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A Simplified Method for Calculating the Response of Aircraft Structures to Internal Detonations
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English
Abstract
This paper discusses a simplified method for analyzing the response of aircraft fuselage structures subjected to internal blast loading. By assuming that the loaded section of the fuselage acts like an expanding membrane, a single-degree-of-freedom (SDOF) model which tracks the radial displacement of the membrane can be used to characterize structural response. Results obtained using the model are evaluated against data obtained from tests conducted on retired aircraft. Comparisons with the test data indicate the method provides reasonable estimates of structural strain- and motion-time histories, as well as combinations of charge size and standoff distance associated with the onset of failure.
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Citation
Whitehouse, S., "A Simplified Method for Calculating the Response of Aircraft Structures to Internal Detonations," SAE Technical Paper 965587, 1996, https://doi.org/10.4271/965587.Also In
References
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- Sewell, R.G.S. Kinney, G.F. “Response of Structures to Blast: A New Criterion,” Naval Weapons Center China Lake, California June 1968
- Bonde, L.W. Jr. Clough, B.T. Flick, P.M. Whitehouse, S.R. “Aircraft Response Test, Series IIB, Follow-On Blast Tests, Data Report,” Wright Laboratory Wright-Patterson Air Force Base, Ohio March 1993
- “Structures to Resist the Effects of Accidental Explosions,” Headquarters of the Army, Navy, and Air Force Washington, D.C. November 1990