Abstract
Crashworthiness has been and will continue to be the main concern in aviation safety. This paper investigates the effects of oblique struts on crashworthiness of fuselage sections for typical transport aircraft. The finite element model of a composite fuselage section is developed to simulate the vertical drop test subjected to 6:67 m=s impact velocity. The impact characteristics of the composite fuselage section are analyzed by changing the oblique strut angle and rigidity. A comparative analysis of acceleration histories and failure modes of a fuselage section with different oblique strut configurations is given. The results show that the seat peak overloads can be significantly reduced and the composite aircraft structure crashworthiness can be effectively improved by selecting the appropriate oblique strut angle and rigidity for composite fuselage section.
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