CN108945512A - A kind of large transport airplane Complex Different Shape shipping main force support structure restorative procedure - Google Patents
A kind of large transport airplane Complex Different Shape shipping main force support structure restorative procedure Download PDFInfo
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- CN108945512A CN108945512A CN201810682995.2A CN201810682995A CN108945512A CN 108945512 A CN108945512 A CN 108945512A CN 201810682995 A CN201810682995 A CN 201810682995A CN 108945512 A CN108945512 A CN 108945512A
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- hole
- template
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- polymorphic structure
- cutting
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- 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
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- 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
- B64F5/40—Maintaining or repairing aircraft
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
This application discloses a kind of large transport airplane Complex Different Shape shipping main force support structure restorative procedure, auxiliary process equipment is made of surplus cutting profile template, theoretical shape cutting template, compensation bushing, first hole step pin, whole hole step pin, hole drilling die.Surplus cutting profile template is for determining failed areas cut coverage；Theoretical cutting profile template is for determining failed areas cut-boundary；First hole compensation positioning bushing is used for the compensation to the whole hole of connection on the lower part mount structure connecting with polymorphic structure；First hole step pin is for connecting whole hole connection lower box and first hole failed areas structure refill-unit；Whole hole positioning pin is for fixing surplus cutting profile template, theoretical shape cutting template and hole drilling die.The program includes that failure polymorphic structure decomposes and fail two process flows of installation of polymorphic structure reinforcing member.
Description
Technical field
This application involves aircraft manufacturing technical field, especially a kind of large transport airplane Complex Different Shape shipping main force support structure
It is accurate to repair.
Background technique
Large transport airplane freight floor runs through head, middle fuselage, rear body, and body length about 20m is divided into central floor, a left side
Side floor, right floor, course direction are that integrated machine adds structure, and assembling in such a way that welding, fastener connection combine is one
Body, there are many shipping bearing structures for setting in structure, wherein being tethered at structure is that main load-carrying construction, structure are in shipping operating condition
Polymorphic structure is distributed in central floor, left side floor, right floor two sides, carries complicated multi-direction 111KN high intensity and carries
Lotus, installation hole location precision prescribed be 0.1mm, hole wall nargin be 0, meanwhile, association structure is more, by the part of failure be tethered at structure into
Accurate repair of row is a difficult point.
Currently, the domestic restorative procedure that there is no for large transport airplane freight floor structure, repairs needs to meet to assemble,
It is badly in need of a kind of accurate, reliable repair process.
Summary of the invention
The purpose of the application is to provide a kind of large transport airplane Complex Different Shape shipping main force support structure repair process, can
To implement to large transport airplane Complex Different Shape shipping main force support structure reparation.
To achieve the above objectives, the application takes following technical scheme to be achieved:
A kind of large transport airplane Complex Different Shape shipping main force support structure repair process, it is real based on auxiliary process equipment
It is existing, include the decomposition of failure polymorphic structure and failure polymorphic structure reinforcing member installation.
Auxiliary process equipment by surplus cutting profile template, theoretical shape cutting template, compensation bushing, first hole step pin,
Whole hole step pin, hole drilling die composition.Surplus cutting profile template is for determining failed areas cut coverage；Theoretical cutting profile
Template is for determining failed areas cut-boundary；Bushing is compensated to be used for the connection on the lower part mount structure connecting with polymorphic structure
The compensation in whole hole；First hole step pin is for connecting whole hole connection lower box and first hole failed areas structure refill-unit；Whole hole positioning
Pin is for fixing surplus cutting profile template, theoretical shape cutting template and hole drilling die.It fails on polymorphic structure reinforcing member
Mounting hole is first hole state, and appearance profile is consistent with theoretical shape.
1, failure polymorphic structure decomposes
1) the forward and backward position of decomposition failure polymorphic structure and its course direction is tethered at structure connection attachment, takes out attachment and company
Connect fastener；
2) surplus cutting profile template is using whole hole positioning pin, and to fail, the forward and backward position in polymorphic structure course is tethered at structure
On the basis of mounting hole, positioning operation is executed, marks appearance profile line according to surplus exterior template；
3) dismantling surplus cutting profile template and whole hole positioning pin；
4) theoretical shape cutting template is using whole hole positioning pin, and to fail, the forward and backward position in polymorphic structure course is tethered at structure
On the basis of mounting hole, positioning operation is executed, marks appearance profile line according to theoretical shape cutting template；
5) theoretical shape cutting template and whole hole positioning pin are disassembled；
6) square aperture is cut between stud at the top of failure polymorphic structure ┲ ┱, observation structure side elevation is used for, after execution
Continuous cutting operation；
7) it crosses according to surplus shape cutting template, executes the cutting behaviour in failure polymorphic structure ┲ ┱ top planes region
Make；
8) fail polymorphic structure ┲ ┱ facade region cutting operation；
9) the preliminary finishing of cut surface is trimmed to Distance Theory contour line 1mm；
2, failure polymorphic structure reinforcing member installation
1) failure polymorphic structure reinforcing member positioning is positioned in compensation bushing insertion lower part connection mount structure end using first hole
Pin carries out just positioning, checks failure polymorphic structure reinforcing member and surrounding structure clearance condition；
2) just hole positioning pin and compensation bushing, gap between finishing failure polymorphic structure reinforcing member and cut surface are disassembled；
3) failure polymorphic structure reinforcing member relocates, and in compensation bushing insertion lower part connection mount structure end, uses first hole
Positioning pin is positioned；
4) hole drilling die cooperation positioning pin and drilling device, execute mounting hole drilling one by one；
5) mounting hole inspection；
6) installation failure polymorphic structure reinforcing member and the structure that is tethered at of dismounting connect attachment.
The application provide utilize large transport airplane fuselage itself architectural characteristic, using easy template, tooling as assist
Process, realize the high-precision reparation of large transport airplane Complex Different Shape shipping main force support structure, process principle is simple,
Easy to operate, craft precision is high, operates especially suitable for semiclosed not open, enclosure space reparation, to large transport airplane knot
The high-precision reparation of structure has universal applicability.
The application is described in further detail with reference to the accompanying drawings and embodiments.
Detailed description of the invention
Fig. 1 surplus shape cutting template positioning method schematic diagram
Fig. 2 theory shape cutting template positioning method schematic diagram
Fig. 3 failure polymorphic structure refill-unit positions schematic diagram
Fig. 4 hole drilling die positioning method schematic diagram
Explanation is numbered in figure: 1, whole hole step pin；2, surplus cutting profile template；4, mount structure；5, fail polymorphic structure；
6, theoretical shape cutting template；7, first hole step pin；8, fail polymorphic structure reinforcing member；9, bushing is compensated；10, hole drilling die is fixed
Position pin；11, hole drilling die.
Specific embodiment
Referring to 1 ~ Fig. 3 of attached drawing, a kind of large transport airplane Complex Different Shape shipping main force support structure repair process is based on
Auxiliary process equipment is realized, decomposes comprising failure polymorphic structure 5 and failure polymorphic structure reinforcing member 8 is installed.It is auxiliary process
Equipment by surplus cutting profile template 2, theoretical shape cutting template 6, compensation bushing 9, first hole step pin 7, whole hole step pin 1,
Hole drilling die 11 forms.Surplus cutting profile template 2 is for determining failed areas cut coverage；Theoretical cutting profile template 6 is used
In determining failed areas cut-boundary；Bushing 9 is compensated to be used for the connection end hole on the lower part mount structure 4 connecting with polymorphic structure
Compensation；First hole step pin 7 is for connecting whole hole connection lower box and first hole failed areas structure refill-unit；Whole hole positioning pin 1
For fixing surplus cutting profile template 2, theoretical shape cutting template 6 and hole drilling die 11.Fail polymorphic structure reinforcing member 8
Upper installing hole is first hole state, and appearance profile is consistent with theoretical shape.
Specific restorative procedure is as follows:
1, fail 5 decomposition method of polymorphic structure
1) the forward and backward position of decomposition failure polymorphic structure 5 and its course direction is tethered at structure connection attachment, takes out attachment and company
Connect fastener；
2) surplus cutting profile template 2 is using whole hole positioning pin 1, and to fail, the forward and backward position in 5 course of polymorphic structure is tethered at knot
On the basis of structure mounting hole, positioning operation is executed, marks appearance profile line according to surplus exterior template 2；
3) dismantling surplus cutting profile template 2 and whole hole positioning pin 1；
4) theoretical shape cutting template 6 is using whole hole positioning pin 1, and to fail, the forward and backward position in 5 course of polymorphic structure is tethered at knot
On the basis of structure mounting hole, positioning operation is executed, marks appearance profile line according to theoretical shape cutting template 6；
5) theoretical shape cutting template 6 and whole hole positioning pin 1 are disassembled；
6) square aperture is cut between stud at the top of failure 5 ┲ ┱ of polymorphic structure, observation structure side elevation is used for, after execution
Continuous cutting operation；
7) it crosses according to surplus shape cutting template 2, executes the cutting behaviour in failure 5 ┲ ┱ top planes region of polymorphic structure
Make；
8) fail 5 ┲ ┱ facade region cutting operation of polymorphic structure；
9) the preliminary finishing of cut surface is trimmed to Distance Theory contour line 1mm；
2, fail 8 installation method of polymorphic structure reinforcing member
1) failure polymorphic structure reinforcing member 8 positions, and compensation bushing 9 was inserted into the connection mount structure end of lower part, uses first Kong Ding
Position pin 7 just position, and checks failure polymorphic structure reinforcing member 8 and surrounding structure clearance condition；
2) just hole positioning pin 7 and compensation bushing 9, gap between finishing failure polymorphic structure reinforcing member 8 and cut surface are disassembled；
3) failure polymorphic structure reinforcing member 8 relocates, and compensation bushing 9 was inserted into the connection mount structure end of lower part, using first
Hole positioning pin 7 is positioned；
4) hole drilling die 11 cooperates positioning pin 10 and drilling device, executes mounting hole drilling one by one；
5) mounting hole inspection and installation failure polymorphic structure reinforcing member 8 and its forward and backward position in course direction are tethered at structure company
Attachment.
Claims (1)
1. a kind of large transport airplane Complex Different Shape shipping main force support structure restorative procedure is realized based on auxiliary process equipment, includes
The polymorphic structure that fails decomposes and failure polymorphic structure reinforcing member installation, it is characterised in that:
1-1 auxiliary process equipment by surplus cutting profile template, theoretical shape cutting template, compensation bushing, first hole step pin,
Whole hole step pin, hole drilling die composition, surplus cutting profile template is for determining failed areas cut coverage, theoretical cutting profile
Template is for determining that failed areas cut-boundary, compensation bushing are used for the connection on the lower part mount structure connecting with polymorphic structure
The compensation in whole hole, first hole step pin is for connecting whole hole connection lower box and first hole failed areas structure refill-unit, whole hole positioning
Pin is for fixing surplus cutting profile template, theoretical shape cutting template and hole drilling die；
1-2 fails polymorphic structure reinforcing member upper installing hole for first hole state, and appearance profile is consistent with theoretical shape；
1-3 failure polymorphic structure decomposes
The forward and backward position of 1-3-1 decomposition failure polymorphic structure and its course direction is tethered at structure connection attachment, takes out attachment and company
Connect fastener；
1-3-2 surplus cutting profile template is using whole hole positioning pin, and to fail, the forward and backward position in polymorphic structure course is tethered at structure
On the basis of mounting hole, positioning operation is executed, marks appearance profile line according to surplus exterior template；
1-3-3 disassembles surplus cutting profile template and whole hole positioning pin；
1-3-4 theory shape cutting template is using whole hole positioning pin, and to fail, the forward and backward position in polymorphic structure course is tethered at structure
On the basis of mounting hole, positioning operation is executed, marks appearance profile line according to theoretical shape cutting template；
1-3-5 disassembles theoretical shape cutting template and whole hole positioning pin；
1-3-6 cuts square aperture between stud at the top of failure polymorphic structure ┲ ┱, observation structure side elevation is used for, after execution
Continuous cutting operation；
1-3-7 crosses according to surplus shape cutting template, executes the cutting behaviour in failure polymorphic structure ┲ ┱ top planes region
Make；
1-3-8 failure polymorphic structure ┲ ┱ facade region cutting operation；
The preliminary finishing of 1-3-9 cut surface is trimmed to Distance Theory contour line 1mm；
1-4 failure polymorphic structure reinforcing member installation method
1-4-1 failure polymorphic structure reinforcing member positioning is positioned in compensation bushing insertion lower part connection mount structure end using first hole
Pin carries out just positioning, checks failure polymorphic structure reinforcing member and surrounding structure clearance condition；
1-4-2 disassembles just hole positioning pin and compensation bushing, gap between finishing failure polymorphic structure reinforcing member and cut surface；
1-4-3 failure polymorphic structure reinforcing member relocates, and in compensation bushing insertion lower part connection mount structure end, uses first hole
Positioning pin is positioned；
1-4-4 hole drilling die cooperates positioning pin and drilling device, executes mounting hole drilling one by one；
1-4-5 mounting hole inspection；
1-4-6 installation failure polymorphic structure reinforcing member and the structure that is tethered at of dismounting connect attachment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810682995.2A CN108945512A (en) | 2018-06-27 | 2018-06-27 | A kind of large transport airplane Complex Different Shape shipping main force support structure restorative procedure |
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| CN201810682995.2A CN108945512A (en) | 2018-06-27 | 2018-06-27 | A kind of large transport airplane Complex Different Shape shipping main force support structure restorative procedure |
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Application publication date: 20181207 |