1-20 of 55 Search Results for

wing spars

Follow your search
Access your saved searches in your account

Would you like to receive an alert when new items match your search?
Close Modal
Sort by
Series: ASM Handbook
Volume: 12
Publisher: ASM International
Published: 01 January 1987
DOI: 10.31399/asm.hb.v12.a0000621
EISBN: 978-1-62708-181-8
...-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. aircraft components corrosion fatigue fatigue crack propagation fatigue cracks fatigue fracture fatigue striations...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003467
EISBN: 978-1-62708-195-5
... or incomplete sanding of the paddles prior to the bond operation. Inadequate sanding resulted in a contaminated surface having a slick, glossy finish, which is unsuitable for subsequent bonding of the paddle to the sleeve. A wing spar on a small aircraft failed prematurely; the aircraft reportedly had some...
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006741
EISBN: 978-1-62708-210-5
...Abstract Abstract The aluminum alloy 7099 is a Kaiser aluminum high-strength Al-Mg-Zn-Cu alloy with zirconium that offers a less quench-sensitive alloy for properties in thicker sections for airframe structures such as wing ribs, spars, and skins, as well as fuselage frames and floor beams...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003463
EISBN: 978-1-62708-195-5
... fatigue test of graphite-epoxy specimen Fig. 9 Edge replica of graphite-epoxy specimen Fig. 8 Mating fracture surfaces of an adhesively bonded wing skin and wing spar. ∼0.2× Abstract Abstract Mechanical and environmental loadings cause a variety of failure modes in composites...
Series: ASM Handbook
Volume: 14A
Publisher: ASM International
Published: 01 January 2005
DOI: 10.31399/asm.hb.v14a.a0004034
EISBN: 978-1-62708-185-6
... on the surfaces of a closed-die forging Fig. 4 Forging for a nozzle boss fitting used in a rocket engine. As shown, draft angles are measured from the direction of the ram, which in this instance is vertical. Dimensions given in inches. Fig. 5 Wing spar forging with a broken parting line...
Series: ASM Handbook
Volume: 14A
Publisher: ASM International
Published: 01 January 2005
DOI: 10.31399/asm.hb.v14a.a0004000
EISBN: 978-1-62708-185-6
... Orbital forging 150–315 300–600 Spin forging 95–315 200–600 Roll forging 95–260 200–500 Hydraulic presses 315–480 600–900 Typical mechanical properties of wing spar forging obtained with three distinct forging processes Table 3 Typical mechanical properties of wing spar forging...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003457
EISBN: 978-1-62708-195-5
... Administration , May 1985 20. Harvill W.E. , Duhig J.J. , and Spencer B.R. , “Program for Establishing Long-Time Flight Service Performance of Composite Materials in Center Wing Structure of C-130 Aircraft. Phase II–Detailed Design,” NASA CR-112272, National Aeronautics and Space...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003477
EISBN: 978-1-62708-195-5
... and 0.16 in.). They are laminated by automated tape laying. During manufacturing, the wing skins are cured first. Afterwards, the solid laminate spars are cured and simultaneously bonded to the already cured lower skin in a second autoclave cycle (co-bonding process). On the Typhoon (Eurofighter...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003455
EISBN: 978-1-62708-195-5
... was used only to carry in-plane loads. Metal fittings were used for all triaxially loaded components—the landing gear, engine mounts, control surface mounting brackets, wing-to-fuselage junction, and so on. Such a policy of avoiding triaxial or interlaminar loads on composite structures makes even more...
Book: Casting
Series: ASM Handbook
Volume: 15
Publisher: ASM International
Published: 01 December 2008
DOI: 10.31399/asm.hb.v15.a0009021
EISBN: 978-1-62708-187-0
... the center, each section tapers in steps to the extreme ends. Fig. 12 A well-designed steel casting in which all sections are accessible to properly located risers Fig. 13 A box-shaped wing spar casting in which heavy sections can be easily risered from the top, the two sides, and the two...
Series: ASM Handbook
Volume: 14B
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v14b.a0005122
EISBN: 978-1-62708-186-3
.... This equipment is primarily used for forming large sheets, such as fuselage skins and the leading edges of airplane wings. Large, cumbersome extrusions, such as wing spars, can be formed by changing or adapting the jaws. Fig. 14 Transverse stretch-forming machine having both movable and tiltable die table...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002416
EISBN: 978-1-62708-193-1
... Fig. 1 Sketches of discrete source damage for fuselage Fig. 2 Tension strengths for impact damage, open holes, and cuts Fig. 3 Compressive strength versus defect size for AS4/3501-6 wing skin laminate Fig. 4 Effect of manufactured wrinkle on compressive strength...
Series: ASM Handbook
Volume: 13C
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v13c.a0004169
EISBN: 978-1-62708-184-9
... and drain valve design. Drain locations are indicated as closed circles in the lower plan view Fig. 13 Wing front spar with corrosion sites. Sealant locations in acceptable design Fig. 14 Corrosion between wing front spar lower chord and web of 747 Fig. 18 Loss of paint...
Series: ASM Handbook
Volume: 14A
Publisher: ASM International
Published: 01 January 2005
DOI: 10.31399/asm.hb.v14a.a0004038
EISBN: 978-1-62708-185-6
.... 21 Conventional aluminum alloy forging for a wing front spar terminal fitting, with a dorsal rib that was preblocked as a web and then blocked and finished as a rib. Dimensions given in inches Fig. 22 Conventional aluminum alloy wing fold rib forgings of original and revised designs...
Book Chapter

Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003364
EISBN: 978-1-62708-195-5
... tolerances provided by the RTM process decreased by half the number of reinforcement parts needed for installing the spars in the wings. The F-22 5250-4RTM applications demonstrate the capability of manufacturing complex parts. One factor that limits wider BMI use is that BMIs require higher cure...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002393
EISBN: 978-1-62708-193-1
... of the CAA had been substantiated by the loss of a Hawker Siddley 748 in Argentina, one of the first aircraft designed by Hawker Siddley Manchester Division on fail-safe principles. Wing bending material, instead of being concentrated in front and rear spar caps (as had been the case with the Manchester...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003425
EISBN: 978-1-62708-195-5
... Fig. 12 Co-consolidated cockpit floor Fig. 13 Schematic for ultrasonic welder and multiunit weld machine. Source: Ref 30 , 31 Fig. 14 Schematic for resistance weld of rib to spar Fig. 15 Resistance welding wing substructure using copper foil and amorphous...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003411
EISBN: 978-1-62708-195-5
... Fig. 1 Contour skin lay-up using a gantry-type automated tape layer Fig. 2 Automated tape lay-up of a contour skin showing the integrated contour tooling Fig. 8 Contour tape lay-up on an F-22 wing skin Fig. 3 Tape head for an automated tape layer Fig. 4...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003428
EISBN: 978-1-62708-195-5
... on the material thickness of the skin and frame, thicker parts have higher allowed tip pressure. This sealing method is generally used in conjunction with fay and fillet seal described above. A typical wing tank without a bladder would use fay seal between the skin and the spar caps, then a fillet seal...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003512
EISBN: 978-1-62708-180-1
... spar mechanically induced during the drilling of the hole. The failure analyst was able to identify the location of the damage and extent of fatigue crack growth, which was used to establish inspection intervals ( Ref 23 ) Fig. 6 Fractographic evaluation for life assessment purposes. (a) Wing...