CN110893590A - Symmetrical positioning tool and positioning method for composite material structural part of airplane - Google Patents
Symmetrical positioning tool and positioning method for composite material structural part of airplane Download PDFInfo
- Publication number
- CN110893590A CN110893590A CN201911255924.5A CN201911255924A CN110893590A CN 110893590 A CN110893590 A CN 110893590A CN 201911255924 A CN201911255924 A CN 201911255924A CN 110893590 A CN110893590 A CN 110893590A
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- symmetrical
- digital display
- jackscrew
- indicator
- positioning
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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
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- 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
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention relates to the technical field of positioning tools, in particular to a symmetrical positioning tool for an aircraft composite structural part, wherein a jackscrew stop block is connected with the upper end of the left inner part of a tool frame through a supporting block, the lower end of the left inner part of the tool frame is symmetrically provided with jackscrew stop blocks, the left side and the right side of the tool frame are respectively provided with a pair of moving guide rails, the sliding direction of the moving guide rails is left-right sliding, the upper right side and the lower right side of the inner part of the tool frame are respectively provided with a digital display symmetrical indicator, and the digital display symmetrical indicator is fixed with the tool frame through. The tool is used for positioning a workpiece, the clamping device and the jackscrew stop block on the movable guide rail are adjusted according to the size and the position of the workpiece, the workpiece is clamped by the clamping device and the jackscrew stop block, the digital display symmetrical indicator is opened, the telescopic probe on the digital display symmetrical indicator is contacted with the surface of the workpiece, and when the number of degrees absolute value on the digital display symmetrical indicator is close to or consistent with the number of degrees absolute value by finely adjusting the jackscrew stop block and the movable guide rail, the positioning is completed.
Description
Technical Field
The invention relates to the technical field of airplane structural member positioning, in particular to a symmetrical positioning tool and a symmetrical positioning method for an airplane composite material structural member.
Background
The C919 large-scale passenger plane vertical tail wing box section force bearing front and rear beams are integrally formed by adopting a composite material, the section is I-shaped, the outer edge strips on two sides are designed with an opening angle and a closing angle, the size is as long as 7 meters, the composite material is easy to deform after part characteristics are cured, particularly the outer edge strips have an irregular angle springback phenomenon after part forming, the positioning is inaccurate, so that after assembly, the wall plates cannot be perfectly attached, errors are accumulated to the appearance, the overall aerodynamic appearance is ultra-poor, wing surface type parts are used as an airplane control surface structure, the requirement on the symmetry of the appearance is stricter than that of a plane body and the like, in order to enable high-quality products to be assembled, the selection of a positioning method is particularly important, the influence caused by deformation is difficult to compensate for some traditional positioning modes, and therefore, a new positioning tool and a method are required to control the beam positioning accuracy.
Disclosure of Invention
In order to solve the above problems, in order to achieve the above object, the patent adopts the following technical solutions: the utility model provides a be used for aircraft combined material structure symmetric location frock, the jackscrew dog passes through the supporting shoe to be connected with the inside upper end in frock frame left side, and the inside lower extreme symmetry in frock frame left side is equipped with the jackscrew dog, and frock frame left side, right side respectively are equipped with mated movable guide, and movable guide's slip direction is the horizontal slip, and the inside upper right side of frock frame and right downside are equipped with digital display symmetry indicator respectively, digital display symmetry indicator is fixed with the frock frame through a plurality of location auricles.
The symmetrical positioning tool for the composite material structural part of the airplane is characterized in that at least two pairs of adjustable moving guide rails are arranged.
The symmetrical positioning tool for the composite material structural part of the airplane is characterized in that the adjustable movable guide rail is provided with a clamping device.
The symmetrical positioning tool for the composite material structural part of the airplane is characterized in that universal wheels are arranged between the clamping device and the adjustable moving guide rail.
The symmetrical location frock that is used for aircraft combined material structure spare of foretell, the model of digital display symmetry indicator be: 543 and 782B.
A symmetrical positioning method for an airplane composite structural member is characterized in that a clamping device and a jackscrew stop block on a movable guide rail are adjusted according to the size and the position of a workpiece, the workpiece is clamped by the clamping device and the jackscrew stop block, a digital display symmetrical indicator is started, a telescopic probe on the digital display symmetrical indicator is contacted with the surface of the workpiece, and when the jackscrew stop block and the movable guide rail are finely adjusted to enable absolute values of degrees on the digital display symmetrical indicator to be close to or consistent with each other, positioning is completed.
The invention has the beneficial effects that: the scheme is applied to the vertical tails 10001, 10101 and 10102, completely meets the requirements of engineering and customers, improves the satisfaction of companies in customer eyes, and finally delivers the products qualified for the customers. Meanwhile, the method has wide application range and can be suitable for similar structure cases.
Drawings
FIG. 1 is a schematic structural diagram of a symmetrical positioning tool for an aircraft composite structural member.
The meanings of the symbols in the figures: 1 tooling frame, 2 supporting blocks, 3 adjustable jackscrew stop blocks, 4 adjustable moving guide rails, 5 positioning lug pieces, 6 digital display symmetrical indicators and 7 telescopic probes.
Detailed Description
The present invention is described in further detail below, but is not to be construed as being limited thereto.
Example 1
The utility model provides a be used for aircraft combined material structure symmetric location frock, jackscrew dog 3 passes through supporting shoe 2 and is connected with the inside upper end in frock frame 1 left side, and the inside lower extreme symmetry in frock frame 1 left side is equipped with jackscrew dog 3, and frock frame 1 left side, right side respectively are equipped with two pairs of movable guide 4, and movable guide 4's slip direction is the horizontal slip, and 1 inside upper right side of frock frame and right downside are equipped with digital display symmetry indicator 6 respectively, digital display symmetry indicator 6 is fixed with frock frame 1 through a plurality of location auricles 5. And a clamping device is arranged on the adjustable movable guide rail 4. Universal wheels are arranged between the clamping device and the adjustable movable guide rail (4). The manufacturer of the digital display symmetrical indicator 6 is as follows: mitutoyo, model number: 543 and 782B.
A symmetrical positioning method for an aircraft composite structural member comprises the following steps: adjusting a clamping device on a movable guide rail 4 according to the size and the position of a workpiece, adopting the clamping device, clamping the workpiece by a jackscrew stop block 3, starting a digital display symmetrical indicator 6, arranging a telescopic probe 7 on each digital display symmetrical indicator 6 to directly contact the measured surface of the workpiece, arranging a theoretical position zeroing stop block in each digital display symmetrical indicator 6 component, installing the zeroing stop blocks to enable each probe to be in a theoretical zero-position state before the part is put on a shelf for use, immediately displaying readings after a plurality of groups of symmetrical probes contact the surfaces of different positions of the workpiece, wherein the readings are mostly positive and negative, finely adjusting the position of a product by utilizing the movable adjusting guide rail 4 device and the jackscrew stop block 3 according to the reading condition of each group, and when the absolute values of the readings of each group of digital display symmetrical indicators 4 are consistent (or very close), proving that the product reaches an accurate position.
Claims (6)
1. The utility model provides a be used for aircraft combined material structure symmetric location frock, its characterized in that, jackscrew dog (3) are connected through supporting shoe (2) and the inside upper end in frock frame (1) left side, and the inside lower extreme symmetry in frock frame (1) left side is equipped with jackscrew dog (3), and frock frame (1) left side, right side respectively are equipped with mated moving guide (4), and the direction of sliding of moving guide (4) is the horizontal slip, and frock frame (1) inside upper right side and right downside are equipped with digital display symmetry indicator (6) respectively, digital display symmetry indicator (6) are fixed with frock frame (1) through a plurality of location auricles (5).
2. The tooling for the symmetrical positioning of composite structural members of airplanes as claimed in claim 1, characterised in that said adjustable moving guides (4) are provided in at least two pairs.
3. The symmetrical positioning tooling for the composite structural members of the airplane as claimed in claim 1, wherein the adjustable moving guide rail (4) is provided with a clamping device.
4. The symmetrical positioning tooling for the composite structural members of the aircraft as claimed in claim 3, wherein universal wheels are arranged between the clamping device and the adjustable moving guide rails (4).
5. The symmetrical positioning tool for the composite structural part of the airplane as claimed in claim 1, wherein the digital display symmetrical indicator is of the type: 543 and 782B.
6. The symmetrical positioning method for the composite material structural part of the airplane is characterized in that a clamping device and a jackscrew stop block (3) on a movable guide rail (4) are adjusted according to the size and the position of a workpiece, the workpiece is clamped by the clamping device and the jackscrew stop block (3), a digital display symmetrical indicator (6) is started, a telescopic probe (7) on the digital display symmetrical indicator (6) is in contact with the surface of the workpiece, and when the jackscrew stop block (3) and the movable guide rail (4) are finely adjusted to enable the absolute value of the degree on the digital display symmetrical indicator to be close to or consistent with each other, the positioning is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911255924.5A CN110893590A (en) | 2019-12-10 | 2019-12-10 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911255924.5A CN110893590A (en) | 2019-12-10 | 2019-12-10 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110893590A true CN110893590A (en) | 2020-03-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911255924.5A Pending CN110893590A (en) | 2019-12-10 | 2019-12-10 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
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| CN (1) | CN110893590A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623260A (en) * | 2020-07-29 | 2021-04-09 | 西安飞机工业（集团）有限责任公司 | Positioning and mounting method of sleeve type structure |
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| CN103406843A (en) * | 2013-06-25 | 2013-11-27 | 常州市双成工具有限公司 | Measurement tool |
| CN103846698A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Composite material long purlin milling flexible tool and clamping method of same |
| CN203864027U (en) * | 2014-05-09 | 2014-10-08 | 浙江华荣航空装备有限公司 | Combined-type forming tooling for airplane composite material component |
| CN204855431U (en) * | 2015-08-04 | 2015-12-09 | 赵欣 | A combined material lamination board anchor clamps for being struck by lightning it is experimental |
| CN204935447U (en) * | 2015-08-28 | 2016-01-06 | 重庆帅昌机械制造有限公司 | Clamping device during workpiece is fixed |
| CN108890559A (en) * | 2018-09-28 | 2018-11-27 | 威海光威精密机械有限公司 | Multifunction clamping device |
| CN108942327A (en) * | 2017-05-26 | 2018-12-07 | 中国商用飞机有限责任公司 | It is a kind of for processing the fixture of technique for aircraft composite beam |
| CN209125407U (en) * | 2018-12-22 | 2019-07-19 | 广联航空(南昌)有限公司 | A kind of technique for aircraft composite fixture |
-
2019
- 2019-12-10 CN CN201911255924.5A patent/CN110893590A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4411415A (en) * | 1981-06-12 | 1983-10-25 | Denaro James J | Compound jaw plate |
| CN2617521Y (en) * | 2003-03-29 | 2004-05-26 | 鸿富锦精密工业（深圳）有限公司 | Clamper of electronic indicator |
| CN102003953A (en) * | 2009-09-03 | 2011-04-06 | 成都远景数控设备实业有限公司 | Device and method for measuring form and position deformation of H-shape steel |
| CN103406843A (en) * | 2013-06-25 | 2013-11-27 | 常州市双成工具有限公司 | Measurement tool |
| CN103846698A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Composite material long purlin milling flexible tool and clamping method of same |
| CN203864027U (en) * | 2014-05-09 | 2014-10-08 | 浙江华荣航空装备有限公司 | Combined-type forming tooling for airplane composite material component |
| CN204855431U (en) * | 2015-08-04 | 2015-12-09 | 赵欣 | A combined material lamination board anchor clamps for being struck by lightning it is experimental |
| CN204935447U (en) * | 2015-08-28 | 2016-01-06 | 重庆帅昌机械制造有限公司 | Clamping device during workpiece is fixed |
| CN108942327A (en) * | 2017-05-26 | 2018-12-07 | 中国商用飞机有限责任公司 | It is a kind of for processing the fixture of technique for aircraft composite beam |
| CN108890559A (en) * | 2018-09-28 | 2018-11-27 | 威海光威精密机械有限公司 | Multifunction clamping device |
| CN209125407U (en) * | 2018-12-22 | 2019-07-19 | 广联航空(南昌)有限公司 | A kind of technique for aircraft composite fixture |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623260A (en) * | 2020-07-29 | 2021-04-09 | 西安飞机工业（集团）有限责任公司 | Positioning and mounting method of sleeve type structure |
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Application publication date: 20200320 |
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