CN109533284A - Rudder face frame-covering structure and its manufacture welding method - Google Patents
Rudder face frame-covering structure and its manufacture welding method Download PDFInfo
- Publication number
- CN109533284A CN109533284A CN201811459871.4A CN201811459871A CN109533284A CN 109533284 A CN109533284 A CN 109533284A CN 201811459871 A CN201811459871 A CN 201811459871A CN 109533284 A CN109533284 A CN 109533284A
- Authority
- CN
- China
- Prior art keywords
- rudder face
- covering
- skeleton
- hole
- rudder
- 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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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/60—Preliminary treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
- B23K26/702—Auxiliary equipment
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laser Beam Processing (AREA)
- Arc Welding In General (AREA)
Abstract
The present invention provides a kind of rudder face frame-covering structure and its manufacture welding method, increase a certain number of minor diameter holes in conventional skeleton structure, hole can communicate with one another the closed cavity of covering skeletal internal, and with extraneous connection.When covering skeleton airvane or aerofoil are by Aerodynamic Heating, if internal air temperature increases expansion, gas can flow out airvane or aerofoil by hole, covering will not bulging will not influence surface covering.Simultaneously, pass through the hole to communicate with one another using covering skeletal internal, it can use vacuum pump and low vacuum be pumped into the inner cavity to communicate with one another, realize that the combination of covering and skeleton is assembled, significantly simplify assembly device and assembling process, and reduce the presence of many presser feets in mechanical installation way, reduce the possibility interference to laser welding head welding movement.
Description
Technical field
The present invention relates to laser welding fields, and in particular, to a kind of rudder face frame-covering structure and its manufacture welding side
Method.
Background technique
Frame-covering structure, especially titanium alloy covering skeleton structure are by high-performance, lightweight and center of gravity Forward etc.
A series of advantages are applied widely on the airvane and stabilizer product of space flight model.Such as patent document
CN103522022A, CN104858542A, CN106425309A etc. have the manufacture of titanium alloy covering skeleton structure
Benefit research, not only has studied laser welding and electron beam welding etc. in process, it is also proposed that the more excellent assembly such as embedded
Relationship.
However, starting heating problems are often faced with when airvane and stabilizer are applied on tactical weapon, in high speed
When long endurance Service Environment, surface temperature rises comparatively fast, and can quickly heat frame-covering structure part entirety, and its internal net
The gas meeting expanded by heating of lattice hollow cavity, may cause the bulging phenomenon of covering, changes the aerodynamic configuration of rudder and the wing, Jin Erke
The Pneumatic power flight performance of rudder and the wing can be influenced, if rudder and wing surface cover thermal protective coating, the bulging of covering may
The peeling for causing thermal protective coating, causes serious consequence.
To sum up, existing rudder face structure and manufacturing method can not effectively solve the problems, such as starting heating.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of rudder face frame-covering structure and its manufacture welderings
Connect method.
A kind of rudder face frame-covering structure provided according to the present invention, including rudder face covering and rudder face skeleton；The rudder face
Covering is embedded on rudder face skeleton, forms the rudder face for having multiple internal cavities.
Preferably, it is provided with through-hole on the rudder face skeleton, so that the multiple internal cavities having inside rudder face are mutually connected
It is logical.
Preferably, the internal cavity can also be communicated with the outside world by the through-hole being arranged on rudder face skeleton.
Preferably, the axis of the through-hole is parallel to rudder face skin-surface.
Preferably, the skeleton structure bosom position of rudder face skeleton is arranged in the through-hole.
A kind of rudder face frame-covering structure manufacture welding method provided according to the present invention, includes the following steps:
Rudder face skeleton manufacturing step: rudder face skeleton of the processing and manufacturing with interior bone, lap weld and lock back welding seam；
Rudder face covering manufacturing step: processing and manufacturing stitches rudder face covering with lap weld and lock back welding；
Formal welding step: rudder face covering and rudder face skeleton are formally welded by rudder face by laser.
Preferably, rudder face frame-covering structure manufacture welding method provided by the invention further includes following steps:
Installation step: combining rudder face covering and rudder face skeleton, and using the through-hole of vacuum pump connection rudder face skeleton and outside
The internal cavity interconnected is evacuated to low vacuum by one end of boundary's connection, realizes closely combining for rudder face covering and rudder face skeleton
Assembly；
Laser spot welding step: stitching path along lap weld and lock back welding, passes through the fixed rudder face covering of laser spot welding and rudder face
Skeleton.
Preferably, rudder face frame-covering structure manufacture welding method provided by the invention further includes following steps:
Weld preparation step: rudder face covering and rudder face skeleton are pre-processed；
Wherein, the pretreatment includes any one of cleaning, pickling and drying or multiple combinations.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, rudder face frame-covering structure provided by the invention has simple structure, good reliability, manufacturing cost lower excellent
Point；
2, rudder face frame-covering structure provided by the invention is made in covering skeleton by increasing hole design on skeleton
Closed cavity interconnect and with extraneous connection, when covering skeleton airvane or aerofoil are by Aerodynamic Heating, if interior
Portion's gas temperature increases expansion, and gas can flow out airvane or aerofoil by hole, covering will not bulging will not influence
Surface covering further increases reliability；
3, rudder face frame-covering structure provided by the invention can by the hole to be communicated with one another using covering skeletal internal
To utilize vacuum pump, low vacuum is pumped into the inner cavity to communicate with one another, realizes that the combination of covering and skeleton is assembled, significantly simplifies
Device and assembling process are assembled, and reduces the presence of many presser feets in mechanical installation way, is reduced to laser welding
The possibility interference of head welding movement.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the preference structural schematic diagram of rudder face frame-covering structure provided by the invention；
Fig. 2 is the preference flow diagram that rudder face frame-covering structure provided by the invention manufactures welding method
It is shown in figure:
Rudder face covering 1
Rudder face skeleton 2
Through-hole 3
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
A kind of rudder face frame-covering structure provided according to the present invention, including rudder face covering 1 and rudder face skeleton 2；The rudder
Face covering 1 is embedded on rudder face skeleton 2, forms the rudder face for having multiple internal cavities.
Preferably, it is provided with through-hole 3 on the rudder face skeleton 2, so that the multiple internal cavities having inside rudder face are mutual
Connection.The internal cavity can also be communicated with the outside world by the through-hole 3 being arranged on rudder face skeleton 2.The axis of the through-hole 3 is flat
Row is in 1 surface of rudder face covering.The skeleton structure bosom position of rudder face skeleton 2 is arranged in the through-hole 3.
A kind of rudder face frame-covering structure manufacture welding method provided according to the present invention, includes the following steps:
Rudder face skeleton manufacturing step: rudder face skeleton of the processing and manufacturing with interior bone 3, lap weld and lock back welding seam
2；
Rudder face covering manufacturing step: processing and manufacturing stitches rudder face covering 1 with lap weld and lock back welding；
Formal welding step: rudder face covering 1 and rudder face skeleton 2 are formally welded by rudder face by laser.
Specifically, rudder face frame-covering structure manufacture welding method provided by the invention further includes following steps:
Installation step: combining rudder face covering 1 and rudder face skeleton 2, and uses the through-hole 3 of vacuum pump connection rudder face skeleton 2
The internal cavity interconnected is evacuated to low vacuum by the one end being in communication with the outside, and realizes the tight of rudder face covering 1 and rudder face skeleton 2
Close combination assembly；
Laser spot welding step: stitching path along lap weld and lock back welding, passes through the fixed rudder face covering 1 of laser spot welding and rudder face
Skeleton 2.
Weld preparation step: rudder face covering 1 and rudder face skeleton 2 are pre-processed；
Wherein, the pretreatment includes any one of cleaning, pickling and drying or multiple combinations.
More specifically, the frame-covering structure being currently widely used, is all made of the closed structure design of internal cavity.This hair
Bright to increase a certain number of minor diameter holes in conventional skeleton structure, hole can communicate with one another the envelope of covering skeletal internal
Closed chamber body, and with extraneous connection.When covering skeleton airvane or aerofoil are by Aerodynamic Heating, if internal air temperature liter
High expansion, gas can flow out airvane or aerofoil by hole, covering will not bulging will not influence surface covering.Together
When, by the hole to be communicated with one another using covering skeletal internal, can use vacuum pump the inner cavity to communicate with one another is pumped into it is low true
Sky realizes that the combination of covering and skeleton is assembled, significantly simplifies assembly device and assembling process, and reduce mechanical clamping
The presence of many presser feets in mode reduces the possibility interference to laser welding head welding movement.Rudder face provided by the invention
Frame-covering structure can continue to use original laser welding process process and its parameter, but the fixed use of assembly of covering skeleton
Vacuum pump.
Further, steps are as follows for preference of the invention:
(1) titanium alloy framework is manufactured using machine Milling Machining, hole diameter Φ 2mm；Covering is using laser cutting manufacture, covering
Thickness 1mm；
(2) titanium alloy covering and skeleton carry out pickling and drying；
(3) skeleton is imbedded in the covering of two sides, is combined assembly, and take out skeleton covering inner cavity using vacuum absorption device
Low vacuum realizes the close fit of covering and skeleton；
(4) realize that the weld seam of covering and skeleton is fixed using laser spot welding technique, the main technologic parameters of spot welding are as follows: laser
Power is 800W, and speed of welding 0.5m/min, defocusing amount is -1mm；
(5) connection of covering skeleton rudder face is realized using double light beam laser mirror image welding procedure；The technique of two beam laser is joined
Number is completely the same: laser power 2000W, speed of welding 1.5m/min, and defocusing amount is -1mm.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (8)
1. a kind of rudder face frame-covering structure, which is characterized in that including rudder face covering (1) and rudder face skeleton (2)；The rudder face covers
Skin (1) is embedded on rudder face skeleton (2), forms the rudder face for having multiple internal cavities.
2. rudder face frame-covering structure according to claim 1, which is characterized in that be provided on the rudder face skeleton (2)
Through-hole (3), so that the multiple internal cavities having inside rudder face interconnect.
3. rudder face frame-covering structure according to claim 2, which is characterized in that the internal cavity can also pass through setting
Through-hole (3) on rudder face skeleton (2) communicates with the outside world.
4. rudder face frame-covering structure according to claim 2 or 3, which is characterized in that the axis of the through-hole (3) is parallel
In rudder face covering (1) surface.
5. rudder face frame-covering structure according to claim 2 or 3, which is characterized in that the through-hole (3) is arranged in rudder face
The skeleton structure bosom position of skeleton (2).
6. a kind of rudder face frame-covering structure manufactures welding method, which comprises the steps of:
Rudder face skeleton manufacturing step: rudder face skeleton of the processing and manufacturing with interior bone (3), lap weld and lock back welding seam
(2)；
Rudder face covering manufacturing step: processing and manufacturing is with lap weld and lock back welding seam rudder face covering (1)；
Formal welding step: rudder face covering (1) and rudder face skeleton (2) are formally welded by rudder face by laser.
7. rudder face frame-covering structure according to claim 6 manufactures welding method, which is characterized in that further include walking as follows
It is rapid:
Installation step: combining rudder face covering (1) and rudder face skeleton (2), and uses the through-hole of vacuum pump connection rudder face skeleton (2)
(3) internal cavity interconnected is evacuated to low vacuum, realizes rudder face covering (1) and rudder face skeleton by the one end being in communication with the outside
(2) closely combine assembly；
Laser spot welding step: path is stitched along lap weld and lock back welding, passes through laser spot welding fixed rudder face covering (1) and rudder face bone
Frame (2).
8. rudder face frame-covering structure according to claim 7 manufactures welding method, which is characterized in that further include walking as follows
It is rapid:
Weld preparation step: rudder face covering (1) and rudder face skeleton (2) are pre-processed；
Wherein, the pretreatment includes any one of cleaning, pickling and drying or multiple combinations.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811459871.4A CN109533284A (en) | 2018-11-30 | 2018-11-30 | Rudder face frame-covering structure and its manufacture welding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811459871.4A CN109533284A (en) | 2018-11-30 | 2018-11-30 | Rudder face frame-covering structure and its manufacture welding method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109533284A true CN109533284A (en) | 2019-03-29 |
Family
ID=65851999
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811459871.4A Pending CN109533284A (en) | 2018-11-30 | 2018-11-30 | Rudder face frame-covering structure and its manufacture welding method |
Country Status (1)
| Country | Link |
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| CN (1) | CN109533284A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110625335A (en) * | 2019-09-02 | 2019-12-31 | 北京星航机电装备有限公司 | Welding deformation control method for high-aspect-ratio framework skin wing type component |
| CN113146622A (en) * | 2021-03-22 | 2021-07-23 | 哈尔滨工业大学 | Visual identification method for laser welding of framework skin structure |
| CN113770531A (en) * | 2021-09-14 | 2021-12-10 | 上海杭和智能科技有限公司 | Laser welding method and system for circular seam lock bottom joint |
| CN115889997A (en) * | 2022-12-30 | 2023-04-04 | 华钛空天(北京)技术有限责任公司 | Method for welding control surface by laser welding |
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| CN104422350A (en) * | 2013-08-28 | 2015-03-18 | 上海精密计量测试研究所 | Foldable control surface and anti-defense missile using the same |
| CN104625406A (en) * | 2014-12-15 | 2015-05-20 | 湖北三江航天红阳机电有限公司 | Adsorption clamping equipment for framework covering laser welding and method achieved through adsorption clamping equipment |
| CN106425309A (en) * | 2016-11-14 | 2017-02-22 | 北京星航机电装备有限公司 | Method for machining and manufacturing titanium alloy folding airfoils |
| CN107717224A (en) * | 2017-09-26 | 2018-02-23 | 北京普惠三航科技有限公司 | The processing method of the hollow lightweight aerofoil of titanium alloy |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2014196881A (en) * | 2013-03-29 | 2014-10-16 | 三菱重工業株式会社 | Cooling device and cooling method |
| CN104422350A (en) * | 2013-08-28 | 2015-03-18 | 上海精密计量测试研究所 | Foldable control surface and anti-defense missile using the same |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110625335A (en) * | 2019-09-02 | 2019-12-31 | 北京星航机电装备有限公司 | Welding deformation control method for high-aspect-ratio framework skin wing type component |
| CN113146622A (en) * | 2021-03-22 | 2021-07-23 | 哈尔滨工业大学 | Visual identification method for laser welding of framework skin structure |
| CN113146622B (en) * | 2021-03-22 | 2022-07-05 | 哈尔滨工业大学 | Visual identification method for laser welding of framework skin structure |
| CN113770531A (en) * | 2021-09-14 | 2021-12-10 | 上海杭和智能科技有限公司 | Laser welding method and system for circular seam lock bottom joint |
| CN115889997A (en) * | 2022-12-30 | 2023-04-04 | 华钛空天(北京)技术有限责任公司 | Method for welding control surface by laser welding |
| CN115889997B (en) * | 2022-12-30 | 2024-03-12 | 华钛空天(北京)技术有限责任公司 | Method for welding control surface by laser welding |
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Application publication date: 20190329 |