This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Airplane Size Effects on Occupant Crash Loads
Annotation ability available
Sector:
Language:
English
Abstract
The effect of airplane size on occupant crash loads has been demonstrated using beam finite element models of Boeing 737-400 and 747-400 airplanes. For the impact survivable accident conditions investigated, it was shown that the 747-400 airplane transmitted a significantly lower level of occupant impulse than the 737-400 airplane. The studies showed that the 747 fuselage structure, though stronger than the 737, permits more deformation to occur over a longer time period. For the cases studied, the results showed that the 747 crash loads were only 1/3 to 1/2 of the crash loads generated for the 737.
The studies indicate it may be impossible to generate the currently specified FAR 25.561 and 25.562 crash loads in impact survivable accidents for the 747 and larger aircraft. As the external crash impact loads increase, crushing of the fuselage structure limits the internal crash loads to less than the current FAR requirements. As a result, larger airplanes such as 747 are required to carry an unnecessary weight penalty.
The crash models were developed using the ABAQUS program's nonlinear structural dynamics features. In this paper, the modeling approach is discussed, results are presented, and recommendations for further modeling improvements are made. The modeling technology was validated by analyzing to the 737-400 accident at Kegworth, England on January 8, 1989.
Recommended Content
Authors
Citation
Jamshidiat, H., Widmayer, E., and McGrew, J., "Airplane Size Effects on Occupant Crash Loads," SAE Technical Paper 922035, 1992, https://doi.org/10.4271/922035.Also In
References
- Wittlin, G. Lackey, D. “Analytical Modeling of Transport Aircraft Crash Scenarios to Obtain Floor Pulses,” DOT/FAA/CT 83/23 April 1983
- Wittlin, G. “KRASH Parametric Sensitivity Study- Transport Category Airplanes,” DOT/FAA/CT 87/13 December 1987
- Wittlin, G. Neri, L. “The Effects of Aircraft Size on Cabin Floor Dynamic Pulses,” DOT/FAA/CT-88/15 1990
- Caiafa, Caesar A. Neri, L.M. “Effects of Aircraft Size on Cabin Floor Dynamic Pulses,” SAE 881379 October 1988
- Soltis, Stephen “Seat Dynamic Performance Standards for a Range of Sizes,” DOT/FAA/CTTN90/23 August 1990
- Reed, W.H. Robertson, S.H. Weinberg, L.W.T. Tyndall, L.H. “Full Scale Dynamic Crash Test of a Douglas DC-7 Aircraft,” FAA/ADS-37 April 1965
- Williams, S. M. Hayduk, R. J. “Vertical Drop Test of a Transport Fuselage Section Located Forward of the Wing,” NASA Technical Memorandum 85679 August 1983
- Johnson, D. Wilson, A. “Vertical Drop Test of a Transport Airframe Section,” DOT/FAA/CT-86/34 October 1986
- DC-10 Fuselage Drop Test Report No. 7251-2 Arvin Calspan report prepared for the FAA Technical Center Atlantic City, N.J. September 1984
- Greer, D.L. Heid, T.L. Weber, J.D. “Design Study and Model Structures Test Program to Improve Fuselage Crashworthiness,” FAA ADS 67-20 October 1967
- Crash Simulation Methods for Vehicle Development at Mazda Cray Channels Fall 1990
- Development and Experimental Verification of Procedures to Determine Nonlinear Load-Deflection Characteristics of Helicopter Substructures Subject to Crash Forces II Test Data and Description of Refined Program “Krash” Including a User's Guide and Sample Case USAAMRDL-TR-74-12B-AD 784192 May 1974
- ABAQUS & ABAQUS-Explicit Hibbit, Karlsson & Sorensen Inc 1080 Main Street, Pawtucket, Rhode Island 02860