Abstract
Space boosters using liquid hydrogen as a propellant require insulation to minimize the heat leak into the liquid for ground and boost operations. Thus, during the early design phase of the Saturn S-II program, it was decided to apply an external insulation primarily to take advantage of the increased strength properties of the aluminum-alloy tank skin at cryogenic temperature.
Work supported under National Aeronautics and Space Administration Contract NAS 7–200.
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References
ASTM “Plastics Specifications: Method of Testing Pipe, Film, Reinforced and Cellular Plastics,” ASTM Committee on Plastics D-20, Method D1638–61T (June 1966), pp. 172–209.
Ibid., Method D1622–63, pp. 159–160.
Ibid., Method D1940–62T, pp. 306–311.
Ibid., Method D1621–64, pp. 156–158.
ASTM “Plastics—General Methods of Testing,” ASTM Committee on Thermal Insulating Materials C-16, Method C-177–63 (June 1966), pp. 1–12.
Ibid., ASTM Committee on Plastics D-20, Method D696–44, pp. 254–257.
Ibid., Method 1692–59T, pp. 553–556.
ASTM “Structural Sandwich Constructions; Wood; Adhesives,” ASTM Committee on Structural Sandwich Constructions C-19, Method C-273–61 (June 1966), pp. 6–10.
M. B. Hammond in: Advances in Cryogenic Engineering, Vol. 15, Plenum Press, New York (1970), p. 332.
Contract NAS7–200, “Spray Foam Insulation Test—X-15 Flights 3–65–96 and 3–65–97,” North American Rockwell Document 69MA5502 (June 10, 1964).
B. B. Cioth, “Spray Foam Insulation Test With MDC (Thor) Tank” North American Rockwell Documents SID 67–696 (Dec. 1967) and SID 68–394 (July 1968).
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Mack, F.E., Smith, M.E. (1971). High-Performance Spray-Foam Insulation for Application on Saturn S-II Stage. In: Timmerhaus, K.D. (eds) Advances in Cryogenic Engineering. Advances in Cryogenic Engineering, vol 16. Springer, Boston, MA. https://doi.org/10.1007/978-1-4757-0244-6_15
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DOI: https://doi.org/10.1007/978-1-4757-0244-6_15
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