Investigation of Potential Low Temperature Insulators

  • J. Hertz
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 11)


The requirement for long-duration (greater than one or two years) space flights is rapidly approaching, and the passive type insulation systems (surface coatings, foams, cork, superinsulations, etc) used for cryogenic tankage In short-duration flights (less than 24 hr) will probably be replaced by active insulation systems (refrigeration systems, reliquefaction systems, etc). The most immediate problem is for intermediate-duration flights (greater than 1 day but less than 1 yr), and for this problem superinsulation or radiation shields appear to be the most attractive insulations. Systems such as NCR-2 and Linde SI-62 have apparent thermal conductivity values when measured under high vacuum between room temperature and -320°F of 1 to 3 × 10-5 Btu-ft/hr-ft2-°F. Evacuated fiberglass and evacuated powder insulations have k-factors approximately 30 to 50 times higher than superinsulations, whereas plastic foams have k-factors 500 to 1000 times higher. If one compares these insulation systems on a kp or (kp) 1/2 basis, the differences between systems are reduced, but the superinsulations are still significantly better than the other passive systems.


Thickness Direction Cryogenic Temperature Insulation System Heat Leak Multilayer Insulation 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.


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  1. 1.
    “Liquid Propellant Losses During Space Flight,” Final Report on Contract No. NAS2–615, Report No, 65008–00-04, Arthur D. Little, Inc. (October 1964).Google Scholar
  2. 2.
    J. F. Haskins, M. D. Campbell, J. Hertz, and J. L. Percy, “Thermophysical Properties of Plastic Materials and Composites to Liquid Hydrogen Temperature (—423°F),” Contract No. AF33-(657)-9160, Report No. ML-TDR-64–33, Part 1 (June 1964).Google Scholar
  3. 3.
    “Propellant Storability in Space,” Report No. RPL-TDR-64–75, General Electric Spacecraft Dept. (June 1965).Google Scholar
  4. 4.
    L. W. Toth, T. J. Boiler, A. H. Kariotis, and F. D. Yoder, “Program for the Evaluation of Structural Reinforced Plastic Materials at Cryogenic Temperatures,” Annual and Fourth Quarterly Report on Contract NAS 8–11070 (July 1964).Google Scholar
  5. 5.
    V. H. Gray and T. F. Gelder, in: Advances in Cryogenic Engineering, Vol. 5, Plenum Press, New York (1960), p. 131.Google Scholar
  6. 6.
    K. Eiermann, K. H. Hellwege, and W. Knappe, Kolloid-Z. 174, (2): (1961) General Dynamics/ Astronautics Translation 63–0848.Google Scholar
  7. 7.
    J. F. Haskins and J. Hertz, in: Advances in Cryogenic Engineering, Vol. 7, Plenum Press, New York (1962), p. 353.Google Scholar
  8. 8.
    R. W. Powell, W. M. Roger, and D. O. Coffin, NBS J. Res. 59 (5): (November 1957).Google Scholar
  9. 9.
    K. Eiermann, Kunstoffe 51 (9): (1961), General Dynamics/Astronautics Translation 63–0834.Google Scholar
  10. 10.
    M. L. Minges, J. M. Meiselmann, and J. G. Broadus, “A System for Measurement of Cryogenic Thermal Conductivity of Solids to Liquid Nitrogen Temperatures (-320°F),” ASD-TDR-63–756 (October 1963).Google Scholar
  11. 11.
    K. H. Hellwege, W. Knappe, and V. Simpson, Z. Angew. Phys. II (8): (1959), General Dynamics/ Astronautics Translation ACW64–016.Google Scholar
  12. 12.
    K. Eiermann and W. Knappe, Z. Angew. Phys. 14 (8): (1962), General Dynamics/Astronautics Translation ACW64–013.Google Scholar
  13. 13.
    K. Eiermann, Kolloid-Z. and Z. Polymer 180 (2), (1962), General Dynamics/Astronautics Translation ACW64–011.Google Scholar
  14. 14.
    J. F. Haskins and J. Hertz, “Thermal Conductivity Testing of Coast F-224–6 Phenolic-Fiberglass Laminate,” General Dynamics/Astronautics Report No. AR-592–1–482 (July 1963).Google Scholar
  15. 15.
    R. L. Davis, Plastics World 21 (11): 62 (November 1963).Google Scholar
  16. 16.
    Modem Plastics Encyclopedia 41 (1A): (1964).Google Scholar
  17. 17.
    Rocketdyne “Final Report-Program of Testing Nonmetallic Materials at Cyrogenic Temperatures,” Contract AF04(611)-6354, Rocket Propulsion Laboratories, Edwards, California (December 1962).Google Scholar
  18. 18.
    Product Literature of the Durez Plastics Division of the Hooker Chemical Corporation.Google Scholar
  19. 19.
    R. H. Knoll and J. С Oglebay, “Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks,” NASA Lewis Research Center, SAE paper 746C, (September 1963).Google Scholar
  20. 20.
    F. E. Swalley and C. D. Nevins, in: Advances in Cryogenic Engineering, Vol. 10, Plenum Press, New York (1965), p. 208.Google Scholar
  21. 21.
    R. F. Crawford and R. I. Hurrah, “Optimum Insulation Proportions for Orbital Storage of Cryogenics,” Tech. Memo. No. 6, Contract NAS 8–5268.Google Scholar

Copyright information

© Springer Science+Business Media New York 1966

Authors and Affiliations

  • J. Hertz
    • 1
  1. 1.General Dynamics/ConvairSan DiegoUSA

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