A Simplified Method for Calculating the Response of Aircraft Structures to Internal Detonations

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.