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aircraft landing gears
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Book: Thermal Spray Technology
Series: ASM Handbook
Volume: 5A
Publisher: ASM International
Published: 01 August 2013
DOI: 10.31399/asm.hb.v05a.a0005739
EISBN: 978-1-62708-171-9
... metals in airframe structures. This article summarizes the results of materials and component testing. It also presents a cost/benefit analysis of HVOF WC/17Co and WC/10Co4Cr coatings on aircraft landing gear components. aircraft landing gears corrosion cost assessment fatigue hard chrome...
Abstract
High-velocity oxyfuel (HVOF)-applied thermal spray coatings are viable candidates for replacement of hard chrome in numerous applications. HVOF thermal spraying can be used to deposit both metal alloy and cermet coatings that are dense and highly adherent to all the commonly used base metals in airframe structures. This article summarizes the results of materials and component testing. It also presents a cost/benefit analysis of HVOF WC/17Co and WC/10Co4Cr coatings on aircraft landing gear components.
Image
Published: 01 January 1987
Fig. 1077 Portion of a broken aircraft landing-gear actuator beam of Al alloy 7079-T6, showing stress-corrosion fractures (at arrow). 0.17×
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Published: 01 January 1987
Fig. 413 Surface of a low-cycle fatigue fracture in an aircraft landing-gear cylinder made of AISI 4340 steel that was hardened and tempered to a tensile strength of 1793 to 1931 MPa (260 to 280 ksi). The cylinder was stressed in the laboratory to its tensile strength four times and broke
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Image
Published: 01 December 1998
Fig. 3 Aluminum alloy 7079-T6 aircraft landing-gear actuator beam fractured because of stress-corrosion cracking (a) Portion of a broken aircraft landing-gear actuator beam of aluminum alloy 7079-T6, showing stress-corrosion fractures (at arrow). See also (b) to (f). Photograph. 1 6
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Image
Published: 01 January 1993
Fig. 17 Oxyacetylene welding of aircraft landing gear support. Use of OAW reduced HAZ hardness and eliminated need for postweld tempering. Measurements shown in schematic are in inches. Welding rod Type RG60 Diameter, mm (in.) 2.4 ( 3 32 ) Torch type Injector Tip
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Series: ASM Handbook
Volume: 6
Publisher: ASM International
Published: 01 January 1993
DOI: 10.31399/asm.hb.v06.a0001366
EISBN: 978-1-62708-173-3
...-welding applications, including chain links, transmission bands, automotive flywheel ring gears, aircraft landing gear, band-saw blades, and crankshaft counter weights. It describes the components of a typical flash-welding machine. The article provides information on the electrical controls of flash...
Abstract
Flash welding (FW) is a resistance welding process in which a butt joint weld is produced by a flashing action and by the application of pressure. Flash welding is used to join metallic parts that have similar cross sections in terms of size and shape. This article discusses flash-welding applications, including chain links, transmission bands, automotive flywheel ring gears, aircraft landing gear, band-saw blades, and crankshaft counter weights. It describes the components of a typical flash-welding machine. The article provides information on the electrical controls of flash-welding equipment. These include programmable controllers, welding current controllers, and either motor or servo-valve controllers.
Image
Published: 01 January 1987
Fig. 1070 TEM p-c replica of the surface of an intergranular fracture in an aircraft landing-gear component of forged aluminum alloy 7075-T6 that fractured as the result of stress-corrosion cracking. Note the secondary cracks between the grains. 1000×
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Image
Published: 01 January 1987
Fig. 112 Fatigue fracture through a region of unfavorable grain flow and large inclusions in an aircraft landing-gear axle forged from AISI 4340 steel. Several fatigue crack origins were found in region A. Numerous small discontinuous marks nearly perpendicular to the direction of crack
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Image
Published: 01 January 1987
Fig. 968 Pieces of the hub of a forged aircraft main-landing-gear wheel half, which broke by fatigue. The material is aluminum alloy 2014-T6. Tensile specimens from elsewhere in the wheel had tensile strength of 493.7 MPa (71.6 ksi) and 8.9% elongation in the transverse direction, and tensile
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Image
Published: 01 January 1987
Fig. 1004 An aluminum alloy 7075-T736 aircraft main landing gear forging, similar to that described in Fig. 1002 and 1003 , which was shot peened on its inner-diameter surface to enhance fatigue resistance. The shot-peened part withstood cycles far beyond the number required for acceptance
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Image
Published: 01 January 1997
Image
Published: 01 June 2024
Fig. 26 (a) Hub of a forged 2016-T6 aircraft main landing gear wheel half, which failed in fatigue. (b) Fatigue crack origin of the hub. The fatigue crack exhibits a so-called thumbnail shape, and beach marks are also visible. Source: Ref 4
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Image
Published: 01 June 2024
Fig. 28 Fatigue fracture surface of a 2014-T6 forged aircraft main landing gear wheel half. The origin is indicated by an arrow. The fatigue crack exhibits a so-called thumbnail shape, and beach marks are also visible. Original magnification: 1.8×. Source: Ref 4
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Published: 01 June 2024
Fig. 29 Fatigue fracture surface of a 7075-T736 aircraft main landing gear forging that was shot peened at the inner-diameter surface to enhance fatigue resistance. Fatigue initiated at a dross inclusion (black line in the center of the nearly circular fatigue crack initiation area), well
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Book Chapter
Book: Fractography
Series: ASM Handbook Archive
Volume: 12
Publisher: ASM International
Published: 01 January 1987
DOI: 10.31399/asm.hb.v12.a0000621
EISBN: 978-1-62708-181-8
.... 966 : 83×. Fig. 967 : 108× Fig. 966 Fig. 967 Fig. 968 Pieces of the hub of a forged aircraft main-landing-gear wheel half, which broke by fatigue. The material is aluminum alloy 2014-T6. Tensile specimens from elsewhere in the wheel had tensile strength of 493.7 MPa (71.6 ksi...
Abstract
This article is an atlas of fractographs that helps in understanding the causes and mechanisms of fracture of wrought aluminum alloys and in identifying and interpreting the morphology of fracture surfaces. The fractographs illustrate the corrosion-fatigue fracture, fatigue striations, tension-overload fracture surface, ductile fracture, cone-shaped fracture surface, intergranular crack propagation, transgranular crack propagation, stress-corrosion cracking, hydrogen damage, and grain-boundary separation of these alloys. Fractographs are also provided for a forged aircraft main-landing gear wheel and actuator beam, an aircraft wing spar, a fractured aircraft propeller blade, shot peened fillet, an aircraft lower-bulkhead cap, and clevis-attachment lugs.
Book: Fractography
Series: ASM Handbook Archive
Volume: 12
Publisher: ASM International
Published: 01 January 1987
DOI: 10.31399/asm.hb.v12.a0000612
EISBN: 978-1-62708-181-8
... of aircraft main landing gears, and aircraft engine mount beams. aircraft main landing gear fatigue fracture fractograph high-pressure compressors intergranular fracture intergranular stress-corrosion cracking precipitation-hardening stainless steel tension-overload fracture Fig. 720...
Abstract
This article is an atlas of fractographs that helps in understanding the causes and mechanisms of fracture of precipitation-hardening stainless steels and in identifying and interpreting the morphology of fracture surfaces. The fractographs illustrate the cup-and-cone tension-overload fracture, low-cycle and high-cycle fatigue fracture, fracture surface, brittle intergranular fracture, hydrogen embrittlement, and intergranular stress-corrosion cracking of stainless steel components of these steels. The components include high-pressure compressor parts, springs, deflector yokes of aircraft main landing gears, and aircraft engine mount beams.
Book Chapter
Series: ASM Handbook
Volume: 6
Publisher: ASM International
Published: 01 January 1993
DOI: 10.31399/asm.hb.v06.a0001377
EISBN: 978-1-62708-173-3
... by forge welding include high-alloy steels, nickel-base alloys, cobalt-base alloys, aluminum alloys, titanium alloys, and tungsten. Applications of this process include welding rods, bars, tubes, rails, aircraft landing gear, chains, and cans. The forge welding process is competitive with flash welding...
Series: ASM Handbook
Volume: 20
Publisher: ASM International
Published: 01 January 1997
DOI: 10.31399/asm.hb.v20.a0002442
EISBN: 978-1-62708-194-8
... the mechanism performance due to changes in mass properties of the part. This in turn may require another iteration in the stress analysis. However, loads are only part of the need for prediction of the behavior of a mechanism. Example 2: Simulation to Predict Loads in Aircraft Landing Gear The first...
Abstract
This article presents an overview of the use of mechanism analysis (kinematics and dynamics) and simulation. It provides indications of the directions in which mechanism simulation is growing and how it is integrated in the evolving computer aided design and computer aided engineering (CAD/CAE) fields. Mechanism simulation is best used as part of a concurrent CAD/CAE approach to design. The article discusses the state, evolution, and direction of application for these techniques in a variety of fields.
Image
Published: 01 January 1987
Fig. 1074 Side view of a piece of fractured aluminum alloy 7079-T6 bogie beam of an aircraft main landing gear. The fracture surface is at top, in profile. The very straight edge at lower right is a saw cut that was made to separate the fracture area from the remainder of the beam
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Image
Published: 01 January 1987
Fig. 499 Fatigue fracture in an AISI 6150 steel spring leg of an aircraft main landing gear, heat treated to a minimum tensile strength of 1550 MPa (225 ksi) and a hardness of 49 HRC. Visual inspection of the fracture surfaces showed that the fatigue crack originated at the location marked
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