Citation

Jackson KE. Int. J. Crashworthiness 2001; 6(1): 107-121.

Copyright

(Copyright © 2001, Informa - Taylor and Francis Group)

DOI

unavailable

PMID

unavailable

Abstract

A composite fuselage concept for light aircraft and rotorcraft has been developed to provide improved crash protection. The fuselage consists of a relatively rigid upper section, or passenger cabin, including a stiff structural floor and a frangible lower section which encloses the crash energy management structure. A 60-in. diameter full-scale fuselage section was manufactured using a composite sandwich construction. Vertical drop tests were conducted at both 0 degrees- and 15 degrees -roll impact attitudes to evaluate the crashworthy features of the fuselage design. The experimental data are correlated with predictions from a finite element model developed using the non-linear, explicit transient dynamic code, MSC.Dytran.

Language: en