US2301759A - Aluminum alloy rivet - Google Patents
Aluminum alloy rivet Download PDFInfo
- Publication number
- US2301759A US2301759A US355457A US35545740A US2301759A US 2301759 A US2301759 A US 2301759A US 355457 A US355457 A US 355457A US 35545740 A US35545740 A US 35545740A US 2301759 A US2301759 A US 2301759A
- Authority
- US
- United States
- Prior art keywords
- per cent
- solution heat
- rivet
- rivets
- heat treatment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 229910000838 Al alloy Inorganic materials 0.000 title description 3
- 229910045601 alloy Inorganic materials 0.000 description 27
- 239000000956 alloy Substances 0.000 description 27
- 238000010438 heat treatment Methods 0.000 description 19
- 229910052782 aluminium Inorganic materials 0.000 description 18
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 18
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 11
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 11
- 238000003483 aging Methods 0.000 description 11
- 229910052802 copper Inorganic materials 0.000 description 11
- 239000010949 copper Substances 0.000 description 11
- 229910052749 magnesium Inorganic materials 0.000 description 11
- 239000011777 magnesium Substances 0.000 description 11
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 10
- 239000011701 zinc Substances 0.000 description 10
- 229910052725 zinc Inorganic materials 0.000 description 10
- 230000032683 aging Effects 0.000 description 8
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 7
- 238000010791 quenching Methods 0.000 description 5
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 4
- 229910052804 chromium Inorganic materials 0.000 description 4
- 239000011651 chromium Substances 0.000 description 4
- 230000000171 quenching effect Effects 0.000 description 4
- 229910052726 zirconium Inorganic materials 0.000 description 4
- 239000012535 impurity Substances 0.000 description 3
- 229910052710 silicon Inorganic materials 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002269 spontaneous effect Effects 0.000 description 2
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical compound [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 229920000136 polysorbate Polymers 0.000 description 1
- 238000011282 treatment Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B19/00—Bolts without screw-thread; Pins, including deformable elements; Rivets
- F16B19/04—Rivets; Spigots or the like fastened by riveting
Definitions
- the alloys used for making high strength aluminum base alloy rivets are ordinarily those which age-harden spontaneously at room temperature following a solution heat treatment, this treatment'being referred to as natural aging," as distinguished from artificial aging,” which is carried out by heating the metal at an elevated temperature-ordinarily around 250 to 400 F.
- this treatment is customary to drive the rivets subsequent to the solution heat treatment, but since more pressure is required for driving the rivets as theirstrength increases and there is a greater tendency for cracks, to develop in the driven head, it is desirable to drive them before aging of the alloy increases the strength of the metal greatly. Alloys which age spontaneously at room temperature may not' reach their ultimate properties until a considerable time after they have been quenched following the solution heat treatment.
- the alloys heretofore used for making high strength aluminum base alloy rivets age-harden rapidly enough following the solution heat treatment that the rivets ordinarily soon become too hard to be driven satisfactorily at normal pressures, and consequently the rivets must bedriven within a very short time after they have been given a solution heat treatment and been quenched.
- rivets made of an alloy containing about 4 per cent copper, 0.5 per cent magnesium, and 0.5 per cent manganese, the balance being aluminum plus impurities must ordinarily be driven within one hour after quenching, or they become too hard and tend to crack at the heads during driving, and must again be given a solution heat treatment before they can be driven.
- One method which has been used to overcome this difllculty store the rivets at low temperatures-for example, a temperature of 32 F. or lower-followin their solution heat treatment and quenching, but
- the rivet alloy in addition to the alloying ingredients mentioned above, itis preferred to add to the rivet alloy from 0.25 to 1.5 per cent of manganese, or 0.1 to 0.5 per cent chromium or zirconium, singly or together, to obtain increased strength.
- the rivets are made of an alloy composed of from 2.5 to
- This alloy is preferably given a solution heat treatment at a temperature between 900 and 970 F., followed by quenching in cold water.
- Rivets made from the alloys described above and retard the aging of the rivets has been. to age-harden slowly enough that they can be driven 3.5 per cent zinc, 1.5 to 2.5 per cent magnesium,-
- specimens of an alloy consisting of 3 per cent zinc, 2 per cent magnesium, 2 per cent copper, .5 per cent manganese, .2 per cent silicon, and 0.2 per cent iron were heat treated at 950 F. for 30 minutes and then quenched in cold water. Immediately after quenching, the material had a tensile strength of 44,000 pounds per square inch and a yield strength of 18,000 pounds per square inch.
- the specimens were allowed to age at room temperature for varying periods of time, with the following efl'ect on their properties:
- the rivets described above In addition to age-hardening slowly to a point where they possess properties which are adequate for purposes where strong aluminum alloy rivets are used, the rivets described above also possess good resistance to corrosion and are easily fabricated.
- a solution heat treated rivet composed of an aluminum base alloy containing from 0.75 to 4.5 per cent zinc, 1 to 3 per cent copper, and 1 to 3 per cent magnesium, said rivet being characterized by initially slow age-hardening at room temperature.
- a solution heat treated rivet composed of an aluminum base alloy containing 2.5 to 3.5
- said rivet beingcharacterized by initially slow age-hardening at room temperature.
- a solution heat treated rivet composed of an aluminum base alloy containing 0.75 to 4.5 per cent zinc, l to 3 per cent copper, 1 to 3 per cent magnesium,- and 0.25 to 1.5 per cent manganese, said rivet being characterized by initially slow age-hardening at room temperature.
- a solution heat treated rivet composed of an aluminum base alloy containing 0.75 to 4.5 per cent zinc, 1 to 3 per cent copper, 1 to 3 per cent magnesium, and 0.1 to 0.5 per cent zirconium, said rivet being characterized by initially slow age-hardening at room temperature.
- a solution heat treated rivet composed of an aluminum base alloy consisting of from 2.5 to 3.5 per cent zinc, 1.5 to 2.5 per cent copper, 1.5 to 2.5 per cent magnesium, and 0.4 to 1.2 per cent'manganese, the balance being substantially aluminum, said rivets being characterized by initially slow age-hardening at room temperaturc.
- a solution heat treated rivet composed of an aluminum base alloy consisting of 2 per cent copper, 2 per cent magnesium, '3 per cent zinc, and 0.5 per cent manganese, the balance being substantially aluminum, said rivet being characterized by initially slow age-hardening at room temperature.
- a solution heat treated rivet composed oi an aluminum base alloy containing from 0.75 to 4.5 per cent zinc, 1 to 3 per cent copper, 1 to 8 per cent magnesium, and 0.1 to 0.5 per cent chromium, said rivet being characterized by initially slow age-hardening at room temperature.
Description
Patented Nov. 10, 1942 ALUMINUM ALLOY RIVE'I' Philip '1'. Stronp, New Kensington, Pa, assignor Alumin um Company of America, Pittsburgh,
Pa, a corporation of Pennsylvania No Drawing. Application September 5, 1940, Serial No. 355,451.
volume;
In the joining of aluminum base alloy parts are those alloyswhich are susceptible to having their strength developed by means of a solution heat treatment followed by a natural or artificial aging process. Such solution heat treatments are well known in the art and ordinarily involve heating the alloy at a temperature be-. tween 750 and 1020" F., after which it is cooled rapidly or quenched by immersion in water or oil, or by a current of air.
The alloys used for making high strength aluminum base alloy rivets are ordinarily those which age-harden spontaneously at room temperature following a solution heat treatment, this treatment'being referred to as natural aging," as distinguished from artificial aging," which is carried out by heating the metal at an elevated temperature-ordinarily around 250 to 400 F. In riveting operations, it is customary to drive the rivets subsequent to the solution heat treatment, but since more pressure is required for driving the rivets as theirstrength increases and there is a greater tendency for cracks, to develop in the driven head, it is desirable to drive them before aging of the alloy increases the strength of the metal greatly. Alloys which age spontaneously at room temperature may not' reach their ultimate properties until a considerable time after they have been quenched following the solution heat treatment. However, the alloys heretofore used for making high strength aluminum base alloy rivets age-harden rapidly enough following the solution heat treatment that the rivets ordinarily soon become too hard to be driven satisfactorily at normal pressures, and consequently the rivets must bedriven within a very short time after they have been given a solution heat treatment and been quenched. For example, rivets made of an alloy containing about 4 per cent copper, 0.5 per cent magnesium, and 0.5 per cent manganese, the balance being aluminum plus impurities, must ordinarily be driven within one hour after quenching, or they become too hard and tend to crack at the heads during driving, and must again be given a solution heat treatment before they can be driven. One method which has been used to overcome this difllculty store the rivets at low temperatures-for example, a temperature of 32 F. or lower-followin their solution heat treatment and quenching, but
that procedure increases the expense of using the 5 rivets.
It is an object of this invention to provide an aluminum base alloy rivet which is susceptible to spontaneous aging, but which can be driven satisfactorily at normal pressures over an extended time following a solution heat treatment. It is a further object of this invention to provide an aluminum base alloy rivet which is capable of achieving a considerable increase in strength through spontaneous aging after a solution heat treatment, but which ischaracterized by an initially slow age-hardening.
It has been discovered that rivets made from an aluminum base alloy containing from 0.75 to 4.5 per cent zinc, from 1 to 3 per cent magnesium, from 1 to 3 per cent copper, when given a solution heat treatment and quenched, not only eventually attain properties upon agehardening at room temperature which make the rivet satisfactory for applications where high strength and hardness are required, but also initially age-harden slowly after the solution heat treatment, with the result that the rivets can be driven satisfactorily at normal pressures for a considerable time after the solution heat treatment. In the above composition it is desirable that silicon, which is normally present as an impurity in aluminum base alloys, should not exceed 0.5 per cent to obtain the desired initially slow age-hardening.
In addition to the alloying ingredients mentioned above, itis preferred to add to the rivet alloy from 0.25 to 1.5 per cent of manganese, or 0.1 to 0.5 per cent chromium or zirconium, singly or together, to obtain increased strength. A 40 small amount of iron--around 0.1 to 0.6 per cent-is also usually present in the alloy as an impurity.
In the preferred form of the invention, the rivets are made of an alloy composed of from 2.5 to
1.5 to 2.5 per cent copper, and not more than 0.25 per cent silicon, and if manganese, chromium, or zirconium is present, it is preferred to keep the manganese at from 0.4 to 1.2 per cent, and the chromium or zirconium at 0.2 to 0.3 per cent. This alloy is preferably given a solution heat treatment at a temperature between 900 and 970 F., followed by quenching in cold water.
Rivets made from the alloys described above and retard the aging of the rivets has been. to age-harden slowly enough that they can be driven 3.5 per cent zinc, 1.5 to 2.5 per cent magnesium,-
without difilculty for at least eight hours, and for as long as twenty-four hours, after solution heat treatment. As an example of the invention, specimens of an alloy consisting of 3 per cent zinc, 2 per cent magnesium, 2 per cent copper, .5 per cent manganese, .2 per cent silicon, and 0.2 per cent iron were heat treated at 950 F. for 30 minutes and then quenched in cold water. Immediately after quenching, the material had a tensile strength of 44,000 pounds per square inch and a yield strength of 18,000 pounds per square inch. The specimens were allowed to age at room temperature for varying periods of time, with the following efl'ect on their properties:
Length of time after quench It will be seen from the above table that there is very little increase in strength for eight hours after the solution heat treatment, and even after twenty-four hours, the strength of the specimens had not increased excessively tor rivet-driving purposes. Yet. they eventually attain a high degree of strength, being comparable to the present maximum strength obtained by natural aging of any aluminum base alloy.
In addition to age-hardening slowly to a point where they possess properties which are adequate for purposes where strong aluminum alloy rivets are used, the rivets described above also possess good resistance to corrosion and are easily fabricated.
I claim:
1. A solution heat treated rivet composed of an aluminum base alloy containing from 0.75 to 4.5 per cent zinc, 1 to 3 per cent copper, and 1 to 3 per cent magnesium, said rivet being characterized by initially slow age-hardening at room temperature.
2. A solution heat treated rivet composed of an aluminum base alloy containing 2.5 to 3.5
per cent zinc, 1.5 to 2.5 per cent copper, and 1.5 to 2.5 per cent magnesium, said rivet beingcharacterized by initially slow age-hardening at room temperature.
3. A solution heat treated rivet composed of an aluminum base alloy containing 0.75 to 4.5 per cent zinc, l to 3 per cent copper, 1 to 3 per cent magnesium,- and 0.25 to 1.5 per cent manganese, said rivet being characterized by initially slow age-hardening at room temperature.
4. A solution heat treated rivet composed of an aluminum base alloy containing 0.75 to 4.5 per cent zinc, 1 to 3 per cent copper, 1 to 3 per cent magnesium, and 0.1 to 0.5 per cent zirconium, said rivet being characterized by initially slow age-hardening at room temperature.
5. A solution heat treated rivet composed of an aluminum base alloy consisting of from 2.5 to 3.5 per cent zinc, 1.5 to 2.5 per cent copper, 1.5 to 2.5 per cent magnesium, and 0.4 to 1.2 per cent'manganese, the balance being substantially aluminum, said rivets being characterized by initially slow age-hardening at room temperaturc.
6. A solution heat treated rivet composed of an aluminum base alloy consisting of 2 per cent copper, 2 per cent magnesium, '3 per cent zinc, and 0.5 per cent manganese, the balance being substantially aluminum, said rivet being characterized by initially slow age-hardening at room temperature.
7. A solution heat treated rivet composed oi an aluminum base alloy containing from 0.75 to 4.5 per cent zinc, 1 to 3 per cent copper, 1 to 8 per cent magnesium, and 0.1 to 0.5 per cent chromium, said rivet being characterized by initially slow age-hardening at room temperature.
PHILIP T. STROUP.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US355457A US2301759A (en) | 1940-09-05 | 1940-09-05 | Aluminum alloy rivet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US355457A US2301759A (en) | 1940-09-05 | 1940-09-05 | Aluminum alloy rivet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2301759A true US2301759A (en) | 1942-11-10 |
Family
ID=23397493
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US355457A Expired - Lifetime US2301759A (en) | 1940-09-05 | 1940-09-05 | Aluminum alloy rivet |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2301759A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2742688A (en) * | 1952-06-18 | 1956-04-24 | Aluminum Co Of America | Duplex aluminous products and articles |
| US2780019A (en) * | 1952-02-19 | 1957-02-05 | George C Sullivan | Gun barrel of aluminum alloy with metallic coatings |
| US3056226A (en) * | 1959-08-20 | 1962-10-02 | Olin Mathieson | Firing pin of light weight material, such as aluminum or titanium |
| US3284193A (en) * | 1963-12-05 | 1966-11-08 | Boeing Co | Aluminum alloy |
| US3404457A (en) * | 1966-07-26 | 1968-10-08 | Diamond Tool And Horseshoe Co | Hand tool |
| US3620854A (en) * | 1968-02-23 | 1971-11-16 | North American Rockwell | Aluminum casting alloy |
| US4620886A (en) * | 1983-08-10 | 1986-11-04 | Suddeutsche Metallindustrie Gmbh & Co. Kg | Method of making aluminum rivets with high ductility retention |
| US4840685A (en) * | 1985-05-21 | 1989-06-20 | Furukawa Aluminum Co., Ltd. | Aluminum alloy for the substrate of magnetic disk |
-
1940
- 1940-09-05 US US355457A patent/US2301759A/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2780019A (en) * | 1952-02-19 | 1957-02-05 | George C Sullivan | Gun barrel of aluminum alloy with metallic coatings |
| US2742688A (en) * | 1952-06-18 | 1956-04-24 | Aluminum Co Of America | Duplex aluminous products and articles |
| US3056226A (en) * | 1959-08-20 | 1962-10-02 | Olin Mathieson | Firing pin of light weight material, such as aluminum or titanium |
| US3284193A (en) * | 1963-12-05 | 1966-11-08 | Boeing Co | Aluminum alloy |
| US3404457A (en) * | 1966-07-26 | 1968-10-08 | Diamond Tool And Horseshoe Co | Hand tool |
| US3620854A (en) * | 1968-02-23 | 1971-11-16 | North American Rockwell | Aluminum casting alloy |
| US4620886A (en) * | 1983-08-10 | 1986-11-04 | Suddeutsche Metallindustrie Gmbh & Co. Kg | Method of making aluminum rivets with high ductility retention |
| US4840685A (en) * | 1985-05-21 | 1989-06-20 | Furukawa Aluminum Co., Ltd. | Aluminum alloy for the substrate of magnetic disk |
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