7075 aluminium alloy

7075 aluminium alloy (AA7075) is an aluminium alloy, with zinc as the primary alloying element. It has excellent mechanical properties, and exhibits good ductility, high strength, toughness and good resistance to fatigue. It is more susceptible to embrittlement than many other aluminium alloys because of microsegregation, but has significantly better corrosion resistance than the 2000 alloys. It is one of the most commonly used aluminium alloy for highly stressed structural applications, and has been extensively utilized in aircraft structural parts.[2]

"Ergal" redirects here. For other uses, see Ergal (disambiguation).
A7075 T6
Physical properties
Density (ρ)2.81
Mechanical properties
Young's modulus (E)71.7 GPa (10,400 ksi)
Tensile strength (σt)572 MPa (83.0 ksi)
Elongation (ε) at break11%
Poisson's ratio (ν)0.33
Hardness—Rockwell87 HRB
Thermal properties
Melting temperature (Tm)477 °C (891 °F)
Thermal conductivity (k) [1]196 W/m*K
Linear thermal expansion coefficient (α)2.36*10−5 K−1
Specific heat capacity (c)714.8 J/kg*K
Electrical properties
Volume resistivity (ρ)51.5 nOhm*m

7075 aluminium alloy's composition roughly includes 5.6–6.1% zinc, 2.1–2.5% magnesium, 1.2–1.6% copper, and less than a half percent of silicon, iron, manganese, titanium, chromium, and other metals. It is produced in many tempers, some of which are 7075-0, 7075-T6, 7075-T651.

The first 7075 was developed in secret by a Japanese company, Sumitomo Metal, in 1935,[3] but introduced by Alcoa in 1943 and was standardized for aerospace use in 1945.[4] 7075 was eventually used for airframe production in the Imperial Japanese Navy.

Basic properties

Aluminium 7075A has a density of 2.810 g/cm³[5] (0.1015 lb/in³).

Mechanical properties

The mechanical properties of 7075 depend greatly on the tempering of the material.[6]

7075-0

Un-heat-treated 7075 (7075-0 temper) has a maximum tensile strength of no more than 280 MPa (40,000 psi), and maximum yield strength of no more than 140 MPa (21,000 psi). The material has an elongation (stretch before ultimate failure) of 9–10%. As is the case for all 7075 aluminum alloys, 7075-0 is highly corrosion-resistant combined with generally acceptable strength profile.

7075-T6

T6 temper 7075 has an ultimate tensile strength of 510–540 MPa (74,000–78,000 psi) and yield strength of at least 430–480 MPa (63,000–69,000 psi). It has a failure elongation of 5–11%.[7]

The T6 temper is usually achieved by homogenizing the cast 7075 at 450 °C for several hours, quenching, and then ageing at 120 °C for 24 hours. This yields the peak strength of the 7075 alloy. The strength is derived mainly from finely dispersed eta and eta' precipitates both within grains and along grain boundaries.[8]

7075-T651

T651 temper 7075 has an ultimate tensile strength of 570 MPa (83,000 psi) and yield strength of 500 MPa (73,000 psi). It has a failure elongation of 3–9%. These properties can change depending on the form of material used. Thicker plate may exhibit lower strengths and elongation than the numbers listed above.

7075-T7

T7 temper has an ultimate tensile strength of 505 MPa (73,200 psi) and a yield strength of 435 MPa (63,100 psi). It has a failure elongation of 13%.[9] T7 temper is achieved by overaging (meaning aging past the peak hardness) the material. This is often accomplished by aging at 100–120 °C for several hours and then at 160–180 °C for 24 hours or more. The T7 temper produces a micro-structure of mostly eta precipitates. In contrast to the T6 temper, these eta particles are much larger and prefer growth along the grain boundaries. This reduces the susceptibility to stress corrosion cracking. T7 temper is equivalent to T73 temper.[8]

7075-RRA

The retrogression and reage (RRA) temper is a multistage heat treatment temper. Starting with a sheet in the T6 temper, it involves overaging past peak hardness (T6 temper) to near the T7 temper. A subsequent reaging at 120 °C for 24 hours returns the hardness and strength to or very nearly to T6 temper levels.[8]

RRA treatments can be accomplished with many different procedures. The general guidelines are retrogressing between 180–240 °C for 15 min 10 s.[10]

Uses

The world's first mass production usage of the 7075 aluminum alloy was for the Mitsubishi A6M Zero fighter. The aircraft was known for its excellent maneuverability which was facilitated by the higher strength of 7075 compared to former aluminum alloys.

7000 series alloys such as 7075 are often used in transport applications due to their high Specific strength, including marine, automotive and aviation.[6][11] These same properties lead to its use in rock climbing equipment, bicycle components, inlineskating-frames and hang glider airframes are commonly made from 7075 aluminium alloy. Hobby grade RC models commonly use 7075 and 6061 for chassis plates. 7075 is used in the manufacturing of M16 rifles for the U.S.A. military as well as AR-15 style rifles for the civilian market. In particular high quality M16 rifle lower and upper receivers as well as extension tubes are typically made from 7075-T6 alloy. Desert Tactical Arms, SIG Sauer, and French armament company PGM use it for their precision rifles. It is also commonly used in shafts for lacrosse sticks, such as the STX sabre, and camping knife and fork sets. It is a common material used in competition yo-yos as well.

Due to its high strength, low density, thermal properties, and its ability to be highly polished, 7075 is widely used in mold tool manufacturing. This alloy has been further refined into other 7000 series alloys for this application, namely 7050 and 7020.

Aerospace applications

7075 was used in the Space Shuttle SRB nozzles, and the External tank SRB beam in the Inter-tank section.

Trade names

7075 has been sold under various trade names including Zicral, Ergal, and Fortal Constructal.

Some 7000 series alloys sold under brand names for making molds include Alumec 79, Alumec 89, Contal, Certal, Alumould, and Hokotol.

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See also

References
  1. Juan J. Valencia, Peter N. Quested, "Thermophysical Properties"
  2. ASM Handbook Volume 2: Properties and Selection: Nonferrous Alloys and Special-Purpose Materials, 1990 p. 137-38
  3. Yoshio, Baba."Extra super duralumin and successive aluminium alloys for aircraft." Journal of Japan Institute of Light Metals (Sumitomo Light Metal Ind. Ltd., Japan), Volume 39, Issue 5, p. 378. Retrieved: 22 November 2015.
  4. Canadian Aeronautics and Space Journal, 1989 vol 35-36 p. 129
  5. "7075 (AlZn5.5MgCu, 3.4365, 2L95, A97075) Aluminum :: MakeItFrom.com". www.makeitfrom.com. Retrieved 22 April 2018.
  6. Alcoa 7075 data sheet Archived 2013-08-29 at the Wayback Machine (PDF), accessed October 13, 2006
  7. "ASM Material Data Sheet". asm.matweb.com. Retrieved 22 April 2018.
  8. Park, J. K., and A. J. Ardell. "Microstructures of the Commercial 7075 AI Alloy in the T651 and T7 Tempers". Metall. Trans. A. 14A (1983): 1957. Print.
  9. "ASM Material Data Sheet". asm.matweb.com. Retrieved 22 April 2018.
  10. Cina, Baruch M. REDUCING THE SUSCEPTIBILITY OF ALLOYS, PARTICULARLY ALUMINIUM ALLOYS, TO STRESS CORROSION CRACKING. Israel Aircraft Industries Ltd., assignee. Patent 3856584. 24 Dec. 1974. Print.
  11. T Hashimoto, S Jyogan (Showa Aluminium), K Nakata, Y G Kin and M Ushio (Osaka University): FSW joining of high strength Al alloy

Further reading
  • "Properties of Wrought Aluminum and Aluminum Alloys: 7075, Alclad 7075", Properties and Selection: Nonferrous Alloys and Special-Purpose Materials, Vol. 2, ASM Handbook, ASM International, 1990, pp. 115–116.
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