Journal
JOURNAL OF AIRCRAFT
Volume 39, Issue 1, Pages 142-147Publisher
AMER INST AERONAUT ASTRONAUT
DOI: 10.2514/2.2908
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Recent advances in computational speed have made aircraft and spacecraft crash simulations using an explicit, nonlinear. transient-dynamic, finite element analysis code more feasible. This paper describes the development of a simple landing-gear model, which accurately simulates the energy absorbed by the gear without adding substantial complexity to the model. For a crash model the landing gear response is approximated with a spring where the force applied to the fuselage is computed in a user-written subroutine. Helicopter crash simulations using this approach are compared with previously acquired experimental data from a full-scale crash test of a composite helicopter.
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