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Data for Fail-Safe Design of the Supersonic Transport Pressure Cabin
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English
Abstract
The concept of fail-safe structure has introduced requirements for evaluation of new types of material properties and new sets of conditions for the design of pressure cabins of high altitude aircraft. A brief review is given of the fracture toughness properties of candidate materials for the SST environment. The results of recent tests on residual strength and rate of crack growth in stiffened and unstiffened panels and cylinders made from titanium and steel are presented. The results of a titanium full-scale fuselage panel tested under heat (550–650 F) and cyclic pressure are discussed in light of SST design requirements.
Citation
Melcon, M. and Mueller, F., "Data for Fail-Safe Design of the Supersonic Transport Pressure Cabin," SAE Technical Paper 640248, 1964, https://doi.org/10.4271/640248.Also In
References
- Crichlow, W. J. “The Ultimate Strength of Damaged Structure - Analysis Methods with Correlating Test Data,” from ICAF-AGARD Symposium on “Full Scale Fatigue Testing of Aircraft Structures,” Amsterdam June 1959 Pergamon Press New York, London
- Kuhn, Paul “Notch Effects on Fatigue and Static Strength,” Symposium on Aeronautical Fatigue sponsored by the International Committee on Aeronautical Fatigue (ICAF) and the Structures and Materials Panel of the Advisory Group for Aeronautical Research and Development (AGARD) Rome, Italy April 1963
- “Fuselage Fail-Safe Design Data and Bomb Resistant Analysis for the Supersonic Transport.” Lockheed-California Co. August 1963
- “Fuselage Fail-Safe Design Data and Bomb Resistant Analysis for the Supersonic Transport,” Lockheed-California Co. November 1963
- Peters, R. W. Kuhn, Paul “Bursting Strength of Unstiffened Pressure Cylinders with Slits,” NASA April 1957