CN104443429A - Suspended beam type clamping plate structure for central position of movable component of airfoil - Google Patents
Suspended beam type clamping plate structure for central position of movable component of airfoil Download PDFInfo
- Publication number
- CN104443429A CN104443429A CN201410732080.XA CN201410732080A CN104443429A CN 104443429 A CN104443429 A CN 104443429A CN 201410732080 A CN201410732080 A CN 201410732080A CN 104443429 A CN104443429 A CN 104443429A
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- CN
- China
- Prior art keywords
- clamping plate
- airfoil
- suspended beam
- clamp
- beam hole
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Abstract
The invention relates to the field of manufacturing aircrafts, in particular to a suspended beam type clamping plate structure for a central position of a movable component of an airfoil. The structure comprises a clamping plate, suspended beam hole positioners, suspended beam hole plug pins and bolts, wherein the clamping plate is platy, and one side of the clamping plate is caverned to be matched with outlines of a fixed component and the movable component of the airfoil; the suspended beam hole positioners are fixed on the clamping plate through the bolts, and the suspended beam hole plug pins can be inserted into the suspended beam hole positioners; a plurality of bosses for jointing the clamping plate and the fixed component of the airfoil are arranged on the clamping plate, and technical spacers are also arranged between the bosses and the fixed component of the airfoil. The structure disclosed by the invention is simple and reasonable, through the use of the clamping plate structure, the problem of regulating the central position of the movable component of the airfoil is solved, the structural form is succinct, the structure is convenient to manufacture and operate, the preparation time of the technology and the regulation time of the central position of the movable component can be effectively shortened, and the structure has a regulating function through the technical spacers, so that a regulation error of the central position caused by an error of a covered shape of the fixed component of the airfoil is compensated.
Description
Technical field
The present invention relates to aircraft manufacturing field, be specifically related to a kind of suspended beam type wing movable part center position clamp structure.
Background technology
The adjustment of aircraft wing movable part center position generally adopts the methods such as horizontal survey point adjustment, the outer equidistant clamp of frame, measurement of angle clamp, the overall clamp of controlsurface now, these methods or special measurement instrument will be adopted, or special wing bracket will be adopted, or clamp is larger, not only need special instrument or frock operation inconvenience, also can bring measured error because of frock form, cause the problems such as the lengthening of technological preparation cycle, development cost rising, production cycle lengthening, difficult quality guarantee.
Summary of the invention
The object of the invention is to solve the problem, a kind of suspended beam type wing movable part center position clamp structure is provided.
In order to realize object of the present invention, the technical solution used in the present invention is:
A kind of suspended beam type wing movable part center position clamp structure, comprise clamp, drop in beam hole locator, drop in beam hole latch, bolt, the shape of clamp is tabular, it is while the Contour matching of the fixed parts that hollows out with wing and movable part, drop in beam hole locator is bolted on clamp, and drop in beam hole latch can insert to be in drop in beam hole locator.
Clamp is provided with some boss for the laminating between clamp and the fixed parts of wing.
Also process gasket is provided with between boss and the fixed parts of wing.
Beneficial effect of the present invention is: designs simplification, rationally, use which solves wing movable part center position adjustment problem, not only version is succinct, be convenient to manufacture, operate, effectively can reduce technological preparation time, movable part center position regulation time, also because it has adjustment function by process gasket, compensate the center position alignment error that wing fixed parts covering (wallboard) configuration error brings.
Accompanying drawing explanation
Fig. 1 is using state schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: see Fig. 1.
A kind of suspended beam type wing movable part center position clamp structure, comprise clamp 1, drop in beam hole locator 2, drop in beam hole latch 3, bolt 4, the shape of clamp 1 is tabular, it is while hollow out the Contour matching with the fixed parts 7 of wing and movable part 6,8, drop in beam hole locator 2 is fixed on clamp 1 by bolt 4, and drop in beam hole latch 3 can insert to be in drop in beam hole locator 2.
Clamp 1 is provided with some boss 9 for the laminating between clamp 1 and the fixed parts 7 of wing.
Process gasket 5 is also provided with between boss 9 and the fixed parts 7 of wing.
Meter description of operation of the present invention: when carrying out the adjustment of movable part center position, first clamp 1 is placed on solid parts 7 covering (or wallboard) of wing, fitted with covering (or wallboard) surface in boss 9 on clamp 1 surface, then clamp 1 position is adjusted, make drop in beam hole latch 3 through drop in beam hole locator 2 and the solid parts 7 drop in beam hole of wing, check the gap of solid parts 7 aerofoil of wing and clamp 1, inching is carried out by the position of process gasket 5 pairs of clamps 1 according to gap situation, ensure that fixed parts 7 aerofoil describes in poor scope to the gap of clamp 1 all outside, the now adjustment of center position clamp completes.
Then, check the gap of movable part 6 and 8 to center position clamp 1 of wing, and adjust according to gap situation movable part 6,8, movable part and clamp gap are described in poor scope all outside (as cannot to adjust to the right place, can adjust process gasket 5 in fixed-wing facial contour range of tolerable variance, movable part and clamp gap is reexamined after adjustment), be now the center position of movable part.
After adjustment, movable part 6,8 carries out center position mark, then take out drop in beam hole latch, remove center position clamp, regain process gasket, movable part center position has adjusted.
Embodiments of the invention announce be one of preferred embodiment also; but be not limited thereto; those of ordinary skill in the art; very easily according to above-described embodiment; understand spirit of the present invention; and make different amplifications and change, but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.
Claims (3)
1. a suspended beam type wing movable part center position clamp structure, it is characterized in that: comprise clamp, drop in beam hole locator, drop in beam hole latch, bolt, the shape of clamp is tabular, it is while the Contour matching of the fixed parts that hollows out with wing and movable part, drop in beam hole locator is bolted on clamp, and drop in beam hole latch can insert to be in drop in beam hole locator.
2. a kind of suspended beam type wing movable part center position clamp structure according to claim 1, is characterized in that: clamp is provided with some boss for the laminating between clamp and the fixed parts of wing.
3. a kind of suspended beam type wing movable part center position clamp structure according to claim 2, is characterized in that: between boss and the fixed parts of wing, be also provided with process gasket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410732080.XA CN104443429A (en) | 2014-12-06 | 2014-12-06 | Suspended beam type clamping plate structure for central position of movable component of airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410732080.XA CN104443429A (en) | 2014-12-06 | 2014-12-06 | Suspended beam type clamping plate structure for central position of movable component of airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104443429A true CN104443429A (en) | 2015-03-25 |
Family
ID=52890339
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410732080.XA Pending CN104443429A (en) | 2014-12-06 | 2014-12-06 | Suspended beam type clamping plate structure for central position of movable component of airfoil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104443429A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367787A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of synchronization provision for disengagement of vertical shaft type Airplane suspension beam |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103569346A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Vertical fin structure of ship-borne transportation airplanes |
| CN204279980U (en) * | 2014-12-06 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of suspended beam type wing movable part center position clamp structure |
-
2014
- 2014-12-06 CN CN201410732080.XA patent/CN104443429A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103569346A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Vertical fin structure of ship-borne transportation airplanes |
| CN204279980U (en) * | 2014-12-06 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of suspended beam type wing movable part center position clamp structure |
Non-Patent Citations (1)
| Title |
|---|
| 龚时金: "用水平测量法代替外检样板法确定襟、副翼中立位置", 《航空工艺技术》, 28 September 1979 (1979-09-28) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367787A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of synchronization provision for disengagement of vertical shaft type Airplane suspension beam |
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Legal Events
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150325 |