, showing that there was no degradation due to thermal shock. 

Important references: 

1. Miller, R. N., Bailey, C. D., et al., Advances in Cryogenic 

Engineering 8, 417-424 (1963). 

62 
Important references (continued): 

2. Reed, R. P., Durcholz, R. L. and Arvidson, J. M., Advances in 

Cryogenic Engineering 16, 36-45 (1971). 

3. Latter, G. I. and Prado, M. E., LRL Report, ENS 71-366, 1-12 

(Feb 1971). 

4. Lazarus, L. J., Bendix Report, EP 46411-00, 1-14 (Dee 1970). 

5. Landrock, A. H., Plastec Report 20, Plastic Technical Evaluation 

Center, Picatinny Arsenal (Jul 1965). 

6. Jelineck, F. J., Cryogenic Properties of Polystyrene and Polyethylene 

Foams, Progress Rept., Battelle Memorial Inst., Columbus, Ohio 

(Dee 1970). 

63 
THERMOPHYSICAL PROPERTIES OF THERMAL INSULATING MATERIALS 

Loser, J. B., Moeller, C. E., and Thompson, M. B. (Midwest Research 

Inst., Kansas City, MO.) 

Air Force Materials Lab., Wright-Patterson AFB, Ohio, Rept. No. 

ML-TDR-64-5, Contract No. AF33(657)-10478 (Apr 1964) 362 pp 

This report is a compilation of data on the thermophysical 

properties of insulating materials, resulting from a comprehensive 

literature survey and analysis of original test data published between 

1940 and 1962. The data are presented graphically, and a reference 

table with each graph gives the sources of the data, the sample forms 

and test methods, and remarks on temperature ranges and accuracies. 

The foam insulations included in the compilation are epoxy, glass, 

polystyrene, polyurethane, polyvinyl chloride, rubber, and silicon 

dioxide. The data for these forms are thermal conductivities as 

functions of temperature or pressure, and linear thermal expansions of 

the polyurethanes. The foam data came from 17 references. 

The data pages are followed in the compilation by a section on 

experimental methods, which describes and evaluates the available 

methods of measuring thermal conductivity, thermal expansion, specific 

heat, total normal emittance, and thermal diffusivity. A glossary of 

synonyms and trade names, conversion factors, references, and an author 

index are part of the report. The report is an excellent and 

comprehensive summary of the available data on foam insulation, and the 

major limitation is the age of the compilation. 

Important references: 

1. Hickman, M. J. and Ratcliffe, E. H., Int. Inst. Refrign/IIF/Bul 

35, No. 4 (presented 9th Int. Cong. Refrign. AG-S), 794 (1955). 

2. Powers, R. W., Johnston, H. L., Hansen, R. H. and Ziegler, J. B., 

ASTIA AD 27-569, TR 264-16, l-29 (May 1, 1963). 

3. Verschoor, J. D., Refrig. Eng. 62, No. 9, 35-7, 98 (1954). 

4. Kropschot, R. H., ASHRAE J. 1, No. 9, 48-54 (Sep 1959). 

5. Corruccini, R. ,.I., Chem. Engng. Progress 53, No. 6 (Jun 1957). 

6. Haskins, J. F. and Hertz, J., Convair Astronautics Rept. MRG-242 

(Jul 25, 1961). 

7. Speil, S., Thermal Performance of Rigid Insulations at Cryogenic 

Temperatures, Presented AFOSR Conf. Aerodynamically Heated 

Structures (Arthur D, Little, Inc., Cambridge, Mass., Jul 1961). 

64 
STUDY OF THERMOPHYSICAL PROPERTIES OF CONSTRUCTIONAL MATERIALS IN 

A TEMPERATURE RANGE FROM 10 TO 400 K 

Luikov, A. V,, Shashkov, A. G., Vasiliev, L. L., Tanaeva, S. A., 

Bolshakov, Yu. P., and Domorod, L. S. (Heat and Mass Transfer Inst., 

Minsk, BSSR, USSR) 

Heat Transmission Measurements in Thermal Insulations, Proc. Symp. 

Thermal and Cryogenic Insulating Materials (Philadelphia, Pa., Apr 

16-7, 1973), American Sot. for Testing and Materials, Philadelphia, 

Pa., Special Tech. Publ. No. STP-544, 290-6 (Jun 1974) 

The thermal conductivities, thermal diffusivities, and specific 

heats of several structural and insulating materials were measured. 

One of the materials was a polyurethane foam, identified by its Russian 

designation. The thennophysical properties are tabulated for the 

temperature range from 30 K to 300 K. The thermal conductivity of the 

material increased with increasing temperature over the entire 

temperature range. The authors note that these results differ from 

those reported by Tye. They attribute the difference to a denser foam, 

49 kg/m3 compared to the 32 kg/m3 tested by Tye. 

The Russian data do not show the s-shape characteristic of the 

thermal conductivity versus temperature curve reported by other 

investigators for polyurethane foam. This difference is attributed 

to the experimental conditions, with vacuum as the external medium, 

and the foam pores filled with helium during thermal treatment before 

the test. Such results emphasize the importance of matching test 

conditions to proposed operating conditions, and demonstrate the ways 

that different applications can affect insulation effectiveness. 

Important references: 

1. Tye, R. P., Proc. XIII International Congress of Refrigeration 1 - 

(Washington, D.C.)(1971). 

65 
HIGH PERFORMANCE SPRAY FOAM INSULATION FOR APPLICATION ON SATURN S-II 

STAGE 

Mack, F. E., and Smith, M. E. {North American Rockwell Corp., Downey, 

Calif.) 

Advances in Cryogenic Engineering 16, Proc. Cryogenic Engineering Conf. 

(Colorado Univ., Boulder, Jun 17-19, 1970), K. D. Timmerhaus, Editor. 

Plenum Press, New York, 118-27 (1971) 

This paper describes the overall program to develop a spray-on 

foam insulation for use as external insulation on the liquid hydrogen 

tanks of the Saturn S-II stage. Six spray foams were screened, and a 

flame retardant polyurethane foam with a density of 32 kg/m3 was selected 

for further development. Evaluations were based on a "cryogenic strain 

compatibility" test, in which a thermal gradient and tensile strain were 

applied to a sample in the presence of liquid hydrogen. Samples were also 

subjected to simulated boost heating with altitude. 

Process development included selection of proper spray equipment, 

selection of primers to insure adhesion of the foam to the aluminum tank 

wall, and evaluation of temperature and humidity effects during spraying 

to establish allowable processing conditions. A coating material was 

developed to protect the foam from weathering effects caused by exposure 

to ultraviolet in direct sunlight. 

Small tank tests were used to verify spray-foam application 

feasibility, retention of insulating characteristics with extended 

environmental exposure, and structural integrity during vibration and 

heating. Smaller samples were subjected to environmental aging and wind 

tunnel tests. Foam panels were applied to surfaces of an X-15, and flights 

of the X-15 subjected the samples to combinations of heating, aeroshear, 

and altitude simulating the S-II flight profile. The resulting erosion of 

the foam led to another test program to develop erosion protection for the 

insulation. Finally, large-scale tank tests qualified the insulation for 

application to the S-II. 

All of the screening, development, verification, and qualification 

tests were successful, and the spray foam material was shown to be an 

applicable insulation for large-scale liquid hydrogen boosters. 

Important references: 

1. Hammond, M. B., Advances in Cryogenic Engineering 15, 332-42 (1970). 

2. North American Rockwell Rept. No. 69MA5502, Contract No. NAS 7-200 

(Jun 1964). 

3. Cioth, B. B., North American Rockwell Rept. No. SID 67-696 (Dee 1967) 

and SID 68-394 (Jul 1968). 

66 
INSULATION BY SYNTHETIC FOAMS IN CRYOGENICS 

Mathes, H. (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn bei Munich, 

West Germany) 

Kaeltetech.-Klim. 22, No. 2, 50-5 (Feb 1970) 

This paper describes a foam insulation developed for use on the 

liquid oxygen and liquid hydrogen tanks of a rocket stage. The insulation 

consisted of foam panels, thermoformed and adhesively bonded to the tank 

surface. The experimental program involved the selection of the foam and 

adhesive, and the development of suitable fabrication methods for applying 

the foam to the tank. 

Three types of foam were considered, a polyurethane foam, a crosslinked polyvinyl chloride foam, and a polymethacrylimide foam. In tests 

of thermoforming, the polyurethane had a tendency to crack and the 

polymethacrylimide required a rather precise high forming temperature. 

The PVC foam was chosen for the formed portion of the insulation. Panels 

were formed within a vacuum jacket in a heating chamber, over molds with 

the tank contours. A polyurethane adhesive was selected to bond the 

molded panels to the tank. Foamed-in-place polyurethane was applied 

around the flange portion of the tank. A polyvinylidene chloride film 

was used as a vapor barrier over the seams of the insulation, to prevent 

air leakage and condensation. The insulation as developed appeared to be 

satisfactory for its intended application. 

Important references: 

1. Zimni, W. F., and Meitzner, K., Kaeltetech.-Klim. 22, No. 2, 34-40 

(Feb 1970). 

2. Kreft, H., and Wagner, D., Kaeltetech.-Klim. 2, No. 9, 258-65 

(1969). 

3. Kreft, H., Schulz, J., and Hoffmann, H., ERNO Raumfahrttechnik 

GmbH, Bremen, Germany, Rept. (1967). 

67 
MECHANICAL PROPERTIES OF INSULATING PLASTIC FOAMS AT LOW TEMPERATURES 

McClintock, R. M. (National Bureau of Standards, Boulder, Colo. 

Cryogenics Div.) 

Advances in Cryogenic Engineering 5, Proc. Cryogenic Engineering Conf. 

(Massachusetts Inst. of Tech., Cambridge, Sep 3-5, 1958), K. D. 

Timmerhaus, Editor. Plenum Press, New York, 132-40 (1960) 

The mechanical properties of a material must be known in order to 

evaluate its response to the thermal stresses imposed in low temperature 

applications. This is important in plastic foam insulations, which are 

often bonded to a more rigid structure, and sustain large temperature 

gradients across the material. This paper reports on the experimental 

determination of important mechanical properties of three expanded plastics. 

The materials were polystyrene foam of two densities, 48 and 66 

kg /m3, and an epoxy foam of density 88 kg/m3. The properties determined 

were elastic modulus in tension and tensile strength at temperatures from 

76 K to 300 K, and a modulus of rigidity in rotational shear at 

temperatures from 20 K to 300 K. In every case, the elastic moduli showed 

a marked increase with decreasing temperature. Results are given in 

terms of the moduli divided by the densities, to take care of the density 

dependence of the elastic properties. The materials showed distinct 

anisotropy, with the properties being different in each of the three 

mutually perpendicular directions. However, the effect of temperature 

was the same in each direction. Microscopic examination confirmed the 

anisotropy of the foams, showing a preferred orientation of the cells in 

a sample. But the direction of the preferred orientation was not the 

same at all locations in a large sample. The best way to analyze the 

foams was judged to be to evaluate properties in the three mutually 

perpendicular directions, and use the average of the values to characterize 

each material. 

Tensile strengths of the foams showed no particular trend of change 

with temperature. This was in contrast to bulk plastics, which showed 

an increase of tensile strength with decreasing temperature. The 

difference in behavior was attributed to the increased brittleness at low 

temperature leading to an increased notch sensitivity, and the inherently 

"notched" structure of a foam. The brittleness was confirmed by the 

decreases in ultimate elongation with decreasing temperature. 

Important references: 

1. Corruccini, R. J., Chem. Eng. Progr. Pt. 3, 53, 8 (Aug 1957). 

68 
POLYURETHANE FOAM INSULATION FOR CRYOGENIC LINES 

McDonnell Aircraft Corp. 

McDonnell Aircraft Corp., St. Louis, MO., Final Rept. No. TR-052 068 44, 

29 pp (Jul 1964) 

An experimental program was conducted to determine some of the 

properties of a number of rigid polyurethane foams proposed for use as 

insulation on cryogenic lines in the Gemini spacecraft. Fourteen 

polyurethane foams were submitted for test, four as premolded specimens 

and the other ten as components to be mixed and molded in the laboratory. 

The premolded samples were tested for thermal embrittlement and water 

absorption. The other materials were molded around an aluminum tube, 

and tested for thermal embrittlement, water absorption, and thermal 

conductivity. Densities of the premolded samples were 29 to 37 kg/m3, 

while the laboratory-molded samples ranged from 46 to 99 kg/m3. The 

molding process in the laboratory used excess material to insure filling 

the mold, and was difficult to control. 

The thermal embrittlement. test was a very rough qualitative test, 

consisting of immersing a sample in liquid nitrogen for 15 s, removing 

the sample and hitting it against a table top, and examining it for 

apparent breaks or cracks. There was no evidence of thermal embrittlement as determined by this test. Water absorption testing consisted of 

measuring weight increase of a sample and penetration depth of water 

after 24 h immersion in dyed water. Water penetrated the foams to a 

depth of three to five cell diameters, thought to be the depth to the 

first undamaged layer of cells. Thermal conductivity measurements were 

made on the samples molded around an aluminum tube, by filling the tube 

with liquid nitrogen and recording the rate of boiloff. Thermal 

conductivities on ten samples ranged from 0.012 to 0.017 W/m-K, with an 

average of 0.015 W/m-K, at a mean temperature of 172 K. 

69 
EFFECTS OF NUCLEAR RADIATION AND CRYOGENIC TEMPERATURES ON NONMETALLIC 

ENGINEERING MATERIALS 

McKannan, E. G., and Gause, R. L. (National Aeronautics and Space 

Administration, Huntsville, Ala. Marshall Space Flight Center) 

J. Spacecraft Rockets 1, No. 4, 558-64 (Jul-Aug 1965) 

The experimental program had the objective of evaluating materials 

for use in nuclear-powered spacecraft. The materials were tested by 

exposure to various combinations of nuclear radiation, cryogenic 

temperature, and vacuum environments. For the combination of nuclear 

radiation with cryogenic temperature, the materials evaluated were two 

structural adhesives, two structural laminates, two thermal insulations, 

and four electrical insulations. The thermal insulations were a 

polyurethane foam and a polystyrene foam. Compressive strength of the 

foam was used to evaluate the response to exposure, and the more 

pertinent property for insulation, the thermal conductivity, was left as 

the subject of some future evaluation. 

Samples were irradiated to two dose levels and tested at 323 K in 

air, at 77 K immersed in liquid nitrogen, and at 20 K in liquid hydrogen. 

The two foams reacted similarly to exposure except that the polyurethane 

had higher compressive strengths than the polystyrene. Without radiation, 

compressive strength and modulus increased with decreasing temperature. 

Maximum compressive strength of unirradiated foam was observed at 20 K 

for polystyrene and at 77 K for polyurethane. Irradiation in air at 323 

K badly degraded both foams. This result is attributed to reactions with 

residual blowing agents, which decompose and attack the foam. These 

reactions are inhibited at cryogenic temperatures, and radiation at low 

dose levels of about 0.5 x 106 J/kg increases the compressive strength 

and modulus of each foam at 77 K and 20 K, apparently by cross-linking. 

At higher dose levels of 1.2 to 1.3 x lo6 J/kg, radiation-induced 

degradation competes with the cross-linking, and reduces strength and 

modulus at cryogenic temperatures. 

Because of the severe degradation at room temperature, neither foam 

can be recommended for application in a nuclear radiation environment. 

Important references: 

1. Lucas, W. R., Symp. on Space Radiation Effects, ASTM Publ. No. 363 

(1964). 

2. Smith, E. T., 1963 Summer General Meeting of the Institute of 

Electrical and Electronics Engineers (Toronto, Canada) (1963). 

3. Lockheed Missiles and Space Co., Palo Alto, Calif., Rept. No. 

NSP-63-35, Contract NAS S-5600 (May 1963). 

4. Aerojet-General Corp., Rept. No. 2339 (Jul 1962). 

5. Smith, E. T., Radiation and Cryotemperature Tests, Annual Rept., 

Contract No. NASA 8-2450 (Nov 1961). 

70 
EVALUATION OF CRYOGENIC INSULATION MATERIALS AND COMPOSITES FOR USE 

IN NUCLEAR RADIATION ENVIRONMENTS. MATERIALS TESTS 

McMillan, W. I)., Bradbury, H. G., Carter, H. G., Lightfoot, R. P., and 

Kerlin, E. E. 

General Dynamics/Fort Worth, Tex., Rept. No. FZK-347. National 

Aeronautics and Space Administration Rept. No. NASA CR-61920, Contract 

No. NAS 8-18024, 264 pp (May 1968) 

The objective of this program was the evaluation of cryogenic 

insulation materials for application to a nuclear rocket vehicle, where 

the materials are exposed to cryogenic temperatures and nuclear radiation. 

The materials tested included foam and corkboard insulation, adhesives, 

and vapor barrier films. The mechanical property tests were tensile 

shear and compressive strengths for the insulation; shear and peel 

strength for the adhesives; and elongation and tensile strength for the 

films. Irradiation was performed at doses ranging from 9 x 105 to 

2.5 x 106 J/kg. Two detonations occurred in the corkboard irradiation 

tests (caused by the reaction of hydrogen with trapped air in the 

corkboard cells). Tests were conducted in air, liquid nitrogen and liquid 

hydrogen. The insulation materials tested were four commercial urethane 

foams and one insulating cork. 

The results showed that all of the foams maintained their 

compressive strength at low temperatures and under radiation. Radiation 

in air decreased the strength. Corkboard is significantly weaker than 

foam under all conditions. Under shear testing the foams performed 

well at all temperatures and radiation levels as did the corkboard 

except that the latter material showed degraded results after irradiation 

in air. 

Tensile tests were also performed on composite insulation-adhesivefilm insulation systems. In all cases failure occurred in the insulation, 

but the foams had higher strength than the corkboard. 

Important references: 

1. Kerlin, E. E;, General Dynamics/Fort Worth, Tex., Division Rept. 

No. FZK-319 (Ott 1966). 

2. Kerlin, E. E., and Lightfoot, R. P., General Dynamics/Fort Worth, 

Tex., Division Rept. No. FZK-328 (Jan 1967). 

3. Kerlin, E. E., and Lightfoot, R. P., General Dynamics/Fort Worth, 

Tex., Division Rept.' No. FZK-329 (Apr 1967). 

4. McMillan, W. D., Carter, H. G., and Lightfoot, A. P,, General 

Dynamics/Fort Worth, Tex., Division Rept. No. FZK-348 (Jun 1968). 

5. Landrock, A. H., Technical Evaluation Center, Plastec Rept. 20, 

Picatinny Arsenal, Dover, N. .I. (Jul 1965). 

71 
Important references (continued): 

6. 

7. 

8. 

9. 

10. 

11. 

12. 

13. 

Kerlin, E. E., General Dynamics/Fort Worth, Tex., Rept. No. 

FZK-161-1 (Jan 1963). 

Smith, E. T., General Dynamics/Fort Worth, Tex., Rept. No. 

FZK-161-2 (Jan 1963). 

Kerlin, E. E., and Smith, E. T., General Dynamics/Fort Worth, Tex., 

Rept. No. FZK-188-1 (May 1964). 

Kerlin, E. E., and Smith, E. T., General Dynamics/Fort Worth, Tex., 

Rept. No. FZK-188-2 (May 1964). 

Kerlin, E. E., and Smith, E. T., General Dynamics/Fort Worth, Tex., 

Division Rept. No. FZK-290 (Jul 1966). 

Eyles, A. G., Advances in Cryogenic Engineering 10, 224 (1965). 

Miller, R. N., et al., Industrial and Engineering Chemistry, 

Product Research and Development 1, 257 (Dee 1962). 

Miller, R. N., Bailey, C. D., Beall, R. T., and Freeman, S. M., 

Advances in Cryogenic Engineering 8, 417 (1963). 

72 
FOAMS AND PLASTIC FILMS FOR INSULATION SYSTEMS 

Miller, R. N., Bailey, C. D., Beall, R. T., and Freeman, S. M. 

(Lockheed-Georgia Co., Marietta) 

Advances in Cryogenic Engineering 8, Proc. Cryogenic Engineering Conf. 

(Los Angeles, Calif., Aug 14-16, 1962), K. D. Timmerhaus, Editor. 

Plenum Press, New York, 417-24 (1963) 

The use of liquid hydrogen as a rocket propellant created a demand 

for reliable and lightweight cryogenic insulation systems. To aid in 

the design of such systems, the properties of a number of materials 

were determined. This paper reports on the mechanical properties of 

three vapor barriers and four foams, and the thermal expansion of four 

adhesives, three vapor barriers, and seven foams. 

The four foams tested for mechanical properties were a flexible 

polyether, a semirigid polyurethane, an epoxy, and a polyester 

polyurethane foam. Tensile and shear strength tests were conducted at 

20 K, 77 K, 298 K, and 394 K. The semirigid polyurethane and the 

epoxy had the highest tensile strength at 20 K, at room temperature 

the polyester polyurethane was strongest, and tensile strengths of all 

the foams dropped off at high and low temperature extremes. The polyester 

polyurethane was strongest of the four at room temperature. Loadcompression tests at 20 K, 77 K, and 298 K showed that the polyether, 

epoxy, and polyester polyurethane foams had good elastic recovery at 

room temperature, but the polyether embrittled and was crushed at 77 K, 

and the polyester polyurethane at 20 K, leaving only the epoxy foam 

retaining elasticity at liquid hydrogen temperatures. 

The foams tested for thermal expansion were two epoxy, three 

polyurethane, a polystyrene, and a filled epoxy polyamide foam. 

Between 77 and 293 K, the polyurethanes and filled epoxy polyamide had 

the highest thermal expansion coefficients, and the epoxies had the 

lowest. 

73 
EXPERIMENTAL STUDY OF A NEW PVC FOAM INSULATION SYSTEM FOR LH2-LO2 

SPACE VEHICLES 

Muller, F. J. (Societe 1'Air Liquide, Sassenage,,France) 

Advances in Cryogenic Engineering,%, Cryogenic Engineering Conf. 

(Boulder, Colo., Jun 17-19, 1970), K. D. Timmerhaus, Editor. Plenum 

Press, New York, 109-17 (1971) 

This paper is an extension of an earlier paper, abstracted on page 

101. The earlier paper described a polyvinyl chloride foam developed 

for use as an external insulationfor spacecraft liquid hydrogen tanks. 

This paper describes an improved formulation of the PVC foam, its 

application as insulation for a launch vehicle, and evaluations of 

insulation system performance. 

The original PVC foam was satisfactory for small scale test tanks, 

but had too little tensile elongation to withstand the combined effects 

of differential thermal contraction and tank pressurization of thinwalled tanks. The reformulated foam was reported to have nearly the 

same properties as the original foam, except for an improved ultimate 

elongation at 20 K. 

The insulation system designed for the liquid hydrogen-liquid 

oxygen stage of the Europa III launch vehicle consisted of a layer of 

foam, 16 mm thick on the liquid hydrogen tank and 10 mm thick on the 

liquid oxygen tank, bonded to the aluminum tank wall with a fiberglass 

cloth reinforced epoxy adhesive, and a similar layer of epoxy-fiberglass 

applied over the foam to provide a base for a 0.5 mm coating of 

ablative material. Insulated test tanks were subjected to pressurization 

cycles while filled with liquid hydrogen, to expected dynamic pressures 

and temperatures in wind tunnel tests, and to vibration while filled 

with liquid hydrogen. No damage to the insulation was observed. A 

complete insulated tank assembly with liquid oxygen and liquid hydrogen 

in compartments separated by a common bulkhead was tested under ground 

hold conditions. The insulation proved satisfactory and remained 

undamaged. The author concludes that all tests have been fully 

successful, showing the suitability of the insulation for application to 

the launch vehicle as well as various other cryogenic equipment. 

Important references: 

1. Tariel, M., et al, Advances in Cryogenic Engineering 12, 274-85, 

Plenum Press (1967). 

2. Muller, F., Thesis (1967). 

74 
THERMAL PERFORMANCE CHARACTERISTICS OF A COMBINED EXTERNAL INSULATION 

SYSTEM UNDER SIMULATED SPACE VEHICLE OPERATING CONDITIONS 

Muller, F. J., and Xlevatt, P. L. (L'Air Liquide, Sassenage, France 

and McDonnell Douglas Astronautics CO.~ Huntington Beach, Calif.) 

Advances in Cryogenic Engineering 19, Proc. Cryogenic Engineering Conf. 

(Georgia ,Inst. of Tech., Atlanta, Aug 8-10, 1973), K. D. Timmerhaus, 

Editor. Plenum Press, New York, 482-9 (1974) 

A combined foam-multilayer external insulation was designed for 

use on space vehicles such as the space shuttle orbiter or the Space 

Tug. This paper reports on tests of the long term thermal performance 

of.the insulation system on a liquid hydrogen tank under simulated space 

vehicle operating conditions. 

The insulation consisted of a 11-mm thick layer of polyvinyl 

chloride foam bonded to the tank, with a lo-shield multilayer aluminized 

mylar assembly attached over the foam, the entire system enclosed in a 

polyimide purge bag for purging with either helium or nitrogen. The 

insulation was applied to a liquid hydrogen tank 1.5 m long by 1.2 m 

diameter, the tank was filled with liquid hydrogen, and tests were run 

under simulated ground-hold steady state, ascent transient, space steady 

state, reentry transient, and post-mission ground-hold conditions. 

Transient and steady state heat fluxes were measured and agreed well 

with predicted values, except for the space flight condition where heat 

flux was twice that expected. The purge bag maintained its integrity 

throughout testing. The foam sublayer sustained some cracking, which 

apparently had no effect on performance and did not cause debonding. 

The authors concluded that the insulation system proved feasible 

and a viable candidate for further consideration for use on space 

vehicles. 

Important references: 

1. Muller, F. J., and Flacon, B. G., CEC/SES/FM/BF/CM/CD/21.860, 

McDonnell Douglas final Rept., L'Air Liquide (Jul 1972). 

2. Muller, F. J., Advances in Cryogenic Engineering 16, Plenum Press, 

New York, 109 (1971). 

75 
A GUARDED HOT PLATE APPARATUS FOR THE MEASUREMENT OF THERMAL 

CONDUCTIVITY OF INSULATING MATERIALS AT LOW TEMPERATURES 

Myncke, H., Van Paemel, O., and De Cnop, L. (Laboratorium voor 

Akoestiek en Warmtegeleiding K.U.L., Heverlee, Belgium) 

Some Thermophysical Properties of Refrigerants and Insulants, Proc. 

International Inst. of Refrigeration Commission Bl (Zurich, Switzerland, 

Sep 27-9, 1973), Bull. Inst. Int. Froid, Annexe 1973-4, 157-61 (1973) 

An apparatus was developed to measure thermal conductivities of 

insulation materials between 113 K and 273 K. This paper describes the 

apparatus and presents results of measurements of the thermal 

conductivity of glass foam. 

of 119 and 129 kg/m3, 

Two samples of the foam, having densities 

were tested simultaneously at mean temperatures 

between 117 K and 274 K. The results are shown in tabulated and graphical 

forms, and are compared to the results obtained by W. F. Cammerer on a 

similar material in the temperature range between 117 K and 302 K. The 

curves of thermal conductivity versus temperature are similar but not 

identical, as would be expected from samples of similar but not 

identical materials. In both cases, the thermal conductivity decreases 

nearly linearly with decreasing temperature down to about 180 K, then 

decreases more slowly with further decrease of temperature. 

76 
POLYURETHANE FOAM INSULATION THERMAL AGING CHARACTERISTICS 

Navickas, J., and Madsen, R. A. (McDonnell Douglas Astronautics Co., 

Huntington Beach, Calif.) 

Cryogenic Engineering Conf. and International Cryogenic Materials 

Conf. Joint Meeting (Queens Univ., Kingston, Ontario, Canada, Jul 

22-5, 1975) 12 pp 

Thermal aging is the time-dependent thermal conductivity 

characteristic shown by closed cell polyurethane insulation. Freshly 

made foam has a relatively low thermal conductivity which gradually 

increases to a significantly higher value. This paper presents an 

analysis of the aging process for trichlorofluoromethane-blown foam 

aged in air at ambient temperature. The model starts with the closed 

cells of the foam filled with the blowing agent. Over a period of time 

air diffuses into the cells and mixes with the blowing agent. The 

thermal conductivity changes as the proportions of gases in the cells 

change. The blowing agent also diffuses out of the cells, but this is 

such a slow process that it is ignored in the analysis. 

Thermal conductivity versus operating temperature curves were 

calculated for various aging times. With aging longer than about 100 h 

the curves show the s-shaped characteristic typical of polyurethane 

foams. After 500 h, the thermal conductivity at temperatures below 200 K 

remains constant, while the thermal conductivity at higher temperatures 

is still increasing slowly. Comparison of the calculations with 

experimental data shows reasonable agreement. 

The authors conclude that the analytical model is valid, and can 

be used to extrapolate available thermal performance and thermal aging 

data to conditions where data are not available. Given diffusion 

characteristics, the model can be used with different blowing agents, 

exposure to different gases, and exposure at different pressures and 

temperatures. The authors note that, since aging effects are manifested 

much more rapidly at cryogenic operating temperatures, great care is 

required in interpreting thermal conductivity data taken at ambient 

operational temperatures. They feel that much of the inconsistency of 

data in the literature is due to differences in aging conditions. 

Important references: 

1. Stengard, R. A., New Information About Urethane Foam, duPont 

Bulletin (1962). 

2. Guenther, F. O., Cellular Materials-Composition, Cell-Size, Thermal 

Conductivity, Society of Plastic Engineers Transactions (1962). 

3. Skochdopole, R. E., Chemical Engineering Progress 57, 55 (1961). 

77 
Important references (continued): 

4. Patten, G. A. and Skochdopole, R. E., Modern Plastics 2, 149 

(1962). 

5. Harding, R. H. and James, B. F., Modern Plastics 39, 133 (1962). 

6. Hallinan, M. R., Himmler, W. A. and Kaplan, M., 19th Annual Conf. 

of the Society of Plastic Engineers (Pittsburgh, PA), Preprint 

Book 20-4, 2 (1962). 

7. LeBras, L. R., Society of Plastic Engineers Journalg, 420 (1960). 

78 
ON THE POTENTIALITIES OF POLYPHENYLENE OXIDE (PPO) AS A WET-INSULATION 

MATERIAL FOR CARGO TANKS OF LNG-CARRIERS 

Opschoor, G. 

Nederlands Scheeps-Studiecentrum TNO, Delft, Technische Afdeling, 

Rept. No. 194-M (Jul 1974) 13 pp 

Polyphenylene oxide foam was evaluated as an internal insulation 

for liquefied natural gas tanks. PPO foam consists of elongated open 

cells oriented in a single direction, so that they are open through 

the entire thickness of a layer of foam. When PPO foam is used as 

internal insulation, it is bonded to a tank wall so that one end of 

each open cell is sealed. The other end of each cell remains open to 

the liquid, the cell fills with gas, and gas pressure and capillary 

forces maintain a stable gas-liquid interface at the open end of the 

cell, making a vapor barrier unnecessary. 

The linear expansion coefficients and the tensile, shear, and 

compressive strengths of PPO foam are given, at temperatures of 77 K 

and 293 K and with orientations parallel and perpendicular to cell 

orientation. The thermal conductivity with the cells filled with 

natural gas at 200 K is about 80% higher than that of polyurethane or 

polyvinyl chloride foam. Immersion of the foam in a mixture of LNG 

and higher hydrocarbons for 50 days resulted in greater flexibility 

and reduced thermal stresses. A urethane adhesive withstood the 

50-day immersion without loss of strength. 

For safety reasons, an internal insulation for LNG tankers must 

consist of two insulation layers separated by a vapor barrier. With 

this structure, a failure of either the primary insulation or the tank 

wall does not necessarily become a catastrophic failure. Several 

possible constructions are considered, using PPO as the primary 

internal insulation, bonded to an intermediate vapor barrier of plywood 

or metal. Cost of the PPO makes it unsuitable for the secondary 

insulation contained between the vapor barrier and the tank wall. 

Polyurethane foam, PVC foam, perlite, fiberglass, or balsa wood can be 

used. Calculations of insulation thickness were made for free-standing 

and membrane tanks using PPO as primary insulation, plywood as vapor 

barrier, and polyurethane or PVC foam as secondary insulation. The 

calculations show that polyurethane and PVC foams are nearly equivalent 

insulations, and both are better than PPO foam. The advantage of the 

PPO is in not requiring a vapor barrier. Calculations of thermal 

stresses show that the insulation systems are feasible. The authors 

recommend that research on PPO foam continue. 

Important references: 

1. Knobbout, J. A. and Colenbrander, C. B., Properties of PPO-Foam 

in Regard to its Application as Liquid Hydrogen Tank Insulation. 

C.T.I. Report No. 69-62195 (May 1969) (not published). 

79 
Important references (continued): 

2. Opschoor, G. and van der Brugh, J., Investigation on the Resistance 

of PPO-Foam Against a Mixture of LNG with Heavier Hydrocarbons. 

C.T.I. Report No. 72-05358 (Ott 1972) (not published). 

3. Een eerste Technische Evaluatie van de Toepasbaarheld van PPO-schulm 

als Isolatie in LNG-Tanks. C.T.I. Report No. 72-04515 (Ott 1972) 

(not published). 

80 
EFFECT OF ENVIRONMENT ON INSULATION MATERIALS 

Parmley, R. T. (Lockheed Missiles and Space Co., Sunnyvale, Calif.) 

Space Transportation System 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, 1411-37 (Apr 1971) 

The purpose of this program is to understand environmental effects 

on insulation by exposing 20 candidate insulation materials to 8 

conditions representin 

3 

operational environments. One of the 20 

materials is a 32 kg/m polyurethane foam, a candidate ground-hold 

insulation material. 

The polyurethane foam was exposed to 40% relative humidity at 

366 K, 95% relative humidity at 308 K, salt spray at 95% relative 

humidity and 308 K, water immersion at 294 K, gaseous oxygen at 294 

K and 0.13 N/m2, and prolonged exposure to vacuum at temperatures 

from 21 K to 365 K. The compressive strength of the foam was used as 

a measure of environmental effects. The compressive strength decreased 

after exposure to all of the environments. The greatest decrease was 

caused by exposure to vacuum and high temperature, and exposure to 

high temperature and 40% humidity had nearly as great an effect. The 

least effect was noted after the water immersion. 

81 
EXPERIMENTAL STUDY UNDER GROUND-HOLD.CONDITIONS OF SEVERAL INSULATION 

SYSTEMS FOR LIQUID-HYDROGEN FUEL TANKS OF LAUNCH VEHICLES 

Perkins, P. J.,Jr. 

National Aeronautics and Space Administration, Cleveland, Ohio, Lewis 

Research Center, Tech. Note No; NASA TN-D-2679, 27 pp (Mar 1965) 

Three proposed external insulation systems for liquid hydrogen fuel 

tanks of launch vehicles were applied to flight-weight tanks and tested 

under ground hold conditions. The three systems tested were corkboard 

insulation bonded to,the tank and sealed with a phenolic varnish and a 

mylar film; polyurethane foam hermetically sealed in an aluminum-mylaraluminum laminate vacuum bag, evacuated, and held in place with a nylon 

filament-wound constrictive wrap; and the sealed and constrictively wrapped 

polyurethane foam with a thin film of liquid nitrogen sprayed on the 

surface to reduce heat flow through the insulation. An uninsulated liquid 

hydrogen tank, with and without a natural accumulation of ice and frost, was 

also included in the investigation. Insulation effectiveness was measured 

by recording insulation surface temperature and rate of liquid hydrogen 

boiloff in the tank. 

The corkboard insulation cracked during the cooldown with liquid 

hydrogen, particularly in areas of complicated geometry at the tank ends. 

The sealed and constrictively wrapped foam insulation performed satisfactorily 

although the outer surface showed wrinkling from thermal contraction. Total 

heat flow was about half that with the corkboard insulation. The liquid 

nitrogen spray provided a heat flow through the insulation only one-fifth 

of that without the liquid nitrogen spray. The uninsulated tank showed a 

very high heat influx, 50 times that with the polyurethane foam insulation, 

with considerable liquefaction of air on the walls of the tank. A natural 

accumulation of ice and frost prevented the formation of liquid air on the 

tank surface and cut the heat influx in half. 

The sealed and constrictively wrapped polyurethane foam was the best 

of the insulation systems tested, in terms of insulation effectiveness and 

system weight. 

Important references: 

1. McGrew, J. L., Advances in Cryogenic Engineering 8, 387-92 (1963). 

2. Gray, V. H., Gelder, T. F., Cochran, R. P., and Goodykoontz, 3. H., 

NASA Tech. Note No. NASA TN-D-476 (1960). 

3. Murphy, D. W., and Covington, D. T., Martin-Denver Co., Data Rept. 

No. 1317-61-4 (Aug 1961). 

4. Haskins, J. F., and Hertz, J., Advances in Cryogenic Engineering L, 

353-9 (1962). 

82 
ANALYTICAL HEAT TRANSFER INVESTIGATION OF INSULATED LIQUID METHANE 

WING TANKS FOR SUPERSONIC CRUISE AIRCRAFT 

Pleban, E. J. 

National Aeronautics and Space Administration, Cleveland, Ohio, Lewis 

Research Center, Tech. Note No. NASA TN-D-5641, 37 pp (Jan 1970) 

This report gives a detailed heat transfer analysis of foam 

insulated wing tanks for storing liquid methane fuel in a supersonic 

cruise aircraft. The analysis considered a range of insulation 

thickness from 1.27 to 5.08 cm, insulation density from 32 to 138 

kg/m3, internal tank pressures from ambient to 0.02 MPa, and both 

saturated and initially subcooled methane for typical SST missions with 

cruise Mach numbers of 2.7, 3.0 and 3.5. It was determined that the 

total vented boiloff losses could be kept to less than 1.5 percent of 

the initial fuel for Mach numbers up to 3.5 with wing tank insulation 

thickness of 2.54 cm under the following conditions: 

1) The fuel stored in the wing tanks (assumed to be about l/2 

the total fuel load) is used during the early part of the 

flight. 

2) Either the fuel is initially subcooled 14 K or the saturated 

liquid methane is subjected to a constant internal tank 

pressure of 0.01 MPa. 

It was also determined that due to a higher fuel usage rate 

during the early part of the mission with high cruise Mach numbers, 

increasing the cruise Mach number from 2.7 to 3.5 did not result in 

increased boiloff. 

Loading fuel for 20 minutes into tanks with an initial temperature 

of 294 K and followed by an additional 10 minute ground-hold resulted 

in a boiloff (recoverable) of less than 1.5% of the methane loaded 

into the tanks. The maximum boiloff rate would be less than l/35 of 

the fill rate. It was verified, however, that regardless of the 

insulation thickness, the wing surface temperature depression during 

fill and ground hold can cause moisture to freeze under some weather 

conditions. 

The insulation considered in the analysis was polyurethane foam. 

After the fuel is expended in the wing tanks, the wing and insulation 

temperatures rise rapidly, therefore, it does not appear feasible to 

use currently available polyurethane because of the excessive wing 

tank temperatures. 

Important references: 

1. Whitlow, J. B., Jr., Eisenberg, J. D., and Shovlin, M. D., NASA 

TN-D-3471 (1966). 

83 
Important references (continued): 

2. Chambellan, R. E., Lubomski, J. F., and Bevevino, W. A., NASA 

TN-D-4295 (1967). 

3. Eisenberg, J. D., and Chambellan, R. E., AIAA Paper 68-196 (Feb 

1968). 

4. Weber, R. J., NASA TM-X-1604 (1968). 

5. Moeller, C. E., Loser, J. B., Snyder, W. E., and Hopkins, V., 

Midwest Research Inst. Rept. No. ASD-TDR-62-215 (Jul 1962). 

84 
THERMAL CONDUCTIVITY OF HEAT INSULATING MATERIALS 

Powers, R. W., and Johnston, H. L. 

Ohio State Univ. Research Foundation, Columbus, Cryogenic Lab., Rept. 

No. TR-264-16, Contract No. W33-038-AC-14794(16243), 59 pp (May 1953) 

The insulating properties of a number of insulation materials were 

studied at liquid air and liquid hydrogen temperatures, with a view 

toward gaining information which could result in the development of 

better insulations, particularly for liquid hydrogen propellant tanks. 

Heat flows were measured with insulation materials placed between two 

concentric copper spheres. The space containing the insulation was 

evacuated or filled with hydrogen or nitrogen gas at various pressures. 

The foam materials tested were two urea resin foams, of densities 

14 and 24 kg/m3, and a polystyrene foam of density 26 kg/m3. Heat flows 

and thermal conductivities were measured on the low-density urea resin 

foam in vacuum at mean temperatures from 48 K to 188 K, in hydrogen at 

various pressures at mean temperatures from 49 K to 141 K, and in nitrogen 

at various pressures at mean temperatures from 110 K to 141 K. The higher 

density urea resin foam was measured in vacuum from 99 K to 188 K and in 

hydrogen at 99 K. The polystyrene foam was measured in vacuum from 102 K 

to 190 K and in hydrogen at 141 K. The authors note that, among the 

three foams tested, the low-density urea resin foam has the highest heat 

conductivity and the polystyrene foam has the lowest. 

85 
HEAT TRANSMISSION IN LOW CONDUCTIVITY MATERIALS 

Pratt; A. W. (Aston Univ., Birmingham, England) 

Thermal Conductivity 1, R. P. Tye, Editor. Academic Press, New York, 

301-405 (1969) 

This paper is principally directed toward the measurement of heat 

flow through thermal insulation materials. Before describing the 

methods of measuring heat flow, the paper discusses the mechanisms of 

heat transfer in thermal insulation. This discussion includes a brief 

summary of the typical properties of nine cellular plastics: two 

densities of expanded polystyrene, two densities of expanded polyvinyl 

chloride, foamed urea-formaldehyde; two densities of foamed phenolformaldehyde, and two foamed polyurethanes, one blown with carbon 

dioxide and the other with fluorinated hydrocarbon. The properties 

given are approximate density, thermal conductivity at 283 K, maximum 

temperature recommended for continuous use,. water absorption in seven 

days, and behavior in fire; Thus the information is not particularly 

valuable for cryogenic insulation. The more valuable part of the paper 

is the comprehensive discussion of measurement methods, the' equipment 

used, and precautions necessary for accurate measurements. A reference 

section with more than 120 citations concludes the paper. 

86 
THERMAL CONDUCTIVITY OF WET-WALL LIQUID HYDROGEN STORAGE TANK 

INSULATIONS FOR SPACE APPLICATIONS 

Raw&a, .A. C., and Yundt, C. G. (Douglas Aircraft Co., Santa Monica, 

Calif.) 

Cryogenic Engineering in the Aerospace Industry, Proc. Symp., National 

Meeting, 56th (San Francisco, Calif., May 16-19, 1965). Chemical 

Engineering Progress Symp. Series 62, No. 61, 1966. American Institute 

of Chemical Engineers, New York, 219-24 (1966) 

Foamed plastic insulation systems have been used successfully as 

internal insulation in liquid hydrogen tanks. To predict performance 

of such systems, it was necessary to measure the thermal conductivity 

of the composite insulation under simulated design conditions. This 

paper describes the measurements, and reports changes in thermal 

conductivity of the insulation during exposure to liquid hydrogen. 

The composite insulation consisted of foam bonded to the internal 

surface of the metal-walled liquid hydrogen tank, with a reinforced 

plastic liner laminated over the foam as a barrier to hydrogen diffusion. 

Two types of polyurethane foam were used, one reinforced with glass 

threads foamed in place at uniform spacings and oriented along the 

three principal directions. The foam was bonded to aluminum plate with 

epoxy adhesive. The barriers consisted of various weaves and weights 

of glass cloth, sometimes in combination with an aluminum-polyesteraluminum film sandwich, laminated to the foam and sealed with epoxy or 

polyurethane resin. 

Tests consisted of measurements of thermal conductivity of 

insulation samples held between a 20 K cold side and a 300 K hot side. 

Samples were exposed directly to liquid hydrogen at various pressures 

for various times, to find the effects on the thermal conductivity. It 

was found that thermal conductivities increased with pressure and with 

time, indicating changes in the composition of the gaseous phase in the 

foam. Differences in foam density produced small differences in thermal 

conductivity, while variations in liner materials produced much larger 

differences. These effects are explained by hydrogen diffusion through 

the barrier layer into the foam. Air, which had originally diffused 

into the foam, migrates to the cold side and condenses leaving a partial 

vacuum into which the hydrogen diffuses. The ,thermal conductivity 

eventually approaches that for hydrogen gas. After long exposure to 

liquid hydrogen, analysis of the gas within the foam confirmed the 

presence of nearly pure hydrogen gas with traces of air. 

The authors conclude that improvements in thermal conductivity of 

internal insulation can be achieved by controlling gaseous diffusion, 

and this depends on the choice of the least permeable liner material. 

87 
Important references: 

1. Skochdopole, R. E., Chem. Eng. Progr. 57, No. 10, 55 (1961). 

2. Lindsay, A. L., and Bromley, L. A., Ind. Eng. Chem. 42, 1508-U 

(1950). 

88 
TENSILE PROPERTIES OF POLYURETHANE AND POLYSTYRENE FOAMS FROM 76 TO 

300 K 

Reed, R. P., Arvidson, J. M., and Durcholz, R. L. (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, 184-93 (1973). 

Polyurethane and polystyrene foams have low thermal conductivity 

and correspondingly low density and are thus useful for cryogenic 

insulation purposes. Their low cost, ease of molding and application 

are also positive factors. Increasingly, foam use in cryogenic 

applications requires load-carrying capacity. For efficient design in 

these cases, mechanical property information is needed. The literature, 

however, contains very little reliable and reproducible mechanical 

property data. This paper reports tensile data (transverse and 

longitudinal) at 76 K, 195 K and 300 K. The specific properties 

measured were modulus of elasticity, proportional limit, yield strength, 

tensile strength and percent elongation. 

The foams tested in this work included 17 densities of polyurethane 

(124.64 kg/m3 to 30.6 kg/m3) 

kg/m3 to 52.23 kg/m3). 

and two densities of polystyrene (100.12 

The results are given as averages, with each 

data value representing the average of about four tests. Variations for 

the various properties were + 5 percent to + 10 percent for tensile 

strength, with the variation-due mainly to material inconsistency. The 

results showed that the modulus of elasticity, yield strength and 

tensile strength increased with decreasing temperature, while the 

elongation decreased. Strength and modulus were found to be approximately linearly dependent on density; however, at low temperatures the 

density dependence was greater. Specimens whose long axis was cut 

parallel to the cell rise direction were stronger than those whose long 

axis was cut normal to the cell rise direction. A companion paper 

abstracted on page 4 on compressive properties compares the tensile 

and compressive results. 

Important references: 

1. Reed, R. P., Durcholz, R. L., and Arvidson, J. M., Advances in 

Cryogenic Engineering 2, 37-45, Plenum Press (1971). 

2. McClintock, R. M., SPE J. 2, 36 (1958). 

3. Doherty, D. J., Hurd, R., and Lester, G. R., Chemistry and 

Industry (London), p. 1340 (Jul 1962). 

4. Kreft, H., and Wagner, D., 

(1969). 

Kaltetechnik-Klimatisierung 2, 258 

5. Patel, M. R., and Finnie, I., UCRL Rept. No. 13193, Inst. Engr. 

Res., California Univ., Berkeley (1965). 

89 
LOW-TEMPERATURE TENSILE PROPERTIES OF POLYETHYLENE TEREPHTHALATE 

MULTIFIBER YARN AND POLYSTYRENE FOAM 

Reed, R. P., Durcholz, R. L., and Arvidson, J. M. (National Bureau 

of Standards, Boulder, Colo. Cryogenics Div.) 

Advances in Cryogenic Engineering 16, Proc. Cryogenic Engineering 

Conf. (Colorado Univ., Boulder, June 17-19, 1970); Plenum Press, 

New York, 37-45 (1971) 

Polystyrene foam is used extensively as an insulating material in 

cryogenic applications. In many applications, knowledge of the temperature dependence of the tensile strength and modulus is beneficial. 

Foam properties are dependent on density, method of forming (mold or 

extrusion), and, very probably, on the conditions of forming. The foam 

data reported in this study were produced by a process using dry nitrogen 

gas and pre-expanded polystyrene beads. The tensile data indicate that 

polystyrene foam fabricated in this way is considerably stronger than 

any types tested previous to this study. Tensile strength, yield 

strength, percent elongation and modulus of.elasticity data were taken 

on two densities of foam (0.094 and 0.051 g/cm3) at temperatures of 20 K, 

76 K, 195 K and 295 K. In both sample densities the tensile strength 

increased as the temperature was lowered. The denser foam had higher 

strength, the average strength at 295 K was 1.3 MPa and at 20 K it was 

2.1 MPa. The lower density foam had a tensile strength average at 295 K 

of 0.74 MPa and at 20 K of 1.4 MPa. In both cases the load rate was 

0.013 cm/min. The tensile strength of the foam samples was of the order 

of twice as great as that of previously reported tests. The paper 

also includes results for the tensile properties of polyethylene 

terephthalate yarn from 4 K to 295 K. 

Important references: 

1. Griffin, J. D. and Skochdopole, R. E., Engineering Design for 

Plastics (ed. E. Baer), Reinhold Publishing Co., N. Y. (1964) 995 p. 

2. McClintock, R. M., SPE J., 14, 36 (1958). 

3. Phillips, T. L. and Lannon, D. A., British Plastics 34, 236 (1961). 

4. Brown, W. B., Plastics Progr. 1959, 149 (1960). 

5. Cooper, A., Plastics Inst. Trans. (London) 26, 299 (1958). 

6. Cooper, A., Plastics Inst. Trans. (London) 2, 39 (1961). 

90 
HEAT INSULATION IN THE SEA TRANSPORT OF LNG 

Richard, L. (Gaz de France, Paris) 

Rev. Prat. Froid 23, No. 284, 15-21 (Jan 1970) 

This French paper discusses the types of insulation used in LNG 

tankers. The primary materials have been perlite and balsa wood, but 

polyvinyl chloride foams have received some use, and polyurethane foams 

have shown some promise. 

The PVC foams for LNG tankers have had to satisfy specifications 

on density, compressive strength, heat transfer coefficient, and water 

absorption. In addition, because of the conditions on shipboard, a test 

of vibration resistance under load and high temperature gradient was 

devised. The foam must withstand the test conditions without cracking 

or deterioration of its physical properties. PVC foam was used on the 

"Jules Verne" to insulate the tank walls and the secondary barrier. It 

was also used to insulate the cryogenic piping, and a protective coating 

of glass cloth reinforced polyester resin proved to be satisfactory 

protection against weather and sea action. The paper lists one LNG 

tanker using PVC foam as supporting insulation and secondary barrier 

insulation, and four other tankers using PVC foam as the insulation of 

self-supporting tanks. 

The polyurethane foams are described as having characteristics 

similar to the PVC foams, and as having the additional advantage of 

foaming in place. However, the polyurethanes are described as being 

susceptible to cracking in the vibration test, because their relatively 

high thermal contraction causes internal strains when the foam is 

subjected to high thermal gradients. Foaming .in place is inexpensive, 

but it is difficult to obtain a homogeneous material with controlled 

properties. 

The author notes that the final choice of insulation material for 

LNG tankers is decided by economic factors. 

91 
ENERGY-ABSORBING CHARACTERISTICS OF FOAMED POLYMERS 

Rusch, K. C. (Ford Motor Co., Dearborn, Mich. Scientific Research 

Staff) 

J. Appl. Polym. Sci. l-& No. 6, 1433-47 (Jun 1970) 

This paper discusses a property of foams which is not generally 

considered in insulation systems. While impact energy absorption is 

not usually a critical property of insulation, it is related to the 

flexibility or brittleness of the material, which is a critical property 

for cryogenic insulation. Energy absorption characteristics also 

provide a measure of how fragile an insulation will be. 

The energy absorption characteristics can be calculated from 

experimental compressive stress-strain data at slow compression rates. 

The calculated quantities are the energy-absorbing efficiency, the 

impact energy per unit volume, and the maximum decelerating force on an 

impacting body. An analytical scheme for determining these quantities 

is given, and calculations for two polyurethanes, at 77 K and 298 K, 

were carried out. The paper uses the results to illustrate the 

differences between flexible and brittle foams. A curve of efficiency 

versus impact energy has a higher peak for brittle than for flexible 

foam. A curve of maximum deceleration has a wider and flatter plateau 

for brittle than for flexible foam. Both of these effects are more 

pronounced for a higher density foam. In terms of impact-energy 

absorption, a brittle foam is superior to a flexible foam. Other 

factors in designing an energy-absorbing foam structure are also 

considered in the paper. 

92 
INVESTIGATION OF FABRICATION AND PROCESSING PARAMETERS ASSOCIATED 

WITH USE OF POLYURETHANE FOAMS IN SEALED CRYOGENIC INSULATION 

Shriver, C. B. 

Goodyear Aerospace Corp., Akron, Ohio, Rept. No. R-12249. National 

Aeronautics and Space Administration, Cleveland, Ohio, Lewis Research 

Center, Rept. No. NASA CR-72025, Contract No. NAS 3-5646, 85 pp 

(Jun 1965) 

The sealed insulation consisted of a number of layers of aluminized 

mylar film separated by thin layers of polyurethane foam, with the 

composite structure enclosed in a vapor barrier. The insulation was 

self-evacuating when residual gases inside the vapor barrier were 

condensed at the cold wall. The experimental program was directed 

toward foam optimization by increasing the hole area in perforated 

foam, pretreating foam to reduce outgassing, developing a rigid open 

cell foam, and selecting foam with the best compression characteristics. 

Foam separators with various open areas in various patterns of 

perforations were used to separate aluminized mylar films, and contact 

between films was monitored as a function of open area and applied 

pressure. Electrical contact between aluminized films was used as a 

conservative indication of thermal contact between films in the 

insulation. Separators with less than about 40% open area prevented 

contact between films at pressures of 100 kN/m2. Multi-layer samples 

were made up using the most promising separator configurations, and 

sent out for thermal conductivity tests. Results of these tests are 

not given in this report. 

Four polyurethane foams, three open cell and one closed cell, 

were tested for outgassing in vacuum and in vacuum at 422 K. Weight 

losses in vacuum alone ranged from 0.65% to 1.4%, and at 422 K were as 

high as 2.2%. The open cell foams lost weight faster than the closed 

cell foams. Attempts to rigidize flexible open cell foams by chemical 

treatment had limited success, but vendors supplied rigid open cell 

polyurethane foams. Compression test samples of one closed cell and 

three open cell rigid foams were made up of ten layers of foam 

alternating with nine layers of mylar film. Compression tests at room 

temperature and 77 K showed that all specimens showed elastic recovery 

at both temperatures after release of a 100 kN/m2 load, and that 

compressive modulus increased with decreasing temperature. The closed 

cell foam was more rigid than the open cell foams. The best open cell 

foam showed a yield point at a load more than double the maximum 

pressure on self-evacuated insulation panels. 

The report also gives permeability and outgassing test results 

on vapor barrier materials. 

93 

I 
THE THERMAL CONDUCTIVITY OF FOAMED PLASTICS 

Skochdopole, R. E. (Dow Chemical Co.) 

Chem. Eng. Progr. 57, No, 10, 55-9 (Ott 1961) 

The effects of the properties of foamed plastic insulations on the 

mechanisms of heat transfer are thoroughly analyzed. Results of the 

analyses are confirmed by comparison with literature data. Data were not 

available on the effects of foam cell size on convection heat transfer, so 

an experimental program was conducted on polystyrene foams with cell sizes 

varying-from 0.6 to 6.0 mm. It was found that there was no convection 

effect with cell diameters less than about 4.0 mm. 

The analysis shows the effects on thermal conductivity of changing 

foam density, cell size, polymer composition, and gas phase composition. 

While each of these factors can affect the thermal conductivity, the most 

important variable is the gas phase composition. The environmental 

effects of aging and temperature are shown to be mostly caused by changes 

in the composition of the gas phase. In aging, the gas phase changes by 

diffusion through cell walls. Temperature changes can change the 

composition of the gas phase by condensing or changing the vapor pressure 

of the foam blowing agent in the cells. 

The aging model was verified by an experimental program, in which 

the thermal conductivity of a trichlorofluoromethane-blown polyurethane 

film was measured at intervals over a period of 206 days of aging in air 

at 333 K. After the aging period, the foam was mechanically compressed, 

then re-expanded by heating. After three such cycles, the foam cells 

were open and filled with air. The thermal conductivity was again 

measured, and the contributions of air and foam were calculated. A 

calculation based on the contribution of the foam and the thermal 

conductivity of the blowing agent agreed with the measured thermal 

conductivity of the foam before aging. 

Important references: 

1. Wilkes, G. B., Heat Insulation, Wiley, New York (1950). 

2. Rowley, F. B., Jordan, R. C., and Lander, F. M., Refrig. Eng. 50, 

541 (1954). 

94 
MEASUREMENT OF THE COMBINED EFFECTS OF NUCLEAR RADIATION AND 

CRYOTEMPERATURES ON NON-METALLIC SPACECRAFT MATERIALS 

Smith, E. T. (General Dynamics/Fort Worth, Tex.) 

AIEE Summer General Meeting (Toronto, Canada, Jun 17-21, 1963), Paper 

No. CP 63-1175, 36 pp (1963) 

This paper presents the experimental results of a program to 

measure the combined effects of nuclear radiation and cryogenic 

temperatures on the mechanical (tensile and compressive) properties of 

nonmetallic structural materials for use in nuclear-powered spacecraft. 

The materials tested included two adhesives, two mechanical seal 

materials, two thermal insulations, two electrical insulation materials 

and a structural laminate. The materials were tested at ambient 

conditions, at 20 K, and at 77 K at zero radiation and up to 6 x lo6 J/kg. 

The irradiation and subsequent testing were done without warming the 

sample, so that no chance was given for annealing out the radiation 

induced defects. 

The two thermal insulations tested were a polyurethane foam and a 

polystyrene foam and both were tested with compressive loads only and 

compressive strength (unirradiated) increased with decreasing temperature 

although the polyurethane showed some degradation in going from 77 K to 

20 K. Radiation levels decreased the compressive strength of both 

materials at ambient temperature but a threshold level between 5 x 105 

J/kg and 0.2 x lo6 J/kg was indicated at the lower temperatures. 

Radiation, up to this level, increased the compressive strength at 77 K 

and 20 K. Above these radiation dose levels, however, the strength 

dropped off severely. Any level of irradiation at ambient temperature 

served to reduce the compressive strength significantly. Both materials 

are recommended for use under relatively low radiation environments at 

cyrotemperatures. Most of the results of this paper are used by 

different authors in the paper abstracted on page 70. 

Important references: 

1. General Dynamics/Fort Worth, Tex. Rept. No. MR-N-254 (May 1961). 

2. General Dynamics/Fort Worth, Tex. Rept. No. FZK-142 (Mar 1962). 

3. General Dynamics/Fort Worth, Tex. Rept. No. FZK-147 (Jun 1962). 

4. General Dynamics/Fort Worth, Tex. Rept. No. FZK-152 (Aug 1962). 

5. General Dynamics/Fort Worth, Tex. Rept. No. FZK-161-2 (Jan 1963). 

95 
MEASURING THE THERMAL CONDUCTIVITY OF IRRADIATED FOAM-TYPE INSULATION 

MATERIALS 

Smith, E. T., and Miller, R. E. (General Dynamics/Fort Worth, Tex.) 

Advances in Cryogenic Engineering 12, Proc. Cryogenic Engineering Conf. 

(Boulder, Colo., Jun 13-15, 1966), K. D. Timmerhaus, Editor. Plenum 

Press, New York, 315-21 (1967) 

This paper reports results of measurements made on four foam 

insulations at room, liquid nitrogen and liquid hydrogen temperatures. 

Control samples in unirradiated conditions were compare 

samples subjected to gamma doses from 5 x lo5 to 3 x 10 zi with irradiated 

J/kg. The 

tests were performed as part of a program to select candidate materials 

for nuclear powered space vehicles. Organic materials are particularly 

vulnerable to radiation and deserve special attention. Insulating 

materials and insulation systems, because of the importance of their 

functions, were prime candidates for early assessment. 

The four materials were polyurethane (polyether-polyester rigid 

foam, manufacturers designation CPR-200-2), polyurethane (polyether, 

rigid, halocarbon blown, manufacturers designation H-1502), epoxy 

(rigid, spray foamed, manufacturers designation EFS-175) and polyurethane 

(rigid foam, CO2 blown, manufacturers designation CPR-1021-2). Tabular 

results for all four materials at room and liquid nitro en temperatures 

are given for radiation levels of zero, 5 x 10 5,lxlO and3x106 g 

J/kg. These results show that changes in the thermal conductivity of 

the four test materials as a result of the irradiation were slight to 

insignificant to the highest dose level achieved. The data obtained 

in the liquid hydrogen tests, both control and post irradiation, are 

questionable. The measured values of thermal conductivity are higher 

than expected and it was concluded that either the cell gases froze out 

completely, or a hydrogen leak occurred. 

This paper contains a more detailed description of the thermal 

conductivity work reported in the paper abstracted on page 44. 

96 
COMPRESSIVE LOAD-DEFLECTION CHARACTERISTICS OF SEVERAL FOAM MATERIALS 

AT ROOM TEMPERATURE, 77 K AND 4.2 K 

Stewart, W. F., Eash, D. T., and May, W. A. (Los Alamos Scientific 

Lab., N. Mex.) 

Advances in Cryogenic Engineering 2, Proc. Cryogenic Engineering Conf. 

(Georgia Inst. of Tech., Atlanta, Aug 8-10, 1973), K. D. Timmerhaus, 

Editor. Plenum Press, New York, 385-92 (1974) 

This report gives results of an experimental program to measure the 

compressive properties of candidate foam materials used as a rigid 

support for the primary coil of a 300 kJ superconducting energy storage 

coil. The coil is a model for a pulsed plasma thermonuclear fusion 

energy source. At the levels of current and voltage involved, large 

transient forces can be produced by misalignment of the primary and 

secondary coils. A foam pad (flexible at room temperature but rigid at 

4.2 K) was considered to be a better means of adapting the coil supporting 

arms to the inner shell of the cryostat than springs or other mechanical 

or pneumatic (gaseous helium) damping systems. 

I 

The materials tested included various densities of gas-blown 

flexible polysiloxane foam, a polyether based flexible polyurethane, a 

proprietary flexible cellular silicone, and a low density rigid 

polystyrene foam. The results are presented as curves of load versus 

deflection at room temperature and 77 K with a few tests conducted at 

4.2 K. Little difference was seen in the compressive tests at 77 K and 

4.2 K. All of the candidate materials performed quite well and none of 

them were observed to crack or break during testing. One polysiloxane 

and a cellular silicone were compressively loaded to over 11.8 x lo7 N/m2 

at 77 K and did not exhibit any sudden shifts in deflection. Following 

the 77 K test, the load-deflection data at room temperature were 

essentially the same as before the test. The report does not make a 

final recommendation as to the material to be used. 

Important references: 

1. Arvidson, M. J., Durcholz, R. L., and Reed, R. P., Advances in 

Cryogenic Engineering 18 (1972). - 

97 
LOW-DENSITY FOAM FOR INSULATING LIQUID-HYDROGEN TANKS 

Sumner, I. E. 

National Aeronautics and Space Administration, Cleveland, Ohio, Lewis 

Research Center, Tech. Note No. NASA TN-D-5114, 52 pp (Mar 1969) 

The objective of this investigation was to develop and test a 

lightweight polyurethane foam insulation for liquid hydrogen tanks of 

space vehicles that 1) could be foamed in place on the outside of the 

tank, 2) would not require any strengthening or reinforcing to prevent 

cracking and splitting when cooled to liquid hydrogen temperature, and 

3) would have a thermal conductivity of approximately 0.015 J/m*K at a 

mean temperature of 135 K. 

Three 0.56 m diameter aluminum spherical tanks having wall 

thicknesses of 0.056 cm were insulated with a 2.54 cm thick, rigid, 

freon-blown, polyurethane foam with a nominal density of 32 kg/m3. 

Two tanks were insulated using a foaming-in-place process with each 

tank suspended in a cylindrical mold. The third tank was insulated 

with a slightly different polyurethane formulation and simplified 

foaming-in-place process where the foam constituents were poured 

directly on the tank wall and allowed to expand in a radial direction. 

Testing of the insulated tank assemblies included 1) cooldown 

and boiloff tests to determine insulation temperature profiles, thermal 

conductivity and structural integrity under simulated ground-hold 

conditions, 2) vibratory compressive tests under simulated ground-hold 

and launch conditions, and 3) cooldown tests for simulated space-hold 

conditions where the entire foam thickness was cooled to temperatures 

near that of liquid hydrogen (21 K). 

The initial (first two tanks) foaming-in-place process produced 

an unsatisfactory insulation, where the direction of foam rise relative 

to the tank wall varied from top to bottom, and which failed 

structurally under both ground-hold and space-hold conditions. The 

simplified process used on the third tank produced a satisfactory 

insulation in which the direction of foam rise was normal to the tank 

wall at all locations, which had uniform cell size and structure and 

which exhibited relatively uniform physical properties. The 

insulation fabricated with this process provided the desired thermal 

performance and remained structurally intact through all ground-hold, 

vibratory and space-hold tests. 

Small samples of the insulation were used to measure the thermophysical properties of the insulation material itself. Graphical 

results are presented for compressive yield strength, compressive 

modulus of elasticity, tensile yield strength, tensile modulus of 

elasticity, shear modulus of elasticity, thermal contraction and 

thermal conductivity. 

98 
Important references: 

1. Dearing, D. L., Advances in Cryogenic Engineering I-& 89-97 (1968). 

2. Hammond, M. B., Jr., Chem. Eng. Progr. Symp. Ser. 62, No. 61, 

213-8 (1966). 

3. Lewis Research Center Staff, NASA TN-D-2685 (1965). 

4. Sterbentz, W. H., and Baxter, J. W., Lockheed Missiles and Space 

co., Rept. No. LMSC-A7944993, Vol 2 and NASA CR-54879, Vol 2 (Nov 

1966). 

5. Haskins, J. F., and Hertz, J., Advances in Cryogenic Engineering 

L, 353-9 (1962). 

6. Sweet, H. S., and Steele, A. J., Lockheed Missiles and Space Co., 

Rept. No. LMSC-A709158 and NASA CR-59622 (1964). 

99 
THE APPLICATION OF RIGID CELLULAR P.V.C. AS AN INSULANT FOR VERY LOW 

TEMPERATURES 

Tachdjian, N. (Ste Kleber Colombes Plastiques, France) 

Bull. IIR Annexe 1965-6, Meeting of Comm. 8 (Sweden, Sep 13-17, 1965), 

369-79 (1965) 

This paper reviews polyvinyl chloride (PVC) rigid foam, its 

properties, and its application as thermal insulation. The problems of 

cracking and of creep are discussed at some length. Cracking results 

from differential thermal contraction between a foam insulation and facing 

or base materials attached to the foam. If the foam is not free to 

contract during cooling, it may crack. The best solution to the problem 

is described as application of the foam in such a way that it is left 

free to contract. Another solution is to increase the density of the foam 

in areas of potential cracking, to the point where the foam itself can 

sustain the loads imposed by thermal contraction. Tests for creep 

tendency are described as only partially complete. Creep characteristics 

are not necessarily constant with time, so that extrapolation from 

short-term tests can be disastrous. PVC foam is described as having very 

slow creep at temperatures below 278 K, and no detectable creep at 

temperatures below 238 K. 

An appendix compares some of the properties of PVC foam with other 

foams. Approximate densities and thermal conductivities at a mean 

temperature of 273 K are tabulated. A nomogram gives the thermal 

conductivity of PVC foam as a function of hot face and cold face 

temperatures. Water vapor permeabilities and tensile and compressive 

strengths are tabulated. In most cases, PVC foam is shown as having 

superior properties. 

100 
KLEGECELL THERMAL INSULATION FOR LIQUID HYDROGEN TANK OF CRYOGENIC 

STAGE 

Tariel, H. M., Boissin, J. C., Segel, M. P. (Societe L'Air Liquide, 

Centre d'Etudes Cryogeniques, Sassenage, France) 

Advances in Cryogenic Engineering 12, Proc. Cryogenic Engineering Conf. 

(Boulder, Colo., Jun 13-15, 1966), K. D. Timmerhaus, Editor. Plenum 

Press, New York, 274-85 (1967) 

Polyurethane foam insulation for liquid hydrogen tanks of spacecraft 

has the disadvantage that the cell walls are permeable, to air in the 

case of external insulation, and to hydrogen for internal insulation. 

Polyurethane foam also has relatively low mechanical strength. A rigid 

crosslinked polyvinyl chloride foam is proposed as a solution to these 

problems. 

Two densities of PVC foam, 30 and 55 kg/m3, were tested. The tests 

were tensile strength and modulus at 20 K, 77 K, and 300 K; compressive 

strength and modulus at 20 K, 7PK and 300 K; thermal contraction 

between 20 K and 373 K; permeability to air before and after exposure 

to liquid hydrogen; impact sensitivity in liquid oxygen; thermal 

conductivity between a surface at 20 K and a surface at 77 K to 345 K; 

and specific heat from 20 K to 300 K. The higher density material had 

higher tensile and compressive strengths. Tensile strengths decreased 

gradually with decreasing temperature. Compressive strengths decreased 

gradually with decreasing temperature to 77 K, then increased sharply at 

20 K. Permeability to air was too small to measure. No reactions were 

observed with impact in liquid oxygen. Thermal conductivity increased 

non-linearly with increasing temperature from 0.007 W/m-K at 50 K to 

0.027 W/m-K at 300 K. Specific heat followed an S-curve with a maximum 

near 50 K and a minimum near 150 K. 

The proposed insulation system consists of the foam bonded to the 

outside of the tank wall with a polyurethane adhesive, and a constrictive 

fiberglass-polyurethane laminate wrapped over the foam as protection from 

vibration and external stresses, and a final external coating of 

ablative material as protection against atmospheric heating during launch. 

Sample small scale tanks insulated as proposed were reported to have 

withstood thermal cycling with liquid hydrogen, with no observable 

damage. 

Important references: 

1. Dearing, D. L., Advances in Cryogenic Engineering 11 89-97 (1966). ---3 

2. Middleton, R. L., Advances in Cryogenic Engineering 10, 216-23 

(1965). 

3. NASA-Lewis Research Center, Tech. Note No. NASA-TN-D-2685. 

101 

I 
INTERNAL INSULATION FOR LNG 

Tatro, R. E., and Bennett, F. O., Jr. (General Dynamics, San Diego, 

Calif. Convair Div.) 

Advances in Cryogenic Engineering 20 (Presented at National Technical 

Meetings during 1973 and 1974), K.5. Timmerhaus, Editor. Plenum 

Press, New York, 315-26 (1975) 

This paper describes the gas-layer-insulation concept, the 

polyphenylene oxide (PPO) foam that accomplishes the concept, the properties of PPO as evaluated for aerospace applications, and the possibilities 

of using PPO as internal insulation for the tanks of liquefied natural 

gas tanker ships. 

PPO foam is made up of parallel elongated open cells, oriented so 

that the cells are open through a layer of the foam. When the foam is 

bonded to a tank wall, so that the wall seals one end of the cells, and 

the tank is filled with a cryogenic liquid, the cells fill with vapors 

of the liquid, and gas pressure and surface tension prevent liquid from 

entering the cells. This forms an ingulating stagnant layer of gas 

between the liquid and the tank wall. The properties of PPO foam 

discussed in the paper are the effects of thermal aging at 450 K and 

thermal cycling from 21 K to 450 K, density and uniformity of the foam, 

lateral permeability as a function of foam density and pressure drop, 

thermal conductivity as a function of density from 50 K to 190 K, 

compressive and tensile yield strengths in longitudinal and lateral 

directions as a function of foam density from 20 K to 400 K, and 

compatibility with liquid ethane and liquid methane. 

Internal insulation in LNG tankers would have a number of advantages. 

Because the tank wall remains warm, structures and materials are less 

critical, heat leak due to structural supports is decreased, and less 

LNG is required for cooldown because the tank structure is not cooled. 

PPO foam, being open-celled, would not trap vapors and could be more 

easily purged than closed-cell foams, reducing the possibility of fires 

such as occurred in the Staten Island disaster. PPO. foam is considered 

a promising candidate for internal insulation for LNG tankers. 

Important references: 

1. Yates, G. B., Advances in Cryogenic Engineering 20, 327 (1975). 

2. General Dynamics, Convair Division Rept. NO. GOCA 632-3-169, 

Contract NAS g-27203 (Feb 15, 1973). 

102 
I 

MEASUREMENTS OF HEAT TRANSMISSION IN THERMAL INSULATIONS AT CRYOGENIC 

TEMPERATURES USING THE GUARDED HOT PLATE METHOD 

Tye, R. P. (Dynatech R/D Co., Cambridge, Mass.) 

Progress in Refrigeration Science and Technology 1, Proc. International 

Conf., XIII (Washington, D. C., 1971). AVI Publishing Co., Inc., 

Westport, Conn., 371-8 (1973) 

The thermal conductivities of five types of commercial insulating 

materials were measured. The materials tested were foamed glass, 

polyurethane foam (2 densities), polyvinyl chloride foam (4 densities 

and 2 blowing agents), vermiculite (3 grades), and a fiberglass blankettype insulation. Thermal conductivities were measured in the temperature 

range from 120 K to 300 K, with some measurements on vermiculite near 

90 K. A guarded hot plate apparatus was used and an accuracy of 3 percent 

is claimed for the results. 

The two polyurethanes behaved identically over the temperature 

range, with an s-shaped curve having a maximum near 240 K and a 

minimum near 260 K. The PVC foams generally showed a steadily increasing 

thermal conductivity with increasing temperature. While the polyurethanes 

had lower thermal conductivities than the PVC foams at temperatures 

above 270 K, the inflected curve resulted in the PVC foams having 

conductivities 11% to 20% below the polyurethanes at temperatures below 

230 K. The other materials had thermal conductivities substantially 

above the foams, increasing through the fiberglass blanket and the 

foamed glass to the three grades of vermiculite. Of the materials tested, 

the lowest thermal conductivity at cryogenic temperature is observed for 

the PVC foams. 

Important references: 

1. Thermal Insulation Systems, NASA SP-5027 (1967). 

2. Dushman, S., Vacuum Technique, John Wiley & Sons, New York, 50 (1945). 

3. Haskins, J. F., and Hertz, J., Advances in Cryogenic Engineering 7, 

353 (1962). 

4. Tariel, H. M., Boissin, J. C., and Segel, M. P., Advances in 

Cryogenic Engineering 12, 274 (1967). 

103 
SOME OBSERVATIONS ON THE COEFFICIENT OF THE THERMAL EXPANSION OF 

PCLYSTYRENE FOAMS AT LOW TEMPERATURE 

Vahl, L. (Technische Hogeschool, Delft, Netherlands) 

Progress in Refrigeration Science and Technology, Proc. International 

Congress of Refrigeration, Xth (Copenhagen, Denmark, 1959) - Vol 1. 

Pergamon Press, 317-24 (1960) 

Polystyrene foam panels used as insulation for low temperature 

equipment developed cracks after a period of operation. The cracks were 

thought to be caused by thermal stresses, but data on thermal contraction 

at low temperatures were not available. An experimental program was 

conducted to measure coefficients of thermal expansion. 

Closed cell polystyrene foams of 12.4, 24.3, and 37.5 kg/m3 

densities were measured during cooling from 288 K to 123 K over a period 

of 3 h, hold at 123 K for 1 h, then rewarming to 288 K. The lowestdensity foam had a relatively large thermal contraction, and contraction 

per degree of cooling was greater at lower temperatures. The contraction 

continued even during the period of hold at constant‘temperature. The 

sample exhibited a hysteresis effect, with the dimensional changes 

following different curves with respect to temperature during cooling 

and warming. The two higher-density foams behaved differently. The rates 

of thermal contraction were lower and remained constant over the 

temperature range, there was no dimensional change during hold at 123 K, 

and there was little or no hysteresis effect. 

The author attributes the behavior of the lowest-density foam to 

differential thermal contraction of polystyrene in the cell walls and 

air contained in the cells. The greater contraction of the air apparently 

caused a breakdown of the cell walls. This breakdown continued as a 

sort of creep during hold at constant temperature. The destruction 

caused by thermal contraction makes foam of this density unsuitable for 

use as insulation at temperatures below about 230 K. Further examinations 

were recommended to determine whether the higher-density foams could be 

used below this temperature. 

104 
VESSELS FOR LIQUEFIED GASES FORMED FROM POLYSTYRENE FOAM PSB 

Vedernikov, M. V., Filippov, V. A., and Krivets, L. I. (Academy of 

Sciences of the USSR, Leningrad. Inst. of Semiconductors) 

Cryogenics 2, No. 5, 386-7 (Ott 1969) 

This paper describes, in detail, a method for producing cryogenic 

containers from foamed polystyrene PSB (polystyrene beads). The method 

can be used in the laboratory with very little equipment and is 

particularly useful in forming vessels of large sizes or complex shapes 

where glass flasks are impractical. Experiments by the authors showed 

that the consumption of liquid nitrogen when using a foamed plastic 

vessel, even with comparatively little heat conduction in the casing of 

the submerged device, exceeds by only 35-50% its evaporation from a 

glass vessel of the same shape and volume. When more massive devices 

are cooled, this difference practically disappears. 

The process of fabricating vessels of foam consists of three 

stages: 1) prefoaming the polystyrene beads in boiling water (they 

expand lo-30 times normal size), 2) curing of the prefoamed beads (in 

air at ambient temperatures), 3) molding, wherein the preformed beads 

are placed in the mold which is immersed in boiling water. This causes 

further expansion of the beads. The article is then removed from the 

mold and allowed to cool under ambient conditions. 

105 
OPEN CELL CRYOGENIC INSULATION 

Yates, G. B. (General Dynamics, San Diego, Calif. Convair Div.) 

Advances in Cryogenic Engineering 2, Proc. Cryogenic Engineering 

Conference (Boulder, Colo., Jun 17-19, 1970), K. D. Timmerhaus, Editor. 

Plenum Press, New York, 128-37 (1971) 

The open-cell insulation concept was considered for use as internal 

insulation in the liquid hydrogen tanks of reusable space vehicles, such 

as the space shuttle. In this concept, narrow open cells are bonded 

to the tank wall at one end and open to the tanked liquid at the other. 

The cells are sized so that surface tension maintains a stable interface 

between liquid in the tank and gas in the cell. This paper describes 

an analysis and some preliminary tests of the concept. 

The analysis showed that the open-cell concept has a lower thermal 

efficiency than previous closed-cell insulations, and about the same 

efficiency as a helium-purged system. The thermal conductivity of the 

insulation is essentially that of the gas filling the cells. Theoretical 

cell sizes to support stable interfaces with water, liquid hydrogen, 

liquid oxygen, and liquid nitrogen were calculated. 

The three open-cell insulations tested were polyphenylene oxide 

(PPO) foam and two sizes of phenolic honeycomb. The larger cell-size 

honeycomb was faced with fine-mesh screen or filled with the PPO foam 

to maintain stable liquid/gas interface. Screening tests were run with 

insulation bonded to the bottom of an open beaker, which was then filled 

with liquid hydrogen. Larger scale tests used the insulation bonded to 

the inner surfaces of a rectangular 0.21 m3 tank, filled with liquid 

hydrogen or liquid nitrogen. In all cases, the PPO foam was the lightest 

and most efficient of the insulations. Ability of the honeycomb to 

maintain a stable liquid/gas interface was marginal in some cases. 

Convection heat transfer was appreciable in the honeycombs but not in 

the PPO foam. The insulation kept the tank external surface at a 

temperature high enough to prevent condensation of air. 

The author concludes that the feasibility of the concept was 

established. 

Important references: 

1. PPO Foam: A Unique High Temperature Insulation, Technical Data 

Sheet, General Electric Company, October 1967. 

2. Kouffeld, R. W. J. and van Riesen, P. E., Ref. No. 67-02294, 

Centraal Technisch Instituut, T.N.O., Delft, 31 Jul 1967. 

106 
PPO FOAM. LIQUID HYDROGEN INSULATION 

Yates, G. B. (General Dynamics, San Diego, Calif. Convair Div.) 

Advances in Cryogenic Engineering 20 (Presented at National Technical 

Mee-tings during 1973 and 1974), K.D. Timmerhaus, Editor. Plenum 

Press, New York, 327-37 (1975) 

An extensive fabrication and test program was carried out to 

demonstrate the use of polyphenylene oxide (PPO) fqam as an internal 

insulation for liquid hydrogen tanks. Early results were reported in 

the paper abstracted on page 102, which described the concept and 

advantages of open-cell internal insulation. This paper describes 

application of the insulation to an aluminum test tank, and the test 

program simulating launch vehicle.flight cycles. 

The PPO foam was heat-formed to the necessary contours, trimmed 

into panels, and bonded to the tank walls with a urethane adhesive. The 

panels were made 2% oversize and compressed 2% during installation to 

form solid joints between panels without using adhesive, and to prevent 

joint gaps caused by thermal contraction. The test program consisted of 

100 cycles of tanking and chilldown with liquid hydrogen, pressurization, 

rapid detanking, and heating of the tank surface. The cycles simulated 

service in a liquid-hydrogen-fueled reusable booster or reusable orbiter. 

Thermal performance of the insulation was determined by measuring boiloff 

rates and temperature gradients, which did not change significantly over 

the test program. Post-test examination showed no apparent deterioration 

of the PPO foam. 

The authors conclude that PPO foam has been demonstrated to be a 

reliable and reusable internal insulation for liquid hydrogen. Its 

primary limitation is its relatively high thermal conductivity. Because 

the open cells of the foam are filled with gaseous hydrogen during 

service, the thermal conductivity must be equal to or greater than that 

of gaseous hydrogen. 

Important references: 

1. Yates, G. B., Advances in Cryogenic Engineering 16, 128 (1971). 

2. Tatro, R. E. and Bennett, F. O., Jr., Advances in Cryogenic 

Engineering 20, 315 (1975). 

3. Space Shuttle Structural Test Program Final Report, Convair 

Division of General Dynamics, Rept. No. 549-3-092 (Mar 1972). 

4. Yates, G. B. and Tatro, R. E., Proceedings of the Space Transportation System Propulsion Technology Conference, Vol. IV, NASA, 

Marshall Space Flight Center, 1441 (Apr 1971). 

107 

la 
PPO FOAM INTERNAL INSULATION 

Yates, G. B., and Tatro, R. E. (General Dynamics/Convair, San Diego, 

Calif.) 

Space Transportation System 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, 1439-52 (Apr 1971) 

The reusable mission of the Space Shuttle imposes new requirements 

on liquid hydrogen tank insulation systems. A candidate system is 

polyphenylene oxide (PPO) open cell foam used as internal insulation. 

Internal insulation is exposed only to a know-n and controlled 

environment, and the tank wall and insulation bond line are kept warm 

to minimize thermal stresses. The PPO foam is open celled and not 

subjected to cyclic pressure fatigue, and is a simple one-component 

insulation. 

The PPO foam was made in thicknesses up to 8 cm, and densities 

from 30 to 180 kg/m3. The open cells are elongated and extend through 

the thickness of the foam. Tests with helium showed the presence of 

some lateral gas movement between cells, but this had no apparent effect 

on thermal performance. At a temperature of 20 K, the foam exhibited 

2% elongation and 2% elastic compression parallel to fiber direction. 

Face tensile, compression, core shear, and climbing drum peel tests 

were conducted between 20 K and 422 K. Tensile strengths decreased 

slightly with temperature increasing from 20 K to 300 K, then decreased 

more sharply with temperature increasing above 300 K. Compressive 

strengths gradually decreased with increasing temperature over the 

entire temperature range. Shear and peel strengths had more complicated 

temperature dependence, but were generally low at 20 K and high at 

422 K. Samples bonded to aluminum were fatigue tested at 20 K, 294 K, 

and 394 K, and withstood 400 cycles at each temperature with no 

observable damage. Thermal conductivity at mean temperatures from 200 

K to 350 K was from 1.10 to 1.25 times the thermal conductivity of 

gaseous parahydrogen at the same temperature. The foam could be 

hot-formed to various desired shapes. 

The authors conclude that the feasibility of using PPO foam as 

internal liquid hydrogen tank insulation has been demonstrated. 

108 
HEAT CONDUCTIVITY MEASUREMENTS ON FOAM PLASTICS AT LOW TEMPERATURES 

Zehendner, H. (Forschungsinstitut fuer Warmeschutz, Munich, Germany) 

Kaeltetechnik.-Klim. 9, No. 1, 2-8 (Jan 1967) 

This paper presents results of an extensive study of the cell 

structures and thermal conductivities of a number of commercially 

available foam insulations. The materials studied were two phenolic 

foams with densities 27 and 104 kg/m3, a polyethylene foam with density 

37 kg/m3, four polystyrene foams with densities 12.7, 24, 37 and 62 

kg/m3, two polyurethane foams, one a cast foam with density 26 kg/m3 

and the other a spray foam with density 43 kg/m3, two polyvinyl chloride 

foams with densities 43 and 70 kg/m3, 

79 kg/m3. 

and a hard rubber foam with density 

Microphotographs of the cell structures of the foams are 

shown. Thermal conductivities of the foams were measured from 93 K to 

323 K. 

The thermal conductivities of the two phenolic foams show a nearly 

linear increase with increasing temperature, but with the high-density 

material having a thermal conductivity consistently higher than that of 

the low-density foam. This is attributed to the high-density foam 

having such small cells and such a high solid content that it acts more 

like solid than foam phenolic. Thermal conductivity of the polyethylene 

foam is higher than that of any of the other foams, and increases 

strongly with increasing temperature. 

Thermal conductivities of the polystyrene foams were studied as a 

function of foam density. The curves of thermal conductivity versus 

temperature show a steady increase with increasing temperature, but 

differences between foams are difficult to see. A presentation of 

thermal conductivity versus foam density reveals that at any temperature 

level, there is a density having minimum thermal conductivity, and that 

this optimum density is higher at higher temperature. 

The polyurethane foams have a complicated thermal conductivity 

curve, increasing with increasing temperature up to about 225 K, then 

decreasing until the temperature reaches about 272 K, then once more 

increasing with increasing temperature. The region between 225 and 

323 K is further complicated by an age effect, in which older foams 

have a higher thermal conductivity than freshly-made samples. This 

aging effect is attributed to the gradual replacement of the fluorotrichloromethane blowing agent with atmospheric air by diffusion 

through the cell walls. This gradual increase in thermal conductivity 

was still continuing steadily at 30 months storage time. 

The thermal conductivities of the polyvinyl chloride foams 

increased non-linearly with increasing temperature, with the low-density 

109 
foam having lower thermal conductivity at temperatures below about 

220 K, and the high-density foam superior above this temperature. The 

hard rubber foam showed a linear increase of thermal conductivity with 

increasing temperature. 

Important references: 

1. Cammerer, W. F., Kaeltetechnik 12, 107-10 (1960). 

2. Achtziger, J., Kaeltetechnik 12, 372-5 (1960). 

3. Schmidt, W., Kunststoffe 53, No. 7, 413-20 (1963). 

4. Eiermann, K., Hellwege, K. H., and Knappe, W., Kolloid Z. 174, 

No. 2, 134-42 (1961). 

110 
INSULATION MATERIALS SELECTION CRITERIA FOR AN AERODYNAMIC PROTECTED 

CRYOGENIC STAGE (AUSWAHL UND EXPERIMENTELLE UNTERSUCHUNG EINES 

AERODYNAMISCHEN NICHT BELASTBAREN SCHAUMSTOFFISOLATIONS-SYSTEMS FUER 

KRYOGENE RAKETENSTUFEN) 

Zimni, W. F., and Breves, E. 0. (ERNO Raumfahrttechnik GmbH, Bremen, 

West Germany) 

Luftfahrttechnik Raumfahrttechnik 16, No. 10, 251-7 (Ott 1970) 

An experimental program was conducted to select an insulation 

system for use as external insulation on the liquid hydrogen and liquid 

oxygen tanks of a launch vehicle. The materials considered were 

polyurethane foam, the material used in the United States space program, 

and polyvinyl chloride foam, the material preferred in the French 

program. The test program included application of the foam to the 

surface of a liquid hydrogen tank and testing under simulated space 

flight conditions. Both foams were applied to tanks in two variations, 

the first with foam panels completely enclosed in mylar film vapor 

barrier, and the panels then bonded to the tank wall, the second with 

the foam bonded directly to the tank without any intervening film. 

Temperatures were measured during boiloff of liquid hydrogen in the tank, 

and heat leaks through the insulation into the tank were determined. 

The test results led to the conclusion that the two materials were 

approximately equal in terms of thermal performance, while the polyurethane had some advantage in ease of application. The polyurethane 

foam has a high thermal expansion coefficient, which can be decreased 

by the addition of glass fiber reinforcement to the foam without degrading 

thermal performance. The tests qualified the materials for use as 

cryogenic tank insulation. 

Important references: 

1. Stumpf, 0. and Zimni, W. F., Proc. of the XVIII Astronautical 

Congress, Vol III (Ott 1966). 

2. Tariel, Boissin and Segel, Adv. Cryog. Eng. 12, 274 (1966). 

3. Zimni, W. and Mertzner, K., Klimatisierung, No. 2 (1970). 

111 
THE THERMAL PROPERTIES OF FOAMS AND FOAMED HONEYCOMBS IN THE 

TEMPERATURE RANGE BETWEEN 20 AND 300 K 

Zimni, W. F., and Meitzner, K. (ERNO-Raumfahrttechnik GmbH, Bremen, 

West Germany) 

Kaeltetech.-Klim. 22, No. 2, 34-40 (Feb 1970) 

This paper reviews measurements made over a period of several years, 

of the thermal properties of a number of foams and composite insulating 

materials. The polyurethanes, which were the most often used foams in 

the United States space program, and polyvinyl chloride foam, preferred 

by the French, were the primary materials investigated. The materials 

also included a phenolic foam, phenolic-fiberglass honeycombs filled 

with foam, and polyurethane foams with 5 to 10% glass fibers added. The 

properties measured were thermal conductivity, thermal expansion and 

specific heat. 

Thermal conductivities were measured at mean temperatures between 

20 K and 320 K. Comparisons of results show the effects of blowing 

agents, aging, densities, and sample thickness. Polyurethane and 

polyvinyl chloride foams of similar density, both blown with trichlorofluoromethane, had nearly identical thermal conductivities. An air-blown 

foam and a halocarbon-blown foam showed the same thermal conductivity up 

to about 250 K, but the air-blown foam lacked the S-curve characteristic 

typical of halocarbon-blown foams at higher temperatures. Thermal 

expansions were measured between 4 K and 380 K. Particularly striking 

was the very high thermal expansion of the polyurethane foam, and the 

great decrease of this expansion caused by the addition of glass fibers. 

Specific heats of foams were difficult to measure, but the specific heat 

of a very high density polyurethane foam is shown between 20 K and 350 K. 

In general, the tests showed a superiority for halocarbon-blown 

foams over air-blown foams as insulation. Reinforcement of the 

polyurethane foam with glass fibers improved its thermal expansion 

coefficient and its elasticity. 

Important references: 

1. Kreft, H., and Wagner, D., Kaeltetech.-Klim. 21, No. 9, 258-65 

(1969). 

2. Koglin, B., and Zimni, W., ERNO Raumfahrttechnik GmbH, Bremen, 

Germany, Rept. (Ott 1967). 

3. Stumpf, O., and Zimni, W., Proc. Astronautical Congress, XVII - Vol 

III (Ott 1966). 

4. Koglin, B., Gesellschaft fuer Weltraumforschung mbH, Bonn-Bad 

Godesberg, Techn. Bericht (No Date). 

5. Koglin, B., and Zimni, W., Techn. Rev. 1, No. 1, 3-28 (1967). 

112 
OTHER DOCUMENTS 

113 
OTHER OOCUHENTS OTHER OC‘CUMENTS 

(CONT.) 

001 

AGRAWAL.K. N. VERIIAIV.V. 

AN APPARATUS FOR THE STUDY OF HEAT AN0 

NASS TRANSFER PROPERTIES OF INSULATING 

HAiERIALS Al LOW MEAN TEMPERATURES. 

JNOIAN J. TECHNOL. VOL 7r NO. 1, 4-a 

(JAN 1969) 

002 

010 

ASKEqH.0. SPENCER,S.E. 

INSULATE0 CRYOGENIC REFRIGERATOR COLO 

HEAO. U. S. PATENT 3,504,505 (APR 1970) 

011 

BACKHAUS,H.W. JANSSEN,R. 

LNG INLANO TRANSPORTATION WITH RAILWAY 

TANK CARS AND RIVER-GOING TANKERS. 

INTE*NATIONAL CONFERENCE ON LIQUEFIES 

NATURAL GAS, PRO:. FOURTb. ALGIEPS, 

ALGERIA, JUN 24-7, 1974. INSTITUTE OF GAS 

TECHNOLOGY, CHICAGO, ILL., 

SESSICN-VI-PAPER-Z, 16PP I19741 

ALLEAUME,J. 

THE TRANSPORT BY SEA OF NATURAL LIPUEFIEO 

GAS AN0 OF ETHYLENE. (IN FRENCH) REV. 

GEN. FRO10 VOL 56, NO. 9, 1027-32 (SEP 

1965) 

003 

ALLEN,R. J. 

SURFACE INSULATION FOR CRYOGENIC FLUIDS. 

REV. SCI. INSTR. VOL 31. NO. 2, 203 (FEB 

1960 I 

012 

BAEHR,F. 

NEW THERMAL INSULATORS COMPARE FAVORABLY 

WITH PRESENT METHCOS. CAN. PET. VOL 14, 

34-6 (1973) 

004 

ALLEN9R.J. VAN PAASSEN,H.L.L. 

FLOATING POLYSTYRENE BEAOS AS INSULATION 

FOR CRYOGENIC FLUIOS. ADVANCES IN 

CRYOGENIC ENGINEERING VOL 61 548-54 

IPROCEEDINGS OF THE 1960 CRYOGENIC 

ENGINEERING CONFERENCE) PLENUM PRESS 

INC.. NEW YORK (1961) 

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GAS ASSOC., ARLINGTONI VA., 1OOPP (1973) 

AMERICAN GAS ASSOCIATION 

ASAY,J.R. URZENO0WSKI.S.R. 

LNG INFORtlATION BOOU - 1973. 

006 

AMERICAN 

GUENTHER,A.H. 

ARNOLDY,C. 

TECHNICAL ANALYSIS. PIPING. AN EXPANDING 

INTERFACE. CRYOGENICS AN0 ENERGY 

PERSONNEL. CRYOGEN. TECHNOL. VOL 7, NO. 

6, 193-7 lNOV/OEC 1971) 

007 

013 

EAHRENBURG,H.H. 

LNZ--FIPE IT. ttAUL IT. CRYOGENIC ENG. 

NEWS VOL 2. NO. Zr 22, 24-5 (FE@ 1967) 

014 

EAHREKBURG,H.H. 

URETHANE FOAM IS FLEXIBLE. CRYOGENICS 

INO. GASES VOL 4r NO. 7, 29-30 (JIJL 1969) 

015 

RICKETSON9B.W.A. 

THE USE OF LIQUID HYDROGEN IFI THE THTRO 

RUCCIArF.E. SCHULTE,C.A. 

STAGE OF A SATELLITE VEHICLE. 

BAILEY.A.8. 

STORAGE, TRANSFER AN0 SERVICING ECUIPMENT 

CRUOOACE,R.G. 

J. BRIT. 

INTERFLANET. sot. VOL ia, NO. 516, 203-24 

(SEP-OEC 1961) 

016 

JAILEY,@.M. BENEOItT,O.C. BYRNES1S.W. 

CAHPSELL,C.R. FGWLE9A.A. MOORF,R.W. 

PESTALOZZ1vW.G. R1CHTER.E.G. 

ULTRASONIC AND THERMAL STUDIES OF 

SELECTEO PL’ASTICS, LAflINATEO MATERIALS 

AND METALS. ALBUQUERQUE UNIV.. N. flEX.. 

REPT. NO. AFWL TR-67-91 (JAN 1968) CONTR. 

NO. F29601-67-C-0042 262 PP 

008 

ASHI0A.K. OHTANI,H. ICHII,fi. 

KOBAYASH1.T. 

CRYOGENIC THERMAL INSULATION. (IN 

GERMAN) GERflAN OFFEk. NO. 2,430,985 (JUN 

1974) 

OG9 

ASHWORTH.1. SM1THeM.G. 

A RAOIAL HEAT-FLOW METHOO FOR POOR 

CONOUCTORS. THERflAL CONOUCTIVITY 

(PROCEEOINGS OF A CONFERENCE 9TH, IOWA 

STATE UNIV., AMES, OCT 6r 7 AN0 8, 1969) 

H. R. SHANKS, ED., NATIONAL TECHNICAL 

INFORMATION SERVICE t SPRINGFIELO, VA. 

(MAR 1970) CONF-691042 PP 524-9 

FOR LIQUID HYDROGEN. LITTLE, ARTHUR D., 

INC., WAOC TECd. REPT. 59-386 (JUL 1959) 

CONTR. AF 33(616)-5641, 772 PF 

017 

BA1LEY.C.A. 

HEAT TRANSFER AND THERMAL INSULATION. 

AOVANCEO CRYOGENICS, 133-53. C.P. 

BAILEY, ED., PLENUM PRESS, NEW YGPK 

(1971) 

318 

BAILEY,C.O. 

LINEAR THERMAL EXPANSION OF ORGANIC 

MATERIALS AT CRYOGENIC TEMPERATURES. 

LOCKHEED AIrZCRAFT CORP.. MARIETTA. tiA. 

REPT. NO. ER-5682 IMAY i962) 39 Pb 

019 

BANCROFT,G.H. 

LIQUIC PROPELLANT STORAGE TANK. U. S. 

PATENT NO. 3r6953050 (OCT 1972) 

114 
OTHER OOCUMENTS OTHER OGCUHENTS 

(CONT.) (CONT.) 

020 029 

BARBER, J.R. BISIAUX rP. 

CRYOGENIC INSULATION TECHNOLOGY REVIEW HYDROGEN-OXYGEN PROPULSION IN FRANCE. (IN 

FOR THE SPACE SHUTTLE. SPACE FRENCH) LASTRONAUTIPUE. NO. I. 27-47 

TRANSPORTATION SYSTEM TECHNOLOGY 

SYtlPOSIUt4r VOL 5, 146-66 (NASA LEMIS 

RESEARCH CENTER, CLEVELAND* OHIO. JUL 

~. ~. 

(1967) 

030 

15-17, 1970) NATIONAL AERONAUTICS AND BLACl(r1.A. GLASER, P.E. 

SPACE ADMINISTRATION TECH. MEMO. NO. THERMAL CONDUCTIVITY TESTS OF CRYOGENIC 

X-52076 INSULPTION. PROC. OF THE SECOND CONF. ON 

THERMAL CONOUCTIVITY, OTTAWA, CANADA, OCT 

021 10-12, 1962, iii-31. NATIONAL RESEARCH 

BARITO,R.W. EASTflAN.W.0. COUNCIL OF CANADA. DIV. OF APPLIED 

PLASTIC AN0 ELASTOMERIC FOAMS. HANOBOOK 

OF PLASTICS AN0 ELASTOMERS, CHAPTER 7, 

7-1 TO 7-79, C. A. HARPER, ED., 

MCGRAW-HILL, INC. (1975) 

c22 

EiARKER,H.H.rJR. L0NG.R.L. ROSELLO.0. 

SOLDAT,G.J. SflITH,T.O. 

CRYOGENIC CONTAINERS. U. S. PATENT 

PHYSICS, OTTAWA. 

031 

BO0LEY.R.W. 

OESIGh CONSIDERATIONS FOR LNG STORAGE 

TANKS. CURRENT UNITED STATES PRACTICE. 

PROC. OF INTERNATIONAL CONFERENCE ON 

LIQUEFIED NATURAL GAS, LONDON, MAR 1969, 

457-60 

3.317.074 (MAY 1967) 

G23 

NASA-CR-121103, CONTRACT NO. NAS3-13316, 

BARTLETT,O.H. ZIHflERMAN.0.K. 

397PP (APR 1973) 

SPACE VEHICLE INTEGRATED THERMAL 

PROTECTION STRUCTURAL - METEOR010 

PROTECTION SYSTEM, VCLUME I. BOEING 

AEROSPACE CO., SEATTLE, WASH., REPT. NO. 

0190-15172-l. NATIONAL AERONAUTICS AN0 

SPACE AOHINISTRATION REPT. NO. 

032 

CONTR. ho. 

3OEING CO., SEATTLE, WASH. 

NAh-21341 52 PP 

DEMONSTRATION OF MANUFACTURING TECHNIQUES 

FOR APPLICATION OF HIGH PERFORMANCE 

CRYOGENIC INSULATION. FINAL REP. 

NATIONAL AERONAUTICS ANC SPACE 

AOMINISTRPTION, HUNTSVILLE, ALA. GEORGE 

C. MARSHALL SPACE FLIGHT CENTER, REP. tJ0. 

NASA-CR-98459. 02-139267-l (SEP 1968) 

024 

9EAUJEAN.J.M. 

TANK FOR LIQUIFIEO GASES. U. S. PATENT 

NO. 3.904.068 (SEP 1975) 

il2E 

BENFOR0,A.E. 

DESIGN CONSIDERATIONS WHEN USING 

POLYURETHANE FOAM IN REFRIGERATION 

APPLICATIONS. ASME OESIGN ENGINEERING 

CONFERENCE AND SHOW, CHICAGO, ILL. (APR 

22-25, 1969) PAPER NC. ASHE 68-DE-199 

7 PP 

026 

3ERGER,9R. 

NOVEL INGROUNG STORAGE UNITS. (IN GERMAN) 

GAS WASSERFACH VOL 1101 iO95-93 (SEP 

1969) 

027 

BETTANINI,E. T4APANESE.G. 

EFFECT OF HUMIDITY Oh THE THERMAL 

CONDUCTIVITY OF INSULATING NATERIALS. (IN 

ITALIAN) FRED00 VOL 20, NO. br 11-b 

(1966) 037 

033 

B0NALLACK.R.F. 3ILLS,H. 

INSULATED EOOIES FOR COMMERCIAL VEHICLES. 

u. S. PATENT NO. 39481,642 (OEC 1969) 

034 

B0RUP.H.H. 

CRYOGENIC TANK. U. S. PATENT NO. 

3.929.247 (OEC 1575) 

035 

BRAN0T.N.B. SVISTOVA,E.A. SEMENCV, H. V. 

A MINIATURE APPARATUS FOR OBTAINING 

INTERMEOIATE TEMPERATURES. CRYOGtNICS 

VOL II, NO. 1, 53-61 (FEB 1971) 

036 

BRISSAU0.J. DE FRONOEVILLE,B. 

APPLICATION OF THE PYTHAGORE I?EHBRANC 

TECHNIQUE TO LAND STORAGE OF LNG. IIN 

FRENCH) ENGINEERING, TRANSPORT AN0 

OPERATICNS RESEARCH VOL 6, 307-14 

(PROCEEOINGS OF THE KORLO PETROLEUM 

CONGRESS 7TH. 1967) ELSEVIER PUirLISI'ING 

CO., LTO. (1967) 

SIAIS,H. 

02.9 

METHOD OF INSULATING TANKS FOR STORING OR 

TRANSPORTING LOW-TEMPERATURE LIPUIOS. 

U. S. >ATENT 3.118,19L, (JAN 19641 

BRITISH CHEblICAL ENGINEERIWG 

SRIT. CHEH. EN;., VOL 121 NO. 4, 573 (APQ 

ECONOHIC TQANSFER OF CRYOGENIC LICUI-IS. 

1967) 

115 
OTHER DOCUMENTS 

(CONT. 1 

030 

BRITISH CHEMICAL ENGINEERING 

PIPELINES FOR LOW TEHPERATURES. BRIT. 

CHEH. ENG. VOL 14, NO. 2. PPR 31-5 <FEB 

19691 

039 

BRITISH CRYOGENICS COUNCIL 

CRYOGENICS SAFETY MANUAL. INSTITUTION OF 

CHEMICAL ENGINEERS, LONDON, ENGLANO 

(19701 107 PP 

040 

OTHER DGCUMENTS 

(CONT.) 

048 

CERQUETTINI,C. 

SPRAYASLE POLYURETHANE FOA?( 

INSULATION, SATURN S-II BOOSTER. SA!lPE 

J. VOL 51 NO. 4r 28-9 (JUN-JUL 19691 

049 

CHEMICAL PROCESS ENGINEERING 

INSULATION WITH URETHANE FOAM. CHEM. 

PROCESS ENG. VOL 46, 659 AND 661 (OEC 

1965) 

050 

CHEMICAL PROCESS ENGINEERIYG 

PROTECTING CRYOGENIC LIQUIDS WITH GALL 

BLANKETS. CHEM. PROCESS ENG. VOL 52, NO. 

2, 54 (FEE 1971) 

051 

CHEYNEY rD.4. 

BR0CHHAGEN.F.K. SCHHIOT,W. 

INSULATION OF PIPES WITH EXPANOEO 

POLYURETHANE. (IN GERMAN) KUNSTSTOFFE 

VOL 579 NO. 4, 220-34 (1967) 

041 

BR0GANvJ.J. 

IHPACT OF PROPELLANT HEATING ON NUCLEAR 

SPACECRAFT INSULATIOA AND PRESSURIZATION 

SYSTEHS DESIGN. J. SPACECRAFT ROCUETS 

VOL 3, NO. 69 932-4 (JUN 19661 

042 

BUIST,J.M. DOHERTY r0.J. HURDvR. 

URETHANE RIGID FOAHS, FACTORS AFFECTING 

THEIR BEHAVIOUR AS THERHAL INSULANTS. 

INTERN. CONGR. OF REFRIGERATION, IlTH, 

MUNICH (AUG 1963) PAPER 11-22, 9 PP 

043 

BULLETIN TECH. BUREAU VERITAS 

THE ANNA SCHULTE LIQUEFIED GAS CARRIER. 

1 IN FRENCH) BULL. TECH. EUR. VERITAS VOL 

56, NO. 2r 36-7 (FEB 1974) 

044 

BURGE,G.W. 

CONCEPTUAL DESIGN OF AN INTEGRATED 

ON-DEMAND FLOW CRYOGEN FEED SYSTEM FOR 

IN-ORBIT APPLICATIONS. CRYOGENIC 

WORKSHOP, PROC.. NATIONAL AERONAUTICS AN@ 

SPACE AOliINISTRiTION, HUNTSVILLE, ALA. 

GEORGE C. WARSHALL SF4CE FLIGHT CENTER, 

299-324 (HAR 19-20, 19721 

045 

BUTTERW0RTH.H.H. 

THE INSUL4TION OF REFRIGERATED CONTAINERS 

AN0 ROAO VEHICLES. MOO. REFRIG. VOL 70, 

NO. 832, 50-3 (JUL 19071 

046 

CAHPBELL.M.9. 

JONESvH. 

HASKIkS. J.F. 

PERCY rJ.L. 

HERTZ.J. 

THIRTY DAY EVALUATIOI\ OF FOAtlS AND 

HONEYCOMB FOR CENTAUR INTERMEDIATE 

BULKHEAD. GENERAL DYNAMICS/ASTRONAUTICS, 

SAN DIEGO, REPT. NO. MRG-312 (APR 1962) 

CONTR. NO. AF 33(616)-7984, 75 PP 

047 

CEINTREY,M. 

HEAT-INSULATED CONDUIT OF UTILITY IN THE 

TRANSPORT OF FUELS OVER LONG DISTANCES. 

U. s. PATENT NO. 3~420,277 (JAN 19691 

INSULATEC TANK. U. S. PATENT NO. 

3,931,908 (JAN 1976.) 

352 

CLARK, J.A. 

TRANSIENT CONDENSATION ON INSULATING 

SUBSTANCES FOR CRYOGENIC APPLICATION. 

ADVANCES IN CRYOGENIC ENGINEERING VOL 7, 

360-6 (PROCEEDINGS OF THE 1961 CRYOGENIC 

ENGINEERING CONFERENCE) PLENUM PRESS 

INC., NEW YORK (1962) 

053 

CLARKE, J.S. KARCHER1G.G. 

INSULATED CRYOGENIC TANK. U. S. PATENT 

3,495,732 (FEE 1970) 

054 

CLARKE,R.C. 

THERMALLY INSULATE2 CONTAINER. U. S. 

PATENT 3,250,416 (MAY 1966) 

055 

CLOSNER,J. J. 

LNG STORAGE WITH PRESTRESSEO CONCRETE. 

PROCEEDINGS OF THE INTERNATIONAL 

CONFEFENCE ON LNG IST, CHICAGO, ILL. (APR 

7-12, 1968) (J.W. WHITE AND A.E.C. 

NEUMANN EOS.1 INSTITUTE OF GAS 

TECHNOLOGY, CHICAGO, ILL. (1963) PAPSR 32 

15 PP 

056 

CLOTFELTER,W.N. BANKSTON,B.F. 

0UREN.P.C. 

THE NONCESTRUCTIVE EVALUATION OF LOW 

DENSITY FOAM-ALUMINUM COMPOSITE 

NATERIALS. NATIONAL AERCNAUTICS AN0 

SPAC.: AOMINISTRATION~ HUNTSVILLE, ALA. 

MARSHALL SPACE FLIGHT CENTER, TECH. MEMO 

X-53340 (OCT 1969) 42 PP 

116 
OTHER OOCUMENTS 

ICONT.) 

057 

C0ChRAN.R.P. CUBBISCN,R.W. 

SUPERSONIC AERODYNAMIC HEATING TESTS ON A 

LIGHTWEIGHT EXTERNAL INSULATION SYSTEH 

FOR LIPUIO-HYOROGEN TANKS OF BOOST 

VEHICLES. NATIONAL AERONAUTICS AN0 SPACE 

ADHINISTRATION, LEWIS RESEARCH CENTER, 

CLEVELAND, OHIOt TECH. NOTE NO. O-3300 

(MAR 1966) 21 PP 

058 

COOEG0NE.C. FERR0.V. 

A SQUAQE PLATE APPARATUS FOR MEASURING 

THE THERflAL CONDUCTIVITY OF INSULATING 

MATERIALS AT LOW TEIIPERATURES. BULL. XIR 

ANNEXE 1964-2. 15-22 (PRESENTED AT 

MEETING OF COUU. 2, TUQIN. ITALY, SEP 

9-il, 1964) 

059 

COOEGONE,C. FERRO, V. SACCHI,A. 

THERMAL OSCILLATIONS THROUGH WALLS. 

PROGR. REFRIG. SCI. TECHNOL. VOL 21 bi-9 

(PROC. INT. CONGR. REFRIG., 12TH. MADRID, 

SPAIN, BUG JO-SEP 6, 1967) INST. INT. 

FROIO, PARIS (1’969) 

060 

COOL1N.E.M. 

CRYOGENICS AND REFRIGERATION. A 

BIBLIOGRAPHICAL GUIDE. IFI/PLENUH DATA 

CORP. NEW YORK (1968) 311 PP, AND VOL 2 

(1970) 283 PP 

061 

COLOING, L. 

INSULATION WITH POLYSTYRENE. (IN DANISH) 

KULOE (COPENHAGEN) VOL 20, NO. 6, 91-9 

lOEC 1966) 

062 

CO0KvH.C. 

METHOD OF MANUFACTURING PIPE SECTIONS FOR 

THE TRANSPORTATION OF CRYOGENIC LIQUIOS. 

U. 5. PATENT 39453,716 (JUL 1969) 

063 

COOPER, A. 

EXPANOEO EBONITE FOR THERMAL INSULATION 

OF LIQUEFIED GASES. MOO. REFRIG. VOL 68, 

NO. 305r 339-42, 359 (APR 1965) 

064 

COOPER+H.C. 

STORAGE RESERVOIR FOR LIQUEFIED GASES. 

U. S. PATENT 2r512,306 (JUN 1950) 

065 

COST0N.R.M. 2IERMAN.C.A. 

CRYOGENIC THERMAL-CONDUCTIVITY 

MEASUREMENTS OF INSULATING HATERIALS. 

AMER. SOC. TESTING MATER. SPEC. TECH. 

FuaL. NO. 411 (1967) PP 25-42 

OTHER DOCUMENTS 

(CONT.) 

066 

COULTER,O.fl. 

JESIGM CONSIDERATIONS FOR A LIQUEFIEO 

NATUQAL GAS PIPELINE. ADVANCES IN 

CRYOGENIC ENGINEERING VOL 159 28-35 

(PROC. OF CRYOGENIC ENGINEERING 

CONFERENCE, LOS ANGELES9 CALIF., JUN 

16-18, 1969) K.D. TIHMERHAUS ED.9 PLENUH 

PRESS, NEW YORK (1970) 

067 

COULTER,O.M. NORRIS.0.H. WALKER,G.W. 

PIPE LINE DESIGNS FOR THE FAR NORTH. 

PIPE LINE INO. VOL 31, 41-5 (DEC 1969) 

068 

CRAWFORO,O .a. 0ERGMAN.R.A. 

INNOVATIONS WILL MARK LNG-RECEIVING 

TERMINAL. OIL GAS J. VOL 72, NQ. 31, 

57-61 (AUG 1974) 

069 

CREASER,L. F. 

FLEXIBLE INSULANTS FOR CONTAINERS AND 

CONDUITS. U. S. PATENT NO. 3r682182r 

(AUG 1972) 

070 

CR0CKETT.L.K. W1TZELLvW.E. 

MATERIALS PROPERTIES AN0 ALLOHABLES FOR 

THE SPACE SHUTTLE. SPACE TRANSPORTATION 

SYSTEMS TECHNOLOGY, PROP. synF. 

(CLEVELAND, OHIO, JUL 15-17. 1970) VOL 3. 

NATIONAL AERONAUTICS AND SPACE 

ADMINISTRATIONI WASHINGTON, D. C. 9 REPT. 

NO. NASA-TM-X-52B76, 273-87 (JUL 1970) 

071 

CROUCH.G.0. 

POLYSTYRENE FOAM. LNG TANK INSULATION. 

CRYOGENICS INO. GASES VOL 6, NO. 51 39 

(SEP/OCT 19711 

072 

CROWL9R.E. 

AN LNG SHIP-LOADING PIPELINE. 

LNG/CRYOGEN. VOL I, NO. 2, b-11 TAPR/MAY 

1973) 

073 

CRYOGENIC TECHNOLOGY 

A SHIFT TOWARO LNG. TECHNICAL ANALYSIS. 

PIPING AN0 PIPING SPECIALTIES. CRYOGENIC 

TECHNOL. VOL 6, NO. 6, 212-b (NOV-OEC 

1970) 

074 

CRYOGENIC TECHNOLOGY 

TECHNICAL PROOUQT ANALYSIS. HATERIALS AND 

INSULATION. CRYOGENICS IMPROVEMENTS* NOW. 

CRYOGENIC TECHNOL. VOL 6, tJ0. I, 22-u 

(JAN-FE@ 1970) 

075 

CRYOGENICS AN0 INDUSTRIAL GASES 

LNG IMPORT TERMINAL. DESIGN 

CONSIOERATIONS. CRYOGEN. INO. GASES VOL 

7, NO. 51 41-8 (SEP-OCT 1972) 

117 
OTHER DOCUMENTS OTHER DOCUMENTS 

(CONT.) (CONT.) 

076 085 

CRYOGENIC$ AND INDUSTRIAL GASES DEASOK, C. 

SINGLE LAYER APPLICATION FOR LNG PIPE SIX-WTLE CRYOGENIC SYSTEM SERVES OFFSHORE 

INSULATION. CRYOGEN. INO. GASES VOL 8, BRUNEI LOADING PLATFORM. PIPE LINE INO. 

NO. 51 21-2 (SEP-OCT 1973) VOL 38, NO. 3, 55-7 (MAR 19731 

677 086 

CRYOGENICS AND INDUSTRIAL GASES 

VOL 3. 

URETHANE FOAM INSULATES BRUNEI PIPELINES. 

NATIONAL AERONAiJTICS AND SPACE 

CRYOGEN. INO. GASES VOL 7, ;NO. 4, 27-9 

(JUL-AUG 19721 

078 

AO~~INISTRATIONI WASHINGTONI 0. C., REPT. 

CURRY rJ.E. 

CRYOGENIC INSULATION. SPACE 

TRANSPORTATION SYSTEMS TECHNOLOGY, PROC. 

SYHP. (CLEVELANOe OHIO, JUL 15-17. 1970) 

DELAN0,R.E. HARJLOSEN.O.0. 

0ELANG.R.E. 

HELLEY,L.R. 

P0RTERsR.N. 

HAROLOSEN.O.0. 

TASK 6 STORABLE PROPELLANT MODULE 

P0RTER.R.N. 

ENVIRCNMENTAL CONTROL TECHNOLOGY. 

SUMM4RY REPORT. 

SPACE STORABLE PROPELLANT MODULE THERMAL 

NATIONAL AERONAUTICS AND 

SPACE AOHINISTRATION, REP. NO. 

NASA-CR-111082, TRW-14051-6007-TO-00 (JuL 

1970) CCINTR. NO. NAS7-750 73 PP 

087 

NO. NASA-TM-X-52876, 297-308 (JUL 1970) 

079 

OAVIES*C.B. 

LNG TRANSPORTATION-ITS GROWTH AND 

OEVELOPYENT. PETROL. REV. VOL 24, NO. 

284, 251-8 (AUG 1970) 

080 

DAVIS,B.K. CARTER. J.H. SIMPSON, W.G. 

9EVELOPMENT OF POLYURETHANE SPRAY FOAM 

INSULATION. NATIONAL AERONAUTICS AND 

SPACE ADMINISTRATION, MARSHALL SPACE 

FLIGHT CENTER, HUNTSVILLE, ALA., 

MANUFACTURING OEVELOFMENT MENO. NO. 

MOM-15-67, NATIONAL AERONAUTICS AN0 SPACE 

ADMINISTRATION TECH. NEMO. NO. X-60658 

(AUG 19671 29 PP * 

081 

i)E WINTONIC. 

THE ACHIEVEMENTS AT GLENMAVIS, GAS WORLD 

VOL 176, NO. 46G4, 415-21 (NOW 1972) 

CONTROL TECHNOLOGY. TRW SYSTEMS GROUP, 

REOONOO BEACH, CALIF., SUMMARY REPT. NO. 

TRW-14051-6009-RO-OO-VOL 2. NATIONAL 

AERONAUTICS AND SPACE ABMINISTRATION 

REPT. NO. NASA-CR-1179599 CONTRACT NO. 

NAS7-75 0, 129PP (MAR 1971) 

088 

0ELANO.R.E. HAROLDSEN,O.O. PORTER* 4. N. 

SPACE STORABLE PROPELLANT MODULE THERNAL 

CONTROL TECHNOLOGY - SUMMARY REPORT, VOL 

I - OF(Z)/B(2) H(6) PROPULSION !4OLULE. 

TRW SYSTEMS GROUP, REOONOO BEACH* CALIF., 

REPT. NO, TRW-14051- 6004-R3-33-VOL 1, 

PREPARE0 FOR JET PROPULSION LAB., 

PASAOENA, CALIF. NATIONAL AERONAUTICS AN0 

SPACE AOHINISTRATION REPT. NO. 

N4SA-CR-117900, CONTRACT NO. NAS7-753, 

215PP (MAR 1971) 

082 

DE W1T.J. WAROALE,J.K.S. OICKIE,O. 

DENHAY, J.B. 

LAND STORAGE TANKS FOR REFRIGERATED 

LIQUIO PROOUCTS. METAL CONSTR. BRIT. 

WELD. J. VOL 6, NO. 3, 96-IOG (MAR 1974) 

083 

0EAN.F.E. 

THE INTERCONTINENTAL TRANSPORT OF 

LIQUEFIED NATURAL GAS. CRYOGENICS VOL 6, 

NO. 2. 65-76 (APR 1966) 

08L 

OEARING1O.L. 

DEVELOPMENT OF THE SATURN S-IV AND S-IVB 

LIQUID HY9ROGEN TANK INTERNAL INSULATION. 

ADVANCES IN CRYOGENIC ENGINEERING VOL. 

119 39-97 (PROCEEDINGS OF THE 1965 

CRYOGENIC ENGINEERING CONFERENCE) PLENUN 

PRESS, INC. I NEW YORK (19661 

089 

DELAN0,R.E. HAROLOSEN.0.0. P0RTERwR.N. 

TASK 3 SPACE STOkABLE PROPELLANT MODULE 

ENVIRCNHENTAL CONTROL TECHNOLOGY. 

SUHMAEY REPORT. NATIONAL AERONAUTICS AND 

SPACE AJMINISTRATION, REP. NO. 

NASA-CR-110941, TRW-14051-6004-TO-00 (JUN 

1970) CONTR. NO. NAS7-750 74 PP 

090 

OESAI.R.4. OOHNJ,G.O. 

STRUCTURAL LIGHT-WEIGHT PANEL FOR 

CRYOGENIC AND ELEVATED TEMPERATURE 

APPLICATIONS. U. S. PATENT NO. 3,669,315 

(JUN 19721 

091 

OESAI 9R.R. UOHN,G. 0. 

STRUCTURAL LIGHT-WEIGHT PANEL OF HIGH 

STRENGTH, HAVING THERMAL INSULATION 

PROPERTIES AND ENCLOSURES FORME@ THERE3Y. 

U. S. PATENT NO. 3,773,6C4 (NOW 19731 

092 

01 MATTE0,G.A. KREISLERvR.1. WOOOS,J.A. 

THER?IAL CON3UCTIVITY OF INSULATING 

YATEIIIALS BY THE GUARDED HOT PLATE 

METHOD. GENERAL OYNANICS/ASTRONAUTICS, 

SAN aIEG0, CALIF., REPT. NO. GOA-7-O-476 

(OCT 1958) 30 PP 

118 
OTHER OCCUHENTS 

(CONT.1 

103 

OUFFY,A.R. 0AINORA.J. 

CONSIDERATIONS FOR LNG PIPE MATERIAL 

SELECTION. PROCEEDINGS OF THE 

INTERNATIONAL CONFERENCE ON LNG IST, 

CHICAGO, ILL. (APR j-12, 1968) (Jew. 

WHITE AND A.E.S. NEUMANN EOS.) INSTITUTE 

OF GAS TECHNOLOGY 9 CHICAGO, ILL. (196Y) 

PAPEQ 42 19 PP 

104 

OUFFY ,A.R. SHOUP,A.J. 

LNG TANK IS INTERNALLY INSULATE09 

FLEXIELY LINED. OIL GAS :. VOL 64, NO. 

32, 52-5 (AUG 1966) 

105 

OUFFY,A.R. SH0UPvA.J. 

600,000-BBL LNG TANK TO USE INTERNAL 

INSULATION, FLEXIBLE LINER. OIL GAS J. 

VOL 6&e NO. 319 114-8 (AUG 1966) 

OTHER DOCUMENTS 

(CONT. 1 

093 

0IMENTBERG.M. 

THE DESIGN AND OPERATION OF AN LNG 

PIPELINE FROM THE ARCTIC. INTERNATIONAL 

CONFERENCE AND EXHIBITION ON LIQUEFIED 

NATURAL GAS, 3R0, WASHINGTON. 0.C.. SEP 

24-28, 1972, INSTITUTE OF GAS TECHNOLOGY, 

CHICAGO, ILL., SESSIGN-VII/PAPER-7, 19 PP 

(1972) 

094 

0IHENTBERG.M. 

DEVELOPMENT OF LNG PIPELINE TECHNOLOGY. 

CRYOGENICS INO. GASES VOL 61 NO. 5, 29-36 

(SEP/OCT 19711 

095 

0IMENTBERG.M. 

LNG VIA PIPELINE. CRYOGENIC ENG. NEWS 

VOL 3, NO. 3, 34-44 (MAR 1968) 

096 

0INAPOLIvR.N. 

DESIGN NEEDS FOR BASE-LOAD LNG STORAGE, 

REGASIFICATION. OIL GAS J. VOL 71, NO. 

431 67-70 (OCT 1973) 

097 

0INAPOLI.R.N. 

DESIGN NEEDS FOR BASE-LOAD LNG. PETROL. 

INT. VOL 149 NO. 3, 58-62 (MAR 1974) 

098 

DOHERTY 90. J. HUROqR. LESTER9G.R. 

THE PHYSICAL PROPERTIES OF RIGID 

POLYURETHANE FOAHS. CHEM. INO. (LONDON) t 

1340-56 (JUL 1962) 

099 

DOUGHTY rR. 0. J0NES.L.R. 

CLIFTON* J. V., JR. 

EXPANOABLE RIGIOIZABLE SOLAR SHIELOS FOR 

PROTECTION OF CRYOGEFtIC PROPELLANTS IN 

SPACE. J. SPACECRAFT ROCKETS VOL 7* NO. 

12* 1419-24 (OEC 1970) 

100 

HOW TO EVALUATE INSULATION FOR CRYOGENIC 

PIPING. HEATING, PIPING, AIR 

CONOITIONING VOL 379 NO. 12. 93-9 (DEC 

1965) 

101 

0RYOEN.H.L. 

tIETHO0 OF MAKING A FILAHENT-WOUND 

CONTAINER. U. S. PATENT 3.555.179 (OCT 

1970 J 

102 

0UONIK~O.M. STEPANENK0.A.N. 

THERMAL CONDUCTIVITY AND OIFFUSIVITY OF 

INSULATING MATERIALS. (IN RUSSIAN1 

KHOLOO. TEKH. VOL 45, NO. 1, 27-9 (1968) 

106 

OUMONT, A. 

PRESENT POSSIBLE USE OF RIGID 

POLYUFETHANES FOR INSULATION. COMtlUt~. 

CENTRE ET. SCI. TECH. FROID, BELG., NO. 

2, 11-23 (JUN 1962) 

107 

DUPUY ,R. 

INDUSTRIAL INSULATING AND HEAT-PCOOF 

MATERIALS. (IN FRENCH) MEH. SOC. INGRS. 

CIVILS FRANCE, NO. 4, 23-30 (APR 1964) 

108 

0URR.C.A. 

PROCESS TECHNIQUES AN0 HARDWARE USES 

OUTLIhED FOR LNG REGASIFICATIGN. OIL GAS 

J. VOL 72, NO. 19, 56-66 (MAY 1974) 

109 

EAK1N.B.E. KHAN1A.R. ANOERSON,P. J. 

HONEYCOMB INSULATION PANEL FOR CRYOGENIC 

TEMPERATURES. U. S. PATENT 3r55br917 

(JAN 1971) 

110 

EOESKUTYqF. J. WILLIAMSON,K.O., JR. 

STORAGE AND HANOLIKG OF CRYOGENS. PAPER 

PRESENTED AT AUERICAN INST. OF CHEMISAL 

ENGINEERS AND INST. MEXICAN0 DE 

INGENIEROS QUIMI:OS JOINT #EETINGq 3201 

OENVER, COLO., AUG 30-SEP 2, 1975. ALSO 

PUBLISHEI? IN ADVANCES Ih CRYOGENIC 

ENGINEERING VOL 17. PLENUM PRESS, NEW 

YORKI 56-66 (1972) 

lli 

EGAN.F.C. TOOLEY 9M.R. 

GLENiAVIS CRYOGENiC PLANT COMMISSIONED. 

GAS WOQCO VOL 176. NO. 4644, 133-7 IAUG 

1973) 

119 
OTHER OOCUMENTS 

(CONT. J 

112 

ELRO0.C.W. 

A COMPARISON OF SUBCOOLEO VERSUS LIQUID 

HYDROGEN RiPUIREJlENTS. AIR FORCE AERO 

PROPULSION LAB., WRIGHT-PATTERSON AFB, 

OHIOI REPT. NO. AFAPL-TR-66-15 (APR 1966) 

OTHER OCCUHENTS 

(CONT. J 

120 

FFO0KS.R.C. 

29 PP 

113 

ESCHER,W.J.O. 

LIQUID HYOROGEN - FUTURE AIRCRAFT FUEL. 

BACKGROUNO, PAYOFF, AN0 C3YOGENIC 

ENGINEERING CHALLENGE. ACIVANCES IN 

CRYOGENIC ENGINEERING, VOL 20 (A 

COLLECTION OF INVITE0 PAFERS AN0 

CONTRIBUTED PAPERS PRESENTED AT NATIONAL 

TECHNICAL tiEETINGS DURING 1973 AND 19741, 

K. 0. TIHMERHALJS, EDITOR. PLENUti PRESS, 

NEW YORK* 70-81 (1975) 

114 

EVENS0N.J.H. 

LIQUIO HYDROGEN TANK INSULATION TESTS. 

GENERAL DYNAMICS/ASTRONAUTICS, SAN DIEGO, 

CALIF., REPT. NO. GOP-lOE-1483 (MAR 1962) 

36 PP 

115 

EW1KG.G.H. Stl1TH.F.L. 

Z)ESIGN, CONSTRUCTiON, AN0 OPERATION OF AN 

LNG PEAKSHAVING PLANT. LIQUEFIED NATURAL 

GAS (PROCEEOINGS OF THE INTERNATIONAL 

CONFERENCE AN0 EXHIl3ITION ZNO, PARIS, 

FRANCE, OCT 19-23, 197!lJ VOL 2 13 PP 

116 

EYLES,A.G. 

THERMAL AN0 PRESSURE-INOUCEO STRAINS IN 

INTERNAL CRYOGENIC INSULATIOM. ADVANCES 

IN CRYOGENIC ENGINEERING VOL 10, 224-32 

(PROC. OF CRYOGENIC ENGINEERING 

CONFERENCE, PHILADELPHIA, PA., AUG 18-21, 

1964) PLENUM PRESS, NEW YORK (1905) 

117 

FALCK-PE0ERSEN.G. 

INSULATION IN GAS TANKERS. (TN NORWEGIAN) 

KULCE (COPENHAGEN) VOL 19, NO. 4. 116-9 

(AUG 1965) 

118 

FEIN0.K. 

THERMAL CONUUCTIVITY 3F INSULATION. (IN 

GERMAN) KALTETECHNIK VOL 19, NO. 6, OKV 

ARBFITSBLATT 2-41A IJUN 1966) 

119 

FERR0.V. SACCH1.A. 

THERMAL CONDUCTIVITY tiEASUREHENTS OF 

INSULATING MATERIALS DOWN TO ASOUT -200 

DEGREES. PIG. SC1.r REND., SEZ. A VOL 8, 

NO. 6, 1667-79 (1965) 

MARINE -TRANSPORT OF L.N.G. ENGINEERING, * 

TRANSFORT AN0 OPtRATIONS .?:ESEASCF VOL c, 

285-94 (PROCEEOIhGS OF THE WOPLO 

PETR3LEUM CoNGRESS 7TH. 1967) ZLSEVI:P 

PUBLISHING CO., LTL. 119671 

121 

FIL1PE.A. LA1NE.F. 

ANISOTROPY OF THE THER:4AL CONDUCTIVITY OF 

POLYUDETHAN: RIG10 FOAMS EXPAN;)ED IN 

SITU. (IN FRFNCHJ BULL. INST. 1t~TEQ.N. 

FRO10 AF;NEXE 1961-3, 165-71 (FRESENTEO AT 

t4EETIF.G OF COMM. 2, 3, 66, + .?, 

CAMBYIOGE~ SEP 20-22, 1961) 

122 

FILSTEAD,C.G.rJR. 

THE DESIGN AND OPERATION OF LNG CHIPS 

‘rlITH FEGARO TO SAFETY. SHIPPIrdG WuRLO 

SHIPBUILOER VOL 165, NO. 3866, 259-62 

(FEB 1372) 

123 

FONESrS. 

SINGLE WALLED, SFACE SAVING, LiCLJIb 

NITROGEh OEWARS. REV. SCI. INSTRUM. VOL 

4tir NO. 10, 1362-3 (OCT 1969) 

124 

FORBES,F.W. MARlEL,C.R. 

EXPAfiCAdLE CRYOGENIC PIFE. ADVANCES III 

CRYOGENIC ENG. VOL 8, 411-6 (PROC, 

CRYOGENIC ENGINEERING CONFERENCE, LOS 

ANGELES, CALIF., BUG 14-10, 1962) PLEt;UM 

PRESS INC., NEH YO?K (146.3) 

125 

FOURNIER,O. LEROY,J.P. aEGENrjE,K. 

A NEW INSTRUMENT FOR FlEASURING THE 

CONTRACTION OF CELLULAR INSULANTS AT LOW 

TEMPERATURE. EARLY EXPERIMENTAL RESULT: 

O~TAIEIEO. (IN FRENCH) SOME 

THERHCPHYSICAL PRCPESTIES OF REFFIGE?AYTS 

AND LNSULANTS. IFROC. INTE?NATiCkAL 

INSTITUTE OF REFRIGERATICN COHMISlIOY 31, 

ZURICH, SWITZERLAND, SEP 27-29, 1973) 

dULL. INST. INT. FROIO, ANNEXE 1973-4, 

163-72 (19731 

126 

FRA0KCV.A. d. 

ON THE QUESTION CF NEW METHODS OF YEfiT 

INSULATION FOR APPARATUS OF INTENSC 3OLi). 

AKAO. NAUK S.S.S.R. OOKLASY VOL 61, UC. 

4, 549-51 (1451) (TRANS. BY MCSkIS 0. 

FRIEL)E:Ah, INC., NEEOHAM HEIGHTS, MASS. 

NO. F-116) 

127 

FREEYPN ,S. 11. 

PRO FECT IES OF VAFOR BARRIERS, ALlt’E SIVEC 

AND FOAMS AT CEYOGENIC AN0 ELEVATE0 

TEMPEFATURZS. L3CKHEEO AI?CRAFT C0R.p.. 

GEORGIA OIV., ?ARIETTAv GA., REFT. t:l. 

ER-5667 (APR 19621 53 PF 

120 
OTHER DOCUMENTS 

(CONT. 1 

128 

FUJIHASH1.Y. NAGOYA,Y. SH1BATA.K. 

CHARACTERISTICS OF THIN WALL 

REFRIGERATORS USING RIGIC POLYURETHANE 

FOAfl. HITACHI REV. VOL 14, NO. 9, 14-8 

(1965) 

129 

FULMER.0. 

MODEL 55 INSULATION INVESTIGATION, WS 

107A. GENERAL OYYAMICS/ASTRONAUTiCS, SAN 

OIEGO, CALIF., REPT. NO. GDA-558-2307-i 

OTHER JCCUMENTS 

(CONT.) 

135 

GENERAL OYNAMICS/CONVAIR 

DESIGN AN0 DEVELOPMENT OF PRESSURE AND 

REPRESSURIZATION PURGE SYSTEM FOR 

REUSAPLE SPACE SHUTTLE MULTILAYER 

INSULATION SYSTEM. GENERAL 

OYNAMICS/CONVAIR, SAN DIEGO, CALIF., 

QUARTERLY PROGRESS REPT., NO. 

REPT-584-4-708-QR-1, JUL-SEP 1971. 

NATIONAL AERONAUTICS AN0 SPACE 

AOMIYISTRATION REPT. NO. N4SA-CR-12iJ73r 

CONTRACT NO. NASB-27419, 173PF (DEC 19711 

(NOV 1959) 39 PP 

139 

GAS WORLD 

CRYOGENIC LOSSES REDUCED 3Y BALLS. GAS 

WORLD VOL 1739 NO. 4521, 291 (APR 19711 

131 

GAUSE9R.L. 

NUCLEAR GROUNO TEST MODULE INSULATION 

DEVELOFMENT. RESEARCH ACHIEVEMENTS 

REVIEW VOLUME 2, NATIONAL AERONAUTICS AND 

SPACE AOMINISTRATION, HUNTSVILLE ALA. 

GEORGE C. MARSHALL SPACE FLIGHT CENTER, 

TECH. ?fEMO. 53670 l19h7) PF 69-79 

132 

GENERAL OY NAMICS/CONVAIR 

CHARACTERISTICS OF A GELLED LIQUIO 

HYDROGEN POLYPHENYLEhE OXIDE (FPOI FOAM 

OPEN-CELL INSULATION SYSTEM. PHASE 1. 

GEfdERAL OY NAHICS/CONVAIR~ SAN CIEGO. 

CALIF.. AEROSPACE DIV., REPT. NO. 

GCCA-632-3-169. NATIONAL AERONAUTICS AN0 

SPACE AOMINISTRATION, HUNTSVILLE. ALA., 

GEORGE C. MARSHALL SFACE FLIGHT CENTER. 

REPT. NO. NASA-CR-124114, CONTRACT NO. 

NASB-272C3. 93PF (FED 1973) 

133 

GENERAL OYNAMICS/CONVAIR 

DESIGN AND OEVtLOPMENT OF POLYPHENYLENE 

OXIDE FOAM AS A REUSABLE INTERNAL 

INSULATION FOR LH2 TANKS. PHASE 1. 

GENERAL DYNAMICS/CONVAIR. SAN DIEGO* 

CALIF.. AEROSPACE DIV., REPT. NC. 

GOCA-632-1-89. NATIOhIL AERONAUTICS AN0 

SPACE ADMINISTRATION REPT. NO. 

NASA-CQ-123798, CONTRACT NO. NASB-27566, 

RIIPP (JUN 1972) 

134 

GENERAL OY NAMICS/CONVAIR 

GESIGN AN0 OEVELOPMENT OF POLYPHENYLENE 

OXIDE FOAM AS A REUSA3LE INTERNAL 

INSULATION FOR LH2 TANKS, PHASE 2. 

GENERAL OYNAMICS/CONV~IRI SAN OIEGO, 

CALIF., PROGRESS REPT. NO. 

GOCA-632-3-140s NATIONAL AERONAUTICS AN0 

SPACE AOMINISTRATION REPT. NO. 

NASA-CR-1239551 CONTRACT NO. NAS8-27566 

LSEP 1972) 07 PP 

136 

GENERAL DYNAMICS/CONVAIR 

FIXEO INSULATION OEVELOPMENT PROGRAM. 

GENERAL OYNAMICS/CONVAIRI SAN DIEGO* 

CALIF., FINAL REPT. NO. GOC-BTO68-059, 

NATIJEiAL AERONAUTICS AND SPACE 

AOMINISTRATION REPT, NO. NASA-CR-105599, 

CONTRACT NO. NAS3-3248 (MAY 1969) 271 PI’ 

137 

GENERAL ELECTRIC CO. 

TESTING OF OIELECTRIC MATERIALS AND 

APPLICATION TECHNIUUES IN ELECTRCNIC 

PACKAGING. NATIONAL AERONAUTICS AND 

SPACE AOMINISTRATION, HUNTSVILLE, ALA. 

GEORGE C. MARSHALL SPACE FLIGhT CENTER, 

FINAL REPT. NO. NASA-CR-102454, 

OOC-6?SD-4371 (DEC 1969) CONTR. NO. 

NASB-21333 128 PP 

138 

GERSTIN,HARRY 

HOW TC EVALUATE THE RIGID PLASTIC FOAMS. 

PROD. ENC. VOL 36, NO. 13, 59-68 (JUN 

1965) 

139 

GIBSON,G.H. WALTERS,W.J. 

CONSIEER SAFETY, RELIABILITY, COST IN 

SELECTING TYPE OF LNG STCRAGE. OIL GAS 

J. VOL 69, NO. 6, 55-9 (FED 1971) 

140 

GIBSON, G. H. WALTERSvW.J. 

SOME ASPECTS OF L.N.G. STORAGE. 

LIQUEFIED NATURAL GAS (PROCEEDINGS OF THE 

INTERNATIONAL CONFERENCE AN0 EXhIEITICN 

2ND. FARIS, FRANCE, OCT 19-23, 19701 VDL 

1 13 PP 

141 

G1ERYGA.J. H. JOE,C. LANDLER,Y. 

EVOLUTION OF THE THERMAL CONDUCTIVITY OF 

CELLULAR PLASTIC MATERIALS. (IN FRENCH) 

PROGq. REFRIG. SCI. TECHNOL. VOL 29 

195-2C7 (PROC. INT. CONGR. REFRIG. 12THt 

MAORIO, SPAIN, AUG 30-SEF 6, 1967) I’JST. 

INTa FROID, PARIS (1969) 

142 

GLASER,P.E. 

CRYOGENIC INSULATIONS. MACHINE OESIGrr 

VOL 399 NO. 199 146-52 IAUG 1967) 

121 
OTHER OOCUMENTS 

(CONT. 1 

143 

OTHER DOCUMENTS 

(CONT.) 

GLASER.P.E. 

THE DEVELOPMENT OF THERHAL INSULATIONS 

AND TECHNIQUES FOR USE AT VERY LOW 

TEMPERATURE. PROGR. REFRIG. SCI. 

TECHNOL, VOL 21 3-27 (PROC. INT. CONGR. 

REFRIG. 12THt tlAOR101 SPAIN, AUG JO-SEP 

6, 1967) INST. INT. FROIOt PARIS (1969) 

144 

GL4SER.P.E. 

EFFECTIVE THERMAL INSULATION. MULTI-LAYER 

SYSTEMS. CRYOGENIC ENC. NEWS VOL 4r NO. 

4, 16-24 (APR 1969) 

145 

GLASER9P.E. 

THERMAL PROTECTION SYSTEMS FOR LIOUIO 

HYOROGEN TANKS. LITTLE, A. 0.9 INC., 

CAMBRIDGE, MASS., REPT. NO. NASA-CR-62859 

(NOV 1962) CONTR. NO. NAS5-664, 64 PP 

146 

GLASER,P.E. BLACK, I.A. 

CRYOGENIC INSULATION SYSTE?4S. BULL. 

INST. INTERN. FRO10 ANNEXE 1960-2, 79-90 

(19601 

147 

GOFtlAN-ZAKHAR0V.P.M. 

COVERINGS FOR LIQUEFIED-GAS STORAGE 

CONTAINERS. NIZKOTEHPERATURNOYE 

KHRANENIYE SZHIZHENNYKH TEKHNICHESKIKH 

GAZOV, IZOATELSTVO TEKHNIKA, KIEV* 

UKRAINIAN SSR (1966) PP 141-5 TRANSL. BY 

JOINT PUBLICATIONS RESEARCH SERVICE, 

WASHINGTON, 0. C., NO. JPRS-42287, 

TT-67-32916, 10-4 (AUG 1967) 

148 

G0RMAN.P.T. 

EXTERNALLY INSULATE0 HULL STRUCTURE. 

U. s. PATENT 3~283,734 TNOV 1966) 

149 

GRAY1V.H. GELOER, T .F. 

EXTERNALLY BONOEO AN0 SEALED INSULATION 

FOR LIQUIO-HYDROGEN-FUELEO ROCKET TANKS. 

AOVANCES IN CRYOGENIC ENGINEERING VOL 5. 

131-8 (PROCEEDINGS OF THE 1959 CRYOGENIC 

ENGINEERING CONFERENCE) PLENUM PRESS, 

INC., NEW YORK (1960) 

150 

GREENBERGIS. 

METHANE FUEL SYSTEMS FOR HIGH MACH NUMBER 

AIRCRAFT. NATIONAL AERONAUTIC AN0 SPACE 

ENGINEERING AND MANUFACTURING MEETING, 

LOS ANGELES, CALIF., OCT. 6-101 1969. 

SOCIETY OF AUTOMOTIVE ENGINEERS PAPER 

690668 16 PP 

151 

GRIFFIN,J.O. SKOCHOOP0LEvR.E. 

PLASTIC FOAflS. ENGINEERING OESIGN FOR 

PLASTICS, CHAPTER 15, REINHOLD PUBLISHING 

CORP., NEW YORK (1964) PP 995-1071 

152 

GUTZHER,H.A. 

THERMAL CONOUCTIVITY OF HELIUM-PERMEATE3 

STYROFOAM. GENERAL 

DYNAMICS/ASTRONAUTICS, SAN DIEGO, CALIF., 

REPT. NO. GOA-7D2399 (AUG 1959) 14 PP 

153 

HALE, 0. 

LNG ECONOUICS AN0 TECHNOLOGY - 2ND 

EDITION. ENERGY COMMUNICATIONS, INC., 

DALLAS. TEX., 238PP (1974) 

154 

HALE, C. 

LNG TANKER JEVELOPMENTS. PIPELINE GAS J. 

VOL 1991 NO. 11, 52-3 (SEP 1972) 

155 

HALE,@.V. 

STUDY OF THERMAL CONDUCTIVITY 

REQUIREMENTS. VOLUME I. HIGH PERFORMAEICE 

INSULATION THERMAL CONOUCT IVITY TEST 

PROGRAM. LOCKHEEO MISSILES ANE SFACE 

CO.1 HUNTSVILLE, ALA., REPT. NO. 

NASA-CR-61279, LHSC/HREC-0143611-1 (1969) 

CONTR. NO. NASB-21347 109 PP 

156 

HALE.0. V. 0NEILL.M.J. 

STUDY 3F THERMAL CONOUCTIVITY 

REQUIREMENTS HIGH PERFORMANCE INSULATION. 

NATIONAL AERONAUTICS AND SPACE 

AOflINISTRATION, HUNTSVILLE, ALA. GEORGE 

C. flARSHALL SPACE FLIGHT CENTER, FINAL 

REPT. NC. NASA-CR-102600, LMSC/HREC 

0162128 (FEE 197C) CONTR. NO. NAS8-21347 

79 PP 

157 

_ HALEv0.V. QENY1G.D. HY0E.E.H. 

A GUARDED ELECTRICAL CYLINDRICAL 

CALORIMETER FOR MEASURING THERMAL 

CONDUCTIVITY OF MULTILAYER INSULATION. 

ADVANCES IN CRYOGENICS ENGINEEQING VOL 

15, 324-31 (PRDC. CRYOGENIC ENGINEERING 

CONFERENCE, LOS ANGELES, CALIF., JlJN 

16-18, 1969) K.O. TIMMERHAUS ED., PLENUM 

PRESS, NEW YORK (1370) 

158 

HAMHOhO ,M. B. gJR. 

AN ANALYTICAL MODEL FOR DETERMINING THE 

THERMAL CONDUCTIVITY OF CLOSED-CELL FOAM 

INSULATION. AIAA THERHOPHYSICS CONF. 

3RO1 LOS ANGELES, CALIF. (JUN 24-26. 

19681 PAPER NO. AIAA 68-766 IO PP 

159 

HAMMOhOeM.8. *JR. 

LIPUIC HYDROGEN TANK INSULATICN FOR THE 

S-II BOOSTER. CHEM. ENC. PROGR. SYMP. 

SER. VOL 62, NO. 61, 213-8 (1966) 

122 
OTHER OOCUMENTS 

(CONT. 1 

160 

HAMPTON, H. A. HURO,R. 

RECENT OEVELOPHENTS IN THE USES OF 

POLYURETHANE RIG10 FGAHS AS HEAT 

INSULATING MATERIALS, PROGRESS IN 

REFRIGERATION SCIENCE AND TECHNOLOGY VOL 

1, 317-24 TPROC. OF XTH INTERN. CONGR. OF 

REFRIG., COPENHAGEN, 1959) PERGAHON PRESS 

(1960) 

OTHER OOCUHENTS 

(CONT.) 

168 

HAYNES, J. HARALS0N.H.S. 

DEVELOPMENT OF NONDESTRUCTIVE TEST DEVICE 

FOR EVALUATION OF 314 INCH THICK 

POLYURETHANE SPRAY-ON FOAM INSULATION 

(SOFII ON THE SATURN S-II STAGE. 

NATIONAL AERONAUTICS AN0 SPACE 

AONINISTRATIONI NARSHALL SPACE FLIGHT 

CENTER* HUNTSVILLE, ALA., TECH. MEMO. NO. 

X-53852 (NAY 1969) 40 PP 

161 

HARD1NGrR.H. 

HEAT TRANSFER THROUGH LOW-OENSITY 

CELLULAR HATERIALS. IND. ENG. CHEH. 

PROCESS DESIGN DEVELOP. VOL. 3, NO. 2r 

117-25 (APR 1964) 

162 

HARO1NGvR.H. 

PREOICTING THE PERFORMANCE OF 

FOAH-INSULATED CONTAINERS. J. CELLULAR 

PLASTICS VOL 29 NO. 4, 206-13 TJUL 1966) 

163 

HASK1NS.J.F. 

MEASURE0 VALUES FOR THE COEFFICIENTS OF 

LINEAR EXPANSION OF FOLYCEL 420 AN0 

CONOLON 506 AT LOW TEMPERATURES. GEN. 

OYNAMICS CORP., CONVAIR ASTRONAUTICS 

DIV., REPT. MRG-154 (HAY 1960) 10 PP 

164 

HAUCK,J.E. 

PLASTIC FOAMS. HATER. OESIGN ENG. VOL 

E3, NO. 5, 87-102 (HAY 1966) 

165 

HAWKER SIOOELEY OYNAMICSI LTO. 

EUROPEAN SPACE TUG. PRE-PHASE A STUOY. 

APPENDIX 3 - PROPELLANT CONTROL AND 

PROPULSION. HAWKER SIOOELEY DYNAMICS, 

LTD., HATFIELD, ENGLAND, REPT. NO. 

HSO-TP-7227-APP-3, EUROPEAN LAUNCHER 

OEVELOPMENT ORGANISATION CONTRACT NO. 

ELOO-CTR-17/7/44, 103PP T JAN 1971) 

166 

HAWKER SIOOELEY DYNAMICS, LTO. 

EUROPEAN SPACE TUG. PRE-PHASE A STUDY, 

PAPT 2, VOLUME 3. PROPELLANT AN0 

PROPULSION. HAWKER SIOOELEY DYNAMICS, 

LTD.9 HATFIELO, ENGLAND, REPT. NO. 

HSO-TP-7264-VOL 31 EUROPEAN LAUNCHER 

OEVELOPHENT ORGANISATION CONTRACT NO. 

ELDO-CTR-17/7/44r 89PP (AUG 19711 

167 

HAYAKAWAIS. 1IJIHA.T. ITO,K. 

HATSUMOTO, T. 0NO.T. UYAtlArK. 

NISHIMURA, T. 

A BALLOON-BORNE INFRARED TELESCOPE COOLED 

BY LIQUID NITROGEN. JPN. J. APPL. PHYS. 

VOL 14, NO. 7, 1041-7 (JUL 1975) 

169 

HEOBERG ,C. R. 

CRYOGENIC INSULATION 

OEFLAGRATION/OETONATION SENSITIVITY TEST 

REPORT. GRUMMAN AEROSPACE CORP., 

BETHPAGE* N.Y.1 REPT. NO. SUBST 

391-100R-03, GIOEP-501.78.19.00-K4-01 

(OCT 19701 I3 PP 

170 

HEFFNER9G.R. 

REEFER TRENDS. J. CELLULAR PLASTICS VOL 

2, NO. 6, 310-6 (NOV 19661 

171 

HEL0ENFELSqR.R. 

STRUCTURAL PROSPECTS FOR HYPERSONIC AIR 

VEHICLES. AEROSPACE PROCEEOINGS 1966 

(ROYAL AERONAUTICAL SOC. CENTENARY CONGR. 

AND INTERNATIONAL COUNCIL OF THE 

AERONAUTICAL SCIENCES CONGRESS 5TH. 

LONDON, ENGLAND, SEP 12-16, 1966) J. 

BRAOBROOKE ET AL EOS, SPARTAN BOOKS, NEW 

YORK (19671 VOL 1 PP 561-83 

172 

HE4TZ.J. 

CAST FOAM INSULATION EVALUATION. GEN. 

3YNA#ICS/ASTRONAUTICS, SAN OIEGO, REPT. 

NO. MRC-275 (OEC 1962) CONTR. HO. AF 

33(616)798‘+, 25 PP 

173 

HERTZqJ. KNOWLES.0. 

SURVEY OF THERMAL PROPERTIES OF SELECTED 

MATERIALS. GENERAL OYNAflICS/CONVAIR~ SAN 

OIEGO, CALIF., REPT. NO. ZZL-65-OGB (FEE 

19651 CONTR. NO. AR-504-l-553, 172 PP 

174 

HIGGINS rR.G. HCCONARTY, W.A. 

ANTHOMY ,F. fl. 

DESIGN AN0 ANALYSIS OF LIGHTWEIGHT 

THERHAL PROTECTION SYSTEMS. BELL 

AEROSYSTEMS CO.9 BUFFALO* N. Y.r REPT. 

NO. AFML-TR-67-377 (OEC 1967) CCNTR. NO. 

F 33(615)-67-C-1091 174 PP 

175 

HILA0CvC.J. PROOPS,W .R. 

THERMAL CON9UCTIVITY OF RIGID URETHANE 

FOAH INSULATION IN LOW TEMPERATURE 

SERVICE. J. CELLULAR PLASTICS VOL 5r NO. 

5, 299-303 (SEP-OCT 1969) 

123 
OTHER OOCUHENTS 

(CONT.) 

176 

HILOENBRANOIC.V. 

URETHANE FOAN INSULATION HAZARDS. SAFETY 

IN AMHONIA PLANTS ANO RELATED FACILITIES, 

109-10 (PROC.. 17TH ANNUAL SYNPOSIUH, 

AICHE NATIONAL MEETING, SALT LAKE CITY, 

UTAH, AUG 19-21 1974) AICHE (AflHONIA 

PLANT SAFETY) 9 NEW YORK (1975) 

OTHER DOCUHENTS 

(CONT.1 

165 

177 

H1LL.H.E. 

NATERIALS FOR FOAN TYPE INSULATION. 

CRYOGENIC RESEARCH AT HSFC. RESEARCH 

ACHIEVEMENTS REVIEW VOL 4r NO. 2, 178-84 

INOV 1971). NATIONAL AERONAUTICS AN0 

SPACE AOl4INISTRATION TECH. NEflO. NO. 

X-64561 

170 

H1LLBERG.E.T. 1SENBERG.L. 

INSULATED TANK BASE AND INSULATED BLOCK. 

U. s. PATENT NO. 3.818.664 (JUN 19741 

179 

HOCK1NG.C.S. 

GAS FILLED THERMAL INSULATION. HIGH 

NOLECULAR WEIGHT GASES AND CELLULAR 

POLYURETHANE. KYLTEKN. TIOSKR. VOL 19, 

NO. 2, 21-3 (APR 19601 

180 

HOLC0NBE.A.H. 

STORAGE AN0 OISTRIBUTION OF CRYOGENIC 

LIQUIDS. CRYOGENICS INO. GASES VOL 49 

NO. 6, 67-70 (JUN 1969) 

181 

HOLLANO.W.0. 

THE tlEASUREHENT OF THERMAL CONDUCTIVITY 

OF A PLASTIC FOAN AT CRYOGENIC 

TENPERATURES. LOCKHEED-GEORGIA CO., 

MARIETTA, GA. REPT. NO. ER-5683 (JUL 

1962) 9 PP 

182 

HOOVERIT .E. 

LNG PIPE LINES ARE FEASIBLE. PIPE LINE 

INO. VOL 35. NO. 6, 21-4 IOEC 1971) 

103 

HO0VER.T.E. 

TECHNICAL FEASIBILITY AN0 COST OF LNG 

PIPELINES. LIQUEFIEO NATURAL GAS 

(PROCEEDINGS OF THE INTERNATIONAL 

CONFERENCE AN0 EXHIBITION 2NO. PARIS, 

FRANCE, OCT 19-23, 1970) VOL 1 IG PP 

184 

HOR0.J. PARRISH1W.R. VOTH.R.0. 

HUST1J.G. FLYNN,T.M. SIN0T.C.F. 

OLIEN,N.A. 

SELECTED TOPICS ON HYDROGEN FUEL. 

NATIONAL BUREAU OF STANDARDS, BOULOER, 

COLO.. CRYOGENICS DIV.. REPT. NO. NBSIR 

75-803 (JAN 1975) 207 PP 

HUOGEFIS,H. R. (JR. 

CELLULAR PLASTICS IN RAILROAD 

REFRIGERATOR CARS AND PIGGYBACK TRAILERS. 

J. CELLULAR PLASTXCS VOL 2, NO. 6, 316-7 

(NOV 1966) 

186 

HUGGETT CC. 

FIRE HAZAROS IN SPACECRAFT ATMOSPHERES. 

NATIONAL AERONAUTICS AND SPACE 

ADMINISTRATION, -lUNTSVILLE, ALA. MARSHALL 

SPACE FLIGHT CENTER , ANNUAL MEETING 5TH 

WORKIKG GROUP ON EXTRATERRESTRIAL 

RESOUGCES, TECH. MEMO. X-63876 (MAR 1967) 

PP 191-0 

187 

HUGGETT CC. VON ELBE, G. HAGGERTY, W. 

GR0SSNAN.J. 

THE EFFECTS OF 100 PERCENT OXYGEN AT 

REDUCE0 PRESSURE ON THE IGNITIJILITY &NJ 

COMBUSTIBILITY OF MATERIALS. ATLANTIC 

RESEARCH CORP., ALEXANORIA, VA., ADVANCED 

TECHNOLOGY DIV., FINAL REPT. NO. SAM 

TR-65-73 (OEC 1965) CONTR. NO. AF41 

(6091-2470 35 PP 

108 

iiUGHES, T.A. 

LIQUIO HYDROGEN INSULATION HATERIALS. 

AEROJET GENERAL CORP., AZUSA, CALIF.. 

REPT. NO. 62-60, MN 442 A (1962) 4 PP 

189 

HURST1S.C. 

THERMAL INSULATION OF CRYOGENIC PLANT. 

CHEH, PROCESS ENG. VOL 52, NO. Zr 43 AND 

46 (FEB 1971) 

190 

ICHINOSE,Y. 

A NEW CONTAINMENT SYSTEM FOR Lt!G 

CARRIERS, APPLICATIONS OF CRYOGENIC 

TECHNOLOGY, VOL 6, PROC. CRY0/73 CONF. t 

6TH. LOS ANGELES, tAL1F.r OCT Z-4, 1373, 

S. H. BOOTH AN0 R. H. VANCE, EDITORS. 

SCHOLIUM INTERNATIONAL INC., FLUSI'ING, 

N. Y., 35-46 (1974) 

191 

ISENBERG,L. 

THERMAL CHARACTERISTICS GF CRYOGENIC 

INSULATION. NO. AM. AVIATION, INC., 

OOWNEYv CALIF.. REPT. (NOV 19631 IOED 

347.15.00.00-Fl-02, 33 PP 

192 

ISENBFRGvL. H1LLBERG.E.T. 

THERflA’mLY INSULATE0 CiNTAINER. U. S. 

PATENT NO. 317579982 (SEP 19731 

193 

1SENBERG.L. JOHNS0N.C.L. 

STRUCTURAL CRYOGENIC INSULATION FOR 

LIQUI@-FUEL ROCKETS. AEROJET-GEb!ERAL 

CORP.9 AZUSAr CALIF., SFEC. REPT. ho. 

2676 (AUG 1963) 31 PP 

124 
OTHER OOCUHENTS OTHER DOCUMENTS 

(CONT. J (CONT .I 

194 204 

JACKS0N.R.G. KELLER. J.P. 

CONTAINERS FOR LIQUEFIED GASES. U. 5. INSULATED UNOERGROUNO CONDUIT. U. S. 

PATENT NO. 31595,424 (JUL 1971) PATENT 3,484,509 (OEC 1969) 

195 205 

JACKS0N.R.G. KERL1N.E.E. SflITH,E.T. 

IMPROVEMENTS IN STORAGE CONTAINERS FOR MEASURED EFFECTS OF THE VARIOUS 

COLO LIQUEFIED GASES. BRITISH PATENT COMBIhATIONS OF NUCLEAR RADIATION, 

lr203.496 (AUG 19701 VACUUM, AND CRYOTEHPERATURES ON 

ENGINEERING MATERIALS. VOLUME I. 

196 RADIATION-VACUUM AND 

JACKSON,R.G. RAOIATION-VACUUM-CRYOTEMPERATURE TESTS. 

THERMAL INSULATION STRUCTURES. U. S. GENERAL OYNAMICS/FORT WORTH* TEX. t ANN. 

PATENT 3r525.661 (AUG 1970) REPT. NO. FZK-168-l (MAY 1964) CONTR. NO. 

NAS0-2450, 509 PP 

197 

JOHNSTON,H.L. 206 

LIQUID HYDROGEN PROPELLANT FOR AIRCRAFT KERLIN,E.E. SM1THqE.T. 

AN0 ROCKETS. OHIO STATE UNIV. RESEARCH MEASURED EFFECTS OF THE VARIOUS 

FOUNOATION. COLUMBUS. PROGR. REPT. NO. 22 COMBINATIONS OF NUCLEAR RAOIATION, 

(MAR 1949) .CONTR. NO; VACUUM, AND CRYOTEHPERATIJRES ON 

bl33-038-AC-14794(16243) 79 PP ENGINEERING MATERIALS. VOLUME II. 

190 

JOURNAL OF REFRIGERATION (LONOON) 

INSULATION OF SHIPBOARD ETHYLENE TANKS. 

J. REFRIG. (LONOON) VOL 9, NO. 8, 203 

(AUG 1966) 

200 

199 

KAHLENBERGrF. 

THE INFLUENCE OF GAS-FILLE9 CELLS ON THE 

THERMAL CONDUCTIVITY OF RIG10 

POLYURETHANE FOAfl. INTERN. CONGR. OF 

REFRIGERATION, IlTH, MUNICH IAUG 1963) 

PAPER 11-19. 3 FP 

RADIATION-CRYOTEHPERATURE TESTS. GENERAL 

DYNAMICS/FORT WORTH, TEX., ANN. REPT. NO. 

FZK-188-Z (MAY 1964) CONTR. NO. 

NASB-2450, 286 PP 

237 

KEY9C.F. GAYLE9J.B. 

EFFECT OF LIQUID NITROGEN OILUTION ON LOX 

IMPACT SENSITIVITY. NAT IONAL AERONAUTICS 

AND SPACE ADMINISTRATION TECH. flEtl0. NO. 

X-53208 (FEB 1965) 31 PP 

CAVERN STORAGE OF LIQUEFIEO NATURAL GAS. 

ENGINEERING, TRANSPORT Ah0 OPERATIONS 

208 

KHAN9A.R. ANOERS0N.P.J. EAKIN,B.E. 

KAO SOAP CO.. LTD., JAPAN 

POLYURETHANE FOAM LAYERS FOR TEMPERATURE 

MAINTENANCE IN LOW-TEHPERATURE 

RESERVOIRS. (IN FRENCH) FRELCH OEMANOE 

RESEARCH VOL 6, 323-32 (PROC. WORLD 

PETROLEUM CONGRESS 7TH. 1967) ELSEVIER 

PUBLISHING CO., LTO. (1967) 

NO. 2r158v 382 (OCT 1972) 209 

KHAN, A. R. EAKIN,B.E. ANOERS0N.P. J. 

201 

CRACK DETECTING MEANS. U. S. PATENT NO. 

KATSUTA,K. 

3.921,430 (NOW 19751 

LOW TEMPERATURE LIQUID STORAGE TANK OF 

THE INTERNAL HEAT INSULATING TYPE HAVING 

202 

KATSUTA,K. 

210 

INSULATING MEANS FOR UNDERGROUND ST09AGE 

K1LPERT.R. WINS0R.E.J. 

SYSTEM. 

BAUERrR.H. 

SPRAYED INTERNALLY INSULATED PIPE. U.S. 

U. S. PATENT 3,418,812 (OEC 31, 

PATENT 3r425.455 lFEB 1969) 

1968) 

LOW TEMPERATURE LIQUIC STORAGE TANK OF 

THE INTERNAL HEAT INSULATING TYPE HAVING 

LEAKAGE DETECTING MEANS. U. S. PATENT 

NO. 3r913.341 (OCT 1975) 

203 

KELLER9E.E. 

SAFETY OF NATERIALS IN CONTACT WITH 

LIQUIO OXYGEN. GENERAL-iYNAWICS/CONVAIR, 

SAN GIEGO, CALIF., REPT. NO. GDC-8614 

211 

KLEHEhS ,P. G. GREENBERG, I. N. 

RADIATIVE HEAT TRANSFER THROUGH COMPOSITE 

MATERIALS. J. APPL. PHYS. VOL 44, NO. 71 

2992- 5 (JUL 1973) 

212 

KNOBB0UT.J.A. COLENBRANOEti.C.8. 

PROPERTIES OF PFO IN REGARO-TO ITS 

APPLICATION IN Lh TANK INSULATION. 

(FEB 1957) 26 PP CENTRAL TECHNICAL INSTITUTE T.N.O.9 

DELFT, NETHERLANDS, REPT. NO. 69-02195 

(MAY 1969) 104 PF 

125 
OTHER OOCUtlENTS 

(CONT. b 

213 

KNOBB0UT.J.A. VAN BEZOOYEN, N. 

THERUAL SHOCK INVESTIGATIONS. CENTRAL 

TECHNICAL INST.. TNOt THE HAGUE, 

NETHERLANDS, REPT. NO. 69-03952s 1lPP 

tOCT 1969) 

OTHER OOCUHENTS 

(CCNT. J 

221 

214 

KNOX,P.H.,JR. MCGREH, J.L. 

LIQUEFIED GAS CONTAINER INSULATION. 

U. S. PATENT 39224,623 (DEC 1965) 

215 

KN0X.R.E. 

INSULATION PROPERTIES OF FLUOROCARBON 

EXPANOEO RIGID URETHANE FOAM. AM. SOC. 

HEATING, REFRIG., AIR CONDITIONING ENGRS. 

SEMI-ANNUAL METING (NEW YORK, FEB 11-14, 

19631 PAPER, 6PP 

216 

KOGL1N.B. 2IflNIqW.F. 

OETERHINATION OF THE THERMAL 

CONOUCTIVITY, THE SPECIFIC HEAT AND THE 

WEIGHT BY VOLUtiE (GROSS DENSITY) OF 

INSULATIONS FOR ROCKET TANKS FILLEO HITH 

LIQUID HYDROGEN. PART I. OESCRIPTION OF 

MEASUREMENT PROCEOURE. ELOOXECLES REV. 

TECH. VOL 21 3-28 (1967) TRANSL. BY 

TECHTRAN CORP., GLEN BURNIE, MO.. NO. 

NASA-TT-F-11146 (JAN 1968) CONTR. NO. 

NASH-1695 27 PP 

217 

K0LFFgA.R. VAN GELSO0RP.B.A. 

PROPERTIES AN0 MANUFACTURE OF HARD 

EXPANOEO POLYURETHANE AOAPTEO TO 

REFRIGERATING INSULATIONS. (IN DUTCH) 

NED. VER. KOELTECHN. flEOE0. VOL 54. NO. 

5, 160-6 (SEP-OCT 19611 

210 

KRAUS,S. 

EROSION OF POLYURETHANE INSULATION. 1. 

SPACECR. ROCKETS VOL 129 NO. 4, 209-12 

(APR 1975) 

219 

KROPSCHOT, R. H. 

ADVANCES IN THERMAL INSULATION. ADVANCES 

IN CRYOGENIC ENGINEERING, VOL 16, 104-8 

(PROCEEDINGS OF THE CRYOGENIC ENGINEERING 

CONFERENCE, COLORAOO UNIV., BOULOER, JUNE 

17-19, 1970). PLENUM PRESS, N. Y. (1971) 

220 

KROPSCH0T.R.H. 

CRYOGENIC INSULATION (MATERIALS AN0 

TECHNIQUES). AN. SOC. HEATING, REFRIG. 

AIR CONOITIONING ENGRS. J. VOL 1, 45-54 

(SEP 1959) PRESENTED AT ASHRAE ANNUAL 

MEETING (LAKE PLACID, N.Y.r JUN 22-24, 

1959) 

KROPSCH0T.R.H. 

LOH TENPERATURE INSULATION. APPLIED 

CRYOGENIC ENGINEERING FOR BALLISTIC 

MISSILES AN0 SPACE VEHICLESI 152-69 JOHN 

WILEY AN0 SONS, INC., NEW YORK (1962) 

222 

KURYLA,W.C. CHILOERS,J.W.,JR. 

COLO CRACK-FREE RIGID URETHANE FOAMS. 

u. S. PATENT 3r472r800 (OCT 1969) 

223 

KVAtlS0AL.R. 

EXPERIENCE FROM DESIGN CONSTRUCTIGN ANG 

INITIAL COMMISSIONING OF THE FIRST MOSS 

ROSENBERG LNG CARRIERS. NEW OEVELCPHENTS. 

LNG 73, PROC. SECOND LNG TaANSPORTATION 

CONF. (LONDON, ENGLAND* CCT 23, 1973). 

IPC INDUSTRIAL PRESS, LTC., LONOON. 

ENGLANO, 50-72 (19741 

224 

KVAHSLAL,R. RAt4STAO.H. BOGNAES ,R. 

FRANK9H.J. 

THE DESIGN OF AN 89 JO0 H(3) LNG CAQQIER 

WITH SPHERICAL CARGO TANKS AN0 NO 

SECONDARY BARREER. LIQUEFIED NhTURAL GAS 

(PROCEEOINGS OF THE INTERNATIONAL 

CONFERENCE AND EXHIBITION 2NDq PARIS, 

FRANCE, OCT 19-23, 1970) VOL 1 30 PP 

225 

LACAZE,A. 

NEUTRON MOOERATION .AT VERY LOki 

TEMPERATURES. (IN FRENCH 1 COMMISSARIAT A 

L ENERGIE ATOHIQUE, GRENOBLE, FRANCE, 

CENTRE 0 ETUOES NUCLEAIRES, REPT. NO. 

CEA 2t12, 99 PP (1962) 

226 

LA1NG.G. 

PRE-INSULATED PIPELINES. NATURAL GAS VOL 

19 NO. 5, 31-3 (AUG 19681 

227 

LAING,G. 

PRE-INSULATED PIPELINES, PIPES PIPELINES 

INTERN. VOL 13, NO. 0, 36-8, 41 (AUG 

1968) 

220 

LANGTON 9R.G. 

LIQUID HYOROGEN TANK THERMAL CALCULATIONS 

FOR A SYNCHRONOUS ORBIT MISSION. ROYAL 

AIRCRAFT ESTABLISHMENT, FA~NBOROUGH, 

ENGLAND, TECH. REPT. NO. 65064 (APR 19651 

9a PP 

229 

LASHMET ,P. K. MEIER,R.N. S1EG~IST.G.W. 

A STU!?Y ON CLOSED-LOOP CRYOGENIC SYSTEMS 

FOR TELEMETRY MASER AMPLIFIERS. AIR 

PRODUCTS AN0 CHEMICALS, INC., ALLENTOWH, 

PA., REPT. NO. ASO-TS-61-311 (AUG 1'3t;l) 

CONTR. NO. AF 33(616)-7231 98 P’ 

126 
OTHER OOCUHENTS OTHER OCCIJrlENTS 

(CONT. b (CONT.1 

230 

LAVERHAN,R. J. 

APPARATUS FOR MEASURING THE THERMAL 

CONOUCTIVTTY OF INSULATING HATERIAL. 

u. S. PATENT 3,592,060 (Jul. 1971) 

231 

LEACH,L.L. 

INSULATIONS FOR CRYOGENIC VESSELS. 

PETROL. REFINER VOL 411 NO. 11, 241-4 

(NOV 1962) 

232 

LEHONSIC.R. 

CRYOGENIC STORAGE VESSEL. U. S. PATENT 

NO. 3r814r275 1JUN 1974) 

233 

LIG1,J.J. 

PROCESSING HITH CRYOGENICS. PART 1. 

HYDROCARBON PROCESS. VOL 48, NO. 4, 93-6 

(APR 1969) 

234 

LIGI9J.J. 

235 

PROCESSING HITH CRYOGENICS. PART 2. 

HYOROCARBON PROCESS. VOL 481 NO. 5. 

137-40 (HAY 1969) 

239 

LOCKHEEO flISSILES AND SPACE CO. 

SHUTTLE CRYOGENIC SUPPLY SYSTEM 

OPTIMIZATION STUDY VOLUME 6 - APPENDIXES. 

LOCKHEEO MISSILES AN0 SPACE CO., 

SUNNYVALE* CALIF., FINAL REPT. NO. 

LtlSC-A991396-VOL-6. NATIONAL AERONAUTICS 

AND SPACE ADMINISTRATION REPT. NO. 

NASA-CR-133959, DONTRACT NO. NAS9-11330, 

202PP (JUN 19731 

240 

L0FGREN.C.L. GIESEKING.0.E. 

DEVELOPMENT OF MANUFACTURING TECHNIQUES 

FOR APPLICATION OF HIGH PERFORMANCE 

CRYOGENIC INSULATION. BOEING CO. 9 

SEATTLE, WASH. MISSILE AN0 INFORIIATION 

SYSTEMS OIJ. t REPT. NO. NASA-CR-61557, 

INTERhAL INSULATION OF CONTAINERS FOR 

02-109005-l (OCT 1967) CGNTR. 140. 

NASB-21172 

LIQUIDS HAVING LOWER BOILING POINT THAN 

50 PP 

241 

L0H.W.L. 

LIQUEFIED NATURAL GAS. JOrlN WILE’ AN@ 

SONS, INC.. NEW YORK, 185PP (1974) 

242 

LORENT2EN.H.L. 

LITTLE (ARTHUR 0.). INC. 

BASIC INVESTIGATION OF MULTI-LAYER 

INSULATION SYSTEMS. LITTLE (ARTHUR 0.1, 

INC., CAM3RIOGE, MASS. FINAL REPT. AOL65958-00-04, NASA CR-54191 (OCT 1964) 

CONTR. NO. NAS3-4181 290 PP 

ATMOSPHERIC TEflPERATURE. U. S. PATENT 

NO. 2.958.442 (NOV 1960) 

243 

LOVEvC.C.vJR. 

LIQUIO HYDROGEN STORAGE PARAMETERS FOR A 

LUNAR VCYAGE. GENERAL 

236 OYNAYICS/ASTRONAUTICSI SAN OIEGOt CALIF. t 

LITlLE (APTHUR 0.1, INC. REPT. NO. GJA- AE600848 (BUG 1960) 36 PP 

DESIGN OF THERMAL FROTECTION SYSTEHS FOR 

LIQUIO HYDROGEN TANKS. LITTLE, ARTHUR 

0.. INC., CAMBRIDGE, MASS., REPT. NO. 

NASA CR 55252 (APR 1963) CONTR. NO. NAS 

5-664 AND NASU-615, 79 PP 

237 

LITTLE (ARTHUR 0.1 t INC. 

REFRIGERATED TRANSMISSION LINE STUDY. 

VOLUME II. TECHNIQUES AND REFRIGERATION 

SYSTEMS FOR COOLING COMPONENTS OF 

HICROWAVE RECEIVING SYSTEHS TO 80-100 

DEGREES K. LITTLE (ARTHUQ 0.1. INC.9 

CAMBRIOGE, MASS., REPT. NO. 

NASA-CR-881201 C-68600, VOL II (MAR 1967) 

CONTR. NO. NAS7-100 AN0 JPL-951638 166 PP 

244 

LUOTKE,P.R. 

DEVELOPMENT OF INSULATION 

TRANSFER-STANOAROS USING A FLAT PLATE 

CALORXMETER. NAT. EUR. STAND. (U.S.), 

INTERNAL REPT. NO. 73-3011 46PP (MAR 

1973) 

245 

LUSKwt. I. OORNEY,G.C. 

LNG STORAGE TANK SYSTEMS. INTERNATIONAL 

CONFERENCE AN0 EXHIBITION ON LIQUEF IEO 

NATURAL GAS, 3RO. WASHINGTON, O.C., SE!’ 

24-23, 1972, INSTITUTE OF GAS TECHNOLOGYI 

CHICAGO, ILL., SESSION-V/PAPER-S, 12 PP 

(1972) 

238 

L0CK.J. 246 

THERMAL INSULATION FOR PROCESS PLANT. LUSK.D.T. 0ORNEY.O.C. 

FROCESSING VOL 21, NO. 4. 31-5.8 (APR LNG STORAGE-TANK ~YSTEHS ARE SAFE ANY 

1975 1 VERSATILE. OIL GAS J. VOL 70, NO. 41, 

91-5 (OCT 1972) 

127 
_,., . . ..___. -- .._.._.--.... 

OTHER DOCUMENTS 

(CONT.) 

247 

LY0NS.R.H. 

LABORATORY TESTS LIQUID HYOROGEN 

INSULATION MATERIAL. AEROJET-GENERAL 

CORP., SACRAMENTO, CALIF., REPT. NO. MN 

538 fNOV 1962) IOEP SEPT. NO. 

501.78.50.00-A6-06, 1 PP 

OTHER 3OCUMENTS 

(CONT.) 

256 

MATTAROLO,F. 

NEW IRSULANTS AND MOOERN INSULATING 

TECHNIQUES. (IN FRENCH) PROGR. REFRIG. 

SCI. TECHNOL. VOL 2. 29-57 (PROC. INT. 

248 

MACCALOUS, J.W. THOMAS,O.A. 

OEVELOPHENT OF EXTERNAL PQOTECTION 

MATERIALS FOR CRYOGENIC TANKS. NEW 

INDUSTRIES AN0 APPLICATIONS FOR ADVANCED 

MATERIALS TECHNOLOGYI 534-41 (PROC. 

NATIONAL SAMPE SYMPOSIUM AN0 EXHIBITION 

19THv BUENA PARK* CALIF., APR 23-25, 

1974) SOCIETY FOR THE ADVANCEMENT OF 

MATERIAL AND PROCESS ENGINEERING* AZUSA, 

CALIF. (1974) 

249 

MARINE ENGINEERING/LOG 

A BIG MARKET FOR EXOTIC, EXPENSIVE 

MATERIALS. MARINE ENG./LOG VOL 77, NO. 

10, 48-9 (SEP 1972) 

250 

HARINE ENGINEERING/LOG 

MANY CARGO CONTAINMENT SYSTEMS ARE 

AVAILABLE. MARINE ENG./LOG VOL 77, NO. 

IO* 40-3 (SEP 1972) 

251 

MARINE ENGINEERING/LOG 

MOSS VERFT DELIVERS ITS FIRST SPHERICAL 

ALUtiINUM-TANK LNG CARRIER. MARINE 

ENC./LOG VOl 79, NO. 3, 50-2 (MAR 1974) 

252 

MARKS, J.B. HOLTON.K.0. 

PROTECTION OF THERMAL INSULATION. CHEM. 

ENG. PROGR. VOL 70, NO. 8, 46-9 (AUG 

1974) 

253 

MARSHALL,J.E. 

AN INFLATABLE THERMAL QAGIATION SHIELD 

FOR SPACE APPLICATIONS. FROCEEOINGS OF 

THE AEROSPACE EXPANDABLE STRUCTURES CONF. 

2N0, HINNEAPOLIS, MINN. (MAY 25-27, 19651 

PP 305-38 

254 

MARTIN,R. 

NEW LNG TANKER IS STEP TOHARO ECONOMIC 

WORLDWIDE GAS MARKET. AM. GAS J. VOL 

193, 41-3 (JUN 1966) 

255 

MATESANZ,A. 

INSULATING FOR CRYOGENICS. CHEM. 

PROCESSING VOL. 24, 28-30, 37 lJUL 19611 

CONGQ. REFRIG. IETH; MAORIO, SPAIN; AIJG 

30-SEF 6r 1967) INST. INT. FRCID, PARIS 

257 

MAY0.F. 

THE STORAGE OF LIPUEFIEC~ HYOROCARBON 

GASES. INST. PETROL. REV. VOL 19, 233-42 

(JUL 1965) 

258 

MCCANOLESS,T.O. 

PHYSICAL PROPERTY STUOY GF PGLYSTYRENE 

FOAM (210-050). ACF INDUSTRIES, INC., 

ALBUQUERQUE, N. MEX.r REFT. NO. ACF-10 

(JUN 1965) CONT. NO. AT(29-I)-1352, 32 PP 

259 

MCCLINTCCK,R.M. 

LOW TEMPERATURE FROPERTIES OF PLASTICS 

FOAMS. SOC. PLASTICS ENGRS. J. VOL 14. 

NO. llr 36-8 INOV 19581 

260 

MCGREHvJ.L. 

A COMFARATIVE STUDY OF AIRYORNE LIQUID 

HY OROGEN TANK INSULATION. ADVANCES IN 

CRYOGENIC ENG. VOL 8, 387-92 (PROC. 3F 

CRYOGENIC ENGINEERING CONFERENCE, LOS 

ANGELES, CALIF., BUG 14-16, 1962) PLENUM 

PRESS INC., NEW YORK (1963) 

261 

tlCINTIRE.0.R. KENNEOY,R.N. 

STYROFOAM FOR LOW-TEMPERATURE INSULATION. 

CHEH. EhG. PROGR. VOL 44, NO. 9, 727-35 

(SEP 19C8) 

262 

MCMILLAN.W.0. CARTER, H. G. 

LIGHTFOCT,R.P. 

EVALUATION OF CRYOGENIC INSULATIGN 

MATERIALS AN0 COMPOSITES FOR USE IN 

NUCLEAR RADIATION ENVIRONMENTS. 

INSULATION SYSTEM TEST. GENERAL 

DYNAMICS/FORT HORTdr TEX., REPT. NO. 

FZK-349 (JUN 1968) CONTR. !jASB-18GLO 

137 PP 

263 

MEARNS,W.,III PEET1J.R. STRACKE1F.H. 

TOBYE.1.T. 

VESSEL FOR TRANSPORTING LOW TEMPCRATURE 

LIQUILS. U. S. PATENT 3,101,8cl (AU5 

1963 1 

264 

MEESEhrH. 

TANKER FOR LIQUID GAS. U. S. PATENT 

39122,259 (FEE 15641 

128 
OTHEQ OOCUMENTS OTHER OGCUMENTS 

(CONT. 1 (CONT .) 

265 274 

MENARO. J. SEGEL,M. MOELLER,C.E. 

CRYOGENIC ASPECTS OF THE DEVELOPMENT OF A SPACECRAFT OEHANOS BRING NEW THERMAL 

HYOROGEN-OXYGEN STAGE STRUCTURE. 

CRYOGENIC ENGINEERING - PRESENT STATUS 

AND FUTUQE DEVELOPMENT (PROC. GF THE 

:$ERNATIONAL CRYOGENIC ENGINEERING CONF. 

, TOKYO AND KYOTO, JAPAN, APR 9-13, 

1967) HEYWOOO TEMPLE INUUSTRIAL . 

PUBLICATIONS, LTO., LONDON, ENGLANO 

(1968) PP 52-7 

266 

MENAROvJ. SEGEL,Y. 

INTEGRAL TANKS OF CRYOGENIC STAGE H3.5. 

(IN FRENCH) EL00 TECH. REV. VOL 2, 

137-57 (1967) 

267 

HEYERS.N. 0ANNENMUELLER.J. HUGHES.1.G. 

A NEH CRYOGENIC STORAGE SYSTEM FOR 

SPACECRAFT. ASTRONAUT. AEROh. VOL 7, NO. 

INSULATIONS. PROD. ENG. VOL 379 NO. 4, 

91-5 (FEB 1966) 

275 

MGELLERtC. E. LOSER, J.B. SNYCER1W.E. 

HOPKINS rV. 

THERHOPHYSICAL PROPERTIES OF THERMAL 

INSULATING MATERIALS. MIOWEST RES. 

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REPT. NO. ASO-TOR-62-215 (JUL 1962) 

CONTR. NO. AF 33(616)-71375, PROJ. NO. 

7381, TASK NO. 735103, 328 PP 

276 

MOLNAG ,H. 

INSULATION. CRYOGENIC FUNOAMENTALS, G. 

G. HASELOEN ED, ACADEMIC PRESS, NEW YORK 

(1971) PP 199;235 

9, 62-7 (SEP 1969) 

268 

HILLER1R.N. BAILEY,C.O. FREEMAN,S.M. 

BEALL ,R.T. COXE,E.F. 

PROPERTIES GF FOAMS, ADHESIVES, AN0 

PLASTIC FILMS AT CRYOGENIC TEMPERATURES. 

INO. ENG. CHEM. PQOOUCT RES. DEVELOP. VOL 

I* NO. 41 257-61 (OEC 1962) 

277 

MORGAN, R. 

HOW TO SELECT CRYOGENIC INSULATION. 

PETRO/CHEtl ENGR. VOL 40, NO. 716, 56-8 

(JUL 1968) 

278 

MORRIS0N.W.L. 

INSULATED CONTAINER. U. S. PATENT NO. 

3.106.307 (OCT 1963) 

26'3 

MILLER,R.T. 279 

CRYOGENICS IN STOQAGE OF NATURAL GAS. J. 

METALS VOL 23, NO. IO. 34-9 (OCT 19711 

MOTOR SHIP 

270 

H1NGES.tl.L. 

FIRST SULZEQ RNMD TYPE DUAL-FUEL DIESEL 

ENGINE ENTERS SERVICE IN LNG SHIP 

VENATGR. MOTOR SHIP VOL 54, NO. 6419 

423-3 IOEC 1973) 

THERMAL INSULATIONS FOR AEROSPACE 

APPLICATIONS. MINUS 423 OEGQEES TO PLUS 283 

3000 DEGREES F. AERONAUTICAL SYSTEMS 

DIV., AF SYSTEMS COMMAND, 

HRIGHT-PATTERSON AFB, OHIO, REPT. NO. 

4SO-TO?-63-699 (DEC 1963) 23 PP 

MUELLER,K. 

A NEW LNG STORAGE TANK DESIGN. (IN 

GERMAN) GAS WASSERFACH VOL 113, 294-5 

(JUN 19721 

271 

MINGES,M.L. ME1SELMANvJ.M. BROADUS* J.G. 

A SYSTEM FOR MEASUREPENT OF CQYGGENIC 

THERMAL CONOUCTIVITY OF SOLIDS TO LIQUID 

NITROGEN TEMPERATURES t-320 DEGREES F). 

AIR FORCE SYSTEMS COMMANOt 

WRIGHT-PATTERSON AFB. OHIO. REPT. NO. 

ASO-TOR-63-756 (OCT 19631 35 PP 

281 

MULLEh ,F. 

A THERMAL INSULATION SYSTEM FOR HIGH 

ENERGY HYDROGEN-OXYGEN LAUNCH VEHICLES. 

ELOO-CECLES/ESRO-CERS SCI. TECH. REV. VOL 

3, 49-6s. (PRESENTED AT ELOG SYMPGSIUM ON 

CRYOGENIC STAGE EXPERIMENTAL WORK, APR 

22-23, 1970) 

272 

MODERN PLASTICS 

URETHANE FOAM INSULATES LARGEST LNG 

SHIP-LOADING SYSTEM. MOO. PLASTICS VOL 

491 NO. 2, 32-4 (FEB 1972) 

282 

MURACArR.F. 

POLYMFRS FOQ SPACECRAFT HARDWARE. 

MATERIALS CHARACTERIZATION, PART I. 

STANFGRO RESEAFCq INST., MENLO PARK, 

CALIF., REPT. ND. NASA-CR-813779 IR-3. 

273 

MODERN REFQIGERATION AN0 AIR CONOITIGNING 

REFRIGER4TEO GAS TANKERS - THEIR DESIGN 

AN0 FUTURE. MOO. REFRIG. AIR CONL. VOL 

72, NO. 853, 67-70 (JAN 1969) 

PT. 1 (OEC 1966) CONTR. NO. NAS7-100, 

JPL-950745 144 PF 

129 
OTHER OOCUMENTS 

(CONT.) 

283 

MYNCKE*H. VAN 1TTERBEEK.A. 

METHOD FOR THE SIMULTANEOUS MEASUREMENTS 

OF THE THERflAL CONOUCTIVITY OF INSULATING 

MATERIALS AT DIFFERENT MEAN TEUPERATURES. 

BULL. IIR ANNEXE 1966-2, 15-22 (MEETING 

OF COtiMISSION 2, TRONOHEIII, NORWAY, JUN 

22-241 1966) 

OTHER DOCUHENTS 

tC0NT.J 

292 

NOMA,f. 

THERHAL INSULATION FOR CRYOGENIC 

CONTAINERS. U. S. FATENT NO. 3r@OZ,9i9 

(APR 19741 

293 

NORE0,O.L. HENN1NGS.G. SINCLA1R.L.d. 

SH1TH.G.T. SM0LAK.G.R. STOFAN,A.J. 

STORAGE AND HANDLING OF CRYOGENIC FLUI3S. 

PROC. CONFERENCE ON SELECTEO TECHNOLOGY 

FOR THE PETROLEUM INDUSTRY, LEWIS 

RESEARCH CENTER, CLEVELAhO, Ok!10 (OEC 

a-9* 19651. NASA SPEC. PUaL. SP-CC53 

(1966) PF 125-53 

294 

284 

NAGANOsH. FUKASAUA ,N. KUtiA,S. 

SUGIYAMA,K. 

FIELD TEST OF LIQUIO NITROGEN COOLEO 

CRYOGENIC POWER CABLE. CRYOGENICS VOL 

139 NO. 4* 219-23 tAPR 1973) 

285 

NAGAOKAvJ. 

HEAT INSULATOR FOR RAPIDLY COOLED LOH 

TEMPERATURE CHAtlBERS. PROGRESS IN 

REFRIGERATION SCIENCE AN0 TECHNOLOGY VOL 

I, 260-7 (PROC, OF XTH INTERN. CONGR. OF 

REFRIG., COPENHAGENI 1959) PERGAMON PRESS 

(1960) 

286 

NAVAL AIR SYSTEtiS COtIMANO 

TECHNICAL MANUAL OF CXYGEN/NITROGEN 

CRYOGENIC SYSTEWS. NAVAL AIR SYSTEHS 

COMHANO. WASHINGTON, II. C., REPT. NO. 

NAVAIR 06-30-501 (HAR 1971) 425 PP 

287 

NICHOLSON*J.O. 

THERMAL INSULATION MATERIALS. CHEt!. 

PROCESS. VOL 17, NO. 3r 41-50 (MAR 1971) 

280 

NIENOORF,L.R. N1ES.G.E. 

INVESTIGATION OF A LIGHTHEIGHT 

SELF-EVACUATING PREFASRICATEO MULTI-LAYER 

INSULATION SYSTEM FOR CRYOGENIC SPACE 

PROPULSION STAGES. LINOE OIV., UNION 

CARBIDE CORP.. TONAWANOA, N. Y., FINAL 

REPT. NASA-CR-72012 (JUL 1966) CONTR. NO. 

NAS3-6289 293 PP 

289 

NIES,G.E. 

LIGHTHEIGHT MODULAR KULTILAYER 

INSULATION. UNION CAQBIOE CORP., 

TONAWANOAt N.Y.9 FINAL REPT.+ NATIONAL 

AERONAUTICS AND SPACE AOMINISTRATION 

REPT. NO, NASA-CR-72856, CONTRACT NO. 

NAS3-12045 (FEB 1971) 257 PP 

290 

NISHIMAKIIK. KUR1HARA.T. 

METHOD AN0 STRUCTURE FOR THERMALLY 

INSULATING LOW TEMPERATURE LIQUIO STORAGE 

TANKS. U. S. PATENT NO. 39895,146 (JUL 

1975) 

291 

NISHIMAKIIK. YOSHIKAWA.1. 

STORAGE TANKS FOR ULTQA-LOW TEMPERATURE 

LIPUIOS. U. S. PATENT NO. 3.670.917 (JUN 

NORR1E.C.H. WALKERrG. 

LNG PIPELINES - A STATUS SURVEY. PROC. 

ANN. CONV. NAT. GAS PROCESSORS ASSOC. 

47TH, TECH. PAPERS (1968) PP 65-70 

295 

NORTH AflERICAN ROCKWELL CORP. 

IN-SPACE PROPELLANT LOGISTICS. VOLUME 3, 

TRADE STUDIES. NORTH AMERICAN ROCKWELL 

CORP., OOWNEY, CALIF., SFACE DIV. REPT. 

NO. SOJ72-SA-0053-3-VOL-3. NATIOIUAL 

AERONAUTICS AN0 SPACE AOHINISTRATIGN 

REPT. NO. NASA-CR-123749, CONTRACT NO. 

NASB-27692, 240PP (JUN 1972) 

296 

OOONNELL, J.P. 

GAS CCUNCIL USING LIQUEFIED NATURAL GAS 

FOR PEAK SHAVING. OIL GAS J. VOL 69, NO. 

40 (3CT 1971) 

297 

OIL Ah0 GAS JOURNAL 

INSULATION METHOD SAID TC CUT HEAT 

LOSSES. OIL GPS J. VOL 73, NO. 35, 

129-31 (SEP 1975) 

298 

OIL At.0 GAS JOURNAL 

URETHANE FOAM TO INSULATE OFFSHOFE LNG 

LINE. OIL GAS J. VCL 70, NO. 16, 82-4 

(APR 1972) 

299 

OREFICE,J.O. 

THE EXPANDING INSULATION IN CONSTPUCTION. 

AIR CCNDITIONING, HEATING, VENTILATING 

VOL 66, 45-8 (JUN 1969) 

300 

PARTIhGTON,L.G. 

SOME ASPECTS OF RIGID URETHANE FGAM 

TECHNOLOGY IN REFRIGERATION. (2). MOC. 

REF. VCL 68, NO. 812, lC73-5 (NOV 1965) 

301 

PASTUH0V.A. GON30UIN.M. 

STATUS REPOQT ON LtjG TANKER DESIGKS. 

ADVANCES IN CRYOSENIC ENGINEERING VOL 19, 

282-31 ( PROC. CFYCGENIC Et~GINSE~ING 

CONFEhENCE, ATLANTA, GA., BUG 1973) 

PLENUM PRESS, NEW YORK (197L) 

1972) 

130 
OTHER OOCUMENTS 

(CONT. 1 

302 

aTHER DOCUMENTS 

(CONT.) 

310 

PIPELINE AND GAS JOURNAL 

DOUBLE BARRIER KELLGAZ TANK USES 

CONCRETEq FLEXIBLE HEMBRANE. PIFELINE 

GAS J. VOL 1991 NO. 11, 69-72 (SEP 1372) 

311 

PITTf4AN,C.M. BRDWN1R.O. 

SURFACE RECESSION CHARACTERISTICS OF A 

CRYOGENIC INSULATION SUBJECTED TO 

ARC-TUNNEL HEATING. NATIONAL AERONAUTICS 

AN0 SPACE A3MINISTRATION TECH. MEMO. NO. 

X-3291 (NOV 1975) 29 PP 

312 

PO0LE.R.R. 

INTER-WALL FOBflED THERHAL INSULATION. 

u. s. PATENT 3~446,881 (MAY 1969) 

313 

POTTIER,H.E.A. ROUX,C.B. 

TANKS FOR THE STORAGE AND TRANSPORT OF 

CRYOGENIC FLUIDS. U. S. PATENT 3,40iJ,Br9 

(SEP 1968) 

314 

PRATER1P.G. 

DESIGN CONSIOERATIONS OF AN LNG PEAK 

SHAVIfiG FACILITY. CRYOGENICS INIJ. G4SES 

VOL 51 NO. 5r 15-9 (MAY 1970) 

315 

PROBEkT.S.0. 

THERflAL INSULATION. CHEM. PROCESS ENC. 

HEAT TRANSFER SURVEY, 175-80 (1968) 

316 

PROBEFT ,S. 0. 

THERYAL INSULATION IN RELATION TO 

CRYOGENICS. UNIVERSITY COLL. OF SWANSEA, 

WALES, r7EPT. NO. TRG 1455 (R/X) (1967) 

105 PF 

317 

RAWUKA,A.C. 

SIGNIFICANCE OF THERMOPHYSICAL PROPERTY 

TESTIFG AT CRYOGENIC TEMFERATURES. 

DOUGLAS AIRCRAFT CO., INC. t SANTA MONICAI 

CALIF. MATERIALS RESEARCH ANC PFrOOUCTION 

METHOC’S, PAPER NG. 3953 (1966) 29 PP 

PRESENTED TO SOCIETY OF PLASTIC ENGINEERS 

REGIONAL MEETING, ANAHEIM, CALIF. (JUN 

27-29, 1966) 

318 

RAWUKA,A.C. YUN0T.C.G. 

THERy(PL CONOUCTIVITY OF WET WALL LIQUID 

HYDROGEN STORAGE TANK INSULATIONS FOR 

SPACE APPLICATIONS. AICHE 56TH FIATL. 

MEETIFiG, SAN FRANCISCO (HAY 16-19. 1955) 

PREPRINT NO. 220 

PAUL rE. WITTENBERG,M. FF?EYSCHtiIOT,E. 

LOU TEtlPERITURE TECHNOLOGY. FACILITIES 

AN0 CONSTRUCTION MATERIALS FOR 

CONOUCTION, TRANSPORT AN0 STORAGE OF 

LIQUID HYOROGEN. LOW-TEllPERATURE 

PROPERTIES OF METALS, ALLOYS. AND 

NON-METALLIC MATERIALS - A SIBLIOGRAPHY. 

KERNFORSCHUNGSANLAGE, JUELICHI WEST 

GERMANY, ZENTRALBIELIOTHEK. REPT. NO. 

JUL-BIBL-4 (SEP 19641 64 PP 

303 

PEARS.C.0. 

THE TiiERt4OPHYSICAL PROPERTIES OF PLASTIC 

MATERIALS FROM -50F TO OVER 70CF. 

SOUTHERN RESEARCH INST.. BfRMINGHAti. 

ALA., FINAL REPT. (AFR i965) CONTR:NO. 

AF33 657 8594, 07 PP. 

304 

PEARS0N.H. R. 

EVALUATION OF COMPOSITE INSULATIONS FOR 

CENTAUR F-2 LIQUID HY’IROGEN TANK. GEM 

‘JYNAflICS/ASTRONAUTICS~ SAN OIEGO, QUART. 

PROGR. REPT. NO. 2, FtiASE 1 (OEC 1962) 

CONTR. NO. AF 33(616)-7934, AR-592-l-333, 

11 PP 

305 

PENh0CK.A.P. 

ANOMALIES IN FOAM COhJUCTIVITY. 

LOCKHEED-GEORGIA CO., MARIETTA, REPT. NO. 

ES-6366, 36pP (AIJG 1963) 

,706 

FERKINS,P.J.,JR. 

INSULATION SYSTEM. b. S. PATENT 

3.392.864 (JUL 1968) 

3c7 

PERK1NS.P. J. DENGLER,R.P. NIENO0RF.L.R. 

N1ES.G.E. 

SELF-EVACUATED MULTILAYER INSULATION OF 

LIGHTWEIGHT PREFABRICATE0 PANELS FOR 

Cf?YOGENIC SPACE PROPULSION VEHICLES. 

LEWIS RESEARCH CENTER, NATTONAL 

PERONAUTICS AND SPACE AONTNISTRATION, 

CLEVELAND, OHIO, TECn. tifflO. NO. X-52266 

(19671 16 PP PRESENTE’J AT AIAA/ASHE 

STRUCTURES, STRUCTURAL OYNAMICS AN0 

MATERIALS CONF. 8TH. PALM SPRINGS. CALIF. 

(MAR 29-31, 1967). NATIONAL AERONiUTIcs 

AN9 SPACE AOMINISTSATION TECH. NOTE NO. 

C-4375 (1968) 25 PP 

309 

PERK1NS.W.E. 

REFRIGERATION REPUIRErENTS FOR PERISHABLE 

FROTECTIVE VEHICLES. J. CELLULAR 

PLASTICS VOL 2, NO. 6, 315-21 (NOV 1966) 

339 

PETROLEUM INTERMATIOhAL 

LNG TECHNOLOGY FACES GROWTH IN WORLD GAS 

TRADE. PETROL. INT. VOL 15, NO. 1, 28-35 

(JAN 1975) 

319 

REVUE GENER4LE 01; FRO10 

THE TERMINAL METHANE PORT AT HAVRE. (114 

FRENCH) REV. GEN. FRO10 VOL 54, NO. 9, 

993-9 (SEP 1968) 

131 
OTHER OOCUMENTS 

(CONT. 1 

320 

REYNOLOS,T.W. 

AIRCRAFT-FUEL-TANK DESIGN FOR LIOUIO 

HY OROGEN. NATL. ADVISORY COHH. AERONAUT. 

RESEARCH MEflO. NO. RH E55F22 IAUG 1955) 

27 PP 

321 

RHO0ES.J.E. 

LARGE SCALE CRYOGENIC TESTING OF HIGH 

PERFORMANCE INSULATION (HPI) SYSTEMS. 

CRYOGENIC WORKSHOP 9 PROC., NAT IONAL 

AERONAUTICS AND SPACE AOHINISTRATION. 

HUNTSVILLE, ALA. GEORGE C. MARSHALL SPACE 

FLIGHT CENTER, 243-65 (MAR 19-20, 1972) 

OTHER JOCUMENTS 

(CONT.) 

328 

SAUERBRIJNN.1. 

COMPLAINTS ABOUT REFRIGEPATING 

INSULATIONS AND THEIR REMEDIES. (Ih 

GERMAF.1 KALTE (HAMBURG) VOL 2’s, NO. 0, 

443-9 (SEP 1967) 

329 

SAUERBRUNN ,I. 

PLASTIC FOAMS IN REFRIGEE4TION 

TECHNIQUES. I IN GERMAN) 

HEIZUhG-LUFTUNG-HAUSTECH. VOL 18, NC. 3, 

346-51 (SEP 19671 

330 

SCHLUk’YERGERvE.H. PLOlJM,A.J.W. 

MEMBRANE TANKS. U. S. PATENT 3,15br794 

(SEP 1964) 

331 

SHIBATA ,F. GONDDLJINrM. 

THE STORAGE OF LNG. THE TECHNIGAZ 

TECHNIQUE. HIRATSUKA EXPERIENCE AND 

REALISATION. INTERNATIGNAL CONFERENCE 

322 

RITTENHOUSE, J.E. SINGLETARY.J.8. 

flATERIALS FOR SPACE STATIONS. METAL 

PROGR. VOL. 89, NO. 2, 57-63 (FEE 19661 

323 

ROBE!INS*M. 0. KELLEY, J.A. ELLI0TT.L. 

blISSION ORIENTED R AND II AND THE 

ADVANCEMENT OF TECHNOLOGY, THE IMPACT OF 

NASA CONTRIBUTIONSI VOLUI’E 2. OENVER 

RESEARCH INST., COLO., INDUSTRIAL 

ECONOHICS OIV. FINAL REPT., NATIONAL 

AERONAUTICS AN0 SPACE ADHINISTRATION 

REPT. NO. NASA-CR-126562, CONTRACT NO. 

NSR-06-004-0639 358 FP (MAY 1972) 

324 

ROBERTS, W. fi. DOHNvG.0. 

CRYOGENIC INSULATING PANEL SYSTEM. U. S. 

PATENT NO. 3,694,372 (JUL 19751 

325 

ROOKE,D.E. FILSTEAO,C.G.rJR. 

SIX YEARS OPERATIONAL EXPERIENCE WITH THE 

METHANE PRINCESS AND METHANE PROGRESS. 

LIQUEFIED NATURAL GAS (PROCEEDINGS OF THE 

INTERNATIONAL CONFERENCE AN0 EXHIBITION 

2N0, PARIS- FRANCE v OCT 19-23, 19701 VOL 

2 I4 PP 

326 

R0SENWASSER.S.N. WATANA8E.S.F. 

OEVELOPHENT OF PULSE0 LASER 

INTERFEROHETRIC HOLOGRAPHY FOR INSPECTION 

OF FOAM INSULATION OK LARGE METALLIC 

STRUCTURES. MCDONNELL DOUGLAS 

ASTRONAUTICS CO.. HUNTINGTON BEACH. 

CALIF., REPT. NO; MOC-G3578 (SEP 1973). 

ASMI SMEg AN0 ASNT. WESTERN METAL AN0 

TOOL EXPOSITION AN0 CONFERENCE9 LOS 

ANGELES, CALIF., MAR ii-15* 1974, PAPERt 

70 PP 

327 

RUSCIGN0.H. 

STITCHEO FOAM THERHAL INSULATION 

PROTECTION SYSTEM FOR THE LH(2l TANK WALL 

OF THE CENTAUR FLIGHT VEHICLE. GENERAL 

DYNAMICS/CONVAIR. SAh DIEGO. CALIF. s 

PROGR. REPT. NO. -GO/C-9TO-64-07a. 

NASA-CR-54418 (APR 1965) CONTR. NO. 

NAS3-3232 77 pP 

AN0 EXHIBITION ON LIQUEFIED NATURAL GAS, 

3R0, HASHINGTON, 0.C.. SEP 24-291 1972, 

INSTITUTE OF GAS TECHNOLOGY, CHICAGO, 

ILL., SESSION-V/PAPER-4, 14 PP (1972) 

332 

SHIPPlNG WORLD SHIPBUILDER 

GERMAN OESIGNED STANDARD SHIPS - A B’JLK 

CARRIER AND AN LNG CARRIER. SHIpFING 

WORLD SHIPBUILDER VOL 166, NO. 3877, 

142-3 I JAN 1973) 

333 

SHRIVER,C.B. 

DESIGN AND FABRICATION OF AN INTERNALLY 

INSULATED FILAMENT WOUND LIPUIO HYDSGGEN 

PROPELLANT TANK. GOOOYEAR AEFOSPACE 

CORP., AKRON, OHIO, REPT. NO. NASA CR-127 

(NOV 1964) CONTR. NO. NBS 3-2291, 62 PC 

334 

SHRIVER,C.B. 

FILAYFNT-WOUND C3NTAINER. U.S. FATENT 

39392,965 (JUL 19661 

335 

SIEOERS ,R. TAAL,L. 

TANK FGR STORAGE AND TRANSPORTATICN GF 

L3W 3CILING LIQUfFIED GAS. U. S. FATEHT 

NO. 39434,277 (DEC 1969) 

336 

SIGMUhD ,F. 

THERMALLY INSULATED PIPE. u. S. ~ATFMT 

NO. 3,685,546 (AVG 1972) 

337 

SIN0T.C.F. 

INSULATION OF LIGuIO OXYGEN r3EHAR.S. :drlT. 

BUR. STAND. (U.S.), INTERN4L REFT. MC). 

73-358, 45PP TAF? 1973) 

132 
OTHER DOCUMENTS 

(CONT.) 

OTHER OOCUHENTS 

(CONT.) 

347 

SPIETl’,C.W. 

ESTASLISHING PROVEN DESIGN CRITERIA FOR 

CRYOGENIC EOOST TANKS. EEECHCRAFT RES. 

AN0 DEVELOP. INC., BOULDERI COLO. ENG. 

REPT. NO. 7074 (SEP 1959) CONTR. NO. AF 

33(61t)-5154, SUPPL. S3(59-207) PROJ. NO. 

3084, Task NO. 30304* FTROI tlR59-1, 

246 PF 

336 

SISLER,C.W. 

PROCEOURE EVOLVED FOR THERMAL INSULATION 

STANDARD. PLANT ENG., 160-l. 164 (OCT 

19651 

339 

SMALL,A.El. GORMAN ,P.T. MCGARRY9F.J. 

CRYOGENIC INSULATION SYSTEH. U. S. 

PATENT NO. 3.6071531 (SEP 19711 

340 

SM1TH.E.T. 

INVESTIGATION OF COflBINED EFFECTS OF 

RAOIATION ANO VACUUM ANO OF RAOIATION AND 

CRYOTEMPERATURES ON ENGINEERING 

HATERIALS. VOLUME II, 

RAOIATION-CRYOTEIIPERATUQE TESTS. GEN. 

DYNAMICS/FORT WORTH, TEXAS, ANNUAL REPT. 

NASA CR 51140 (NOV 1962) CONTR. NO. 

NASB-2450. 253 PP 

341 

SMITH,H.L. ,JR. 

CRYOGENIC CONSTRUCTION AND ARTICLE 

THEREFOR. U. S. PATENT NO. 31924,339 

(OEC 19751 

342 

SMITH, J.C. KUMMINS, J.S. 

PROTFCTIVE COATINGS FOR FOAM INSULATION. 

CHEH. ENG. PROGR. VOL 70, NO. 0, 57-9 

(AUG 1974) 

343 

StlITH,J.C. KUMU1NS.J.S. 

PROTECTIVE COATINGS FOR POLYURETHANE FOAM 

TANK INSULATION. AMERICAN INSTITUTE OF 

CHEMICAL ENGINEERS NATIONAL MEETING, 

76TH, TULSA, 0KLA.r MAR 10-13. PAPER 

(1974) 9 PP 

344 

SMITH,J.K. 

A STUDY OF THE GEVELOPMENT OF A NEW LOH 

COST INSULATION SYSTEH FOR USE ON SATURN 

J S-II STAGE. BOEING CO., HUNTSVILLE, 

ALA. LAUNCH SYSTEMS BRANCH, REPT. NO. 

05-13496 (FEE 1969) 37 PP 

3-5 

SMYLY.E.0. SWOGER, W.F. PEARS.C.0. 

PROPERTIES OF ABLATICN AN0 INSULATION 

MATERIALS. VOLUME 3. THERMAL AN0 

MECHANICAL PROPERTIES OF LOW-DENSITY 

PHENOLIC-NYLON ANO SILICONE-PHENOLIC 

ASLATORS. SOUTHERN RESEARCH INST.. 

91RtlINGHAMv ALA., REPT. NATIONAL 

AERONAUTICS ANO SPACE ADMINISTRATION 

REPT. NO. NASA-CR-111309~ CONTRACT NO. 

NASl-7732-l. 32lPP (JUN 19711 

346 

SOLLAMI.2. J. LUNoEEhrH.9. GERTH9B.F. 

COMPGSITE INSULATION FOR CRYOGENIL 

VESSEL. U. S. PATENT NO. 3r72k.223 (APR 

1973) 

348 

SP1ETHqC.W. 

ESTA3LISHING PROVEN DESIGN CRITERIA FOR 

CRYOGENIC BOOST TANKS. BEECHCRAFT RES. 

AN0 OEVELOP. INC., BOULCER, COLO. ENG. 

REPT. NO. 7602 (MAR 1960) CONTR. NO. AF 

33(61E)-5154, SUPPL. S3(59-207) PROJ. No. 

3084, TASK NO. 30304, FTRDI HP 60-l. 

222 PF 

349 

SPIETH,C.W. 

STUOY OF INTEGRATED CRYOGENIC FUELED 

POWER GENERATING AND ENVIRONMENTAL 

CONTROL SYSTEMS. VOLUME II. CRYCGE:JIC 

TANKAGE INVESTIGATION. BEECHCRAFT 

RESEARCH ANO DEVELOPHENT, INC., BO’JLOER, 

COLO., REPT. NO. ASD-TR-61-327, V.2 (NOV 

1961) CONTR. NO. AF 33(616J-7509 389 PP 

350 

SPIETH,C.W. BELL1J.E. CONNELLY9J.G. 

CORBETT rR. J. COVINGTON~G.0. 

STOECKER,L .R. SUTTON,H.E. 

ROCKET VEHICLE TANKAGE RESEARCH FOR A 

CRYOGENIC PROPELLANT. BEECH AIRCRAFT 

CORP., BOULDER, COLO., REPT. NO. KADC TR 

5a-53c (SEP 1958) CONTR. No. AF 

33 (616) -5178, 152 pp 

351 

SRIN1VASAN.K. SESHAGIRI Q40,V. 

KRISHNA MURTHY ,M. V. 

OPTIHUM INSULATIGN THICKNESS FOR 

CRYOGENIC TRANSFEP LINES. INTERNATIONAL 

CRYOGENIC ENGINEERING COKF., PROC. 5TH 

(KYOTO, JAPAN, MAY 7-10, 19741, K. 

MENOELSSOHN, EDITOR. IPC SCIEhCE AN0 

TECHNOLCGY PRESS, SUSSEX, ENGLAND* 570-3 

(19740 

352 

SRIN1VASAN.K. SESHAGIRI RA0.V. 

KRISHNA MURTHY,M.V. 

SELECTION OF INSJLATION FO? CRYOGENIC 

TRANSFER LINES. CRYOGENICS VGL 15, NO. 

4, 23C-1 (APR 1975) 

353 

STASThY ,E. 

APPLICATION OF PLASTIC FOAMS, ESPECIALLY 

OF STYROFOR, AS INSULATIIdG MATERIALS IN 

THE xFFdIGERATION INOUSTRY. (IN GERMAN) 

KALTETECHNIK. VOL 12, NO. 3, 75-at (MA? 

1960 I 

133 
OTHER DOCUMENTS 

(CONT. 1 

35k 

OTHER DOCUMENTS 

(CONT. t 

362 

STASTNY,F. 

PLASTICS FOR REFRIGERITING INSULATION. 

KALTE (HAflBURG) VOL 14, h0. 5, 249-54 

(flAY 1961) 

355 

STILES,R.E. 

TEXAS EASTERN PIONEERS LNG STORAGE 

TECHNOLOGY. PIPE LIKE INO. VOL 33, NO. 

6, 30-2 (DEC 1970) 

356 

STOECKE4,L.R. 

ON THE EVACUATION OF PLASTIC FOAMS TO 

REOUCE THEIR THERHAL CONDUCTIVITY. 

ADVANCES IN CRYOGENIC ENGINEERING VOL 5, 

273-81 (PROCEEDINGS CF THE 1959 CRYOGENIC 

ENGINEERING CONFERENCE) FLENUH PRESS, 

INC.. NEW YORK (1360) 

357 

STUCKEY I J. M. 

DEVELOPMENT OF A COMZINED HIGH 

PERFORMANCE MULTILAYER INSULATION AND 

tlICROMETEOROIO PROTECTION SYSTEM. 

RESEARCH ACHIEVEMENTS REVIEW VOLUME 2, 

NATIONAL AERONAUTICS AN0 SPACE 

ADMINISTRATION, HUNTSVILLE ALA. GEORGE C. 

UARSHALL SPACE FLIGHT CENTFR, TECH. MEMO. 

53670 (1967) PP 55-68 

359 

STUMPF.0. ZIMN1,Y.F. 

THE THERMODYNAMIC DESIGN OF CRYOGENIC 

HIGH-ENERGY H(2)-O(2) UPPER STAGES AND 

SPACE PROBES FOR LCNG DURATION MISSIONS 

WITH SPECIAL CONSIDERATION OF THE ELOO-B 

LAUNCHERS. PROBLEMS OF PROPULSION AN0 

SE-ENTRY (PROC. INTERN. ASTRONAUTICAL 

CONGRESS 17TH. MADRID, SPAIN, OCT 9-15, 

1966) M. LUNC ET AL EDS., GORDON AND 

BREACH, INC.9 NEW YORU (1967) VOL 3, PP 

39-50 

359 

SURD1vV.L. ROMAINE,D. 

LOW TEMPERATURE PIFIHG DESIGN. PETRO. 

REFINER VOL 43. NO. 6, 116-24 (JUN 1964) 

351 

TAR1EL.H. 

THERMALLY INSULATE0 RECEPTACLE FOP A 

CRYOGENIC FLUID. U. S. PATENT 3r578.541 

(9AY 1971) 

351 

TAR1EL.H. GUYON.9. GAGNEUX.Y. 

MULLERsF. LOU1S.Y. 

THERMAL INSULATION OF RECEPTACLES FOR 

CRYOGENIC FLUIDS. U. S. PATENT NO. 

TAYLOE*a.N. HACl<rE.E. 

EFFECT OF CONVECTION IN HELIUM-CHPRGfDr 

PARTIAL-FOAM INSULATIONS FOK LIQUID 

HYGROGEN PROPELLANT TANKS. ACVAKCES IN 

CRYOGENIC ENGIt!EERING VOL. Iir 65-76 

(PROCEEOINGS GF THE 1965 C?YOGEtdIC 

ENGINEERING CONFERENCE) PLENUM PRESS, 

INC., NEH YORK (1566) 

363 

TEHPLE,R.W. 

THE WCRLOS LONGEST FROCESS PLAtdT. 

LIQUEFIED NATURAL GAS (PROCEEDINGS OF THE 

INTERkATION4L CONFERENCE AND EXHI6ITIC:l 

ZND, FARIS, FRANCE, OCT 19-23, 1476) V3L 

1 22 PP 

364 

TIENI C.L. CUNNINGTON,G.R. 

CRYOGENIC INSULATION HEAT TRANSFEF.. 

AD VAN. HEAT TRANSFER VOL Y, 349-L17 

(1573) 

365 

TORN4Y, E.G. 

LIQUEFIED GAS TANKER CONST?UCTION USIrli, 

STIFFENER MEMBERS. U. S. PATENT b;G. 

3.922.987 (3EC 1975) 

366 

TRENNER,L. 

RECEPTACLES FOR THE STORi\GE OF LICUEFIC3 

GASES AT CRYOGENIC TEMPERATURES. U. S. 

PATENT NO. 3rE55r095 (APF 1972) 

367 

TURNEF, K.C. 

CRITEPIA FOR INSTALLING IN~ULPTICh 

SYSTEES IN PETROCHEMICAL PLANTS. CHE’i. 

ENG. FRJGR. VOL 70, NO. c, 41-5 (PUT, 

1974) 

368 

TYE,R.D. 

THE THERMAL CONDUCTIVITY CF ThO THLRM~L 

INSULATING tiATERIALS. CYNUTEtl+ CCRF., 

CANRRIDGE, YASS., REPT. 79dr 

NASA-CR-61915 (JIJL 1963) ClNTf-. 

NAS 8-21262 1G F? 

364 

VAHLvL. 

CHARACTERISTICS LF EXPAF:iiJ =CLYC?Y@:h! 

PLATES. II’4 DUTCI’I NED. VEI?. r(OE L TECHr<. 

HECEJ. uOL j&v ND. 5, 1'11-3 (TEP-CCT 

1961) 

570 

VAN 3bSKIRK,E.C. CURL4FuL 1C.C. 

SANDEFS ,v 

LOW-TE’tPEiATURf INSVLATILN. CllEV. t’lo. 

PRCGI. iljL -4, NC. 1C, dti3-6 (OCT lc--.+I 

3,769,118 (OCT 1973) 

134 
OTHER DOCUMENTS 

(CONT.) 

371 

OTHER JCCUMENTS 

(CONT.1 

381 

JEERL1NG.C.W.N. 

A SUSMARINE OFFSHORE LOADING LINE FOR 

LNG. IYTERNATIONAL CONFFRENCE AND 

FXHIElITIOti ON LIOUEFIEO NATURAL GAS, 3RD. 

WASHINGTON, D.C., SEP 24-28, 1972, 

INSTITUTE OF GAS TECHNOLOGY. CHICAGO, 

ILL. t SESSION-II/PAPER-8r 17 PP (1972) 

372 

VE?SCHOOR. J.D. 

THERMAL CCNDUCTIVITY OF COMMERCIAL 

INSULATION AT LOW TEMPER4TUQE. REFRIG. 

ENG. VOL 62, 35-7 (SEP 1954) 

373 

VRANCKEN.P.L.L. 

CURRENT L.N. G. TANKEW OESIGNS. GAS J. 

VOL 343, NO. 5b5Ir 173-7 (MA? 1972) 

374 

WA1TE.H. J. 

STYRCFDAH (EXPANDEO POLYSTYRENE) 

INSULATION AT LOW TEMPERATUQE. ACVANCES 

IPI CRYOGFYIC ENGINEERING VOL lr 230-4 

(PROCEEDINGS OF THE 1954 CQYCGENIC 

iNGINEERING CONFERENCE) PLENUM PRESS 

INC., NEH YORK (19601 

375 

WALKER,G. COULTER, 0. SOODIN. 

LIDUEFIED NATURAL GA S PIPELINES FOR ARTIC 

GAS RECOVERY. PROC. OF INTERNATIONAL 

CONFFRENCE ON LIQUEFIED NATURAL GAS, 

LONGON, MA4 1969, 503-23 

3 7 6 

WAL1ERS.W. 1. GIBS0N.G.H. 

LAND-BASE? L.N.G. STORAGE TANKS. GAS J. 

VUL 349, NO. 5651. 179-8~ (MAR 1972) 

1’77 

PIPELINE AlJD GAS JDUFNAL 

SFRAY-ON FOAM INSULATES TANKS. PIPELINE 

GAS J. VOL 201, NO. 8, 76 (JCL 19741 

378 

WATS0N.J.F. 

FROPERTIES OF ENGINEERING HATEiIALS AT 

EXTREME SUBZERO TEMPERAfUSES WITH 

SUPPLEHENTARY INFORMATION ON LlQUID 

HYOROGEN. GENERAL OYNAMICS/ASTRONAUTICS, 

SAN DIEGO, REPT. NO. EHG-44 IOEC 1958) 

l?E PP 

379 

HATS0N.J.F. 

FQJFERTIFS OF OFGANIC YATEkIALS AT LOW 

1FMFCQATUYE INCLUDING COMQPTIBILITY WITH 

LIrlU13 OXYGEN. GCb;E.QAL 

~IYNA’IICS/ASTRONAUTICS. SAh DIEGO, CALIF., 

QEFT. NO. GDA-MRG-80 (JUN 1959) 77PF 

3 u, : 

WE1SHAUPT.J. SELLMAIER, A. 

INSULATION FOR LARGE TECHNICAL LCW 

TEMPERATURE PLANT. (IN GERMAN1 

LINDE-aER. TECHNIK WISS., 3-13 (NOV 19t.I) 

382 

WEN,SHU-LIN 

PROGliFSS ON THERMAL INSULATION MATERIALS. 

(IN CHINESE) dlJA HSUEH TUNG PA0 NO. 3, 

58-64 (1974) 

383 

WENT,P.R. IVERSIA.P. 

OES IGN AND OPERATION CONSIOERATICNS - 

INSULATED AND REFRIGERATE0 TRANSPORT. 

J. REFRIG. VOL II, NO. 5, 125-36 (MAY 

1968) 

784 

WESTERN PLASTICS 

RIGII) URETHANE FOAM IN THE WEST. WESTEQN 

PLASTICS VOL 15, NO. 3, 15-21 (MAR 136d) 

395 

WHITE,G.W. PENN9W.H. 

TECHNICAL PROBLEMS WITH INGROUNU STORAGE. 

AMERICAN GAS ASSDCIATION OPERATING 

SECTICN CONFERENCES, PHILADELPHIA* PA. 

(MAY 12-15, 19691 PAPER IO PP 

386 

WHITEL0CKE.A.J.E. 

RIG13 POLYURETHANE FOAM PIPE SECTIONS. 

PIFES PIPELINES INT. VOL 15, 17-9 (1371) 

397 

WIJNBE2CvJ.G. 

RELIDUEFACTION PLANT OF THE LFG-TANKER 

ANTILLA CAPE. BULL. INST. INS. FROID 

ANNEXE VCL 1963-5, 103-8 (1969) 

388 

wl~SGh.9.J. HALErL.V. WHITACRE,W.E. 

049ITAL PROPELLANT DEPOT SYSTEM. 

ADVANCES IN CRYOGENIC ENGINEERING VOL 17. 

165-5 (FRESENTED AT CRYOGENIC ENGINEERIKG 

CONFEFEKCE, BOULGER, COLO., JUN 17-191 

1970) PLENUM PRESS, INC., NEW YORK (1972) 

389 

W1LSOE.rG.C. BALL1NGER.J.C. 

THER.dAL DESIGN CRITERIA FOR CENTAUR 

PQOPE LLANT TANKS. GENERAL 

DYNA,dICS/ASTRONAUTICS, SAN DIEGO, CALIF.. 

REFT. NO. GUA-AEtO-0072 (JAN 196b) CON’+. 

AF 13 (650) -1775 15 PP 

390 

W1LS.JArJ.J. 

AN II~TRODUCTION TO THE MAZINE 

T~ANSFJt?TATIoN OF BULK LKG PNC THE DESIGI! 

OF L,JG CCRQIERS. CaYOGEhIrS VSL 14. >!‘I. 

39 li5-20 (MAR 1574) 

‘dATSCK,J.M. SEVCIKrV. PETFCR,J. 

FOAM-INSULATED LIQUIO HYDROGEN TARGET FOR 

STQEAMER CHAMBERS. NUCL. INSTRUM. 

.+FTHOOS VOL 165. NO. 1, 33-6 (1972) 

135 
OTHER DOCUMENTS 

(CONT. 1 

391 

WITHERS*O.O. 

CRYOGENIC TANK OESIGk AN0 METHOD OF 

MANUFACTURE. U. S. PATENT NO. 39765,558 

(OCT 1973) 

392 

wOOo,C*C. PAUL,H.C. 

CRYOGENIC TECHNOLOGY ASPECTS OF SPACE 

FLIGHT. CRYOGENIC ENGINEER1 LG - PRESENT 

STATUS AN0 FUTURE DEVELOPMENT (PROC. OF 

THE INTERNATIONAL CRYOGENIC ENGINEERING 

CONF. lST, TOKYO AN0 KYOTO, JAPAN, APR 

9-13, 1967) HEYWOOO TEMPLE INDUSTRIAL 

PUBLICATIONS, LTD., LONDONI ENGLANO 

(1968) PP 13-9 

OTHER OCCUMENTS 

(CONT.) 

400 

YOSHIMURA, K. 

LOW TEMPERATURE INSULATING MATERIAL. (IN 

FRENCH) FRENCH DEMANOE NO. 2,2OE,,292 

(NOV 19731 

393 

WOOO,G. 

TEMPERATURE LIHITATIONS OF POLYHERIC 

MATERIALS. PART I - GENERAL REVIEW. 

ROYAL AIRCRAFT ESTABLISHMENT, 

FARNBOROUGH, ENGLAND, REPT. NO. 

RAE-TN-CPM-34 (OCT 19631 22 PP 

394 . 

WOOO*H. 

MANUFACTURERS OPTIMISTIC ABOUT U.S. AND 

FOREIGN LNG MARKETS. LNGICRYOGEN. VOL 1, 

NO. 2, 17-22 fAPR/HAY 19731 

395 

WORE0YS.R. V. ESTEf3ANEZ.J. 

THERMALLY INSULATED CONTAINER FOR 

TRANSPORTING LOW TEMPERATURE LIQUIDS. 

u. s. PATENT 3,502,239 (UAR 1970) 

396 

WYCKAERTqL. 

THE BRUNEI LNG SHIP LOADING SYSTEf4. 

PAPER PRESENTED AT THE AMERICAN INSTITUTE 

OF CHEMICAL ENGINEERS 71ST NATIONAL 

MEETING, HELO AT THE STATLER HILTON 

HOTEL, DALLAS. TEXAS. FEB. 20-23. 

PAPER-IOB (1972) PAPER PREPARED FOR 

CRYOGENIC SOCIETY OF AMERICA INC. 6TH 

CRYOTECHNOLOGY EXPOSITION AN0 CONF., 

WASHINGTON, 0.C.r AUG 30, 1971 

397 

YAHAMOTO,K. 

STORAGE TANK OF COLD LIQUEFIED GAS. 

U. s. PATENT 3r58lr931 (JUN 1971) 

398 

YASUI,G. 

RIFT RAOIATION EFFECTS PROGRAM 

IRRAOIATIONS NO. 1 AN0 2. CRYOGENIC 

INSULATION MATERIALS. LOCKHEEO AIRCRAFT 

CORP., MISSILES AN0 SPACE DIV., 

SUNNYVALE9 CALIF., REPT. NO. NSP-63-35 

(MAY 19631 CONTR. NO. NASB-5600, 67 PP 

399 

YOSH1flURA.K. 

CRYOGENIC INSULATING tiATERIAL. U. S, 

PATENT NO. 31895r159 (JUL 1975) 

401 

r ZINN1GER.T.C. BURKE,P.J. 

CRYOGENIC LIQUID CCNTAINMENT SYSTEM. 

u. s. PATENT NO. 3*927,7d8 (OEC 1975) 

136 
AUTHOR INDEX 

137 
Abstract page 

numbers 

4, 89, 90 

Agrawal, K. N. 

Alleaume, J. 

Allen, R. J. 

Anderson, P. J. 

Anthony, F. M. 

Arden, B. 2 

Arnoldy, C. 

Arvidson, J. M. 

Asay, J. R. 

Ashida, K. 

Ashworth, T. 

Aske, H. D. 

Atterbury, T. J. 13 

Backhaus, H. W. 

Baehr, F. 

Bahrenburg, H. H. 

Bailey, A. B. 

Bailey, B. M. 

Bailey, C. A. 

Bailey, C. D. 73 

Ballinger, J. C. 

Bancroft, G. H.' 

Bankston, B. F. 

Barber, J. R. 

Barito, R. W. 

Barker, H. H., Jr. 5 

Bartlett, D. H. 

Bauer, R. H. 

Beall, R. T. 73 

Beaujean, J. M. 

Bell, J. E. 

Other document 

numbers 

001 

002 

003, 004 

109, 208, 209 

174 

006 

007 

008 

009 

010 

011 

012 

013, 014 

015 

016 

017 

018, 268 

389 

019 

056 

020 

021 

022 

023 

210 

268 

024 

350 

138 
Abstract page 

numbers 

Benedict, D. C. 

Benford, A. E. 

Bennett, F. O., Jr. 102 

Bennett, R. B. 6 

Berger, Dr. 

Bergman, R. A. 

Bettanini, E. 

Biais, M. 

Bills, H. 

Bisiaux, P. 

Black, I. A. 26 

Bodley, R. W. 

Bognaes, R. 

Boissin, J. C. 101 

Bolshakov, Yu. P. 65 

Bonallack, R. F. 

Borup, H. H. 

Bourne, J. G. 7 

Bradbury, H. G. 71 

Brandt, N. B. 

Breves, E. 0. 111 

Brissaud, J. 

Broadus, J. G. 

Brochhagen, F. K. 8 

Brogan, J. J. 

Brown, R. D. 

Buist, J. M. 

Burge, G. W. 

Burke, P. J. 

Burkinshaw, L. D. 9 

Buskirk, D. L. 5 

Other document 

numbers 

016 

025 

026 

068 

027 

028 

033 

029 

030, 146 

031 

224 

033 

034 

035 

036 

271 

040 

041 

311 

042 

044 

401 

139 
Butterworth, H. H. 

Byrnes, R. W. 

Campbell, C. R. 

Campbell, M. D. 

Carter, H. G. 71 

Carter, J. M. 10 

Ceintrey, M. 

Cerquettini, C. 

Cheyney, D. R. 

Childers, J. W., Jr. 

Clark, J. A. 

Clarke, J. S. 

Clarke, R. C. 

Clifton, J. V., Jr. 

Closner, J. 3. 

Clotfelter, W. N. 

Cochran, R. P. 29 

Codegone, C. 

Codlin, E. M. 

Colding, L. 

Colenbrander, C. B. 

Connelly, 3. G. 

Cook, H. C. 

Cooper, A. 

Cooper, H. C. 

Corbett, R. J. 

Coston, R. M. 

Coulter, D. M. 

Covington, G. D. 

Coxe, E. F. 11 

Crawford, D. B. 

Abstract page 

numbers 

Other document 

numbers 

045 

016 

016 

046 

262 

080 

047 

048 

051 

222 

052 

053 

054 

099 

055 

056 

057 

058, 059 

060 

061 

212 

350 

062 

063 

064 

350 

065 

066, 067, 375 

350 

268 

068 

140 
Abstract page 

numbers 

Creaser, L. F. 

Crockett, L. K. 

Crouch, G. D. 

Crowl, R. E. 

Cruddace, R. G. 

Cubbison, R. W. 

Cunnington, G. R. 

Curry, J. E. 

Dainora, J. 13 

Dannenmueller, R. J. 

Davies, C. B. 

Davis, B. K. 

De Cnop, L. 76 

De Frondeville, B. 

De Winton, C. 

De Wit, J. 

Dean, F. E. 

Dearing, D. L. 

Deason, D. 

Degenne, M. 

Deland, R. E. 

Dengler, R. P. 

Denham, J. B. 

Desai, R. R. 

Di Matteo, G. A. 

Dickie, D. 

Dickson, E. M. 15 

Dimentberg, M. 

Dinapoli, R. N. 

Dodd, P. 16 

Doherty, D. J. 

Other document 

numbers 

069 

070 

071 

072 

015 

057 

364 

078 

103 

267 

079 

080 

036 

081 

082 

083 

084 

085 

125 

086, 087, 088, 

307 

082 

090, 091 

092 

082 

093, 094, 095 

096, 097 

042, 098 

089 

I .- 

141 
Abstract page 

numbers 

65 

17 

13 

Dohn, G. D. 

Domorod, L. S. 

Dorney, D. C. 

Doughty, R. 0. 

Doyle, W. E. 

Dryden, H. L. 

Dudnik, D. M. 

Duffy, A. R. 

Dumont, A. 

Dupuy, R. 

Durcholz, R. L. 4, 89, 90 

Duren, P. C. 

Durga Prasad, K. A. 18 

Durr, C. A. 

Eakin, B. E. 

Eash, D. T. 97 

Eastman, W. 0. 

Edeskuty, F. J. 

Egan, P. C. 

Elliott, L. 

Elrod, C. W. 

Escher, W. J. D. 

Estebanez, J. 

Evenson, J. H. 

Ewing, G. H. 

Eyles, A. G. 

Faddoul, J. R. 19 

Falck-Pedersen, G. 

Feind, K. 

Ferro, V. 

Ffooks, R. C. 

Other document 

numbers 

090, 091, 324 

245, 246 

099 

100 

101 

102 

103, 104, 105 

106 

107 

056 

108 

109, 208, 209 

021 

110 

111 

323 

112 

113 

395 

114 

115 

116 

117 

118 

058, 059, 119 

120 

142 
Filipe, A. 

Filippov, V. A. 

Filstead, C. G., 

Flynn, T. M. 

Foley, R. J. 

Foner, S. 

Forbes, F. W. 

Foster, C. S. 

Fournier, D. 

Fowle, A. A. 

Fradkov, A. B. 

Frank, H. J. 

Freeman, S. M. 

Freyschmidt, E. 

Fujihashi, Y. 

Fukasawa, M. 

Fulmer, D. 

Gagneux, Y. 

Gause, R. L. 

Gayle, J. B. 

Gelder, T. F. 

Gerrish, R. W. 

Gerstin, H. 

Gerth, B. F. 

Gibson, G. H. 

Gieryga, J. M. 

Gieseking, D. E. 

Gille, J. P. 

Glaser, P. E. 

Glemser, N. N. 

Abstract page Other document 

numbers numbers 

121 

105 

Jr. 122, 325 

184 

20 

123 

124 

21 

22 125 

016 

126 

224 

11, 73 127, 268 

302 

128 

284 

129 

361 

70 131 

23, 46, 47 207 

29 149 

25 

138 

346 

139, 140, 376 

141 

240 

5 

26 

28 

030, 142, 143, 144, 145, 146 

Gofman-Zakharov, P. M. 147 

143 
Gondouin, M. 

Goodykoontz, J. H. 

Gorman, P. T. 

Gray, V. H. 

Greenberg, I. N. 

Greenberg, S. 

Griffin, J. D. 

Grossman, J. 

Guenther, A. H. 

Gutzmer, H. A. 

Guyon, R. 

Haggerty, W. 

Hale, D. V. 

Hammond, M. B., Jr. 

Hampton, H. A. 

Haralson, H. S. 

Harding, R. H. 

Haroldsen, 0. 0. 

Haskins, J. F. 

Hauck, J. E. 

Hayakawa, S. 

Hayes, R. G. 

Haynes, J. 

Hedberg, C. R. 

Heffner, G. R. 

Heidelberg, L. J. 

Heldenfels, R. R. 

Hennings, G. 

Hertz, J. 

Higgins, R. G. 

Hilado, C. J. 

Abstract page 

numbers 

29 

29 

31, 32 

33, 37 

34, 35 

36 

33, 37 

38, 39 

Other document 

numbers 

301, 331 

148, 339 

149 

211 

150 

151 

187 

007 

152 

361 

187 

153, 154, 155, 156, 157, 388 

158, 159 

160 

168 

161, 162 

086, 087, 088, 089 

046, 163 

164 

167 

168 

169 

170 

171 

293 

046, 172, 173 

174 

175 

144 
Hildenbrand, C. V. 

Hill, W. E. 

Hillberg, E. T. 

Hocking, C. S. 

Holcombe, A. H. 

Holland, W. D. 

Holton, K. D. 

Hoover, T. E. 

Hopkins, V. 

Hord, J. 

Hudgens, H. R., Jr. 

Huggett, C. 

Hughes, I. G. 

Hughes, T. A. 

Hunt, R. T. 

Hurd, R. 

Hurst, S. C. 

Hust, J. G. 

Hyde, E. H. 

Ichii, M. 

Ichinose, Y. 

Iijima, T. 

Isenberg, L. 

Ito, K. 

Ivers, A. P. 

Jackson, R. G. 

Janssen, R. 

Jelinek, F. J. 

Job, C. 

Johnson, C. L. 

Johnston, H. L. 

Abstract page 

numbers 

Other document 

numbers 

176 

177 

178, 192 

179 

180 

181 

252 

182, 183 

275 

184 

185 

186, 187 

267 

188 

11 

042, 098, 160 

189 

184 

157 

008 

190 

167 

178, 191, 192, 193 

167 

383 

194, 195, 196 

011 

20 

41 

85 

141 

193 

197 

145 
Abstract page 

numbers 

44, 71 

45, 46, 47 

Jones, H. 

Jones, L. R. 

Jonke, R. J. 42 

Kaganer, M. G. 43 

Kahlenberg, F. 

Karcher, G. G. 

Katsuka, K. 

Keller, E. E. 

Keller, J. P. 

Kelley, J. A. 

Kelley, L. R. 

Kennedy, R. N. 

Kerlin, E. E. 

Key, C. F. 

Khan, A. P. 

Kilpert, R. 

Klarsfeld, S. 22 

Klemens, P. G. 

Klevatt, P. I,. 75 

Knobbout, J. A. 

Knowles, D. 

Knox, P. M., Jr. 

Knox, R. E. 

Kobayashi, T. 

Koglin, B. 49 

Kolff, A. R. 

Kraus, S. 

Kreft, H. 50 

Kreisler, R. I. 

Krishna Murthy, M. V. 18 

Krivets, L. E. 105 

146 

Other document 

numbers 

046 

099 

199 

053 

201, 202 

203 

204 

323 

086 

261 

205, 206 

207 

109, 208, 209 

210 

211 

212, 213 

173 

214 

215 

008 

216 

217 

218 

092 

351, 352 

I 

- -_._-__ __-,..a m..,.. .m..,- ,.,, .,a” .B.““. -...“““,l .m....,m ,.,.... . a..,.-. ma -mm.-mw,, a-- 
Kropschot, R. H. 

Kuma, S. 

Kummins, J. S. 

Kurihara, T. 

Kuryla, W. C. 

Kvamsdal, R. 

Lacaze, A. 

Laine, P. 

Laing, G. 

Landler, Y. 

Landrock, A. H. 

Langton, R. G. 

Lashmet, P. K. 

Laverman, R. J. 

Leach, L. L. 

Lemons, C. R. 

Leroy, J. P. 

Lester, G. R. 

Leupold, M. 

Lightfoot, R. P. 

Ligi, J. J. 

Lindquist, C. R. 

Lindstrom, R. S. 

Lock, J. 

Lofgren, C. L. 

Lom, W. L. 

Long, R. L. 

Lorentzen, H. L. 

Lormis, F. E. 

Loser, J. B. 

Louis, Y. 

Abstract page 

numbers 

51, 52, 54 

56, 57, 58 

59 

71 

19 

26 

62 

64 

Other document 

numbers 

219, 220, 221 

284 

342, 343 

290 

222 

223, 224 

225 

121 

226, 227 

141 

228 

229 

230 

231 

232 

125 

098 

262 

233, 234 

238 

240 

241 

022 

242 

275 

361 

147 
Love, C. C., Jr. 

Lowrey, R. 0. 

Ludtke, P. R. 

Luikov, A. V. 

Lundeen, H. R. 

Lusk, D. T. 

Lyons, R. H. 

Maccalous, J. W. 

Mack, F. E. 

Madsen, R. A. 

Marks, J. B. 

Marshall, J. E. 

Martel, C. R. 

Martin, R. 

Matesanz, A. 

Mathes, H. 

Matsumoto, T. 

Mattarolo, F. 

May, W. A. 

Mayo, F. 

McCandless, T. D. 

McClintock, R. M. 

McConarty, W. A. 

McGarry, F. J. 

McGrew, J. L. 

McIntire, 0. R. 

McKannan, E. C. 

McMillan, W. D. 

Mearns, W., III 

Meesen, H. 

Meier, R. N. 

Abstract page 

numbers 

11 

65 

66 

77 

Other document 

numbers 

243 

244 

346 

245, 246 

247 

248 

362 

67 

97 

68 

5 

70 

71 

252 

253 

124 

254 

255 

167 

256 

257 

258 

259 

174 

339 

214, 260 

261 

262 

263 

264 

229 

148 
Meiselman, J. M. 

Meitzner, K. 

Menard, J. 

Meyers, N. 

Miller, R. E. 

Miller, R. N. 

Miller, R. T. 

Minges, M. L. 

Moeller, C. E. 

Molnar, W. 

Moore, R. W. 

Morgan, R. 

Morrison, W. L. 

Mueller, E. 

Mueller, K. 

Muller, F. J. 

Muraca, R. F. 

Myncke, H. 

Nagano, H. 

Nagaoka, J. 

Nagoya, Y. 

Navickas, J. 

Nicholson, J. D. 

Niendorf, L. R. 

Nies, G. E. 

Nishimake, K. 

Nishimura, T. 

Noma, T. 

Nored, D. L. 

Norrie, D. H. 

Norris, D. H. 

Abstract page 

numbers 

112 

96 

73 

64 

59 

74, 75 

76 

Other document 

numbers 

271 

265, 266 

267 

268 

269 

270, 271 

274, 275 

276 

016 

277 

278 

280 

281, 361 

282 

283 

284 

285 

128 

77 

287 

288, 307 

288, 289, 307 

290, 291 

167 

292 

293 

294 

067 

149 
Abstract page 

numbers 

O'Donnell, J. P. 

Ohtani, M. 

Olien, N. A. 

O'Neill, M. J. 

Ono, T. 

Opschoor, G. 79 

Orefice, J. D. 

Parmley, R. T. 81 

Parrish, W. R. 

Partington, L. G. 

Pastuhov, A. 

Paul, E. 

Paul, H. G. 

Pears, C. D. 

Pearson, H. R. 

Peet, J. R. 

Peifer, J. 

Penn, W. H. 

Pennock, A. P. 

Percy, J. L. 

Perkins, P. J., Jr. 82 

Perkins, W. E. 

Pestalozzi, W. G. 

Pittman, C. M. 

Pleban, E. J. 83 

Ploum, A. J. W. 

Poole, R. R. 

Porter, R. N. 

Pottier, M. B. A. 

Powers, R. W. 85 

Prater, P. G. 

Other document 

numbers 

296 

008 

184 

156 

167 

299 

184 

300 

301 

302 

392 

303, 345 

304 

263 

380 

385 

305 

046 

306, 307 

308 

016 

311 

330 

312 

086, 087, 088, 089 

313 

314 

150 
Pratt, A. W. 

Probert, S. D. 

Proops, W. R. 

Ramstad, H. 

Rawuka, A. C. 

Reed, R. P. 

Reny, G. D. 

Reynolds, T. W. 

Rhodes, J. E. 

Richard, L. 

Richter, E. G. 

Ricketson, B. W. A. 

Rittenhouse, J. B. 

Robbins, M. D. 

Roberts, W. M. 

Romaine, D. 

Rooke, D. E. 

Rosello, D. 

Rosenwasser, S. N. 

Roux, C. B. 

Ruccia, F. E. 

Rusch, K. C. 

Ruscigno, H. 

Sacchi, A. 

Salmassy, 0. K. 

Sanders, V. 

Sauerbrunn, I. 

Schlumberger, E. M. 

Schmidt, W. 

Schulte, C. A. 

Segel, M. P. 

Abstract page 

numbers 

86 

87 

4, 89, 90 

Other document 

numbers 

315, 316 

175 

224 

317, 319 

157 

320 

321 

91 

26 

92 

016 

015 

322 

323 

324 

359 

325 

022 

326 

313 

016 

327 

059, 119 

56, 57, 58 

8 

101 

370 

328, 329 

330 

040 

016 

265, 266 

151 
Sellmaier, A. 

Semenov, M. V. 

Seshagiri Rao, V. 

Sevcik, V. 

Shashkov, A. G. 

Sheffield, T. B. 

Shibata, F. 

Shibata, K. 

Shoup, A. J. 

Shriver, C. B. 

Sieders, R. 

Siegrist, G. W. 

Sigmund, F. 

Simpson, W. G. 

Sinclair, D. H. 

Sindt, C. F. 

Singletary, 3. B. 

Sisler, C. W. 

Skochdopole, R. E. 

Small, A. B. 

Smith, E. T. 

Smith, F. L. 

Smith, G. T. 

Smith, H. S., Jr. 

Smith, J. C. 

Smith, J. K. 

Smith, M. E. 

Smith, M. G. 

Smith, T. D. 

Smolak, G. R. 

Smyly, E. D. 

Abstract page 

numbers 

Other document 

numbers 

381 

035 

351, 352 

380 

65 

15 

93 

94 

44, 95, 96 

331 

128 

104, 105 

333, 334 

335 

229 

336 

080 

293 

184, 337 

322 

338 

151 

339 

205, 206, 340 

115 

293 

341 

342, 343 

344 

66 

009 

022 

293 

345 

152 
Snyder, W. E. 

Soldat, G. J. 

Sollami, B. J. 

Sood, N. 

Spencer, S. E. 

Spieth, C. W. 

Srinivasan, K. 

Stastny, E. 

Stepanenko, A. N. 

Stewart, W. F. 

Stiles, R. E. 

Stoecker, L. R. 

Stofan, A. J. 

Stracke, F. H. 

Stuckey, J. M. 

Stumpf, 0. 

Sugiyama, K. 

Sumner, I. E. 

Surdi, V. L. 

Surland, C. C. 

Sutton, H. E. 

Svistova, E. A. 

Swoger, W. F. 

Taal, L. 

Tachdjian, N. 

Tanaeva, S. A. 

Tariel, H. M. 

Tatro, R. E. 

Taylor, B. N. 

Temple, R. W. 

Thomas, D. A. 

Abstract page 

numbers 

18 

97 

Other document 

numbers 

275 

022 

346 

375 

010 

347, 348, 349, 350 

351, 352 

353, 354 

102 

355 

350, 356 

293 

263 

357 

358 

284 

98 

359 

370 

350 

035 

345 

335 

100 

65 

101 

102, 108 

360, 361 

362 

363 

248 

153 
,- 

Thompson, M. B. 

Tien, C. L. 

Tobye, I. T. 

Todd, G. 

Tooley, M. R. 

Tornay, E. G. 

Trapanese, G. 

Trenner, L. 

Turner, W. C. 

Tye, R. P. 

Urzendowski, S. R. 

Uyama, K. 

Vahl, L. 

Van Bezooyen, N. 

Van Buskirk, E. C. 

Van Gelsdorp, B. A. 

Van Itterbeek, A. 

Abstract page ' Other document 

numbers numbers 

64 

364 

263 

16 

111 

365 

027 

366 

367 

7, 103 368 

007 

167 

369 

213 

370 

217 

283 

104 

Van Paassen, H. L. L. 

Van Paemel, 0. 76 

Vasiliev, L. L. 65 

Vedernikov, M. V. 105 

Veerling, C. W. N. 

Verma, V. V. 

Verschoor, J. D. 

Von Elbe, G. 

Voth, R. 0. 

Vrancken, P. L. L. 

Wagner, D. 50 

Waite, H. J. 

Walker, G. W. 

Walters, W. J. 

004 

371 

001 

372 

187 

184 

373 

374 

067, 294, 375 

139, 140, 376 

154 
Abstract page 

numbers 

Wardale, J. K. S. 

Watanabe, S. F. 

Watson, J. H. 

Watson, J. M. 

Watts, C. R. 57, 58 

Wechsler, A. E. 26 

Weishaupt, J. 

Wen, Shu-Lin 

Went, A. R. 

Whitacre, W. E. 

White, G. W. 

Whitelocke, A. J. B. 

Wijnberg, J. G. 

Williamson, K. D., Jr. 

Wilson, D. J. 

Wilson G. C. 

Wilson, J. J. 

Winsor, E. J. 

Withers, D. D. 

Wittenberg, M. 

Witzell, W. E. 

Wood, C. C. 

Wood, G. 

Wood, M. 

Woods, J. A. 

Worboys, R. V. 

Wyckaert, L. 

Yamamoto, K. 

Yasui, G. 

Yates, G. B. 106, 107, 108 

Yoshikawa, I. 

Other document 

numbers 

082 

326 

378, 379 

380 

381 

382 

383 

388 

385 

386 

387 

110 

388 

389 

390 

210 

391 

302 

070 

392 

393 

394 

092 

395 

396 

397 

398 

291 

155 
Yoshimura, K. 

Yundt, C. G. 

Zehendner, H. 

Zierman, C. A. 

Zimmerman, D. K. 

Zimni, W. F. 

Zinniger, T. C. 

Abstract page 

numbers 

87 

109 

Other document 

numbers 

399, 400 

318 

065 

023 

111, 112 216, 358 

401 

156 

.I 
SUBJECT INDEX 

157 
Abstract page numbers Other document numbers 

Aging effects 

6, 28, 31, 77, 81, 94, 

102, 109 

Anisotropy 

20, 42, 62, 102 

Balsa wood 

7, 29, 91 

025, 040, 042, 141, 151, 158, 

162, 175, 179, 199, 215, 305, 

329 

121, 133, 134, 137, 212 

005, 036, 064, 079, 083, 090, 

091, 120, 122, 154, 194, 241, 

249, 250, 263, 273, 276, 277, 

301, 324, 325, 365, 373, 390, 

398 

Bibliography 

060, 302 

Blowing agents 

33, 86, 112 

Cellulosic foam 

Commercial or proprietary designation 

17, 45, 46 

Compressive properties 

4, 6, 9, 12, 13, 16, 19, 

20, 25, 26, 38, 44, 50, 

51, 52, 54, 58, 70, 71, 

79, 81, 92, 93, 95, 97, 

98, 100, 101, 102, 108 

019, 021, 040, 042, 106, 151, 

179, 199, 244, 305 

021, 151, 164, 393 

only 

001, 009, 065, 092, 186, 187, 

235, 247, 350, 356 

021, 026, 040, 046, 061, 063, 

074, 098, 105, 127, 134, 

136-138, 151, 160, 164, 174, 

188, 205, 212, 217, 226, 227, 

238, 256, 258, 268, 287, 288, 

299, 329, 333, 340, 350, 374, 

398 

Concrete foam 

001, 026, 241, 381, 385, 397 

Corkboard 

13, 21, 29, 43, 71, 82 018, 049, 131, 149, 193, 203, 

214, 216, 238, 260, 268, 276, 

277, 283, 285, 287, 300, 369, 

372, 379, 381 

Electrical properties 

137 

Epoxy foam 

11, 12, 26, 44, 46, 51, 

54, 64, 68, 73, 96 

007, 008, 018, 021, 127, 138, 

146, 151, 164, 174, 220, 221, 

231, 259, 275, 282, 315, 316, 

322, 349, 378, 379, 393 

158 
Abstract page numbers Other document numbers 

Evacuated foam 

12 

External insulation 

017, 030, 126, 171, 244, 

348-350, 356, 368 

2, 10, 19, 21, 24, 26, 29, 002, 008, 010, 014, 016, 019, 

32, 35, 41, 42, 47, 50, 020, 023, 028, 029, 032, 035, 

59, 60, 66, 67, 74, 75, 036, 043, 044, 048, 053, 056, 

82, 93, 98, 101, 111. 057, 064, 069, 070, 071, 

078-080, 086-091, 101, 109, 

112, 113, 120, 122, 129, 135, 

136, 142, 147-150, 152,- 154, 

156, 159, 165, 166, 168, 171, 

172, 178, 190, 194-196, 198, 

200, 213, 214, 218, 223, 224, 

228, 239, 240, 245, 248, 250, 

251, 254, 262-267, 273, 

278-281, 289-293, 295, 297, 

301, 306, 309-311, 319-321, 

324-328, 330-332, 337, 338, 

341, 343-346, 358, 360-362, 

365, 366, 373, 377, 380, 383, 

387, 390-392, 397, 400, 401 

Fatigue properties 

046 

Flammability 

021, 138, 159, 164, 169, 176, 

186-189, 247, 257, 299, 300 

Floating beads or balls 

003, 004, 050, 130 

Fluorocarbon (teflon) foam 

12, 33 

Foam-filled honeycomb 

2, 26, 29, 32, 33, 46 

013, 174 

022, 046, 142, 143, 149, 159, 

207, 214, 275, 304, 344, 345, 

362 

Gelled hydrocarbon foam 

069 

159 
Abstract page numbers 

Glass or silica foam 

7, 12, 13, 16, 17, 21, 25, 

39, 43, 64, 76, 103 

Internal insulation 

2, 5, 6, 11, 15, 36, 56, 

57, 58, 79, 87, 102, 106, 

107, 108 

Liquefied natural gas application 

6, 13, 16, 34, 35, 79, 

91, 102 

Mathematical analysis 

7, 31, 32, 77 

Nuclear radiation effects 

44, 52, 70, 71, 95, 96 

Other document numbers 

001, 005, 016, 031;037, 039, 

064, 075, 081, 082, 091,.107, 

108, 111, 139;,140, 146, 153, 

176, 180, 188, 189, 201, 203, 

216, 220, 221, 231, 233, 238, 

241, 245, 246, 252, 255, 270, 

274-277, 283, 287, 296, 299, 

301, 315, 316, 319, 328, 342, 

356, 370, 372, 376, 379, 381 

015, 020, 022, 024, 026, 031, 

034, 041, 051, 052, 054, 055, 

078, 084, 104, 105, 111, 

114-117, 123, 132-134, 139, 

150, 167, 177, 192, 201, 202, 

209, 210, 232, 242, 246, 260, 

296, 309, 314, 318, 333-335, 

355, 385, 388, 392, 395, 399 

002, 005, 011, 024, 031, 034, 

036, 043, 047, 051, 053, 055, 

064, 066-069, 071-073, 075-077, 

079, 081-083, 085, 090, 091, 

093-097, 103-105, 108, 110, 

111, 115, 117, 120, 122, 139, 

140, 148, 150, 153, 154, 178, 

182, 183, 190, 192, 194-196, 

198, 201, 202, 208, 209, 219, 

223, 224, 232, 241, 242, 245, 

246, 249-252, 254, 257, 263, 

264, 269, 272, 273, 279, 280, 

290-292, 294, 296-298, 301, 

309, 310, 313, 314, 319, 324, 

325, 331, 332, 336, 339, 355, 

363, 365-367, 371, 373, 375, 

376, 385, 387, 390, 391, 

394-397, 401 

041, 141, 158, 161, 191, 211, 

338, 351, 358 

041, 099, 131, 205, 206, 262, 

322, 340, 398 

Outgassing 

19, 93 156, 240, 282, 307, 350, 356 

160 
Abstract page numbers 

Oxygen compatibility 

23, 45, 46, 47, 52, 60, 

101 

Patents 

Phenolic foam 

13, 86, 109, 112 

Pipe insulation 

8, 13, 18, 34, 69 

Other document numbers 

013, 039, 159, 186-188, 203, 

207, 247, 276, 379 

008, 010, 019, 022, 024, 028, 

033, 034, 047, 051, 053, 054, 

062, 064, 069, 090, 091, 101, 

109, 148, 178, 192, 194-196, 

200-202, 204, 209, 210, 214, 

222, 230, 232, 242, 263, 264, 

278, 290-292, 306, 312, 313, 

324, 330, 334-336, 339, 341, 

346, 360, 361, 365, 366, 391, 

395, 397, 399-401 

021, 102, 107, 119, 125, 138, 

151, 164, 216, 241, 300, 303, 

322, 329, 345, 379, 393 

006, 013, 014, 037, 038, 040, 

047, 062, 066-069, 072, 073, 

076, 077, 085, 093-097, 100, 

103, 108, 124, 172, 182, 183, 

204, 210, 226, 227, 234, 269, 

272, 284, 294, 298, 319, 336, 

351, 352, 359, 363, 371, 375, 

386, 394, 396 

Polybenzimidazole foam 

078, 177 

Polyester foam 

23 

Polyether foam 

12, 26, 51, 54, 73 

Polyethylene foam 

20, 109 

146 

127, 174, 235, 268, 322 

021, 151, 201, 268, 339, 341, 

353, 393 

Polyimide foam 

078, 177 

Polymethacrylimide foam 

42, 67 

Polyphenylene oxide foam 

9, 42, 79, 102, 106, 107, 

108 

Polypropylene foam 

113 

132-135, 177, 212, 213, 244, 

335 

021, 050, 130, 164, 339, 341 

161 
Abstract page numbers Other document numbers 

Polystyrene foam 

4, 6, 7, 12, 13, 15, 17, 

18, 20, 21, 22, 33, 43, 

44, 45, 49, 51, 54, 62, 

64, 68, 70, 73, 85, 86, 

89, 90, 94, 95, 97, 104, 

105, 109 

Polyurethane foam 

2, 4, 5, 7, 8, 10, 11, 12, 

13, 17, 19, 21, 24, 26, 

28, 29, 31, 32, 33, 34, 

35, 36, 37, 38, 39, 41, 

42, 43, 44, 46, 47, 49, 

50, 51, 52, 54, 56, 57, 

58, 59, 60, 62, 64, 65, 

66, 67, 69, 70, 71, 73, 

77, 81, 82, 83, 86, 87, 

89, 91, 92, 93, 94, 95, 

96, 97, 98, 103, 109, 111, 

112 

003, 004, 009, 016, 021, 

026-028, 037, 046, 049, 

052-054, 058, 059, 061, 071, 

088, 091, 094, 095, 102, 107, 

112, 118, 125, 128, 138, 146, 

147, 151, 152, 164, 170, 173, 

174, 176, 188, 193, 196, 197, 

201, 216, 220, 221, 225, 229, 

231, 233, 238, 241, 243, 244, 

251, 252, 256, 258, 259, 261, 

264, 270, 271, 275-279, 283, 

285-287, 290, 293, 299, 300, 

305, 308, 315, 316, 320, 324, 

328, 329, 339-342, 349, 350, 

353, 354, 356, 369, 372, 374, 

378, 379, 381, 383, 393, 397 

001, 005, 006, 008, 010, 011, 

013, 014, 016-027, 030, 

032-034, 036-040, 042, 043, 

045-049, 051, 053, 055-057, 

062, 066-068, 070, 072-078, 

080, 083-085, 087-099, 101-106, 

108-110, 112, 114, 115, 121, 

123-125, 127-129, 131, 135-138, 

142-145, 148, 149, 151, 

153-160, 162-164, 167-170, 

172-183, 165, 188-190, 192-196, 

198-202, 204-210, 214-218, 

221-224, 226-229, 232, 233, 

236-241, 244, 248-250, 252, 

253, 255-257, 260, 262, 263, 

267-270, 272, 273, 275-278, 

282, 284, 286-295, 297-301, 

304-309, 311-319, 322-324, 

326-330, 333, 334, 336-338, 

340-344, 347-357, 362, 363, 

365, 366, 368, 371, 373, 375, 

377-379, 381, 383-387, 390-396, 

398-401 

162 
Abstract page numbers Other document numbers 

Polyvinyl chloride foam 

42, 50, 59, 64, 67, 74, 

75, 86, 91, 100, 101, 103, 

109, 111, 112 

Review and discussion papers 

2, 8, 10, 12, 13, 21, 26, 

38, 42, 43, 51, 52, 54, 

64, 83, 86, 91, 100, 102 

Rubber foam 

12, 43, 64 

Shear properties 

12, 26, 38, 50, 51, 52, 

58, 59, 62, 68, 71, 73, 

79, 98, 108 

Silicone foam 

97 

002, 021, 026, 029, 033, 036, 

044, 049, 053, 091, 107, 122, 

125, 141, 153, 154, 164-166, 

196, 201, 216, 241, 249, 250, 

254, 265, 266, 275-277, 280, 

281, 300, 310, 324, 328-331, 

339, 341, 342, 360, 361, 369, 

380, 393 

002, 005, 006, 011-014, 016, 

017, 020, 021, 023, 029, 031, 

036-039, 043, 044, 048, 049, 

061, 066-068, 070-083, 085-087, 

089, 093-097, 107, 108, 

110-113, 115, 117, 118, 120, 

122, 135, 138-140, 143, 145, 

146, 150, 151, 153, 154, 

164-167, 170, 171, 173, 174, 

176, 177, 180, 182-185, 

188-190, 216, 219-221, 223, 

225, 228, 229, 231, 233, 234, 

236-239, 241, 243, 245, 246, 

249-252, 255, 257, 267, 269, 

270, 272-277, 279-281, 286, 

287, 293-301, 308-310, 314-316, 

319, 322, 323, 325, 328, 329, 

331, 332, 342, 343, 352, 354, 

355, 359, 363, 364, 367, 371, 

373, 375-379, 381-384, 386-388, 

390, 392-394, 396 

021, 039, 049, 063, 146, 189, 

216, 220, 221, 238, 241, 268, 

275, 277, 287, 300, 315, 316, 

372, 379, 393, 401 

040, 046, 099, 127, 138, 151, 

164, 188, 304, 398 

021, 078, 138, 151, 164, 282, 

322, 345, 393 

163 
Abstract page numbers Other document numbers 

Spacecraft application 

2, 5, 10, 11, 19, 26, 29, 

32, 36, 41, 42, 47, 50, 

56, 57, 58, 59, 60, 66, 

67, 69, 74, 75, 82, 83, 

87, 93, 98, 101, 106, 107, 

108, 111 

Specific heat 

43, 64, 65, 101, 112 

Syntactic foam 

Tensile properties 

12, 20, 26, 38, 42, 50, 

51, 52, 54, 58, 59, 68, 

73, 74, 79, 89, 90, 98, 

100, 101, 102, 108 

Test methods and procedures 

33, 39, 64, 76, 86 

015, 019, 020, 023, 029, 032, 

041, 044, 046, 048, 056, 057, 

070, 078, 080, 084, 086-089, 

099, 101, 112-114, 116, 129, 

131-136, 142, 145, 149, 150, 

152, 156, 159, 165, 166, 168, 

171, 172, 177, 186, 187, 193, 

212, 214, 218, 219, 228, 236, 

239, 240, 248, 260, 262, 

265-267, 274, 281, 282, 289, 

293, 295, 306, 311, 318, 320, 

321, 323, 326, 327, 333, 337, 

344-346, 357, 358, 360, 362, 

388, 392 

007, 165, 173, 216, 303, 345 

018, 021, 138, 174, 193, 276 

021, 063, 074, 078, 098, 127, 

134, 138, 151, 164, 188, 212, 

216, 226, 227, 253, 259, 304, 

338, 378, 398 

009, 030, 056, 065, 092, 100, 

125, 157, 168, 230, 244, 283, 

321, 326 

164 
Abstract page numbers Other document numbers 

Thermal conductivity and heat flux 

2, 5, 6, 7, 9, 11, 12, 13, 

15, 18, 19, 20, 21, 22, 

24, 29, 31, 32, 33, 35, 

36, 37, 38, 39, 41, 42, 

43, 44, 49, 51, 54, 57, 

59, 60, 62, 64, 65, 69, 

75, 76, 77, 82, 83, 85, 

86, 87, 94, 96, 98, 100, 

101, 102, 103, 105, 106, 

i07, 108, 109, 111, 112 

001, 009, 011, 012, 015-017,. 

021, 025-027, 030, 032, 035, 

037, 040-042, 044-046, 049, 

050, 056, 058, 059, 063, 

065-067, 072, 074, 078, 084, 

086-089, 092, 093, 096, 098, 

100, 102-107, 110, 112, 113, 

118, 119, 121, 123, 124, 126, 

128-130, 132, 133, 135-146, 

149, 151, 152, 155-162, 164, 

165, 170, 171, 173-175, 

179-184, 188, 191, 193, 197, 

199, 206, 208, 211, 215-217, 

220, 221, 225-230, 233-240, 

243-245, 255-258, 260-262, 

266, 267, 270, 271, 275-277, 

283-285, 287, 289, 295, 297, 

299, 300, 303, 305, 308, 

315-318, 320, 321, 327, 329, 

331, 337, 338, 343-345, 

347-350, 352-354, 356-358, 

362-364, 368-370, 372, 374-376, 

378, 379, 381, 383, 385-387, 

392, 396 

Thermal expansion 

20, 26, 35, 42, 43, 51, 

52, 54, 62, 64, 73, 79, 

98, 101, 104, 112 

007, 018, 021, 026, 063, 116, 

125, 163, 164, 174, 212, 226, 

227, 258, 303, 345, 353 

Thermal stability and ablation properties 

5, 28, 29, 57, 59, 60, 66, 007, 021, 057, 070, 078, 133, 

74, 102, 107 134, 136, 137, 156, 172, 177, 

213, 218, 248, 282, 311, 343, 

345, 393 

Urea-formaldehyde foam 

17, 43, 85, 86 021, 064, 107, 126, 151, 164, 

216, 231, 276, 329, 370, 393 

165 
. Report No. 2. Government Accession No. 

Title and Subtitle 

CRYOGENIC FOAM INSULATION -ABSTRACTED 

PUBLICATIONS 

Author(s) 

Frank R. Williamson 

3. Recipient’s Catalog No. 

5.;Report Date 

September 1977 

6. Performing Organization Code 

8. Performing Organization Report No. 

10. Work Unit No. 

Performing Organization Name and Address 

National Bureau of Standards 

Cryogenics Division 

Boulder, Colorado 80302 

Sponsoring Agency Name and Address 

National Aeronautics and Space Administration 

Washington, D. C. 20546 

Supplementary Notes 

11. Contract or Grant No. 

13. Type of Report and Period Covered 

Reference Publication 

14. Sponsoring Agency Code 

Abstract 

This survey is composed of information from the reports and publications available in January 

1976 on cryogenic foam insulation. One group of documents 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. Anoth:r group of documents generally includes less important 

papers than those in the first gro?w-, &ome important papers are in the second group because 

information from them has been reviewed or repeated in documents included in the first group. 

Key Words (Suggested by Author(s)) 

Insulation 

Foams 

Cryogenic equipment 

Cryogenics 

18. Distribution Statement 

Unclassified - unlimited 

STAR Category 27 

Security Classif. (of this report) 20. Security Classif. (of this page) 

Unclassified Unclassified 

21. No. of Pages 

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22. Price’ 

A08 

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NASA-Langley, 1977 
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20546 

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