CN110842845A - Large-curvature composite material cone structural member assembling tool and assembling process thereof - Google Patents
Large-curvature composite material cone structural member assembling tool and assembling process thereof Download PDFInfo
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- CN110842845A CN110842845A CN201911264738.8A CN201911264738A CN110842845A CN 110842845 A CN110842845 A CN 110842845A CN 201911264738 A CN201911264738 A CN 201911264738A CN 110842845 A CN110842845 A CN 110842845A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a large-curvature composite material cone structural member assembling tool which comprises a supporting leg fixed at the bottom of a cone support, wherein the cone support comprises a top ring for detachably installing a positioning ring, a bottom ring for positioning and installing the bottom of the cone structural member and a plurality of supporting plates for supporting the middle part of the cone structural member, the supporting plates are fixedly connected between the top ring and the bottom ring, the diameter of the top ring is smaller than that of the bottom ring, and the positioning ring for positioning and installing the top of the cone structural member is installed on the top ring.
Description
Technical Field
The invention relates to a large-curvature composite material cone structural member, in particular to an assembly tool for the large-curvature composite material cone structural member.
Background
Common big camber structure, like the aircraft organism, adopt skeleton benchmark assembly methods usually, the main frame or the annular muscle that inside adopted the flat structure promptly, overlap joint crossbeam between the frame, the main frame, the crossbeam face are directly laminated to the big camber covering in outside, and whole appearance relies on inner frame to realize, and this kind of structural style is relatively stable, is difficult for producing deformation, ensures the positioning accuracy of main frame in the assembling process, finally can satisfy the appearance requirement basically.
The structure has no internal supporting piece, the structural shape precision is maintained only by the outer cylindrical or centrum thin-wall piece, the structure is limited to a part of products in special fields, the assembly difficulty is high, and the deformation is easy to generate in the assembly process, so that the product is out of tolerance. This construction cannot be implemented using conventional assembly solutions, because of its small range of use.
Disclosure of Invention
The invention aims to provide an assembly tool and an assembly process for a large-curvature composite material cone structural member, which can be used for manufacturing a cone structural product with the size and the quality meeting the technical requirements, reducing the assembly difficulty and avoiding deformation in the assembly process.
The purpose of the invention is realized as follows: the utility model provides a big curvature combined material cone structure assembly fixture and assembly process thereof, is including fixing the supporting leg in the cone support bottom, the cone support includes a top ring, a bottom ring and a plurality of backup pads that are used for supporting cone structure middle part that are used for dismantling installation location ring, are used for fixing a position installation cone structure bottom, backup pad fixed connection is between top ring and bottom ring, and top ring diameter is less than the bottom ring, installs the location ring that is used for fixing a position installation cone structure top on the top ring.
As a further limitation of the invention, a plurality of support plates are symmetrically arranged on two sides of the central axial plane of the cone structural member in pairs and are used for being matched with the two semi-cone structural members for assembly, at least six support plates are arranged, and at least three support plates are arranged on each semi-cone structural member.
As a further limitation of the invention, the periphery of the top surface of the bottom circular ring is provided with a bottom concave platform for positioning and installing the cone structural member.
As a further limitation of the present invention, the lower recessed platform is provided with a plurality of lower locating pins.
As a further limitation of the invention, the positioning ring is arranged on the top of the top ring through bolts, and a concave platform for positioning and installing the top of the cone structural member is machined on the periphery of the bottom surface of the positioning ring.
As a further limitation of the present invention, the upper recessed platform is provided with a plurality of upper positioning pins.
As a further limitation of the present invention, at least two support blocks are disposed outside the support plate.
A large-curvature composite material cone structural member assembling process comprises the following steps:
1) preparing two front mounting edges, two rear mounting edges, a front skin and a rear skin which are required by the assembly of the cone structural member;
2) the upper half and the lower half of the front mounting edge and the lower half of the rear mounting edge which are arranged in pairs are respectively sleeved on an upper concave platform and a lower concave platform through positioning pins, the sections of the front mounting edge and the rear mounting edge are both L-shaped structures and comprise a vertical surface and a horizontal surface, and the front mounting edge and the rear mounting edge are arranged in a manner of being tightly attached to the concave platforms;
3) the upper end and the lower end of the front skin and the rear skin are respectively fixedly installed on the upper half and the lower half of the front installation edge and the rear installation edge, the upper side and the lower side of the skin are lapped on the vertical surface of the installation edge and tightened through a tightening belt, and a gap is reserved at the butt joint of the front skin and the rear skin; the skin and the mounting edge are connected and fixed by rivets;
4) the front skin and the rear skin are clamped and fixed at the butt joint position by using an inner cover plate and an outer cover plate, and the inner cover plate and the outer cover plate are connected through a bolt;
5) and disassembling the positioning ring, and taking down the cone structural member from the top to obtain a final product.
As a further limitation of the invention, a plurality of through holes are arranged at the joints of the skin and the mounting edge, and rivets are arranged in the through holes. (through holes are not necessary in the early stage, and can be installed by subsequent self-drilling)
Compared with the prior art, the invention has the beneficial effects that: the invention effectively solves the problem of large span and changeability in the manufacturing process of the centrum product, reduces the assembly difficulty, has reasonable assembly tool layout, provides sufficient space for personnel inside, and is convenient for the personnel to construct from the inner side and the outer side simultaneously; the roundness, the total length and the parallelism of the product assembled at present all meet the requirements, and the phenomena of deformation, over-tolerance, fracture and the like do not occur in each test.
Drawings
Fig. 1 is a schematic perspective view of an assembly fixture according to the present invention.
Fig. 2 is a sectional view of the assembly tool of the present invention.
Fig. 3 is an enlarged view of a portion a in fig. 2.
Fig. 4 is an enlarged view of fig. 2 at B.
FIG. 5 is a schematic view of a large curvature composite cone structure of the present invention.
FIG. 6 is a schematic view of the assembly of the large curvature composite material cone structural member and the assembly fixture of the present invention.
Fig. 7 is a schematic view of the assembly of a tying lace of the present invention.
FIG. 8 is a schematic view of the assembly of the inner cover plate and the outer cover plate according to the present invention.
Fig. 9 is a schematic view of the present invention in disassembly.
Wherein, 1 supporting leg, 2 toper supports, 2a bottom ring, 2b backup pad, 2c top ring, 2d concave station down, 3 location rings, 3a go up the concave station, 4 go up the locating pin, 5 lower locating pins, 6 supporting shoes.
Detailed Description
As shown in figures 1-4, the assembly fixture for the large-curvature composite material conical structural part comprises a supporting leg 1 fixed at the bottom of a conical support 2, the conical support 2 comprises a top ring 2c for detachably installing a positioning ring 3, a bottom ring 2a for positioning and installing the bottom of the conical structural part and a plurality of supporting plates 2b for supporting the middle of the conical structural part, the supporting plates 2b are fixedly connected between the top ring 2c and the bottom ring 2a, the diameter of the top ring 2c is smaller than that of the bottom ring 2a, the top ring 2c is provided with the positioning ring 3 for positioning and installing the top of the conical structural part, the supporting plates 2b are symmetrically arranged at two sides of the central shaft surface of the conical structural part in pairs and are used for matching with two halves of the conical structural part for assembly, at least six supporting plates 2b are arranged, at least three supporting plates are arranged at each half, a lower concave platform 2d for positioning and installing the bottom of the conical structural part is machined at the, be provided with a plurality of locating pins 5 down on the concave station 2d down, location ring 3 is installed at top ring 2c top through the bolt, and 3 bottom surface periphery processing of location ring have and are used for location installation cone structure spare top concave station 3a, go up and be provided with a plurality of locating pins 4 on the concave station 3a, the backup pad 2b outside is provided with two at least supporting blocks 6.
The assembly process of the large-curvature composite cone structural member shown in fig. 5-9 comprises the following steps:
1) preparing two front mounting edges, two rear mounting edges, a front skin and a rear skin which are required by the assembly of the cone structural member; the front mounting edge and the rear mounting edge are machined and formed through a numerical control machine, the precision is high, the structure with the flange is not easy to deform, and the flange is suitable for serving as a structural benchmark; taking the inner cylindrical surface, the bottom plane and the plurality of prefabricated connecting holes of the mounting edge as positioning references, and clamping and fixing the positioning pins with the positioning surfaces and the positioning holes on the conical support to limit the position of the mounting edge;
2) the upper half and the lower half of the front mounting edge and the lower half of the rear mounting edge which are arranged in pairs are respectively sleeved on the upper concave platform and the lower concave platform through positioning pins, the sections of the front mounting edge and the rear mounting edge are both L-shaped structures and comprise a vertical surface and a horizontal surface, and the front mounting edge and the rear mounting edge are arranged in a manner of being tightly attached to the concave platforms;
3) respectively and fixedly mounting the upper end and the lower end of a front skin and the lower end of a rear skin on the upper half and the lower half of a front mounting edge and a rear mounting edge, overlapping the upper edge and the lower edge of the skin on a vertical surface of the mounting edge, tightening the skin, the mounting edge and a conical support by using 4 groups of tightening belts, and respectively arranging the front mounting edge, a support block and the rear mounting edge at corresponding positions, then completing hole making and riveting procedures, wherein a gap is reserved at the butt joint position of the front skin and the rear skin, and a gap of 0.5mm is reserved at the butt joint position of the left side and the right side;
4) the front skin and the rear skin are clamped and fixed at the butt joint position by using an inner cover plate and an outer cover plate, and the inner cover plate and the outer cover plate are connected through a bolt;
5) and disassembling the positioning ring, and taking down the cone structural member from the top to obtain a final product.
The structure manufactured by the invention is a cone structure and comprises 2 composite material skins, 4 titanium alloy front mounting edges, 2 titanium alloy inner cover plates and 2 titanium alloy outer cover plates. The product structure is shown in fig. 5, the composite skin is a main body structure, and the metal piece is a butt joint connecting piece. The integral structure is conical and is formed by butt joint of two halves of conical composite material skins, the upper end and the lower end of each skin are riveted with a metal part with a flange, and the two halves are connected by a metal belt plate in a screwed mode. Overall structure is comparatively simple, and except front and back installation limit, there is not any support piece inside the centrum structure, from the assembly angle consideration, has very big difficulty.
Firstly, the assembly form of the product is determined, and whether the product is assembled in half or integrally is selected. The product is formed by the butt joint of two parts about by, if two parts assemble alone, assemble at last, and the assembly precision requirement to each half subassembly is very high, will guarantee the assembly back, and structural curvature can not take place great change, nevertheless because the existence of riveting stress (riveting under theoretical tapering, can appear deformation after the release stress), this is difficult to realize, is difficult to guarantee the circularity of butt joint back overall structure. Therefore, the fixture must be integrally assembled on an assembly fixture, which requires that the fixture must also be a cone, and the inner wall of the composite material is smooth and flat, and the fixture adopts cone inner type positioning. The assembled fixture form is shown in fig. 1.
Next, an assembly reference is selected. The length and the parallelism of the upper end and the lower end of the casing are strict, metal parts at two ends are machined parts, the size precision is high, a whole circle of connecting holes are arranged, the total length and the parallelism are limited by taking the end face of the metal part as a reference, the circumferential rotation is limited by taking the connecting holes as a reference, and the composite material skin is attached to the mounting edge along with the shape.
And thirdly, structural support. The total length of the structure is 0.9m, edges are installed at two ends, no structural member is arranged in the middle, in the assembling process, any large external force can cause the composite material skin to be sunken, the deformation is out of tolerance, and two rows of supporting blocks are set on the fixture to avoid the condition. The molded surface of the supporting block is processed in a numerical control mode by taking the molded surface in the product as a reference, so that the two theoretical positions are superposed, the skin is supported by a span, the strength is increased, and the requirement of the overall dimension of the product is met.
Fourth, the off-shelf problem. And (4) selecting integral assembly, taking the flange surfaces of the upper and lower metal parts as a positioning reference, and if the fixture is also an integral, the product cannot be put down. The method comprises the steps of changing a frame into an assembly part, arranging a detachable positioning ring on one side of a small end, sleeving the small end ring on a frame fixing structure by adopting a spigot structure, limiting the length of an end face, arranging a positioning pin hole, limiting the circumferential position and meeting the assembly requirement.
The main body of the assembly fixture is welded and formed, and key positions (a positioning surface, a positioning hole and a supporting block) are machined and formed, so that the precision requirement of the product is met.
The invention effectively solves the problem of large span and changeability in the manufacturing process of the centrum product, reduces the assembly difficulty, has reasonable assembly tool layout, provides sufficient space for personnel inside, and is convenient for the personnel to construct from the inner side and the outer side simultaneously; the roundness, the total length and the parallelism of the product assembled at present all meet the requirements, and the phenomena of deformation, over-tolerance, fracture and the like do not occur in each test.
The present invention is not limited to the above-mentioned embodiments, and based on the technical solutions disclosed in the present invention, those skilled in the art can make some substitutions and modifications to some technical features without creative efforts according to the disclosed technical contents, and these substitutions and modifications are all within the protection scope of the present invention.
Claims (7)
1. The utility model provides a big curvature combined material cone structure assembly fixture, its characterized in that, is including fixing the supporting leg in the cone support bottom, the cone support includes a top ring, a bottom ring and a plurality of backup pads that are used for supporting cone structure middle part that are used for the demountable installation location ring that is used for fixing a position the installation cone structure bottom, backup pad fixed connection is between top ring and bottom ring, and top ring diameter is less than the bottom ring, installs the location ring that is used for fixing a position the installation cone structure top on the top ring.
2. The assembly fixture for the large-curvature composite material cone structural member according to claim 1, wherein a plurality of support plates are symmetrically arranged on two sides of a central axial plane of the cone structural member in pairs and are used for being matched with two semi-conical structural members to be assembled, at least six support plates are arranged, and at least three support plates are arranged on each semi-conical structural member.
3. The assembly tooling for the large-curvature composite material cone structural member as claimed in claim 1 or 2, wherein a concave platform for positioning and mounting the bottom of the cone structural member is machined on the periphery of the top surface of the bottom ring.
4. The assembly tooling for the large-curvature composite material cone structural member as claimed in claim 3, wherein a plurality of lower positioning pins are arranged on the lower concave table.
5. The assembly tooling for the large-curvature composite material cone structural member as claimed in claim 1 or 2, wherein the positioning ring is mounted on the top of the top ring through bolts, and a concave table for positioning and mounting the top of the cone structural member is machined on the periphery of the bottom surface of the positioning ring.
6. The assembly tooling for the large-curvature composite material cone structural member as claimed in claim 5, wherein a plurality of upper positioning pins are arranged on the upper concave table.
7. The assembly tooling for the large-curvature composite material cone structural member as claimed in claim 1 or 2, wherein at least two support blocks are arranged outside the support plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911264738.8A CN110842845B (en) | 2019-12-11 | 2019-12-11 | Large-curvature composite cone structural member assembly tool and assembly process thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911264738.8A CN110842845B (en) | 2019-12-11 | 2019-12-11 | Large-curvature composite cone structural member assembly tool and assembly process thereof |
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| Publication Number | Publication Date |
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| CN110842845A true CN110842845A (en) | 2020-02-28 |
| CN110842845B CN110842845B (en) | 2023-07-18 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247296A (en) * | 2021-05-31 | 2021-08-13 | 浙江万丰飞机制造有限公司 | Installation tool of thin-wall part of airplane, tool manufacturing method and using method |
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| US20190144134A1 (en) * | 2016-04-20 | 2019-05-16 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft fuselage assembling jig and method of handling aircraft fuselage panel |
| CN211491300U (en) * | 2019-12-11 | 2020-09-15 | 江苏新扬新材料股份有限公司 | Large-curvature composite material cone structural member assembling tool |
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2019
- 2019-12-11 CN CN201911264738.8A patent/CN110842845B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5033178A (en) * | 1988-07-06 | 1991-07-23 | The Boeing Company | Assembly jig and method for making wing panels |
| CN103447792A (en) * | 2013-08-08 | 2013-12-18 | 上海飞机制造有限公司 | Flexible measurement and control tool system and flexible measurement and control method for large wall panels with complicated surfaces |
| CN105035354A (en) * | 2015-08-04 | 2015-11-11 | 航天材料及工艺研究所 | Composite material skin net edge coordination tools and assembling method for skins |
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| US20190144134A1 (en) * | 2016-04-20 | 2019-05-16 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft fuselage assembling jig and method of handling aircraft fuselage panel |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113247296A (en) * | 2021-05-31 | 2021-08-13 | 浙江万丰飞机制造有限公司 | Installation tool of thin-wall part of airplane, tool manufacturing method and using method |
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| CN110842845B (en) | 2023-07-18 |
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