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  • 11
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    Structural response of transport airplanes in crash situations (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report highlights the results of contractural studies of transport accident data undertaken in a joint research program sponsored by the FAA and NASA. From these accident data studies it was concluded that the greatest potential for improved transport crashworthiness is in the reduction of fire related fatalities. Accident data pertaining to fuselage integrity, main landing gear collapse, fuel tank rupture, wing breaks, tearing of tank lower surfaces, and engine pod scrubbing are discussed. In those accidents where the energy absorbing protective capability of the fuselage structure is expended and the airplane experiences major structural damage, trauma caused fatalities are also discussed. The dynamic performance of current seat/restraint systems are examined but it is concluded that the accident data does not adequately define the relationship between occupant response and the dynamic interaction with the seat, floor and fuselage structure.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85654 , NAS 1.15:85654
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Plastic behavior of circular plates under transverse impulse loadings of Gaussian distribution (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Plastic response of circular uniform plate to axisymmetric impulse load of Gaussian distribution
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TR-R-279
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Simulation of aircraft crash and its validation (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA Langley Research Center is engaged in an extensive research and development task aimed at providing the general aviation industry with reliable crashworthy airframe design technology. This paper describes the full-scale crash tests of general aviation airplanes being conducted to generate data on simulated crashes and to study the nonlinear dynamic behavior of aircraft structures. Analytical techniques under development for predicting nonlinear behavior of general airframe structures under crash-loading conditions are also described. Data are presented from the full-scale crash tests as well as comparison of analytical predictions with experimental results on some simplified structures.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 75-271 , American Institute of Aeronautics and Astronautics, Annual Meeting and Technical Display; Feb 24, 1975 - Feb 26, 1975; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Development of airframe design technology for crashworthiness. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the NASA portion of a joint FAA-NASA General Aviation Crashworthiness Program leading to the development of improved crashworthiness design technology. The objectives of the program are to develop analytical technology for predicting crashworthiness of structures, provide design improvements, and perform full-scale crash tests. The analytical techniques which are being developed both in-house and under contract are described, and typical results from these analytical programs are shown. In addition, the full-scale testing facility and test program are discussed.
    Keywords: AIRCRAFT
    Type: SAE PAPER 730319 , Business Aircraft Meeting; Apr 03, 1973 - Apr 06, 1973; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
  • 15
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    An improved analytical treatment of the denting of thin sheets by hail (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mathematical analysis of denting of thin aircraft skin by hail
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6102 , L-7343
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Ballistic limit of aluminum plates determined by an exploding foil gun technique (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exploding foil gun technique for simulated meteoroid protection
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-4259
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    NASA/FAA general aviation crash dynamics program - An update (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Work in progress in the NASA/FAA General Aviation Crash Dynamics Program for the development of technology for increased crash-worthiness and occupant survivability of general aviation aircraft is presented. Full-scale crash testing facilities and procedures are outlined, and a chronological summary of full-scale tests conducted and planned is presented. The Plastic and Large Deflection Analysis of Nonlinear Structures and Modified Seat Occupant Model for Light Aircraft computer programs which form part of the effort to predict nonlinear geometric and material behavior of sheet-stringer aircraft structures subjected to large deformations are described, and excellent agreement between simulations and experiments is noted. The development of structural concepts to attenuate the load transmitted to the passenger through the seats and subfloor structure is discussed, and an apparatus built to test emergency locator transmitters in a realistic environment is presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: International Society of Air Safety Investigators, Annual Seminar; Sept. 24-27, 1979; Montreal; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 18
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    Hydroxyapatite fiber reinforced poly(alpha-hydroxy ester) foams for bone regeneration (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A process has been developed to manufacture biodegradable composite foams of poly(DL-lactic-co-glycolic acid) (PLGA) and hydroxyapatite short fibers for use in bone regeneration. The processing technique allows the manufacture of three-dimensional foam scaffolds and involves the formation of a composite material consisting of a porogen material (either gelatin microspheres or salt particles) and hydroxyapatite short fibers embedded in a PLGA matrix. After the porogen is leached out, an open-cell composite foam remains which has a pore size and morphology defined by the porogen. By changing the weight fraction of the leachable component it was possible to produce composite foams with controlled porosities ranging from 0.47 +/- 0.02 to 0.85 +/- 0.01 (n = 3). Up to a polymer:fiber ratio of 7:6, short hydroxyapatite fibers served to reinforce low-porosity PLGA foams manufactured using gelatin microspheres as a porogen. Foams with a compressive yield strength up to 2.82 +/- 0.63 MPa (n = 3) and a porosity of 0.47 +/- 0.02 (n = 3) were manufactured using a polymer:fiber weight ratio of 7:6. In contrast, high-porosity composite foams (up to 0.81 +/- 0.02, n = 3) suitable for cell seeding were not reinforced by the introduction of increasing quantities of hydroxyapatite short fibers. We were therefore able to manufacture high-porosity foams which may be seeded with cells but which have minimal compressive yield strength, or low porosity foams with enhanced osteoconductivity and compressive yield strength.
    Keywords: Life Sciences (General)
    Type: Biomaterials (ISSN 0142-9612); 19; 21; 1935-43
    Format: text
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    NASA TECHNICAL REPORTS
  • 19
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    Designing for aircraft structural crashworthiness (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This report describes structural aviation crash dynamics research activities being conducted on general aviation aircraft and transport aircraft. The report includes experimental and analytical correlations of load-limiting subfloor and seat configurations tested dynamically in vertical drop tests and in a horizontal sled deceleration facility. Computer predictions using a finite-element nonlinear computer program, DYCAST, of the acceleration time-histories of these innovative seat and subfloor structures are presented. Proposed application of these computer techniques, and the nonlinear lumped mass computer program KRASH, to transport aircraft crash dynamics is discussed. A proposed FAA full-scale crash test of a fully instrumented radio controlled transport airplane is also described.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-0803 , International Air Transportation Conference; May 26, 1981 - May 28, 1981; Atlantic City, NJ; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 20
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    Light aircraft crash safety program (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA is embarked upon research and development tasks aimed at providing the general aviation industry with a reliable crashworthy airframe design technology. The goals of the NASA program are: reliable analytical techniques for predicting the nonlinear behavior of structures; significant design improvements of airframes; and simulated full-scale crash test data. The analytical tools will include both simplified procedures for estimating energy absorption characteristics and more complex computer programs for analysis of general airframe structures under crash loading conditions. The analytical techniques being developed both in-house and under contract are described, and a comparison of some analytical predictions with experimental results is shown.
    Keywords: AIRCRAFT
    Type: SAE PAPER 740353 , Business Aircraft Meeting; Apr 02, 1974 - Apr 05, 1974; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
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