CN104708286A - Method of connection between aircraft skin and rib or frame or connection between aircraft skins - Google Patents
Method of connection between aircraft skin and rib or frame or connection between aircraft skins Download PDFInfo
- Publication number
- CN104708286A CN104708286A CN201510137526.9A CN201510137526A CN104708286A CN 104708286 A CN104708286 A CN 104708286A CN 201510137526 A CN201510137526 A CN 201510137526A CN 104708286 A CN104708286 A CN 104708286A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- aircraft skin
- laser
- frame
- skin
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 22
- 239000000843 powder Substances 0.000 claims abstract description 32
- 239000000463 material Substances 0.000 claims abstract description 11
- 238000004519 manufacturing process Methods 0.000 claims abstract description 5
- 239000013307 optical fiber Substances 0.000 claims abstract description 5
- 230000001681 protective effect Effects 0.000 claims abstract description 5
- 230000002787 reinforcement Effects 0.000 claims description 17
- 238000000465 moulding Methods 0.000 claims description 4
- 230000003014 reinforcing effect Effects 0.000 abstract 4
- 238000010586 diagram Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 241001074085 Scophthalmus aquosus Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000003205 muscle Anatomy 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention provides a method of rapid connection between an aircraft skin and a reinforcing rib or frame or connection between aircraft skins. The method is implemented based on a laser rapid prototyping system. The method comprises the steps that a laser head and a powder feeder guide tube are installed on a mechanical arm, and the laser head is connected with a laser device through an optical fiber; allowance removal is performed on the joint between the aircraft skin and the reinforcing rib or frame or the joint between the aircraft skins according to forming requirements, and meanwhile, the folding or lapping-in surface of the aircraft skin is made into a slope shape, and then folding is performed on the aircraft skin and the reinforcing rib or frame, or lapping-in is performed on the aircraft skins; a walking track program of the laser head is complied, or teaching programming is performed through the mechanical arm; the pressure of protective gas or powder-feeding gas is adjusted, forming powder is charged, and laser coaxial powder feeding material increase manufacturing is performed according to the program; the surface is ground to make the surface of a material increase area flush with the surface of the skin; connection between the aircraft skin and the reinforcing rib or frame or connection between the aircraft skins is completed finally. By means of the method, metallurgical bonding of the aircraft skins is achieved, and high-quality connection is achieved.
Description
Technical field
The present invention relates to the quick connecting method between a kind of aircraft skin and reinforcement, frame or between aircraft skin and covering, belong to rapid laser-shaping technique field.
Background technology
At present, what the connection between aircraft skin and reinforcement, frame or between aircraft skin and covering adopted usually is bore to rivet, brill is adopted to rivet transmission, the increase aircraft vapour lock of not only influence power, and affect the requirement of the overall weight of aircraft and the property of aircraft, add the chance that aircraft fifth wheel is left over simultaneously.
Summary of the invention
For above deficiency, the invention provides the quick connecting method between a kind of aircraft skin and reinforcement, frame or between aircraft skin and covering, achieve the metallurgical binding of aircraft skin, reach high-quality connection.
Technical scheme of the present invention: the quick connecting method between a kind of aircraft skin and reinforcement, frame or between aircraft skin and covering, it realizes based on Laser Rapid Prototyping System, described Laser Rapid Prototyping System comprises computer, laser instrument, powder feeder, manipulator, Manipulator Controller, wherein Manipulator Controller is up is connected with computer, Manipulator Controller is descending to be connected with laser instrument, powder feeder, manipulator, and laser instrument is controlled by computer, concrete quick connecting method step is as follows:
(1) laser head and powder feeder conduit are installed on manipulator, adopt optical fiber to be connected with laser instrument by laser head simultaneously;
(2) surplus is removed according to forming requirements in the junction of aircraft skin and reinforcement, frame or surplus is removed according to forming requirements in the junction of aircraft skin and covering, ramp shaped is made in face that is aircraft skin is involutory or lapping-in simultaneously, then aircraft skin and reinforcement, frame are carried out involutory, or aircraft skin and covering are carried out lapping-in;
(3) work out the run trace program of laser head or utilize manipulator to carry out teach programming;
(4) adjust the pressure of protective gas and powder feeding gas, load moulding powder, follow procedure carries out laser coaxial powder feeding and increases material manufacture;
(5) lapped face, makes increasing material region surface flush with skin-surface;
(6) aircraft skin and reinforcement, the connection of frame or the connection of aircraft skin and covering is finally completed.
Beneficial effect of the present invention: the inventive method is simple, because laser head is installed on a robotic arm, manipulator moves flexibly, programming easy, therefore, it is possible to realize the running of arbitrary surface curvilinear path, shaping powder can be changed according to skin material at any time with the need simultaneously, thus can reach high-quality connection; In addition, due to the realization of covering junction is metallurgical binding, makes the covering of aircraft become as a whole, therefore adds the structural strength of aircraft greatly, extend the service life of aircraft, meet the various performance requirements of aircraft simultaneously.
Accompanying drawing explanation
Fig. 1 is the connection diagram of embodiment one.
Fig. 2 is the connection diagram of embodiment two.
Detailed description of the invention
embodiment one
As shown in Figure 1, quick connecting method between a kind of aircraft skin and reinforcement, frame, it realizes based on Laser Rapid Prototyping System, described Laser Rapid Prototyping System comprises computer, laser instrument, powder feeder, manipulator, Manipulator Controller, wherein Manipulator Controller is up is connected with computer, Manipulator Controller is descending to be connected with laser instrument, powder feeder, manipulator, and laser instrument is controlled by computer, and concrete quick connecting method step is as follows:
(1) laser head 1 and powder feeder conduit 2 are installed on manipulator, adopt optical fiber to be connected with laser instrument by laser head simultaneously;
(2) aircraft skin 5 and the junction of reinforcement, frame 6 are removed surplus according to forming requirements, 40 ° of-60 ° of ramp shaped are made in face involutory for aircraft skin simultaneously, then aircraft skin 5 and reinforcement, frame 6 are carried out involutory; Time involutory, be first overlapped on reinforcement, frame 6 by covering 5 one end with groove, amount of lap is 3mm-5mm, then applies pressure and covering 5 and reinforcement, frame 6 are fitted tightly;
(3) adjust the height of laser head 1 and powder feeder conduit 2, make laser beam 3 and powder aim at the root of groove;
(4) according to the run trace program of the present situation of groove and size establishment laser head or utilize manipulator to carry out teach programming;
(5) adjust the pressure of protective gas and powder feeding gas, load moulding powder, follow procedure carries out laser coaxial powder feeding and increases material manufacture, namely fills up groove and is combined with two side skins 5;
(6) lapped face, makes increasing material region surface flush with skin-surface;
(7) connection of aircraft skin and reinforcement, frame is finally completed.
embodiment two
As shown in Figure 2, quick connecting method between a kind of aircraft skin and covering, it realizes based on Laser Rapid Prototyping System, described Laser Rapid Prototyping System comprises computer, laser instrument, powder feeder, manipulator, Manipulator Controller, wherein Manipulator Controller is up is connected with computer, Manipulator Controller is descending to be connected with laser instrument, powder feeder, manipulator, and laser instrument is controlled by computer, and concrete quick connecting method step is as follows:
(1) laser head 1 and powder feeder conduit 2 are installed on manipulator, adopt optical fiber to be connected with laser instrument by laser head simultaneously;
(2) aircraft skin 5 and the junction of covering 5 are removed surplus according to forming requirements, 40 ° of-60 ° of ramp shaped are made in face involutory for aircraft skin simultaneously, then aircraft skin 5 and covering 5 are carried out involutory;
(3) adjust the height of laser head 1 and powder feeder conduit 2, make laser beam 3 and powder aim at the root of groove;
(4) according to the run trace program of the present situation of groove and size establishment laser head or utilize manipulator to carry out teach programming;
(5) adjust the pressure of protective gas and powder feeding gas, load moulding powder, follow procedure carries out laser coaxial powder feeding and increases material manufacture, namely fills up groove and is combined with two side skins 5;
(6) lapped face, makes increasing material region surface flush with skin-surface;
(7) connection of aircraft skin and covering is finally completed.
Claims (1)
1. the quick connecting method between an aircraft skin and reinforcement, frame or between aircraft skin and covering, it realizes based on Laser Rapid Prototyping System, described Laser Rapid Prototyping System comprises computer, laser instrument, powder feeder, manipulator, Manipulator Controller, wherein Manipulator Controller is up is connected with computer, Manipulator Controller is descending to be connected with laser instrument, powder feeder, manipulator, and laser instrument is controlled by computer, it is characterized in that quick connecting method step of the present invention is as follows:
(1) laser head and powder feeder conduit are installed on manipulator, adopt optical fiber to be connected with laser instrument by laser head simultaneously;
(2) surplus is removed according to forming requirements in the junction of aircraft skin and reinforcement, frame or surplus is removed according to forming requirements in the junction of aircraft skin and covering, ramp shaped is made in face that is aircraft skin is involutory or lapping-in simultaneously, then aircraft skin and reinforcement, frame are carried out involutory, or aircraft skin and covering are carried out lapping-in;
(3) work out the run trace program of laser head or utilize manipulator to carry out teach programming;
(4) adjust the pressure of protective gas and powder feeding gas, load moulding powder, follow procedure carries out laser coaxial powder feeding and increases material manufacture;
(5) lapped face, makes increasing material region surface flush with skin-surface;
(6) aircraft skin and reinforcement, the connection of frame or the connection of aircraft skin and covering is finally completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510137526.9A CN104708286B (en) | 2015-03-27 | 2015-03-27 | Connection method between aircraft skin and muscle, frame or between aircraft skin and covering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510137526.9A CN104708286B (en) | 2015-03-27 | 2015-03-27 | Connection method between aircraft skin and muscle, frame or between aircraft skin and covering |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104708286A true CN104708286A (en) | 2015-06-17 |
| CN104708286B CN104708286B (en) | 2017-08-25 |
Family
ID=53408282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510137526.9A Active CN104708286B (en) | 2015-03-27 | 2015-03-27 | Connection method between aircraft skin and muscle, frame or between aircraft skin and covering |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104708286B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106335651A (en) * | 2015-07-07 | 2017-01-18 | 波音公司 | Alignment fixture and method for aligning first component and second component |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5841098A (en) * | 1996-09-27 | 1998-11-24 | Daimler-Benz Aerospace Airbus Gmbh | Method and apparatus for laser welding sectional members onto large-format aluminum structural components |
| CN101687287A (en) * | 2007-05-31 | 2010-03-31 | 空中客车控股有限公司 | Method for producing a composite skin in the field of aeronautics and astronautics |
| CN102295076A (en) * | 2010-05-27 | 2011-12-28 | 空中客车营运有限公司 | Manufacturing method for a rib of an aerodynamic engine strut fairing |
| US20120181255A1 (en) * | 2011-01-13 | 2012-07-19 | Bruck Gerald J | Flux enhanced high energy density welding |
| CN102672315A (en) * | 2012-06-07 | 2012-09-19 | 中国东方电气集团有限公司 | Autonomous mobile double-sided double-arc welding robot system |
| CN204053232U (en) * | 2014-07-09 | 2014-12-31 | 南京中科神光科技有限公司 | A kind of laser cladding welding gun |
-
2015
- 2015-03-27 CN CN201510137526.9A patent/CN104708286B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5841098A (en) * | 1996-09-27 | 1998-11-24 | Daimler-Benz Aerospace Airbus Gmbh | Method and apparatus for laser welding sectional members onto large-format aluminum structural components |
| CN101687287A (en) * | 2007-05-31 | 2010-03-31 | 空中客车控股有限公司 | Method for producing a composite skin in the field of aeronautics and astronautics |
| CN102295076A (en) * | 2010-05-27 | 2011-12-28 | 空中客车营运有限公司 | Manufacturing method for a rib of an aerodynamic engine strut fairing |
| US20120181255A1 (en) * | 2011-01-13 | 2012-07-19 | Bruck Gerald J | Flux enhanced high energy density welding |
| CN102672315A (en) * | 2012-06-07 | 2012-09-19 | 中国东方电气集团有限公司 | Autonomous mobile double-sided double-arc welding robot system |
| CN204053232U (en) * | 2014-07-09 | 2014-12-31 | 南京中科神光科技有限公司 | A kind of laser cladding welding gun |
Non-Patent Citations (1)
| Title |
|---|
| 杨武雄: ""高强铝合金的激光填粉焊接"", 《中国优秀硕士学位论文全文数据库工程科技Ⅰ辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106335651A (en) * | 2015-07-07 | 2017-01-18 | 波音公司 | Alignment fixture and method for aligning first component and second component |
| CN106335651B (en) * | 2015-07-07 | 2018-12-11 | 波音公司 | Alignment and fixation part and method for being directed at the first component with second component |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104708286B (en) | 2017-08-25 |
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