A full-scale crash test of a prototype composite helicopter was performed at the Impact Dynamics Research Facility at NASA Langley Research Center in 1999 to obtain data for validation of a finite element crash simulation. The helicopter was the flight test article built by Sikorsky Aircraft during the Advanced Composite Airframe Program (ACAP). The composite helicopter was designed to meet the stringent Military Standard (MIL-STD-1290A) crashworthiness criteria and was outfitted with two crew and two troop seats and four anthropomorphic dummies. The test was performed at 38-ft/s vertical and 32.5-ft/s horizontal velocity onto a rigid surface. An existing modal vibration model of the Sikorsky ACAP helicopter was converted into a model suitable for crash simulation. A two-stage modeling approach was implemented and an external user-defined subroutine was developed to represent the complex landing gear response. The crash simulation was executed with a nonlinear, explicit transient dynamic finite element code. Predictions of structural deformation and failure, the sequence of events, and the dynamic response of the airframe structure were generated and the numerical results were correlated with the experimental data to validate the simulation. The test results, the model development, and the test-analysis correlation are described.
Full-Scale Crash Test and Finite Element Simulation of a Composite Prototype Helicopter
2003
121 pages
Report
Keine Angabe
Englisch
Aircraft , Composite Materials , Composite materials , Helicopters , Crash landings , Simulations , Velocity , Impact phenomena , Aerospace structures , Shock testing , Energy absorption (structures) , Dynamic structural analysis , Acap(advanced composite airframe program) , Idrf(impact dynamics research facility)
Finite Element Simulation of a Full-Scale Crash Test of a Composite Helicopter
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