CN107574358A - A kind of aircraft wing rib material and preparation method thereof - Google Patents
A kind of aircraft wing rib material and preparation method thereof Download PDFInfo
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- CN107574358A CN107574358A CN201710752883.5A CN201710752883A CN107574358A CN 107574358 A CN107574358 A CN 107574358A CN 201710752883 A CN201710752883 A CN 201710752883A CN 107574358 A CN107574358 A CN 107574358A
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Abstract
The invention discloses a kind of aircraft wing rib material and preparation method thereof, includes following component according to mass fraction：16 34 parts of cast iron, 0.4 0.6 parts of chromium, 2.5 4.5 parts of manganese, 0.06 0.09 parts of vanadium, 24 parts of chromium, 9 11 parts of cobalt, 0.7 1.1 parts of nickel, 0.03 0.07 parts of titanium, 0.5 0.9 parts of lanthanum, 0.3 0.5 parts of boron, 0.5 0.8 parts of sulphur, a kind of aircraft wing rib material of the present invention, there is provided a kind of hardness is high, plasticity is good, can improve the aircraft wing rib of security.
Description
Technical field
The present invention relates to a kind of metal material, in particular to a kind of aircraft wing rib material and preparation method thereof.
Background technology
The security of aircraft wing rib is the part of Flight Safety core, the intensity of aircraft wing rib with
Durometer properties is the basis for ensureing aircraft wing support, and the selection of aircraft wing rib material is vital, and intensity hardness is not
The material of foot can directly result in wing fracture, currently without the high aircraft wing rib material of intensity hardness, therefore research and develop a kind of
The high aircraft wing rib material of intensity hardness turns into current urgent problem.
The content of the invention
The invention provides a kind of aircraft wing rib material and preparation method thereof.
To achieve the above object, the present invention provides following technical scheme：
A kind of aircraft wing rib material, include following component according to mass fraction：
Cast iron 16-34 parts, chromium 0.4-0.6 parts, manganese 2.5-4.5 parts, vanadium 0.06-0.09 parts, chromium 2-4 parts, cobalt 9-11 parts, nickel
0.7-1.1 parts, titanium 0.03-0.07 parts, lanthanum 0.5-0.9 parts, boron 0.3-0.5 parts, sulphur 0.5-0.8 parts.
Further, following composition is included according to mass fraction：
16 parts of cast iron, 0.4 part of chromium, 2.5 parts of manganese, 0.06 part of vanadium, 2 parts of chromium, 9 parts of cobalt, nickel 0.7-1.1 parts, 0.03 part of titanium, lanthanum
0.5 part, 0.3 part of boron, 0.5 part of sulphur.
Further, following composition is included according to mass fraction：
25 parts of cast iron, 0.5 part of chromium, 3.5 parts of manganese, 0.08 part of vanadium, 3 parts of chromium, 10 parts of cobalt, 0.9 part of nickel, 0.05 part of titanium, lanthanum 0.7
Part, 0.4 part of boron, 0.6 part of sulphur.
Further, following composition is included according to mass fraction：
34 parts of cast iron, 0.6 part of chromium, 4.5 parts of manganese, 0.09 part of vanadium, 4 parts of chromium, 11 parts of cobalt, 1.1 parts of nickel, 0.07 part of titanium, lanthanum 0.9
0.8 part of part, 0.5 part of boron, sulphur part.
Further, the preparation method of aircraft wing rib material, is comprised the following steps：
1) by cast iron 16-34 parts, chromium 0.4-0.6 parts, manganese 2.5-4.5 parts, vanadium 0.06-0.09 parts, chromium 2-4 parts, cobalt 9-11
Part, nickel 0.7-1.1 parts, titanium 0.03-0.07 parts, lanthanum 0.5-0.9 parts, 1500 degree of -1800 degree is heated to, cools down 3-5 hours and fill
Divide stirring that mixture A is made；
2) by mixture A made from step 1, addition boron 0.3-0.5 parts, sulphur 0.5-0.8 parts, continue to be heated to 2200-
2500 degree are sufficiently mixed, and mixture B are made, by mixture B air coolings.
The beneficial effects of the invention are as follows：
1st, the security of aircraft flight is improved.
2nd, intensity hardness is high.
Embodiment
Below in conjunction with the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described,
Obviously, described embodiment, only part of the embodiment of the present invention, rather than whole embodiments.Based in the present invention
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made,
Belong to the scope of protection of the invention.
Embodiment one：
A kind of aircraft wing rib material and preparation method thereof, include following component according to mass fraction：
Cast iron 16-34 parts, chromium 0.4-0.6 parts, manganese 2.5-4.5 parts, vanadium 0.06-0.09 parts, chromium 2-4 parts, cobalt 9-11 parts, nickel
0.7-1.1 parts, titanium 0.03-0.07 parts, lanthanum 0.5-0.9 parts, boron 0.3-0.5 parts, sulphur 0.5-0.8 parts.
The preparation method of above-mentioned formula：
1) by cast iron 16-34 parts, chromium 0.4-0.6 parts, manganese 2.5-4.5 parts, vanadium 0.06-0.09 parts, chromium 2-4 parts, cobalt 9-11
Part, nickel 0.7-1.1 parts, titanium 0.03-0.07 parts, lanthanum 0.5-0.9 parts, 1500 degree of -1800 degree is heated to, cools down 3-5 hours and fill
Divide stirring that mixture A is made；
2) by mixture A made from step 1, addition boron 0.3-0.5 parts, sulphur 0.5-0.8 parts, continue to be heated to 2200-
2500 degree are sufficiently mixed, and mixture B are made, by mixture B air coolings.
Embodiment two：
A kind of aircraft wing rib material includes following component according to mass fraction：
16 parts of cast iron, 0.4 part of chromium, 2.5 parts of manganese, 0.06 part of vanadium, 2 parts of chromium, 9 parts of cobalt, nickel 0.7-1.1 parts, 0.03 part of titanium, lanthanum
0.5 part, 0.3 part of boron, 0.5 part of sulphur.
Embodiment three：
A kind of aircraft wing rib material and preparation method thereof, include following composition according to mass fraction：
25 parts of cast iron, 0.5 part of chromium, 3.5 parts of manganese, 0.08 part of vanadium, 3 parts of chromium, 10 parts of cobalt, 0.9 part of nickel, 0.05 part of titanium, lanthanum 0.7
Part, 0.4 part of boron, 0.6 part of sulphur.
Example IV：
A kind of aircraft wing rib material and preparation method thereof, include following composition according to mass fraction：
34 parts of cast iron, 0.6 part of chromium, 4.5 parts of manganese, 0.09 part of vanadium, 4 parts of chromium, 11 parts of cobalt, 1.1 parts of nickel, 0.07 part of titanium, lanthanum 0.9
Part, 0.5 part of boron, 0.8 part of sulphur.
Moreover, it will be appreciated that although the present specification is described in terms of embodiments, not each embodiment is only wrapped
Containing an independent technical scheme, this narrating mode of specification is only that those skilled in the art should for clarity
Using specification as an entirety, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
It is appreciated that other embodiment.
Claims (5)
1. a kind of aircraft wing rib material, include following component according to mass fraction：
Cast iron 16-34 parts, chromium 0.4-0.6 parts, manganese 2.5-4.5 parts, vanadium 0.06-0.09 parts, chromium 2-4 parts, cobalt 9-11 parts, nickel 0.7-
1.1 parts, titanium 0.03-0.07 parts, lanthanum 0.5-0.9 parts, boron 0.3-0.5 parts, sulphur 0.5-0.8 parts.
2. a kind of aircraft wing rib material according to claim 1, include following composition according to mass fraction：
16 parts of cast iron, 0.4 part of chromium, 2.5 parts of manganese, 0.06 part of vanadium, 2 parts of chromium, 9 parts of cobalt, nickel 0.7-1.1 parts, 0.03 part of titanium, lanthanum 0.5
Part, 0.3 part of boron, 0.5 part of sulphur.
3. a kind of aircraft wing rib material according to claim 1, include following composition according to mass fraction：
25 parts of cast iron, 0.5 part of chromium, 3.5 parts of manganese, 0.08 part of vanadium, 3 parts of chromium, 10 parts of cobalt, 0.9 part of nickel, 0.05 part of titanium, 0.7 part of lanthanum,
0.4 part of boron, 0.6 part of sulphur.
4. a kind of aircraft wing rib material according to claim 1, include following composition according to mass fraction：
34 parts of cast iron, 0.6 part of chromium, 4.5 parts of manganese, 0.09 part of vanadium, 4 parts of chromium, 11 parts of cobalt, 1.1 parts of nickel, 0.07 part of titanium, 0.9 part of lanthanum,
0.5 part of boron, 0.8 part of sulphur.
5. a kind of preparation method of aircraft wing rib material as described in claim 1-4 is any, is comprised the following steps：
1) by cast iron 16-34 parts, chromium 0.4-0.6 parts, manganese 2.5-4.5 parts, vanadium 0.06-0.09 parts, chromium 2-4 parts, cobalt 9-11 parts, nickel
0.7-1.1 parts, titanium 0.03-0.07 parts, lanthanum 0.5-0.9 parts, 1500 degree of -1800 degree is heated to, cools down 3-5 hours and be sufficiently stirred
Mixture A is made；
2) by mixture A made from step 1, addition boron 0.3-0.5 parts, sulphur 0.5-0.8 parts, continue to be heated to 2200-2500 degree
It is sufficiently mixed, mixture B is made, by mixture B air coolings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710752883.5A CN107574358A (en) | 2017-08-28 | 2017-08-28 | A kind of aircraft wing rib material and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710752883.5A CN107574358A (en) | 2017-08-28 | 2017-08-28 | A kind of aircraft wing rib material and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107574358A true CN107574358A (en) | 2018-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710752883.5A Pending CN107574358A (en) | 2017-08-28 | 2017-08-28 | A kind of aircraft wing rib material and preparation method thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN107574358A (en) |
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2017
- 2017-08-28 CN CN201710752883.5A patent/CN107574358A/en active Pending
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180112 |