Design, Fabrication, and Testing of a Composite Main Landing Gear Retracting Beam PDF Download
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Author: Kevin A. McAfee
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 14
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Book Description
Author: Kevin A. McAfee
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 14
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 282
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Book Description
The objective of this program was to explore the utility of boron/ epoxy composite materials in aircraft landing gear construction. The design, fabrication and test of a boron composite material landing gear assembly interchangeable in both geometry and performance with the main landing gear of A.37B aircraft. This report describes the fabrication and processing of boron composites. The processing procedures associated with the design trial specimens and prototype components designed during this program are described.
Author: Sotiris Kellas
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720460602
Category :
Languages : en
Pages : 28
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Book Description
A lightweight energy-absorbing keel-beam concept was developed and retrofitted in a general aviation type aircraft to improve crashworthiness performance. The energy-absorbing beam consisted of a foam-filled cellular structure with glass fiber and hybrid glass/kevlar cell walls. Design, analysis, fabrication and testing of the keel beams prior to installation and subsequent full-scale crash testing of the aircraft are described. Factors such as material and fabrication constraints, damage tolerance, crush stress/strain response, seat-rail loading, and post crush integrity, which influenced the course of the design process are also presented. A theory similar to the one often used for ductile metal box structures was employed with appropriate modifications to estimate the sustained crush loads for the beams. This, analytical tool, coupled with dynamic finite element simulation using MSC.Dytran were the prime design and analysis tools. The validity of the theory as a reliable design tool was examined against test data from static crush tests of beam sections while the overall performance of the energy-absorbing subfloor was assessed through dynamic testing of 24 in long subfloor assemblies.Kellas, Sotiris and Knight, Norman F., Jr.Langley Research CenterGENERAL AVIATION AIRCRAFT; COMPOSITE STRUCTURES; KEELS; FOAMS; GLASS FIBERS; KEVLAR (TRADEMARK); CRASHWORTHINESS; FULL SCALE TESTS; STRESS-STRAIN RELATIONSHIPS; FINITE ELEMENT METHOD
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 237
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Book Description
The objective of this program was to explore the utility of boron composite materials in aircraft landing gear construction. The contract work statement required the design, fabrication and test of a boron composite material landing gear assembly interchangeable in both geometry and performance with the main landing gear of the A-37B aircraft. The use of Borsic-aluminum and boron epoxy materials was explored. Hardware designs were evolved for both materials. One full size landing gear assembly was tested. This assembly was composed of a boron epoxy outer cylinder, inner cylinder and side brace. All attachment fittings were metallic. The assembly was tested for hydraulic pressure containment and static structural strength.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 700
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 984
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 132
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Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Author:
Publisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 680
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Book Description
Author: Myron J. Bieber
Publisher:
ISBN:
Category :
Languages : en
Pages : 154
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Book Description
This report summarizes work performed to design, fabricate and test a graphite epoxy composite material upper drag brace suitable for direct replacement of the current titanium upper drag brace for the F-15 aircraft landing gear assembly. Design, fabrication, test procedures, test results, and failure analysis are presented in detail. The composite material brace failed at less than design load. The program established, at the present time, that drag braces and similar landing gear hardware can not be satisfactorily fabricated from graphite epoxy material for use as a direct replacement of existing metallic hardware in some applications. The volume and shape of available space in these direct replacement applications does not normally allow the use of optimum graphite epoxy material design and fabrication techniques. However, as demonstrated by the successful development of a graphite epoxy side brace suitable for direct replacement of existing metallic hardware on the A-37B aircraft, weight and cost saving applications to current aircraft are feasible. Therefore, each potential application must be individually evaluated. Work is required to improve analytical, fabrication and nondestructive inspection techniques for graphite epoxy materials. It can be reasonably expected that current and future efforts by the Air Force, industry and the educational community, aimed at these improvements, will increase the profitable application of graphite epoxy material to landing gear hardware. (Author).
