Composites deforming a metal during strain hardening

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Unformatted text preview: efficiently. varied by control of the microstructure. In contrast, both the modulus and strength of plm QC2 rps MP1 579 v v strain hardening Hardening that occurs as a result of - or ferrimagnetic materials withcan be varied considerably. composites deforming a metal. During strain hardening, dislocations . are generated and the high dislocation density makes it technique for making ceramics in FIGURE 14.2–1 difficult for other dislocations to move. s are reacted with water to make a A schematic illustration of into a fiber when the reaction striations Parallel ridges that are seen on the surfacesthe idealized structure of rtain viscosity. The pure oxide is of many fatigue failures at high magnifications. In some concrete containing large gravel stones and small S each fatigue ntly driving off the remaining cases one striation forms forand (fine aggregate) cycle. sand particles in a matrix heating. Gravel (coarse aggregate) stress corrosion cracking (SCC) A type of corrosionof cement. The wide partiss used to join metals by sandthat results from the application of a tensile stress in cle size distribution aids in achieving a higher volume Cement (matrix) elting-point alloy (less than 450 C) conjunction with a specific material-electrolyte pair. fraction of the reinforcing ting to form a good bond. phase. stress intensity parameter K The parameter that The temperature at which a liquid characterizes the stresses and strains at a given location ng equilibrium cooling conditions. ahead of a crack. It is a valid parameter for situations in ion species that is dissolved in a which plastic deformation ahead of the crack tip is nonexistent or very limited. ent A high-temperature heat stress relaxation Reduction in stress that occurs when take into solution the soluble a component is subjected to a constant value of strain. | Typically polymersMenu metals at relatively high | e-Text Main and | Textbook Table of Contents temperatures exhibit stress relaxation. ecies for a solute. pg580 [V] G2 7-27060 / IRWIN / Schaffer 580 Part III iq 12.01.98 plm QC2 rps MP1 Properties FIGURE 14.2–2 A picture of the AV-88 Harrier aircraft, in which composites account for 28% of structural weight. (Source: Journal of Metals 43, no. 12 (December 1991), p. 16, a publication of the Minerals, Metals & Materials Society, Warrendale, PA.) Aft flaps • Outboard (graphite) • Inboard (graphite/fiberglass) FIGURE 14.2–3 List of composite parts in the main structure of the Boeing 757-200 aircraft. (Source: Boeing Commercial Airplane Company.) Flap support fairings • Fwd segment (graphite/Kevlar + non-woven Kevlar mat) • Aft segment (graphite/fiberglass) Rudder (graphite) Tip fairings (fiberglass) Fixed trailing edge panels (graphite/Kevlar + non-woven Kevlar mat) Elevators (graphite) Ailerons (graphite) Engine strut fairings (Kevlar/fiberglass) Auxiliary power inlet (graphite) Environmental control system ducts (Kevlar) Fixed trailing edge panels (graphite/Kevlar + non-woven Kevlar mat) Spoilers (graphite) Nose landing gear doors (graphite) Cowl components (graphite) Fixed trailing edge panels upper (graphite/fiberglass) lower (graphite/Kevlar + non-woven Kevlar mat) Wing leading edge lower panels (Kevlar/fiberglass) Wing-to-body fairings (graphite/Kevlar/fiberglass) and (graphite/Kevlar + • Body main landing gear doors (graphite) non-woven Kevlar mat) • Trun...
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This note was uploaded on 02/25/2013 for the course PHYS 2202 taught by Professor Sowell during the Spring '10 term at Georgia Institute of Technology.

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