CN114226999A - Laser cutting clamp for aircraft structural part - Google Patents
Laser cutting clamp for aircraft structural part Download PDFInfo
- Publication number
- CN114226999A CN114226999A CN202111536328.1A CN202111536328A CN114226999A CN 114226999 A CN114226999 A CN 114226999A CN 202111536328 A CN202111536328 A CN 202111536328A CN 114226999 A CN114226999 A CN 114226999A
- Authority
- CN
- China
- Prior art keywords
- supporting seat
- positioning pin
- laser cutting
- sliding rail
- lead screw
- 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
Links
- 238000003698 laser cutting Methods 0.000 title claims abstract description 18
- 238000005520 cutting process Methods 0.000 abstract description 15
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
- B23K26/36—Removing material
- B23K26/38—Removing material by boring or cutting
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention provides a laser cutting clamp for an aircraft structural part, which comprises a rotating wheel, a first expansion platform, a sliding rail, a first positioning pin, a supporting block, a second positioning pin, a second supporting seat, a second expansion platform, a first supporting seat, a lead screw and a lead screw of the sliding block, wherein the two ends of the first supporting seat and the second supporting seat are fixedly supported by the first supporting seat and the second supporting seat and are fixed with the two ends of the sliding rail; the sliding block is connected with a first positioning pin; and the second support seat is connected with a second positioning pin. The invention aims to provide a laser cutting clamp for an aircraft structural part, which can meet the requirements of fixing and positioning various parts during laser cutting, has strong adaptability, simple structure and simple manufacturing, and improves the cutting quality of the parts at lower cost.
Description
Technical Field
The invention belongs to the technical field of laser cutting, and particularly relates to a laser cutting clamp for an aircraft structural part.
Background
At present, in aircraft manufacturing, aircraft structural part cutting, especially thickness are thicker, and the structure is complicated, and the part cutting of hardness height (such as titanium alloy) is more difficult, and traditional manual cutting, the cutting degree of difficulty is big, and the cutting precision is poor, and cutting efficiency is low, and cutting surface quality is poor, and the cutting quality state can't guarantee unanimously. And the laser cutting is adopted, so that the surface quality of the part is good, and the efficiency is high. However, due to the fact that parts with partial structures are large in size and poor in rigidity, the parts are greatly deformed under the influence of gravity in a free state, laser cutting is conducted under the condition, cutting errors are large, positioning of the parts is inconvenient, and a part cutting clamp needs to be designed, so that the clamp is low in cost, simple in structure and simple to manufacture.
Disclosure of Invention
In order to solve the technical problems, the invention provides the laser cutting clamp for the aircraft structural part, which can play a role of supporting parts, is convenient to position, has low cost and is simple to process.
The technical scheme of the invention is as follows:
a laser cutting clamp for an aircraft structural part comprises a rotating wheel, a first expansion platform, a sliding rail, a first positioning pin, a supporting block, a second positioning pin, a second supporting seat, a second expansion platform, a first supporting seat, a lead screw and a sliding block; the screw penetrates through the sliding block, two ends of the screw are fixedly supported by the first supporting seat and the second supporting seat and are fixed with two ends of the sliding rail, the screw slides in the sliding rail, and one end of the screw is connected with the rotating wheel; the sliding block is connected with a first positioning pin; a second positioning pin is connected to the second supporting seat; one side of the upper surface of each of the two sides of the sliding rail is connected with a first expansion platform, and the other side of the upper surface of each of the two sides of the sliding rail is connected with a second expansion platform; the supporting blocks are multiple and are respectively placed on the first expansion platform and the second expansion platform.
Furthermore, the screw rod is controlled by rotating the rotating wheel to enable the sliding block to slide on the sliding rail.
Furthermore, in order to cut structural parts with different sizes, the first positioning pin and the second positioning pin control the relative distance through the sliding of the sliding block.
The invention has the advantages that:
the laser cutting device has the advantages that the laser cutting device meets the requirements of fixing and positioning various parts during laser cutting, has high adaptability, simple structure and simplicity in manufacturing, and improves the cutting quality of the parts at low cost.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a schematic view of the part clamp of the present invention;
shown in the figure: the device comprises a rotating wheel 1, an expansion platform I2, a sliding rail 3, a positioning pin I4, a supporting block 5, a positioning pin II 6, a supporting seat II 7, an expansion platform II 8, a supporting seat I9, a screw rod 10 and a sliding block 11.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure. The described embodiments are only some embodiments of the invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be understood that the structures, proportions, and dimensions shown in the drawings and described herein are for illustrative purposes only and are not intended to limit the scope of the present invention, which is defined by the claims, but rather by the claims. In addition, the terms such as "upper", "lower", "left", "right" and "middle" used in the present specification are for convenience of description only, and are not intended to limit the scope of the present invention, and changes or modifications of the relative relationship thereof may be regarded as the scope of the present invention without substantial changes in the technical contents.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The laser cutting clamp for the aircraft structural part comprises a rotating wheel 1, an expansion platform I2, a sliding rail 3, a positioning pin I4, a supporting block 5, a positioning pin II 6, a supporting seat II 7, an expansion platform II 8, a supporting seat I9, a lead screw 10 and a sliding block 11, wherein the rotating wheel is fixedly connected with the supporting block I2; the lead screw 10 penetrates through the sliding block 11, two ends of the lead screw are fixedly supported by the first supporting seat 9 and the second supporting seat 7 and are fixed with two ends of the sliding rail 3, the lead screw 10 slides in the sliding rail 3, and one end of the lead screw 10 is connected with the rotating wheel 1; the sliding block 11 is connected with a first positioning pin 4; a second positioning pin 6 is connected to the second supporting seat 7; one side of the upper surface of the two sides of the sliding rail 3 is connected with a first expansion platform 2, and the other side of the upper surface of the two sides of the sliding rail is connected with a second expansion platform 8; the supporting blocks 5 are multiple and are respectively placed on the first expansion platform 2 and the second expansion platform 8.
The screw rod is controlled by rotating the rotating wheel to enable the sliding block to slide on the sliding rail.
In order to cut structural parts with different sizes, the relative distance between the first positioning pin and the second positioning pin is controlled by the sliding of the sliding block.
The working principle of the invention is as follows: when an airplane structural part is formed, the relative position of the part on a forming tool is generally positioned under the action of a pin hole and a pin, so that when a cutting clamp is used, the positioning pin of the cutting clamp is required to be kept consistent with the positioning pin standard of the forming tool, firstly, a rotating wheel 1 is required to be rotated to drive a lead screw 10 to rotate, a sliding block 11 is enabled to move in a sliding rail 3, and the positions of a positioning pin I4 on the sliding block 11 and a positioning pin II 6 on a supporting seat II 7 are enabled to be consistent with a positioning hole on the part by adjusting the position of the sliding block 11,
then place the part on anchor clamps, make the round pin hole cover on the part on the locating pin, the relative position of part on anchor clamps has been fixed up to this moment, but when meetting the size great, or the part is irregular, and the focus skew is big part, because the influence of gravity leads to the part to warp, influences part cutting accuracy, consequently adopts supporting seat 5 to place under with the deformation position, supports the part and avoids warping, and supporting shoe 5 quantity, size can be adjusted as required.
Other parts of the invention not described in detail are conventional techniques known to the person skilled in the art.
It is to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The scope of the present invention is not limited to the technical solutions disclosed in the embodiments, and any modifications, equivalent substitutions, improvements, etc. made to the above embodiments according to the technical spirit of the present invention fall within the scope of the present invention.
Claims (3)
1. The laser cutting clamp for the aircraft structural part is characterized by comprising a rotating wheel (1), an expansion platform I (2), a sliding rail (3), a positioning pin I (4), a supporting block (5), a positioning pin II (6), a supporting seat II (7), an expansion platform II (8), a supporting seat I (9), a lead screw (10) and a sliding block (11); the lead screw (10) penetrates through the sliding block (11), two ends of the lead screw are fixedly supported by the first supporting seat (9) and the second supporting seat (7) and are fixed with two ends of the sliding rail (3), the lead screw (10) slides in the sliding rail (3), and one end of the lead screw (10) is connected with the rotating wheel (1); the sliding block (11) is connected with a first positioning pin (4); a second positioning pin (6) is connected to the second supporting seat (7); one side of the upper surface of each of the two sides of the sliding rail (3) is connected with a first expansion platform (2), and the other side of the upper surface of each of the two sides of the sliding rail is connected with a second expansion platform (8); the supporting blocks (5) are multiple and are respectively placed on the first expansion platform (2) and the second expansion platform (8).
2. The laser cutting clamp for the structural part of the airplane as claimed in claim 1, wherein the slider (11) slides on the sliding rail (3) by rotating the rotating wheel (1) to control the lead screw (10).
3. The laser cutting clamp for the structural part of the airplane as claimed in claim 1 or 2, wherein the relative distance between the first locating pin (4) and the second locating pin (6) is controlled by sliding of the sliding block (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111536328.1A CN114226999A (en) | 2021-12-16 | 2021-12-16 | Laser cutting clamp for aircraft structural part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111536328.1A CN114226999A (en) | 2021-12-16 | 2021-12-16 | Laser cutting clamp for aircraft structural part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114226999A true CN114226999A (en) | 2022-03-25 |
Family
ID=80756629
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111536328.1A Pending CN114226999A (en) | 2021-12-16 | 2021-12-16 | Laser cutting clamp for aircraft structural part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114226999A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105108363A (en) * | 2015-08-24 | 2015-12-02 | 北京星航机电装备有限公司 | Butt welding deformation control method for large thin-wall missile wings |
| CN105798471A (en) * | 2016-05-31 | 2016-07-27 | 哈尔滨工业大学 | Device and method for inhibiting welding hot cracks of T-shaped structural member |
| DE102016208510A1 (en) * | 2016-05-18 | 2017-11-23 | Airbus Operations Gmbh | System and method for temporary connection of components in the assembly of aircraft components |
| WO2018010136A1 (en) * | 2016-07-14 | 2018-01-18 | 深圳欣锐科技股份有限公司 | Positioning device |
| CN109759975A (en) * | 2019-03-21 | 2019-05-17 | 成都飞机工业（集团）有限责任公司 | A kind of positioning fixture of augmented reality artificial target's object of aircraft freight space auxiliary operation |
| CN110900481A (en) * | 2019-11-06 | 2020-03-24 | 浙江大学 | Flexible array aircraft skin adsorbs frock |
| US20200192407A1 (en) * | 2018-12-13 | 2020-06-18 | Guangdong University Of Technology | Rigid-flexible coupling motion platform driven by ball screw and control method thereof |
| CN113059289A (en) * | 2021-06-03 | 2021-07-02 | 成都飞机工业（集团）有限责任公司 | Aviation titanium alloy laser cutting clamp and method |
-
2021
- 2021-12-16 CN CN202111536328.1A patent/CN114226999A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105108363A (en) * | 2015-08-24 | 2015-12-02 | 北京星航机电装备有限公司 | Butt welding deformation control method for large thin-wall missile wings |
| DE102016208510A1 (en) * | 2016-05-18 | 2017-11-23 | Airbus Operations Gmbh | System and method for temporary connection of components in the assembly of aircraft components |
| CN105798471A (en) * | 2016-05-31 | 2016-07-27 | 哈尔滨工业大学 | Device and method for inhibiting welding hot cracks of T-shaped structural member |
| WO2018010136A1 (en) * | 2016-07-14 | 2018-01-18 | 深圳欣锐科技股份有限公司 | Positioning device |
| US20200192407A1 (en) * | 2018-12-13 | 2020-06-18 | Guangdong University Of Technology | Rigid-flexible coupling motion platform driven by ball screw and control method thereof |
| CN109759975A (en) * | 2019-03-21 | 2019-05-17 | 成都飞机工业（集团）有限责任公司 | A kind of positioning fixture of augmented reality artificial target's object of aircraft freight space auxiliary operation |
| CN110900481A (en) * | 2019-11-06 | 2020-03-24 | 浙江大学 | Flexible array aircraft skin adsorbs frock |
| CN113059289A (en) * | 2021-06-03 | 2021-07-02 | 成都飞机工业（集团）有限责任公司 | Aviation titanium alloy laser cutting clamp and method |
Non-Patent Citations (1)
| Title |
|---|
| 叶建斌 等: "《激光切割技术》", 31 July 2012, 上海科学技术出版社, pages: 8 - 9 * |
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