Crash simulation of composite and aluminum helicopter fuselages using a finite-element program

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

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

Authors

• Winter, R. Grumman Aerospace Corp.
• Pifko, A. B. Grumman Aerospace Corp.
• Cronkhite, J. D. Bell Helicopter Textron, Inc.