CN107699814A - A kind of aircraft wing back rest web material and preparation method thereof - Google Patents

A kind of aircraft wing back rest web material and preparation method thereof Download PDF

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Publication number
CN107699814A
CN107699814A CN201710751965.8A CN201710751965A CN107699814A CN 107699814 A CN107699814 A CN 107699814A CN 201710751965 A CN201710751965 A CN 201710751965A CN 107699814 A CN107699814 A CN 107699814A
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CN
China
Prior art keywords
parts
back rest
web material
aircraft wing
wing back
Prior art date
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Pending
Application number
CN201710751965.8A
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Chinese (zh)
Inventor
徐淑美
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Love To Fly Off Qingdao Aviation Technology Co Ltd
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Love To Fly Off Qingdao Aviation Technology Co Ltd
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Priority to CN201710751965.8A priority Critical patent/CN107699814A/en
Publication of CN107699814A publication Critical patent/CN107699814A/en
Pending legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C22/00—Alloys based on manganese
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C22C30/04—Alloys containing less than 50% by weight of each constituent containing tin or lead
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C33/00—Making ferrous alloys
    • C22C33/04—Making ferrous alloys by melting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/005—Ferrous alloys, e.g. steel alloys containing rare earths, i.e. Sc, Y, Lanthanides
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/008—Ferrous alloys, e.g. steel alloys containing tin
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/50—Ferrous alloys, e.g. steel alloys containing chromium with nickel with titanium or zirconium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/52—Ferrous alloys, e.g. steel alloys containing chromium with nickel with cobalt
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/58—Ferrous alloys, e.g. steel alloys containing chromium with nickel with more than 1.5% by weight of manganese

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Tires In General (AREA)

Abstract

The invention discloses a kind of aircraft wing back rest web material and preparation method thereof, includes following component according to mass fraction：5 12 parts of iron, 0.07 0.15 parts of molybdenum, 0.05 0.07 parts of gadolinium, 0.05 0.13 parts of cobalt, 0.8 1.2 parts of nickel, 0.1 0.3 parts of neodymium, 0.4 0.6 parts of titanium, 0.06 0.08 parts of tin, 4.5 7.5 parts of manganese, 0.2 0.4 parts of chromium, 0.01 0.04 parts of lanthanum, 0.2 0.4 parts of boron, a kind of aircraft wing back rest web material of the present invention, there is provided a kind of intensity hardness is high, corrosion resistant aircraft wing back rest web material.

Description

A kind of aircraft wing back rest web material and preparation method thereof
Technical field
The present invention relates to a kind of alloy material, in particular to a kind of aircraft wing back rest web material and its preparation side Method.
Background technology
Web is subject to where the core of the whole weight of aircraft after aircraft wing, the back rest be aircraft primary load bearing parts it One, aircraft is on high in flight course, and wing rear spar is repeatedly subjected to change simultaneously the load of size and Orientation, in long-term use Easily it is broken, so very high to its material requirements, unimach on the market, flies in the case where aircraft bears adverse circumstances now OK, stress is larger, toughness deficiency, heavier mass, endangers the safety of aircraft traveling, at present urgent problem, currently without Intensity hardness is high, the aircraft wing back rest web material of good corrosion resistance, therefore researches and develops a kind of intensity hardness height, good corrosion resistance Aircraft wing back rest web material turn into current urgent problem.
The content of the invention
The invention provides a kind of aircraft wing back rest web material and preparation method thereof.
To achieve the above object, the present invention provides following technical scheme：
A kind of aircraft wing back rest web material, include following component according to mass fraction：
Iron 5-12 parts, molybdenum 0.07-0.15 parts, gadolinium 0.05-0.07 parts, cobalt 0.05-0.13 parts, nickel 0.8-1.2 parts, neodymium 0.1- 0.3 part, titanium 0.4-0.6 parts, tin 0.06-0.08 parts, manganese 4.5-7.5 parts, chromium 0.2-0.4 parts, lanthanum 0.01-0.04 parts, boron 0.2- 0.4 part.
Further, following composition is included according to mass fraction：
5 parts of iron, 0.07 part of molybdenum, 0.05 part of gadolinium, 0.05 part of cobalt, 0.8 part of nickel, 0.1 part of neodymium, 0.4 part of titanium, 0.06 part of tin, manganese 4.5 parts, 0.2 part of chromium, 0.01 part of lanthanum, 0.2 part of boron.
Further, following composition is included according to mass fraction：
8 parts of iron, 0.11 part of molybdenum, 0.06 part of gadolinium, 0.08 part of cobalt, 1 part of nickel, 0.2 part of neodymium, 0.5 part of titanium, 0.07 part of tin, manganese 6 Part, 0.3 part of chromium, 0.03 part of lanthanum, 0.3 part of boron.
Further, following composition is included according to mass fraction：
12 parts of iron, 0.15 part of molybdenum, 0.07 part of gadolinium, 0.13 part of cobalt, 1.2 parts of nickel, 0.3 part of neodymium, 0.6 part of titanium, 0.08 part of tin, manganese 7.5 parts, 0.4 part of chromium, 0.04 part of lanthanum, 0.4 part of boron.
Further, the preparation method of aircraft wing back rest web material, is comprised the following steps：
1) by iron 5-12 parts, molybdenum 0.07-0.15 parts, gadolinium 0.05-0.07 parts, cobalt 0.05-0.13 parts, nickel 0.8-1.2 parts, neodymium 0.1-0.3 parts, titanium 0.4-0.6 parts, tin 0.06-0.08 parts, manganese 4.5-7.5 parts, chromium 0.2-0.4 parts, lanthanum 0.01-0.04 parts, add Heat cools down 3-5 hours and is sufficiently stirred obtained mixture A to 700 degree of -1000 degree；
2) by mixture A made from step 1, boron 0.2-0.4 parts are added, continue to be heated to 1500-2000 degree fully mixed Close, mixture B is made, by mixture B water coolings.
The beneficial effects of the invention are as follows：
1st, intensity is high.
2nd, good corrosion resistance.
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 back rest web material and preparation method thereof, include following component according to mass fraction：
Iron 5-12 parts, molybdenum 0.07-0.15 parts, gadolinium 0.05-0.07 parts, cobalt 0.05-0.13 parts, nickel 0.8-1.2 parts, neodymium 0.1- 0.3 part, titanium 0.4-0.6 parts, tin 0.06-0.08 parts, manganese 4.5-7.5 parts, chromium 0.2-0.4 parts, lanthanum 0.01-0.04 parts, boron 0.2- 0.4 part.
The preparation method of above-mentioned formula：
1) by iron 5-12 parts, molybdenum 0.07-0.15 parts, gadolinium 0.05-0.07 parts, cobalt 0.05-0.13 parts, nickel 0.8-1.2 parts, neodymium 0.1-0.3 parts, titanium 0.4-0.6 parts, tin 0.06-0.08 parts, manganese 4.5-7.5 parts, chromium 0.2-0.4 parts, lanthanum 0.01-0.04 parts, add Heat cools down 3-5 hours and is sufficiently stirred obtained mixture A to 700 degree of -1000 degree；
2) by mixture A made from step 1, boron 0.2-0.4 parts are added, continue to be heated to 1500-2000 degree fully mixed Close, mixture B is made, by mixture B water coolings.
Embodiment two：
A kind of aircraft wing back rest web material includes following component according to mass fraction：
5 parts of iron, 0.07 part of molybdenum, 0.05 part of gadolinium, 0.05 part of cobalt, 0.8 part of nickel, 0.1 part of neodymium, 0.4 part of titanium, 0.06 part of tin, manganese 4.5 parts, 0.2 part of chromium, 0.01 part of lanthanum, 0.2 part of boron.
Embodiment three：
A kind of aircraft wing back rest web material and preparation method thereof, include following composition according to mass fraction：
8 parts of iron, 0.11 part of molybdenum, 0.06 part of gadolinium, 0.08 part of cobalt, 1 part of nickel, 0.2 part of neodymium, 0.5 part of titanium, 0.07 part of tin, manganese 6 Part, 0.3 part of chromium, 0.03 part of lanthanum, 0.3 part of boron.
Example IV：
A kind of aircraft wing back rest web material and preparation method thereof, include following composition according to mass fraction：
12 parts of iron, 0.15 part of molybdenum, 0.07 part of gadolinium, 0.13 part of cobalt, 1.2 parts of nickel, 0.3 part of neodymium, 0.6 part of titanium, 0.08 part of tin, manganese 7.5 parts, 0.4 part of chromium, 0.04 part of lanthanum, 0.4 part of boron.
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 back rest web material, include following component according to mass fraction：
Iron 5-12 parts, molybdenum 0.07-0.15 parts, gadolinium 0.05-0.07 parts, cobalt 0.05-0.13 parts, nickel 0.8-1.2 parts, neodymium 0.1-0.3 Part, titanium 0.4-0.6 parts, tin 0.06-0.08 parts, manganese 4.5-7.5 parts, chromium 0.2-0.4 parts, lanthanum 0.01-0.04 parts, boron 0.2-0.4 Part.
2. a kind of aircraft wing back rest web material according to claim 1, include following composition according to mass fraction：
5 parts of iron, 0.07 part of molybdenum, 0.05 part of gadolinium, 0.05 part of cobalt, 0.8 part of nickel, 0.1 part of neodymium, 0.4 part of titanium, 0.06 part of tin, manganese 4.5 Part, 0.2 part of chromium, 0.01 part of lanthanum, 0.2 part of boron.
3. a kind of aircraft wing back rest web material according to claim 1, include following composition according to mass fraction：
8 parts of iron, 0.11 part of molybdenum, 0.06 part of gadolinium, 0.08 part of cobalt, 1 part of nickel, 0.2 part of neodymium, 0.5 part of titanium, 0.07 part of tin, 6 parts of manganese, chromium 0.3 part, 0.03 part of lanthanum, 0.3 part of boron.
4. a kind of aircraft wing back rest web material according to claim 1, include following composition according to mass fraction：
12 parts of iron, 0.15 part of molybdenum, 0.07 part of gadolinium, 0.13 part of cobalt, 1.2 parts of nickel, 0.3 part of neodymium, 0.6 part of titanium, 0.08 part of tin, manganese 7.5 Part, 0.4 part of chromium, 0.04 part of lanthanum, 0.4 part of boron.
5. a kind of preparation method of aircraft wing back rest web material as described in claim 1-4 is any, is comprised the following steps：
1) by iron 5-12 parts, molybdenum 0.07-0.15 parts, gadolinium 0.05-0.07 parts, cobalt 0.05-0.13 parts, nickel 0.8-1.2 parts, neodymium 0.1- 0.3 part, titanium 0.4-0.6 parts, tin 0.06-0.08 parts, manganese 4.5-7.5 parts, chromium 0.2-0.4 parts, lanthanum 0.01-0.04 parts, be heated to 700 degree of -1000 degree, cool down 3-5 hours and be sufficiently stirred obtained mixture A；
2) by mixture A made from step 1, boron 0.2-0.4 parts are added, continues to be heated to 1500-2000 degree to be sufficiently mixed, makes Mixture B is obtained, by mixture B water coolings.
CN201710751965.8A 2017-08-28 2017-08-28 A kind of aircraft wing back rest web material and preparation method thereof Pending CN107699814A (en)

Priority Applications (1)

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CN201710751965.8A CN107699814A (en) 2017-08-28 2017-08-28 A kind of aircraft wing back rest web material and preparation method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710751965.8A CN107699814A (en) 2017-08-28 2017-08-28 A kind of aircraft wing back rest web material and preparation method thereof

Publications (1)

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CN107699814A true CN107699814A (en) 2018-02-16

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Application publication date: 20180216

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