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Helicopters
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Book: Composites
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003440
EISBN: 978-1-62708-195-5
Abstract
A test plan specifies material properties to be evaluated, selects test methods, eliminates options offered by standard test methods by selecting specific specimen and test configurations, and defines success criteria. This article discusses various testing objectives that affect the execution of testing programs. The testing objectives include development of test matrices, testing standards, specimen preparation, environmental conditioning, instrumentation and data acquisition, failure modes, and data interpretation and recording.
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Published: 01 January 1987
Fig. 929 A broken extension-housing yoke, part of a helicopter tail-rotor drive assembly, that fractured by fatigue in service. The fracture occurred through the left and right lugs at the points of attachment to the tail boom. The yoke was cast from aluminum alloy 356.0 and heat treated
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Published: 01 January 1987
Fig. 455 Matching fracture surfaces of an AISI 4340 steel helicopter bolt that was broken by notch bending. The fine markings are fibrous tear ridges. Note the very large shear lips. 2.5× (Fig. 455 in printed volume)
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Published: 01 January 2002
Fig. 6 Fatigue cracking of a helicopter tail rotor blade. (a) Scanning electron micrograph of the blade showing lead wool ballast in contact with the 2014-T652 aluminum spar bore cavity wall at the failure origin ∼13×. (b) Greater magnification (∼63×) in this same area shows the multiple pits
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Published: 01 January 2005
Fig. 1 Helicopter transmission casing forged from magnesium alloy ZK60A shown in the (a) as-forged and (b) forged and finish machined conditions
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Published: 01 January 2005
Fig. 22 Helicopter ring gear, shown as (a) a conventional forging, and (b) a ring-rolled forging. Machined contours of the gear are shown in phantom on the sectional views. Dimensions given in inches
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in Microbiologically Influenced Corrosion in Military Environments
> Corrosion: Environments and Industries
Published: 01 January 2006
Fig. 1 Interiors of H-53 helicopter showing fungal growth on polyurethane painted surfaces. (a) Overview. (b) Detail of cable penetration
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Published: 01 December 2008
Fig. 4 Main transmission housing for a heavy lift helicopter that was sand cast in WE43B magnesium alloy having a T6 temper. Courtesy of Fansteel Wellman Dynamics. Casting weight = 206 lb (93 kg).
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Published: 01 August 2013
Fig. 19 Single-part production intensive quenching system for processing helicopter gears up to 200 by 480 mm (8 by 19 in.) diameter. Source: Ref 25
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in Induction Hardening for the Aeronautic and Aerospace Industry
> Induction Heating and Heat Treatment
Published: 09 June 2014
Fig. 6 Example of transmission parts in the aerospace industry (helicopter transmission). Source: Ref 7
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Published: 31 December 2017
Fig. 7 Ferrograms from AH-1S helicopter assemblies with (a) severe wear and (b) normal wear. The operative recommendation will be immediate disassembly or next sampling after additional 25 h of flight, respectively. Source: Ref 54 . Reprinted with permission from Springer
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Published: 01 August 2018
Fig. 31 (a) Computed tomography (CT) image across a sample helicopter tail rotor blade showing outer fiberglass airfoil and center composite spar. (b) Planar reformation through the composite spar from a series of CT slices. The dark vertical lines are normal cloth layup boundaries, while
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Published: 15 January 2021
Fig. 6 Fatigue cracking of a helicopter tail rotor blade. (a) Scanning electron micrograph of the blade showing lead wool ballast in contact with the 2014-T652 aluminum spar bore cavity wall at the failure origin. Original magnification: ~13×. (b) Greater magnification (~63×) in this same area
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Published: 30 November 2018
Fig. 1 Handling of a sand cast helicopter gearbox. Courtesy of Avio Aero
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Published: 01 January 2001
Fig. 14 Bell Helicopter Model 412 tail boom made from BMI composite (Cycom 5250-4)
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Published: 01 January 2001
Fig. 7 Testing of helicopter composite rotor hub flexbeams in tension and bending. (a) Full beam and one-sixth size beam. (b) Drawing of one-sixth size section in test fixture. (c) Flexbeam specimen in the tension and bending test load frame
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Published: 01 January 2001
Fig. 4 EC-120 helicopter rotor application. (a) Rotor blade sleeve. The part is made of forged 2009/SiC/15p discontinuously reinforced aluminum (DRA). The scale below the part is 30 cm long. (b) Rotor assembly showing the DRA blade sleeves. Photos courtesy of DWA Aluminum Composites, Inc.
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Published: 15 June 2020
Fig. 12 Laser-sintered Bell Helicopter parts used to reduce part count, assembly cost, and weight. The line indicates the black powder bed fusion parts. Courtesy of EOS
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Published: 01 August 2018
Fig. 2 Typical applications of adhesive-bonded joints in aircraft. (a) Helicopter components. (b) Lockheed C-5A transport plane, with various types of honeycomb sandwich structures totaling 2230 m 2 (24,000 ft 2 ) in area
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