CN112045193A - Outer cylinder of aircraft landing gear and landing gear thereof - Google Patents
Outer cylinder of aircraft landing gear and landing gear thereof Download PDFInfo
- Publication number
- CN112045193A CN112045193A CN202010946893.4A CN202010946893A CN112045193A CN 112045193 A CN112045193 A CN 112045193A CN 202010946893 A CN202010946893 A CN 202010946893A CN 112045193 A CN112045193 A CN 112045193A
- Authority
- CN
- China
- Prior art keywords
- landing gear
- aircraft landing
- strength steel
- aircraft
- thick bamboo
- 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.)
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Links
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 38
- 239000010959 steel Substances 0.000 claims abstract description 38
- 238000000034 method Methods 0.000 claims abstract description 32
- 229910000797 Ultra-high-strength steel Inorganic materials 0.000 claims abstract description 15
- 239000000843 powder Substances 0.000 claims description 24
- 238000001513 hot isostatic pressing Methods 0.000 claims description 8
- 235000017166 Bambusa arundinacea Nutrition 0.000 abstract description 12
- 235000017491 Bambusa tulda Nutrition 0.000 abstract description 12
- 241001330002 Bambuseae Species 0.000 abstract description 12
- 235000015334 Phyllostachys viridis Nutrition 0.000 abstract description 12
- 239000011425 bamboo Substances 0.000 abstract description 12
- 238000004519 manufacturing process Methods 0.000 description 23
- 238000002347 injection Methods 0.000 description 6
- 239000007924 injection Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 239000000243 solution Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000009694 cold isostatic pressing Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000007712 rapid solidification Methods 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/06—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of threaded articles, e.g. nuts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
The application specifically relates to an aircraft landing gear urceolus includes: an inner layer tube made of high strength steel; the outer layer cylinder is made of ultra-high strength steel and is sleeved outside the inner layer cylinder. Above-mentioned aircraft landing gear urceolus design aircraft landing gear urceolus is including being located the inboard inlayer section of thick bamboo, be located the outer section of thick bamboo in the outside, the inlayer section of thick bamboo, outer section of thick bamboo cup joints together, closely combine to form the aircraft landing gear urceolus, its outer section of thick bamboo is made with the super strength steel, when being applied to the aircraft landing gear, can take off at the aircraft, the landing in-process bears great impact load, furthermore, this aircraft landing gear inlayer section of thick bamboo is made with the high strength steel, density is less, the quality is lighter, can effectively avoid the aircraft landing gear wholly overweight, and compare in the aircraft landing gear urceolus. The application also specifically relates to an aircraft landing gear, and the outer cylinder of the aircraft landing gear is the aircraft landing gear outer cylinder.
Description
Technical Field
The application belongs to the technical field of design of an aircraft landing gear, and particularly relates to an aircraft landing gear outer barrel and an aircraft landing gear thereof.
Background
The aircraft landing gear bears huge impact load at the aircraft take-off and landing process, and for making the landing gear effectively bear huge impact load, its part adopts super strength steel forging to process to obtain at present, because super strength steel density is big, makes the landing gear have great quality, easily makes the landing gear wholly overweight, in addition, the processing difficulty, and the cost is high.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
The present application aims to provide an outer barrel for an aircraft landing gear and a landing gear therefore, which overcome or mitigate at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
one aspect provides an aircraft landing gear outer barrel comprising:
an inner layer tube made of high strength steel;
the outer layer cylinder is made of ultra-high strength steel and is sleeved outside the inner layer cylinder.
According to at least one embodiment of the application, in the aircraft landing gear outer barrel, the high-strength steel is 300M high-strength steel.
According to at least one embodiment of the application, in the aircraft landing gear outer barrel, the high-strength steel is 30CrMnSiNi2A high-strength steel.
According to at least one embodiment of the application, in the aircraft landing gear outer barrel, the ultra-high strength steel is A100 high strength steel.
According to at least one embodiment of the application, in the outer barrel of the aircraft landing gear, the outer barrel is consolidated outside the inner barrel in a hot isostatic pressing powder forming process.
Another aspect provides an aircraft landing gear, the outer barrel of the aircraft landing gear being any of the above-mentioned aircraft landing gear outer barrels.
In a further aspect, there is provided a method of manufacturing an outer barrel of an aircraft landing gear, comprising:
a process sheath is arranged on the outer side of the inner layer cylinder; wherein the inner layer cylinder is made of high-strength steel;
injecting ultrahigh-strength powder between the inner-layer cylinder and the process sheath, and placing in a hot isostatic pressing device to solidify the ultrahigh-strength steel powder to form an outer-layer cylinder;
and removing the process sheath to obtain the outer cylinder of the aircraft landing gear.
According to at least one embodiment of the application, in the method for manufacturing the outer cylinder of the aircraft landing gear, the high-strength steel is 300M high-strength steel.
According to at least one embodiment of the application, in the manufacturing method of the outer cylinder of the aircraft landing gear, the high-strength steel is 30CrMnSiNi2A high-strength steel.
According to at least one embodiment of the application, in the manufacturing method of the outer cylinder of the aircraft landing gear, the ultra-high-strength steel is A100 ultra-high-strength steel.
According to at least one embodiment of the application, in the manufacturing method of the outer cylinder of the aircraft landing gear, the ultrahigh-strength powder is injected between the inner cylinder and the process sheath, and specifically:
and (3) arranging a powder injection hole on the process sheath, injecting ultrahigh-strength powder between the inner layer cylinder and the process sheath through the powder injection hole, and then plugging the powder injection hole.
Drawings
FIG. 1 is a cross-sectional view of an outer barrel of an aircraft landing gear provided in an embodiment of the present application;
FIG. 2 is a schematic view of the outer barrel of an aircraft landing gear according to an embodiment of the present application;
wherein:
1-an inner layer cylinder; 2-outer layer cylinder; and 3-process wrapping.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
One aspect provides an aircraft landing gear outer barrel comprising:
an inner layer cylinder 1 made of high strength steel;
the outer layer cylinder 2 is made of ultra-high strength steel and is sleeved outside the inner layer cylinder 1.
To the aircraft landing gear urceolus that the above-mentioned embodiment disclosed, the technical personnel in the field can understand is, its design aircraft landing gear urceolus is including being located inboard inlayer section of thick bamboo 1, be located the outer section of thick bamboo 2 in the outside, inlayer section of thick bamboo 1, outer section of thick bamboo 2 cup joints together, it forms the aircraft landing gear urceolus to combine closely, to this can understand, the outer section of thick bamboo 2 of this aircraft landing gear urceolus is made with super strength steel, when being applied to the aircraft landing gear, can take off at the aircraft, bear great impact load in the landing process, in addition, this aircraft landing gear inlayer section of thick bamboo 1 is made with high strength steel, density is less, the quality is lighter, can effectively avoid the aircraft landing gear wholly overweight, and compare in the aircraft landing gear and.
In some optional embodiments, in the aircraft landing gear outer barrel, the high-strength steel is 300M high-strength steel.
In some alternative embodiments, the high strength steel in the outer barrel of the aircraft landing gear is 30CrMnSiNi2A high strength steel.
In some alternative embodiments, in the aircraft landing gear outer barrel, the ultra-high strength steel is a100 high strength steel.
In some alternative embodiments, in the aircraft landing gear outer cylinder, the outer cylinder 2 is consolidated outside the inner cylinder 1 in a hot isostatic pressing powder forming process, so that the outer cylinder 2 and the inner cylinder 1 are tightly combined.
On the other hand, the outer cylinder of the aircraft landing gear is any one of the outer cylinders, so that the aircraft landing gear can bear larger impact load in the take-off and landing processes of the aircraft, has lighter weight, avoids the overall overweight of the aircraft landing gear, and reduces the overall cost of the aircraft landing gear.
In a further aspect, there is provided a method of manufacturing an outer barrel of an aircraft landing gear, comprising:
a process sheath 3 is arranged outside the inner layer cylinder 1; wherein, the inner layer tube 1 is made of high-strength steel;
injecting ultrahigh-strength powder between the inner-layer cylinder 1 and the technological sheath 3, and placing in a hot isostatic pressing device to solidify the ultrahigh-strength steel powder to form an outer-layer cylinder 2;
and removing the process sheath 3 to obtain the outer cylinder of the aircraft landing gear.
With regard to the manufacturing method of the outer cylinder of the landing gear of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the manufacturing method is implemented based on a hot isostatic pressing powder forming process, the hot isostatic pressing powder forming process enables the material to be solidified by applying high-temperature and high-pressure media to the whole surface of the material at the same time, the dual advantages of powder metallurgy and cold isostatic pressing are integrated, the two steps of powder forming and sintering are combined into one step by combining with a rapid solidification technology, the product pressed by the forming process has a compact structure, the material properties are all the same, and the product properties can be greatly improved.
With regard to the manufacturing method of the outer cylinder of the landing gear of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the manufacturing method is implemented based on a hot isostatic pressure powder forming process, the inner cylinder 1 is used as a core mold, the outer cylinder 2 is formed by solidifying the ultra-steel strength steel powder outside the inner cylinder by matching with the process sheath 3, and the outer cylinder is tightly combined with the outer cylinder 2 to form the outer cylinder of the landing gear of the airplane, that is, the inner cylinder 1 is used as the core mold in the manufacturing process of the landing gear of the airplane, but does not need to be removed after the manufacturing of the outer cylinder of the landing gear of the airplane is completed, and is.
For the manufacturing method of the outer cylinder of the aircraft landing gear disclosed in the above embodiment, it can be understood by those skilled in the art that the manufacturing method is implemented based on a hot isostatic pressing powder forming process, and two different materials are tightly combined together in a mutual diffusion connection manner through a solid/powder interface, so that the manufacturing of a gradient structure is realized, the defect that the two materials cannot be tightly combined in the prior art is overcome, and the inner cylinder 1 and the outer cylinder 2 in the manufactured outer cylinder of the aircraft landing gear are tightly combined.
For the manufacturing method of the outer cylinder of the aircraft landing gear disclosed in the above embodiment, as can be understood by those skilled in the art, the outer cylinder 2 of the aircraft landing gear manufactured by the manufacturing method is made of ultra-high-strength steel, and when the manufacturing method is applied to the aircraft landing gear, the outer cylinder can bear larger impact load during the takeoff and landing processes of the aircraft, and in addition, the inner cylinder 1 is made of high-strength steel, has smaller density and lighter weight, can effectively prevent the whole overweight of the aircraft landing gear, and is lower in manufacturing cost compared with the case that the outer cylinder of the aircraft landing gear is made of single ultra-high-strength steel.
In some optional embodiments, in the method for manufacturing an outer cylinder of an aircraft landing gear, the high-strength steel is 300M high-strength steel.
In some optional embodiments, in the method for manufacturing the outer cylinder of the aircraft landing gear, the high-strength steel is 30CrMnSiNi2A high-strength steel.
In some optional embodiments, in the method for manufacturing an outer cylinder of an aircraft landing gear, the ultra-high strength steel is a100 ultra-high strength steel.
In some optional embodiments, in the above method for manufacturing an outer cylinder of an aircraft landing gear, ultra-high strength powder is injected between the inner cylinder 1 and the process sheath 3, specifically:
and (3) arranging a powder injection hole on the process sleeve 3, injecting ultrahigh-strength powder between the inner-layer cylinder 1 and the process sleeve 3 through the powder injection hole, and then plugging the powder injection hole.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (6)
1. An aircraft landing gear outer barrel, comprising:
an inner layer cylinder (1) made of high-strength steel;
the outer layer cylinder (2) is made of ultra-high strength steel and is sleeved on the outer side of the inner layer cylinder (1).
2. The outer barrel for an aircraft landing gear according to claim 1,
the high-strength steel is 300M high-strength steel.
3. The outer barrel for an aircraft landing gear according to claim 1,
the high-strength steel is 30CrMnSiNi2A high-strength steel.
4. The outer barrel for an aircraft landing gear according to claim 1,
the ultrahigh-strength steel is A100 high-strength steel.
5. The outer barrel for an aircraft landing gear according to claim 1,
the outer layer cylinder (2) is consolidated outside the inner layer cylinder (1) in a hot isostatic pressing powder forming process.
6. An aircraft landing gear, wherein the outer barrel of the landing gear is as claimed in any one of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010946893.4A CN112045193A (en) | 2020-09-10 | 2020-09-10 | Outer cylinder of aircraft landing gear and landing gear thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010946893.4A CN112045193A (en) | 2020-09-10 | 2020-09-10 | Outer cylinder of aircraft landing gear and landing gear thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112045193A true CN112045193A (en) | 2020-12-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010946893.4A Pending CN112045193A (en) | 2020-09-10 | 2020-09-10 | Outer cylinder of aircraft landing gear and landing gear thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN112045193A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06122974A (en) * | 1992-10-12 | 1994-05-06 | Daido Steel Co Ltd | Production of cylindrical target body |
| CN101138790A (en) * | 2007-08-09 | 2008-03-12 | 航天材料及工艺研究所 | Method of preparing titanium steel composite liquid route connecting tube of the complex construction connecting surface |
| CN105458255A (en) * | 2015-11-24 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for inspecting quality consistency of undercarriage product made of direct laser deposited and formed A-100 steel |
| CN105537274A (en) * | 2016-02-17 | 2016-05-04 | 安泰科技股份有限公司 | Preparation method of roll collar for rolling mill and roll collar prepared with method |
| CN105861953A (en) * | 2016-05-07 | 2016-08-17 | 惠安县泰达商贸有限责任公司 | Alloy material for aircraft landing gear |
| CN107538013A (en) * | 2017-06-19 | 2018-01-05 | 安泰科技股份有限公司 | A kind of circle shears blade and preparation method thereof |
| CN108247063A (en) * | 2018-01-29 | 2018-07-06 | 北京汇越新材料科技有限公司 | A kind of composite bimetal pipe material preparation method based on heat and other static pressuring processes |
| CN109158605A (en) * | 2018-08-24 | 2019-01-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of undercarriage outer cylinder and hound integral structure preparation method |
| CN109277573A (en) * | 2018-08-24 | 2019-01-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of production method of undercarriage piston rod |
| CN111570795A (en) * | 2020-05-13 | 2020-08-25 | 中国航发北京航空材料研究院 | Preparation of Ti2Method for manufacturing ALNb/Ti60 double-alloy disk |
-
2020
- 2020-09-10 CN CN202010946893.4A patent/CN112045193A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06122974A (en) * | 1992-10-12 | 1994-05-06 | Daido Steel Co Ltd | Production of cylindrical target body |
| CN101138790A (en) * | 2007-08-09 | 2008-03-12 | 航天材料及工艺研究所 | Method of preparing titanium steel composite liquid route connecting tube of the complex construction connecting surface |
| CN105458255A (en) * | 2015-11-24 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for inspecting quality consistency of undercarriage product made of direct laser deposited and formed A-100 steel |
| CN105537274A (en) * | 2016-02-17 | 2016-05-04 | 安泰科技股份有限公司 | Preparation method of roll collar for rolling mill and roll collar prepared with method |
| CN105861953A (en) * | 2016-05-07 | 2016-08-17 | 惠安县泰达商贸有限责任公司 | Alloy material for aircraft landing gear |
| CN107538013A (en) * | 2017-06-19 | 2018-01-05 | 安泰科技股份有限公司 | A kind of circle shears blade and preparation method thereof |
| CN108247063A (en) * | 2018-01-29 | 2018-07-06 | 北京汇越新材料科技有限公司 | A kind of composite bimetal pipe material preparation method based on heat and other static pressuring processes |
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| CN111570795A (en) * | 2020-05-13 | 2020-08-25 | 中国航发北京航空材料研究院 | Preparation of Ti2Method for manufacturing ALNb/Ti60 double-alloy disk |
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Application publication date: 20201208 |
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