CN109590420A - A kind of contour forging technique method of aircraft Main joint - Google Patents
A kind of contour forging technique method of aircraft Main joint Download PDFInfo
- Publication number
- CN109590420A CN109590420A CN201811570468.9A CN201811570468A CN109590420A CN 109590420 A CN109590420 A CN 109590420A CN 201811570468 A CN201811570468 A CN 201811570468A CN 109590420 A CN109590420 A CN 109590420A
- Authority
- CN
- China
- Prior art keywords
- blank
- main joint
- forging
- aircraft main
- technique method
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/04—Shaping in the rough solely by forging or pressing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/02—Preliminary treatment of metal stock without particular shaping, e.g. salvaging segregated zones, forging or pressing in the rough
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/06—Heating or cooling methods or arrangements specially adapted for performing forging or pressing operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K29/00—Arrangements for heating or cooling during processing
Abstract
The invention discloses a kind of aircraft Main joint contour forging technique methods, comprising: 1) heats ingot casting blank, the method for open die forging is used to carry out cogging to blank is turned to form open die forging blank；2) open die forging blank is processed as to the prefabricated blank of preset shape；3) prefabricated blank is processed into the pre-press with preforming high muscle；4) pre-press is formed into Main joint die forging final pressure part by final pressure process.By above-mentioned process, the contour forging technique method of aircraft Main joint disclosed in the embodiment of the present invention, can effectively avoid filling at the high muscle of Main joint it is discontented, fold, percolation phenomena such as, to obtain dimensional accuracy height, the uniform forging part of Deformation structure.
Description
Technical field
The present invention relates to aviation machine technical field, in particular to a kind of contour forging technique method of aircraft Main joint.
Background technique
Main joint is stress members important on aircraft, and the comprehensive performance of Main joint is to measure airframe quality
Major criterion.With the high speed development of aviation industry, the requirement to aircraft safety performance is continuously improved, and Main joint is as winged
Important load position when machine flight, directly affects the flight safety of aircraft.The Main joint of aircraft is generally high muscle complexity knot
The forging part of structure, structure is complicated, type chamber is more and deep, and wall is thin, fillet is small, and machining allowance is small, and molding difficulty is big.
Existing contour forging technique generally uses the square billet one-pass molding or post forming of simple shape, is easy when die forging
Phenomena such as filling is discontented with, folds, flowing at existing high muscle.
Therefore, how a kind of contour forging technique method of aircraft Main joint is provided, the high muscle of Main joint can be effectively avoided
Phenomena such as place's filling is discontented with, folds, flowing, to obtain dimensional accuracy height, the uniform forging part of Deformation structure is this field skill
The technical issues of art personnel's urgent need to resolve.
Summary of the invention
In view of this, the purpose of the present invention is to provide a kind of contour forging technique method of aircraft Main joint, it can be effective
Phenomena such as discontented, folding, percolation are filled at the high muscle of Main joint is avoided, to obtain dimensional accuracy height, Deformation structure is uniform
Forging part.
To achieve the goals above, the invention provides the following technical scheme:
A kind of aircraft Main joint contour forging technique method, comprising:
1) ingot casting blank is heated, the method for open die forging is used to carry out cogging to the ingot casting blank to form free forging stock
Material；
2) the open die forging blank is processed as to the prefabricated blank of preset shape；
3) prefabricated blank is processed into the pre-press with preforming high muscle；
4) pre-press is formed into final pressure part by final pressure process.
Preferably, in the step 1), the ingot casting blank heating temperature is 400 DEG C -450 DEG C.
Preferably, in the step 2), the prefabricated blank is provided with chamfering.
Preferably, in the step 2), the open die forging blank forms the prefabricated blank by machining processes.
Preferably, in the step 3), the pre-press is formed by prepressing procedures.
As can be seen from the above technical solutions, aircraft Main joint contour forging technique method disclosed in the embodiment of the present invention,
Include: 1) to heat ingot casting blank, the method for open die forging is used to carry out cogging to blank is turned to form open die forging blank；It 2) will be free
Forging stock material is processed as the prefabricated blank of preset shape；3) prefabricated blank is processed into the pre-press with preforming high muscle；4) will
Pre-press forms Main joint die forging final pressure part by final pressure process.By above-mentioned technique, fly disclosed in the embodiment of the present invention
The contour forging technique method of machine Main joint can effectively avoid phenomena such as discontented, folding, percolation are filled at the high muscle of Main joint,
To obtain dimensional accuracy height, the uniform forging part of Deformation structure.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below to embodiment or existing
Attached drawing needed in technical description is briefly described, it is clear that, the accompanying drawings in the following description is only this hair
Bright embodiment for those of ordinary skill in the art without creative efforts, can also be according to mentioning
The attached drawing of confession obtains other attached drawings.
Fig. 1 is the flow diagram of aircraft Main joint contour forging technique method disclosed in the embodiment of the present invention；
Fig. 2 is the structural schematic diagram of ingot casting blank disclosed in the embodiment of the present invention；
Fig. 3 is the structural schematic diagram of open die forging blank disclosed in the embodiment of the present invention；
Fig. 4 is the structural schematic diagram of prefabricated blank disclosed in the embodiment of the present invention；
Fig. 5 is the structural schematic diagram of pre-press disclosed in the embodiment of the present invention；
Fig. 6 is the structural schematic diagram of final pressure part disclosed in the embodiment of the present invention.
Wherein, the names of the parts are as follows:
1- ingot casting blank, 2- open die forging blank, 3- prefabricated blank, 4- pre-press, 5- final pressure part.
Specific embodiment
In view of this, core of the invention is to provide a kind of contour forging technique method of aircraft Main joint, it can be effective
Phenomena such as discontented, folding, percolation are filled at the high muscle of Main joint is avoided, to obtain dimensional accuracy height, Deformation structure is uniform
Forging part.
To make those skilled in the art more fully understand the present invention program, below connection with figures and specific embodiment pair
The present invention is described in further detail.
Aircraft Main joint contour forging technique method disclosed in the embodiment of the present invention, comprising: 1) heat ingot casting blank 1, adopt
Cogging is carried out to form open die forging blank 2 to blank 1 is turned with the method for open die forging；2) open die forging blank 2 is processed as default shape
The prefabricated blank 3 of shape；3) prefabricated blank 3 is processed into the pre-press 4 with preforming high muscle；4) pre-press 4 is passed through into final pressure
Process forms final pressure part 5.By above-mentioned technique, the contour forging technique method of aircraft Main joint disclosed in the embodiment of the present invention,
Phenomena such as discontented, folding, percolation are filled at the high muscle of Main joint can be effectively avoided, to obtain dimensional accuracy height, deformation group
Knit uniform forging part.
It is to be understood that the pre-compaction process of pre-press 4 is to be molded by pre-pressing die, so that the deformation of prefabricated blank 3, metal
It is flowed in die cavity, achievees the effect that reasonable deposit, to form the pre-press 4 with preforming high muscle.
It should be noted that the heating temperature of ingot casting blank 1 is 400 DEG C -450 DEG C in step 1).When ingot casting blank 1
When being heated to 400 DEG C -450 DEG C and spending, it can the method for open die forging is used to carry out cogging to ingot casting blank to form free forging stock
Material 2.
In step 2), prefabricated blank 3 is provided with chamfering, and the setting of chamfering can effectively improve the molding precision of forging and matter
Amount.
In step 2), open die forging blank 2 forms prefabricated blank 3 by machining processes.
In step 3), pre-press 4 is formed by prepressing procedures.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (5)
1. a kind of aircraft Main joint contour forging technique method characterized by comprising
1) ingot casting blank (1) is heated, the method for open die forging is used to carry out cogging to the ingot casting blank (1) to form free forging stock
Expect (2)；
2) the open die forging blank (2) is processed as to the prefabricated blank (3) of preset shape；
3) prefabricated blank (3) is processed into the pre-press (4) with preforming high muscle；
4) pre-press (4) are formed into final pressure part (5) by final pressure process.
2. aircraft Main joint contour forging technique method according to claim 1, which is characterized in that in the step 1),
Ingot casting blank (1) heating temperature is 400 DEG C -450 DEG C.
3. aircraft Main joint contour forging technique method according to claim 1, which is characterized in that in the step 2),
The prefabricated blank (2) is provided with chamfering.
4. aircraft Main joint contour forging technique method according to claim 1, which is characterized in that in the step 2),
The open die forging blank (2) forms the prefabricated blank (3) by machining processes.
5. aircraft Main joint contour forging technique method according to claim 1, which is characterized in that in the step 3),
The pre-press (4) is formed by prepressing procedures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811570468.9A CN109590420A (en) | 2018-12-21 | 2018-12-21 | A kind of contour forging technique method of aircraft Main joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811570468.9A CN109590420A (en) | 2018-12-21 | 2018-12-21 | A kind of contour forging technique method of aircraft Main joint |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109590420A true CN109590420A (en) | 2019-04-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811570468.9A Pending CN109590420A (en) | 2018-12-21 | 2018-12-21 | A kind of contour forging technique method of aircraft Main joint |
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| CN (1) | CN109590420A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20170136308A (en) * | 2016-06-01 | 2017-12-11 | 정명률 | Drone |
| CN107745063A (en) * | 2017-12-06 | 2018-03-02 | 西南铝业（集团）有限责任公司 | A kind of contour forging technique of aircraft wheel hub |
| CN108472712A (en) * | 2016-01-14 | 2018-08-31 | 奥科宁克公司 | Method for producing forging product and other converted products |
| US20180281933A1 (en) * | 2017-03-31 | 2018-10-04 | Qualcomm Incorporated | Double Folding Drone Arms with Landing Gear |
-
2018
- 2018-12-21 CN CN201811570468.9A patent/CN109590420A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108472712A (en) * | 2016-01-14 | 2018-08-31 | 奥科宁克公司 | Method for producing forging product and other converted products |
| KR20170136308A (en) * | 2016-06-01 | 2017-12-11 | 정명률 | Drone |
| US20180281933A1 (en) * | 2017-03-31 | 2018-10-04 | Qualcomm Incorporated | Double Folding Drone Arms with Landing Gear |
| CN107745063A (en) * | 2017-12-06 | 2018-03-02 | 西南铝业（集团）有限责任公司 | A kind of contour forging technique of aircraft wheel hub |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190409 |
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| RJ01 | Rejection of invention patent application after publication |