This paper describes a mathematical investigation of the crash-impact responses of an all-composite helicopter cockpit section incorporating an energy absorbing concept and one of conventional aluminum construction, using the Grumman DYCAST finite-element nonlinear structural dynamics computer program. The overall objective of this initial investigation was to explore the application of DYCAST to the design of future helicopter structures. The specific purposes are to assess the value of the finite-element code as a crashworthiness design analysis tool, and to compare the responses of the two fuselage sections. The results indicate that the finite-element simulation is a powerful analysis tool, providing sufficient detail to evaluate individual structural components, and that the crashworthiness of an all-composite cockpit section could be enhanced with energy-absorbing concepts
Crash simulation of composite and aluminum helicopter fuselages using a finite-element program
Structures, Structural Dynamics, and Materials Conference ; 1979 ; St. Louis, MO
1979-01-01
Miscellaneous
No indication
English
Finite Element Simulation of a Full-Scale Crash Test of a Composite Helicopter
British Library Conference Proceedings | 2000
|Finite Element Simulation of a Full-Scale Crash Test of a Composite Helicopter
Online Contents | 2002
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