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Structural Considerations in the Design of a Liquid Hydrogen Tank for Hypersonic Vehicles
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Abstract
In order to utilize liquid hydrogen efficiently as a fuel for hypersonic cruise vehicles, it is necessary to design an optimum weight tank of high structural reliability. The structural design, analysis, and testing aspects of such a liquid hydrogen tank are discussed. The tank was required to occupy an elliptic space envelope and be allowed to buckle elastically under inertia loading and the effect of temperature gradients. The support system minimizes load deflection and thermal deformation interaction between tank and vehicle. The tank must meet burst pressures of 60 psi and yet be stable for certain loading conditions with negligible internal pressure.
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Fischer, J. and Hausrath, A., "Structural Considerations in the Design of a Liquid Hydrogen Tank for Hypersonic Vehicles," SAE Technical Paper 660679, 1966, https://doi.org/10.4271/660679.Also In
References
- Heathman John H. and Kelly Larry G., “Hydrogen Tankage for Hypersonic Cruise Vehicles.” Paper presented at AIAA/ASME Seventh Structures and Materials Conference, April 1966.
- Girton L. D., “Evaluation of Sheet Alloy 718 for Formed and Welded Missile Parts.” General Dynamics Convair Report GD/A-ERR-AN-656, December 1964.
- “Metallic Materials and Elements for Flight Vehicle Structures.” MIL-HDBK-5, August 1962.
- Boley B. A., and Weimer J. H., “The Theory of Thermal Stresses.” Columbia University Institute of Flight Structures. New York: John Wiley & Sons., Inc., 1960.