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Structural Design Considerations for the Storage of Liquid Hydrogen in a Space Vehicle
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English
Abstract
The S-IV and S-IVB stages for the Saturn vehicles were designed to utilize the high specific impulse of the liquid hydrogen - liquid oxygen propulsion system. The use of liquid hydrogen presented special structural problems that led to the development of the reinforced foam internal insulation and the sandwiched honeycomb common bulkhead. The major design problem in each case was the high thermal stress resulting from the steep thermal gradient across the depth of the structure. For the extreme temperatures involved the thermal stresses were very high and were dominant factors in establishing the designs.
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Citation
Sagata, J., "Structural Design Considerations for the Storage of Liquid Hydrogen in a Space Vehicle," SAE Technical Paper 650118, 1965, https://doi.org/10.4271/650118.Also In
References
- “Interim Status Report of Development of A Wet-Wall Insulation for Saturn S-IV Model No. DSV-IV.” Douglas Report SM-38797. Prepared for NASA under Contract No. NAS7-1 July 11 1962
- Dearing D. L. “Evaluation Of The Saturn S-IV Internal Insulation In The Eight-Foot Scale Tank.” Douglas Report SM-42545. Prepared for NASA under Contract No. NAS7-1 November 1962
- Herstine Glen L. “Why Internal Insulation For The Saturn S-IV Liquid Hydrogen Tank?” Prepared for presentation at the Cryogenic Engineering Conference Los Angeles, Calif. Aug. 14 16 1962
- Stockton A. C. Paleno V. A. “Fabrication Of The Saturn S-IV Common Bulkhead.” Douglas Report SM-42686. Prepared for NASA under Contract No. NAS7-1 Dec. 6 1962