CN112124571B - Outer cylinder of aircraft landing gear, manufacturing method and aircraft landing gear - Google Patents
Outer cylinder of aircraft landing gear, manufacturing method and aircraft landing gear Download PDFInfo
- Publication number
- CN112124571B CN112124571B CN202010947738.4A CN202010947738A CN112124571B CN 112124571 B CN112124571 B CN 112124571B CN 202010947738 A CN202010947738 A CN 202010947738A CN 112124571 B CN112124571 B CN 112124571B
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- China
- Prior art keywords
- cylinder
- landing gear
- ultra
- high strength
- aircraft landing
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 claims abstract description 46
- 229910000797 Ultra-high-strength steel Inorganic materials 0.000 claims abstract description 32
- 239000000843 powder Substances 0.000 claims abstract description 27
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 20
- 238000001513 hot isostatic pressing Methods 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 description 5
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000010959 steel Substances 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
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- 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
- B22F7/02—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 layers
- B22F7/04—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 layers with one or more layers not made from powder, e.g. made from solid metal
-
- 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
-
- 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
- B22F7/02—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 layers
- B22F7/04—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 layers with one or more layers not made from powder, e.g. made from solid metal
- B22F2007/042—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 layers with one or more layers not made from powder, e.g. made from solid metal characterised by the layer forming method
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Materials Engineering (AREA)
- Transportation (AREA)
- Powder Metallurgy (AREA)
Abstract
The application relates to an aircraft landing gear outer barrel, comprising: an inner tube made of ultra-high strength steel; the middle cylinder is made of titanium alloy and sleeved on the outer side of the inner cylinder; the outer layer cylinder is made of ultra-high strength steel and sleeved on the outer side of the middle cylinder. Furthermore, another aspect is directed to a method of manufacturing an outer cylinder of an aircraft landing gear, comprising: an inner-layer process sheath is arranged on the inner side of the middle cylinder, and an outer-layer process sheath is arranged on the outer side of the middle cylinder; injecting ultra-high strength steel powder between the inner process sheath and the middle cylinder, injecting ultra-high strength high powder between the outer process sheath and the middle cylinder, placing the ultra-high strength high powder in hot isostatic pressing equipment, solidifying the ultra-high strength steel powder between the inner process sheath and the middle cylinder to form an inner layer cylinder, and solidifying the ultra-high strength high powder between the outer process sheath and the middle cylinder to form an outer layer cylinder; and removing the inner technological sheath and the outer technological sheath to obtain the outer cylinder of the landing gear of the aircraft. And to an aircraft landing gear having the above-described outer aircraft landing gear cylinder.
Description
Technical Field
The application belongs to the technical field of aircraft landing gear design, and particularly relates to an aircraft landing gear outer cylinder, a manufacturing method and an aircraft landing gear thereof.
Background
The landing gear of the aircraft bears huge impact load in the process of taking off and landing of the aircraft, in order to enable the landing gear to effectively bear huge impact load, the current parts are mostly obtained by forging and processing ultra-high strength steel, and the ultra-high strength steel has large density, so that the landing gear has large mass, is easy to be overweight as a whole, is difficult to process and has high manufacturing cost.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an outer cylinder of an aircraft landing gear, a method of manufacturing the same and an aircraft landing gear thereof, which overcome or mitigate the technical drawbacks of at least one aspect known to exist.
The technical scheme of the application is as follows:
one aspect provides an aircraft landing gear outer barrel comprising:
an inner tube made of ultra-high strength steel;
the middle cylinder is made of titanium alloy and sleeved on the outer side of the inner cylinder;
the outer layer cylinder is made of ultra-high strength steel and sleeved on the outer side of the middle cylinder.
According to at least one embodiment of the present application, in the outer cylinder of the landing gear of the aircraft, the ultra-high strength steel is a100 ultra-high strength steel.
According to at least one embodiment of the present application, in the outer cylinder of the landing gear of the aircraft, the titanium alloy is TC11 titanium alloy.
Another aspect provides a method of manufacturing an outer cylinder of an aircraft landing gear, comprising:
an inner-layer process sheath is arranged on the inner side of the middle cylinder, and an outer-layer process sheath is arranged on the outer side of the middle cylinder;
injecting ultra-high strength steel powder between the inner process sheath and the middle cylinder, injecting ultra-high strength high powder between the outer process sheath and the middle cylinder, placing the ultra-high strength high powder in hot isostatic pressing equipment, solidifying the ultra-high strength steel powder between the inner process sheath and the middle cylinder to form an inner layer cylinder, and solidifying the ultra-high strength high powder between the outer process sheath and the middle cylinder to form an outer layer cylinder;
and removing the inner technological sheath and the outer technological sheath to obtain the outer cylinder of the landing gear of the aircraft.
According to at least one embodiment of the present application, in the method for manufacturing an outer cylinder of an aircraft landing gear described above, the intermediate cylinder is made of a titanium alloy.
According to at least one embodiment of the present application, in the method for manufacturing an outer cylinder of an aircraft landing gear described above, the titanium alloy is TC11 titanium alloy.
According to at least one embodiment of the present application, in the method for manufacturing an outer cylinder of an aircraft landing gear described above, the ultra-high strength steel is a100 ultra-high strength steel.
A further aspect provides an aircraft landing gear having an outer barrel of any one of the aircraft landing gear outer barrels described above.
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;
wherein:
1-an inner layer cylinder; 2-an intermediate cylinder; 3-an outer layer cylinder.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like, are intended to cover an element or article that appears before the term and that is recited after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1.
One aspect provides an aircraft landing gear outer barrel comprising:
an inner tube 1 made of ultra-high strength steel;
the middle cylinder 2 is made of titanium alloy and sleeved on the outer side of the inner cylinder 1;
the outer layer cylinder 3 is made of ultra-high strength steel and sleeved outside the middle cylinder 2.
For the outer cylinder of the landing gear disclosed in the above embodiment, it can be understood by those skilled in the art that the outer cylinder of the landing gear is designed to include the inner cylinder 1 located at the inner side, the middle cylinder 2 located at the middle and the outer cylinder 3 located at the outer side, the inner cylinder 1, the middle cylinder 2 and the outer cylinder 3 are sleeved together and tightly combined to form the outer cylinder of the landing gear, and in this way, the inner cylinder 1 and the outer cylinder 3 of the outer cylinder of the landing gear are made of ultra-high strength steel, and when the outer cylinder is applied to the landing gear of the aircraft, the inner cylinder 1 and the outer cylinder 3 of the landing gear can bear larger impact load in the process of taking off and landing the landing gear of the aircraft, in addition, the middle cylinder 2 of the landing gear of the aircraft is made of titanium alloy, the density is smaller, the mass is lighter, the overall overweight of the landing gear of the aircraft can be effectively avoided, and compared with the outer cylinder of the landing gear of the aircraft made of single ultra-high strength steel, the manufacturing cost is relatively lower.
In some alternative embodiments, the ultra-high strength steel in the outer cylinder of the landing gear is a100 ultra-high strength steel.
In some alternative embodiments, the titanium alloy in the outer cylinder of the landing gear is TC11 titanium alloy.
In another aspect, a method of manufacturing an outer cylinder of an aircraft landing gear is provided, comprising:
an inner-layer process sheath is arranged on the inner side of the middle cylinder 2, and an outer-layer process sheath is arranged on the outer side of the middle cylinder; wherein the intermediate cylinder 2 is made of titanium alloy;
injecting ultra-high strength steel powder between the inner process sheath and the middle cylinder 2, injecting ultra-high strength high powder between the outer process sheath and the middle cylinder 2, placing the ultra-high strength high powder in hot isostatic pressing equipment, solidifying the ultra-high strength steel powder between the inner process sheath and the middle cylinder 2 to form an inner cylinder 1, and solidifying the ultra-high strength high powder between the outer process sheath and the middle cylinder 2 to form an outer cylinder 3;
and removing the inner technological sheath and the outer technological sheath to obtain the outer cylinder of the landing gear of the aircraft.
As can be appreciated by those skilled in the art, the method for manufacturing the outer cylinder of the landing gear of the aircraft disclosed in the above embodiment is implemented based on a hot isostatic pressing powder forming process, wherein the hot isostatic pressing powder forming process is implemented by simultaneously and equally applying a high-temperature and high-pressure medium to the whole surface of a material, so that the material is solidified, the dual advantages of powder metallurgy and cold isostatic pressing are integrated, the two steps of powder forming and sintering are combined with a rapid solidification technology to form a single step, and the product pressed by the forming process has compact structure and the same material performance, so that the performance of the product can be greatly improved.
As for the method for manufacturing the outer cylinder of the landing gear of the aircraft disclosed in the above embodiment, it is also understood by those skilled in the art that the method is implemented based on the hot isostatic pressing powder forming process, the middle cylinder 2 is used as a core mold, the inner cylinder 1 and the outer cylinder 3 are formed by solidifying super steel strength steel powder on the inner side and the outer side of the middle cylinder by matching with the inner process sleeve and the outer process sleeve, and the middle cylinder 2 is tightly combined with the inner cylinder 1 and the outer cylinder 3 to form the outer cylinder of the landing gear of the aircraft, namely, the middle cylinder 2 is used as the core mold in the manufacturing process of the landing gear of the aircraft, but the middle cylinder 2 does not need to be removed after the manufacturing process of the outer cylinder of the landing gear of the aircraft is completed, but is reserved as a part in the outer cylinder structure of the landing gear of the aircraft, so that the manufacturing process is simple.
As can be further appreciated by those skilled in the art, the manufacturing method of the outer cylinder of the landing gear disclosed in the above embodiment is implemented based on a hot isostatic pressing powder forming process, which is implemented by tightly combining two different materials together in a manner of mutually diffusing and connecting through a solid/powder interface, so as to realize the manufacturing of a gradient structure, overcome the defect that the prior art cannot tightly combine the two materials, and enable the inner cylinder 1, the middle cylinder 2 and the outer cylinder 3 in the manufactured outer cylinder of the landing gear to be tightly combined.
In some alternative embodiments, in the method for manufacturing the outer cylinder of the landing gear of the aircraft, the titanium alloy is TC11 titanium alloy.
In some alternative embodiments, the ultra-high strength steel in the method of manufacturing an outer cylinder of an aircraft landing gear is a100 ultra-high strength steel.
In a further aspect, the outer cylinder of the aircraft landing gear is any one of the outer cylinders of the aircraft landing gear, so that the aircraft landing gear can bear larger impact load in the process of taking off and landing of an aircraft, has lighter weight, avoids the overall overweight of the aircraft landing gear, and reduces the overall manufacturing cost of the aircraft landing gear.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (7)
1. An outer cylinder of an aircraft landing gear, comprising:
an inner cylinder (1) made of ultra-high strength steel;
the middle cylinder (2) is made of titanium alloy and sleeved on the outer side of the inner cylinder (1);
and the outer layer cylinder (3) is made of ultra-high strength steel and sleeved outside the middle cylinder (2).
2. The outer cylinder of aircraft landing gear according to claim 1,
the ultra-high strength steel is A100 ultra-high strength steel.
3. An outer cylinder of an aircraft landing gear according to claim 2,
the titanium alloy is TC11 titanium alloy.
4. A method of manufacturing an outer cylinder for an aircraft landing gear, comprising:
an inner-layer process sheath is arranged on the inner side of the middle cylinder (2), and an outer-layer process sheath is arranged on the outer side of the middle cylinder;
injecting ultra-high strength steel powder between the inner layer process sheath and the middle cylinder (2), injecting ultra-high strength high powder between the outer layer process sheath and the middle cylinder (2), placing the ultra-high strength high powder in hot isostatic pressing equipment, solidifying the ultra-high strength steel powder between the inner layer process sheath and the middle cylinder (2) to form an inner layer cylinder (1), and solidifying the ultra-high strength high powder between the outer layer process sheath and the middle cylinder (2) to form an outer layer cylinder (3);
removing the inner-layer process sheath and the outer-layer process sheath to obtain an outer cylinder of the landing gear of the aircraft;
the intermediate cylinder (2) is made of titanium alloy.
5. The method for manufacturing an outer cylinder of an aircraft landing gear according to claim 4,
the titanium alloy is TC11 titanium alloy.
6. The method for manufacturing an outer cylinder of an aircraft landing gear according to claim 4,
the ultra-high strength steel is A100 ultra-high strength steel.
7. An aircraft landing gear, wherein the outer cylinder of the aircraft landing gear is the outer cylinder of the aircraft landing gear according to any one of claims 1 to 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010947738.4A CN112124571B (en) | 2020-09-10 | 2020-09-10 | Outer cylinder of aircraft landing gear, manufacturing method and aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010947738.4A CN112124571B (en) | 2020-09-10 | 2020-09-10 | Outer cylinder of aircraft landing gear, manufacturing method and aircraft landing gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112124571A CN112124571A (en) | 2020-12-25 |
| CN112124571B true CN112124571B (en) | 2023-07-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN202010947738.4A Active CN112124571B (en) | 2020-09-10 | 2020-09-10 | Outer cylinder of aircraft landing gear, manufacturing method and aircraft landing gear |
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| Country | Link |
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Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB676964A (en) * | 1949-01-14 | 1952-08-06 | Electro Hydraulics Ltd | Aeroplane landing gear |
| US4738339A (en) * | 1985-03-08 | 1988-04-19 | Tayco Developments, Inc. | Energy absorber device with composite plastic casing having high strength inner cylinder |
| DE102006004783A1 (en) * | 2005-03-26 | 2006-09-28 | Zf Friedrichshafen Ag | Vibration damper piston rod in steel of specific carbon and manganese content, used for engines and machines with piston rods and cylinders, comprises aluminum and titanium alloying additions |
| FR2939407B1 (en) * | 2008-12-05 | 2011-02-11 | Messier Dowty Sa | DEVICE FOR SHORTENING AN AIRCRAFT AIRCRAFT |
| US20120031516A1 (en) * | 2010-06-18 | 2012-02-09 | National Machine Company | Axle Sleeve Manufacturing Process |
| FR2975030B1 (en) * | 2011-05-10 | 2014-06-13 | Aubert & Duval Sa | HOT SPINNING METHOD FOR MAKING A METAL PIECE, WIRING TOOL FOR ITS USE AND ROD OF LANDING TRAIN SO REALIZED |
| RU119323U1 (en) * | 2012-03-06 | 2012-08-20 | Нижегородское открытое акционерное общество "Гидромаш" | AIRCRAFT CHASSIS RACK |
| DE102013014893A1 (en) * | 2013-09-06 | 2015-03-12 | Liebherr-Aerospace Lindenberg Gmbh | landing gear |
| CN104668417B (en) * | 2015-02-06 | 2016-06-29 | 西安交通大学 | Undercarriage urceolus forging radial forging formula strain-induced semisolid die forging technique |
| EP3279085A1 (en) * | 2016-08-04 | 2018-02-07 | Safran Landing Systems UK Limited | Aircraft landing gear shock absorber strut |
| CN207161597U (en) * | 2017-08-09 | 2018-03-30 | 安徽誉林汽车部件有限公司 | A kind of automotive suspension damping device |
| CN109296691B (en) * | 2018-11-09 | 2021-02-26 | 中国直升机设计研究所 | Double-cavity buffer |
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2020
- 2020-09-10 CN CN202010947738.4A patent/CN112124571B/en active Active
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| Publication number | Publication date |
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| CN112124571A (en) | 2020-12-25 |
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