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Simulation of Aircraft Landing Gears with a Nonlinear Dynamic Finite Element CodeRecent 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.
Document ID
20000112939
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Lyle, Karen H. (Army Vehicle Technology Center Hampton, VA United States)
Jackson, Karen E. (Army Vehicle Technology Center Hampton, VA United States)
Fasanella, Edwin L. (Army Vehicle Technology Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2000-4090
Meeting Information
Meeting: Modeling and Simulation Technologies
Location: Denver, CO
Country: United States
Start Date: August 14, 2000
End Date: August 17, 2000
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

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