MIL-S-18729C-BASE(alloy4130)_图文_百度文库
两大类热门资源免费畅读
续费一年阅读会员，立省24元！
MIL-S-18729C-BASE(alloy4130)
&&美军4130合金规范
阅读已结束，下载文档到电脑
想免费下载本文？
定制HR最喜欢的简历
下载文档到电脑，方便使用
还剩5页未读，继续阅读
定制HR最喜欢的简历
你可能喜欢From Wikipedia, the free encyclopedia
Aluminium alloy bicycle wheel. 1960s
Aluminium alloys (or aluminum alloys; see ) are
(Al) is the predominant metal. The typical alloying elements are , , , ,
and . There are two principal classifications, namely
alloys and wrought alloys, both of which are further subdivided into the categories
and non-heat-treatable. About 85% of aluminium is used for wrought products, for example rolled plate, foils and . Cast aluminium alloys yield cost-effective products due to the low melting point, although they generally have lower
than wrought alloys. The most important cast aluminium alloy system is , where the high levels of silicon (4.0–13%) contribute to give good casting characteristics. Aluminium alloys are widely used in engineering structures and components where light weight or corrosion resistance is required.
Alloys composed mostly of aluminium have been very important in
since the introduction of metal-skinned aircraft. Aluminium-magnesium alloys are both lighter than other aluminium alloys and much less flammable than alloys that contain a very high percentage of magnesium.
Aluminium alloy surfaces will develop a white, protective layer of
if left unprotected by anodizing and/or correct painting procedures. In a wet environment,
can occur when an aluminium alloy is placed in electrical contact with other metals with more positive corrosion potentials than aluminium, and an electrolyte is present that allows ion exchange. Referred to as dissimilar-metal corrosion, this process can occur as exfoliation or as intergranular corrosion. Aluminium alloys can be improperly heat treated. This causes internal element separation, and the metal then corrodes from the inside out.[]
Aluminium alloy compositions are registered with . Many organizations publish more specific standards for the manufacture of aluminium alloy, including the
standards organization, specifically its aerospace standards subgroups, and .
Aluminium alloys with a wide range of properties are used in engineering structures. Alloy systems are classified by a number system () or by names indicating their main alloying constituents ( and ). Selecting the right alloy for a given application entails considerations of its , , , formability, workability, , and
resistance, to name a few. A brief historical overview of alloys and manufacturing technologies is given in Ref. Aluminium alloys are used extensively in aircraft due to their high . On the other hand, pure aluminium metal is much too soft for such uses, and it does not have the high tensile strength that is needed for airplanes and .
Aluminium alloys typically have an
of about 70 , which is about one-third of the elastic modulus of most kinds of steel and . Therefore, for a given load, a component or unit made of an aluminium alloy will experience a greater deformation in the elastic regime than a steel part of identical size and shape. Though there are aluminium alloys with somewhat-higher tensile strengths than the commonly used kinds of steel, simply replacing a steel part with an aluminium alloy might lead to problems.
With completely new metal products, the design choices are often governed by the choice of manufacturing technology. Extrusions are particularly important in this regard, owing to the ease with which aluminium alloys, particularly the Al–Mg–Si series, can be extruded to form complex profiles.
In general, stiffer and lighter designs can be achieved with Aluminium alloy than is feasible with steels. For instance, consider the bending of a thin-walled tube: the
is inversely related to the stress in the tube wall, i.e. stresses are lower for larger values. The second moment of area is proportional to the cube of the radius times the wall thickness, thus increasing the radius (and weight) by 26% will lead to a halving of the wall stress. For this reason, bicycle frames made of aluminium alloys make use of larger tube diameters than steel or titanium in order to yield the desired stiffness and strength. In automotive engineering, cars made of aluminium alloys employ
made of extruded profiles to ensure rigidity. This represents a radical change from the common approach for current steel car design, which depend on the body shells for stiffness, known as
Aluminium alloys are widely used in automotive engines, particularly in
due to the weight savings that are possible. Since aluminium alloys are susceptible to warping at elevated temperatures, the cooling system of such engines is critical. Manufacturing techniques and metallurgical advancements have also been instrumental for the successful application in automotive engines. In the 1960s, the aluminium
earned a reputation for failure and stripping of , which is not seen in current aluminium cylinder heads.
An important structural limitation of aluminium alloys is their lower
strength compared to steel. In controlled laboratory conditions, steels display a , which is the stress amplitude below which no failures occur – the metal does not continue to weaken with extended stress cycles. Aluminium alloys do not have this lower fatigue limit and will continue to weaken with continued stress cycles. Aluminium alloys are therefore sparsely used in parts that require high fatigue strength in the high cycle regime (more than 107 stress cycles).
Often, the metal's sensitivity to heat must also be considered. Even a relatively routine workshop procedure involving heating is complicated by the fact that aluminium, unlike steel, will melt without first glowing red. Forming operations where a blow torch is used can reverse or remove heat treating, therefore is not advised whatsoever. No visual signs reveal how the material is internally damaged. Much like welding heat treated, high strength link chain, all strength is now lost by heat of the torch. The chain is dangerous and must be discarded.
Aluminium is subject to internal stresses and strains. Sometimes years later, as is the tendency of improperly welded aluminium bicycle frames to gradually twist out of alignment from the stresses of the welding process. Thus, the aerospace industry avoids heat altogether by joining parts with rivets of like metal composition, other fasteners, or adhesives.
Stresses in overheated aluminium can be relieved by heat-treating the parts in an oven and gradually cooling it—in effect
the stresses. Yet these parts may still become distorted, so that heat-treating of welded bicycle frames, for instance, can result in a significant fraction becoming misaligned. If the misalignment is not too severe, the cooled parts may be bent into alignment. Of course, if the frame is properly designed for rigidity (see above), that bending will require enormous force.
Aluminium's intolerance to high temperatures has not precluded even for use in constructing combustion chambers where gases can reach 3500 K. The
upper stage engine used a regeneratively cooled aluminium design for some parts of the nozzle, including the thermally cr in fact the extremely high thermal conductivity of aluminium prevented the throat from reaching the melting point even under massive heat flux, resulting in a reliable, lightweight component.
Because of its high conductivity and relatively low price compared with copper in the 1960s, aluminium was introduced at that time for household electrical wiring in North America, even though many fixtures had not been designed to accept aluminium wire. But the new use brought some problems:
The greater
of aluminium causes the wire to expand and contract relative to the dissimilar metal
connection, eventually loosening the connection.
Pure aluminium has a tendency to
under steady sustained pressure (to a greater degree as the temperature rises), again loosening the connection.
from the dissimilar metals increases the electrical resistance of the connection.
All of this resulted in overheated and loose connections, and this in turn resulted in some fires. Builders then became wary of using the wire, and many jurisdictions outlawed its use in very small sizes, in new construction. Yet newer fixtures eventually were introduced with connections designed to avoid loosening and overheating. At first they were marked "Al/Cu", but they now bear a "CO/ALR" coding.
Another way to forestall the heating problem is to
the aluminium wire to a short "" of copper wire. A properly done high-pressure crimp by the proper tool is tight enough to reduce any thermal expansion of the aluminium. Today, new alloys, designs, and methods are used for aluminium wiring in combination with aluminium terminations.
Wrought and cast aluminium alloys use different identification systems. Wrought aluminium is identified with a four digit number which identifies the alloying elements.
Cast aluminium alloys use a four to five digit number with a decimal point. The digit in the hundreds place indicates the alloying elements, while the digit after the decimal point indicates the form (cast shape or ingot).
The temper designation follows the cast or wrought designation number with a dash, a letter, and potentially a one to three digit number, e.g. 6061-T6. The definitions for the tempers are:
As fabricated
Strain hardened (cold worked) with or without thermal treatment
Strain hardened without thermal treatment
Strain hardened and partially annealed
Strain hardened and stabilized by low temperature heating
Second digit 
A second digit denotes the degree of hardness
-HX2 = 1/4 hard
-HX4 = 1/2 hard
-HX6 = 3/4 hard
-HX8 = full hard
-HX9 = extra hard
Full soft (annealed)
Heat treated to produce stable tempers
Cooled from hot working and naturally aged (at room temperature)
Cooled from hot working, cold-worked, and naturally aged
Solution heat treated and cold worked
Solution heat treated and naturally aged
Cooled from hot working and artificially aged (at elevated temperature)
-T51 
Stress relieved by stretching
-T510 
No further straightening after stretching
-T511 
Minor straightening after stretching
-T52 
Stress relieved by thermal treatment
Solution heat treated and artificially aged
Solution heat treated and stabilized
Solution heat treated, cold worked, and artificially aged
Solution heat treated, artificially aged, and cold worked
-T10 
Cooled from hot working, cold-worked, and artificially aged
Solution heat treated only
Note: -W is a relatively soft intermediary designation that applies after heat treat and before aging is completed. The -W condition can be extended at extremely low temperatures but not indefinitely and depending on the material will typically last no longer than 15 minutes at ambient temperatures.
The International Alloy Designation System is the most widely accepted naming scheme for . Each alloy is given a four-digit number, where the first digit indicates the major alloying elements, the second — if different from 0 — indicates a variation of the alloy, and the third and fourth digits identify the specific alloy in the series. For example, in alloy 3105, the number 3 indicates the alloy is in the manganese series, 1 indicates the first modification of alloy 3005, and finally 05 identifies it in the 3000 series.
1000 series are essentially pure aluminium with a minimum 99% aluminium content by weight and can be .
2000 series are alloyed with copper, can be
to strengths comparable to steel. Formerly referred to as , they were once the most common aerospace alloys, but were susceptible to
and are increasingly replaced by 7000 series in new designs.
3000 series are alloyed with manganese, and can be .
4000 series are alloyed with silicon. Variations of Aluminum-silicon alloys intended for casting (and therefore not included in 4000 series) are also known as .
5000 series are alloyed with magnesium, and offer superb corrosion resistance, making them suitable for marine applications. Also,
has the highest strength of not heat-treated alloys.
6000 series are alloyed with magnesium and silicon. They are easy to machine, are , and can be precipitation hardened, but not to the high strengths that 2000 and 7000 can reach.
is one of the most commonly used general-purpose aluminium alloys.
7000 series are alloyed with zinc, and can be
to the highest strengths of any aluminium alloy (ultimate tensile strength up to 700 MPa for the ).
8000 series are alloyed with other elements which are not covered by other series.
are an example
1000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Drawn tube, chemical equipment
Thick-wall drawn tube
Universal,
Sheet, plate, foil
2000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Universal, aerospace
Sheet, plate
0.7; 0.5; 0.6;
Aerospace,
Aerospace, cryogenics
Aerospace, cryogenics
aerospace, , and the
second stage launch vehicles.
0.3; 0.06;
Universal,
Bar and wire
3000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Universal, sheet, rigid foil containers
Universal, beverage cans
Work-hardened
Work-hardened
Work-hardened
Sheet, high strength foil
4000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Work-hardened or aged
Work-hardened
Work-hardened
Sheet, cladding, fillers
architectural extrusions
5000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Sheet, plate, rod,
Universal, aerospace ()
rocket cryogenic tanks
Universal, welding
Universal, welding
Sheet, automobile trim
Sheet, automobile trim
Sheet, Rod
6000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Extrusions, angles
Heat-treatable
Universal, structural, aerospace ()
Heat-treatable
Heat-treatable
Extrusions
Heat-treatable
Heat-treatable
Extrusions
Heat-treatable
Heat-treatable
Extrusions
Extrusions
Extrusions
Heat-treatable
7000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Extrusions
Ultimate tensile strength 750 MPa
Universal, aerospace
Aerospace, Ultimate tensile strength 710 MPa
Sheet, foil
Universal, aerospace ()
Heat-treatable
8000 series aluminium alloy nominal composition (% weight) and applications
Al contents
Alloying elements
Uses and refs
Work-hardened
aerospace, cryogenics
Wrought aluminium alloy composition limits (% weight)
0.95 Si+Fe
0.05–0.20
0.20–0.40
0.05–0.15
0.02–0.10
0.10–0.25
0.05–0.20
0.05–0.40
0.15–0.35
0.05–0.25
0.05–0.25
3.10–3.90
0.15–0.35
4.50–5.50
0.05–0.20
0.06–0.20
0.05–0.20
0.05–0.20
0.10–0.30
0.15–0.40
0.04–0.35
0.15–0.40
0.15–0.40
0.04–0.14
0.20–0.70
0.06–0.20
0.01–0.06
0.08–0.20
0.50–1.00
0.10–0.40
2.60–3.70
0.10–0.30
4.30–5.20
1.60–2.40
2.20–3.00
7.30–8.30
0.05–0.15
0.18–0.28
0.40–0.80
0.10–0.30
0.10–0.25
0.18–0.28
+Manganese plus chromium must be between 0.12–0.50%.
++This column lists the limits that apply to all elements, whether a table column exists for them or not, for which no other limits are specified.
(AA) has adopted a nomenclature similar to that of wrought alloys.
and DIN have different designations. In the AA system, the second two digits reveal the minimum percentage of aluminium, e.g. 150.x correspond to a minimum of 99.50% aluminium. The digit after the decimal point takes a value of 0 or 1, denoting casting and ingot respectively. The main alloying elements in the AA system are as follows:[]
1xx.x series are minimum 99% aluminium
2xx.x series copper
3xx.x series silicon, copper and/or magnesium
4xx.x series silicon
5xx.x series magnesium
7xx.x series zinc
8xx.x series tin
9xx.x other elements
Minimum tensile requirements for cast aluminium alloys
Alloy type
Tensile strength (min) in
Yield strength (min) in ksi (MPa)
Elongation in 2 in %
60.0 (414)
50.0 (345)
45.0 (310)
28.0 (193)
23.0 (159)
32.0 (221)
20.0 (138)
29.0 (200)
29.0 (200)
32.0 (221)
20.0 (138)
36.0 (248)
28.0 (193)
29.0 (200)
16.0 (110)
23.0 (159)
25.0 (172)
31.0 (214)
20.0 (138)
25.0 (172)
34.0 (234)
21.0 (145)
32.0 (221)
20.0 (138)
25.0 (172)
18.0 (124)
30.0 (207)
22.0 (152)
36.0 (248)
25.0 (172)
19.0 (131)
30.0 (207)
20.0 (138)
31.0 (214)
23.0 (159)
16.0 (110)
25.0 (172)
18.0 (124)
34.0 (234)
24.0 (165)
35.0 (241)
26.0 (179)
17.0 (117)
17.0 (117)
17.0 (117)
22.0 (152)
42.0 (290)
22.0 (152)
35.0 (241)
18.0 (124)
30.0 (207)
17.0 (117)+
37.0 (255)
30.0 (207)+
32.0 (221)
20.0 (138)
34.0 (234)
25.0 (172)+
32.0 (221)
22.0 (152)
42.0 (290)
38.0 (262)
32.0 (221)
27.0 (186)
36.0 (248)
30.0 (207)
42.0 (290)
35.0 (241)
48.0 (331)
45.0 (310)
16.0 (110)
17.0 (117)
24.0 (165)
18.0 (124)
+Only when requested by the customer
an aluminium-iron alloy developed by , used for aircraft manufacture by
aluminium sheet formed from high-purity aluminium surface layers bonded to high strength aluminium alloy core material
(aluminium, magnesium) a product of The Birmetals Company, basically equivalent to 5251
(copper, aluminium)
(aluminium, magnesium, manganese, silicon) product of Hindustan Aluminium Corporation Ltd, made in 16ga rolled sheets for cookware
Pratt&Whitney proprietary alloy, supposedly having high strength and superior high temperature performance.
(magnesium, aluminium)
(aluminium, silicon)
(aluminium, zinc, magnesium, copper, zirconium) a product of . Commonly used in high performance sports products, particularly snowboards and skis.
, , : pre-war , used in aerospace and engine pistons, for their ability to retain strength at elevated temperature.
Parts of the Mig–29 are made from Al–Sc alloy.
The addition of
to aluminium creates nanoscale Al3Sc precipitates which limit the excessive grain growth that occurs in the heat-affected zone of welded aluminium components. This has two beneficial effects: the precipitated Al3Sc forms smaller crystals than are formed in other aluminium alloys and the width of precipitate-free zones that normally exist at the grain boundaries of age-hardenable aluminium alloys is reduced. Scandium is also a potent grain refiner in cast aluminium alloys, and atom for atom, the most potent strengthener in aluminium, both as a result of grain refinement and precipitation strengthening.
An added benefit of scandium additions to aluminium is that the nanoscale Al3Sc precipitates that give the alloy its strength are coarsening resistant at relatively high temperatures (~350 °C). This is in contrast to typical commercial 2xxx and 6xxx alloys, which quickly lose their strength at temperatures above 250 °C due to rapid coarsening of their strengthening precipitates.
In principle, aluminium alloys strengthened with additions of scandium are very similar to traditional nickel-base , in that both are strengthened by coherent, coarsening resistant precipitates with an ordered L12 structure. However, Al-Sc alloys contain a much lower volume fraction of precipitates and the inter-precipitate distance is much smaller than in their nickel-base counterparts. In both cases however, the coarsening resistant precipitates allow the alloys to retain their strength at high temperatures.
The increased operating temperature of Al-Sc alloys has significant implications for energy efficient applications, particularly in the automotive industry. These alloys can provide a replacement for denser materials such as
that are used in 250-350 °C environments, such as in or near engines. Replacement of these materials with lighter aluminium alloys leads to weight reductions which in turn leads to increased fuel efficiencies.
Additions of
have been shown to increase the coarsening resistance of Al-Sc alloys to ~400 °C. This is achieved by the formation of a slow-diffusing zirconium-rich shell around scandium and erbium-rich precipitate cores, forming strengthening precipitates with composition Al3(Sc,Zr,Er). Additional improvements in the coarsening resistance will allow these alloys to be used at increasingly higher temperatures.
, which are stronger but heavier than Al-Sc alloys, are still much more widely used.
The main application of metallic scandium by weight is in
for minor aerospace industry components. These alloys contain between 0.1% and 0.5% (by weight) of scandium. They were used in the Russian military aircraft
Some items of sports equipment, which rely on high performance materials, have been made with scandium-aluminium alloys, including ,
sticks, as well as bicycle frames and components, and tent poles. U.S. gunmaker
produces revolvers with frames composed of scandium alloy and cylinders of titanium.
The following aluminium alloys are commonly used in aircraft and other
structures:
Note that the term aircraft aluminium or aerospace aluminium usually refers to 7075.
4047 alumunium is a unique alloy used in both the aerospace and automotive applications as a cladding alloy or filler material. As filler, aluminum alloy 4047 strips can be combined to intricate applications to bond two metals.
6951 is a heat treatable alloy providing additional strength to the fins while incre this allows the manufacturer to reduce the gauge of the sheet and therefore reducing the weight of the formed fin. These distinctive features make aluminum alloy 6951 one of the preferred alloys for heat transfer and heat exchangers manufactured for aerospace applications.
alloys are heat treatable with moderately high strength, excellent corrosion resistance and good extrudability. They are regularly used as architectural and structural members.
The following list of aluminium alloys are currently produced,[] but less widely[] used:
These alloys are used for boat building and shipbuilding, and other marine and salt-water sensitive shore applications.
, 6005A, 6082 also used in marine constructions and off shore applications.
These alloys are used for cycling frames and components[]
are extensively used for external automotive , with
used for inner body panels. Bonnets have been manufactured from , , and 6111 alloys. Truck and trailer body panels have used .
Automobile frames often use
formed sheets,
extrusions.
Wheels have been cast from
or formed 5xxx sheet.
are often cast made of aluminium alloys. The most popular aluminium alloys used for cylinder blocks are A356, 319 and to a minor extend 242.
are widely used in breathing gas cylinders for
I. J. Polmear, Light Alloys, Arnold, 1995
(PDF) from the original on 6 September .
, accessed 8 October 2006. Also
27 September 2006 at the ., accessed 8 October 2006.
R.E. Sanders, Technology Innovation in aluminium Products, The Journal of The Minerals, 53(2):21–25, 2001.
17 March 2012 at the .
. Archived from
on 15 June .
Degarmo, E. P Black, J T.; Kohser, Ronald A. (2003). Materials and Processes in Manufacturing (9th ed.). Wiley. p. 133.  .
from the original on 29 July .
. aluMATTER.org.
from the original on 5 May .
10 February 2017 at the .
(PDF) from the original on 26 October .
6 April 2017 at the .
4 April 2017 at the .
23 November 2013 at the ., NASA, retrieved 12 Dec 2013.
. SpaceX. 2013. Archived from
on 1 December 2011.
Bjelde, B Max V Gwynne Shotwell (August 2007). . 21st Annual AIAA/USU Conference on Small Satellites (SSC07 ‐ III ‐ 6).
from the original on 15 December .
Kaufman, John Gilbert (2000). "Applications for Aluminium Alloys and Tempers". . ASM International. pp. 93–94.  .
31 March 2017 at the .
4 February 2012 at the .
MEE433B Aluminum-Lithium Alloys
ASM Metals Handbook Vol. 2, Properties and Selection of Nonferrous Alloys and Special Purpose Materials, ASM International (p. 222)
ASTM B 26 / B 26M – 05
Parker, Dana T. Building Victory: Aircraft Manufacturing in the Los Angeles Area in World War II, p. 39, 118, Cypress, CA, 2013.  .
Ahmad, Zaki (2003). "The properties and application of scandium-reinforced aluminum". JOM. 55 (2): 35. :. :.
Marquis, Emmanuelle (2002). "Precipitation strengthening at ambient and elevated temperatures of heat-treatable Al(Sc) alloys". Acta Materialia. 50 (16): 4021. :.
Vo, Nhon (2016). "Role of silicon in the precipitation kinetics of dilute Al-Sc-Er-Zr alloys". Materials Science and Engineering: A. 677 (20): 485. :.
. NanoAl. 2016.
from the original on 12 November .
Vo, Nhon (2014). "Improving aging and creep resistance in a dilute Al-Sc alloy by microalloying with Si, Zr, and Er". Acta Materialia. 63 (15): 73. :.
Schwarz, James A.; Contescu, Cristian I.; Putyera, Karol (2004). . 3. CRC Press. p. 2274.  .
from the original on 28 January 2017.
Bjerklie, Steve (2006). "A batty business: Anodized metal bats have revolutionized baseball. But are finishers losing the sweet spot?". Metal Finishing. 104 (4): 61. :.
(PDF) from the original on 23 November .
. Smith & Wesson.
from the original on 30 October .
Fundamentals of Flight, Shevell, Richard S., 1989, Englewood Cliffs, Prentice Hall,  , Ch 18, pp 373–386.
from the original on 21 April 2009.
Wagner, PennyJo (Winter 1995). .
from the original on 5 April 2009.
. Lynch Metals, Inc.
from the original on 27 February .
. Lynch Metals, Inc.
from the original on 27 February .
Karthikeyan, L.; Senthil Kumar, V.S. (2011). "Relationship between process parameters and mechanical properties of friction stir processed AA6063-T6 aluminum alloy". Materials and Design. 32: . :.
Boatbuilding with aluminium, Stephen F. Pollard, 1993, International Marine,  
Kaufman, John (2000).
(PDF). ASM International. pp. 116–117.  .
(PDF) from the original on 15 December .
. Professional Scuba Inspectors. 1 July 2011.
from the original on 10 December .
: Hidden categories:}