Development and Calibration of a System-Integrated Rotorcraft Finite Element Model for Impact Scenarios
Development and Calibration of a System-Integrated Rotorcraft Finite Element Model for Impact Scenarios
- Neue Suche nach: M. S. Annett
- Neue Suche nach: L. G. Horta
- Neue Suche nach: K. E. Jackson
- Neue Suche nach: M. A. Polanco
- Neue Suche nach: J. D. Littell
- Neue Suche nach: M. S. Annett
- Neue Suche nach: L. G. Horta
- Neue Suche nach: K. E. Jackson
- Neue Suche nach: M. A. Polanco
- Neue Suche nach: J. D. Littell
Two full-scale crash tests of an MD-500 helicopter were conducted in 2009 and 2010 at NASA Langley's Landing and Impact Research Facility in support of NASA s Subsonic Rotary Wing Crashworthiness Project. The first crash test was conducted to evaluate the performance of an externally mounted composite deployable energy absorber (DEA) under combined impact conditions. In the second crash test, the energy absorber was removed to establish baseline loads that are regarded as severe but survivable. The presence of this energy absorbing device reduced the peak impact acceleration levels by a factor of three. Accelerations and kinematic data collected from the crash tests were compared to a system-integrated finite element model of the test article developed in parallel with the test program.
Dokumentinformationen
Development and Calibration of a System-Integrated Rotorcraft Finite Element Model for Impact Scenarios
2012
63 pages
Report
Keine Angabe
Englisch
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