CN213891431U - Novel fixed wing aircraft longeron mould - Google Patents
Novel fixed wing aircraft longeron mould Download PDFInfo
- Publication number
- CN213891431U CN213891431U CN202022589977.5U CN202022589977U CN213891431U CN 213891431 U CN213891431 U CN 213891431U CN 202022589977 U CN202022589977 U CN 202022589977U CN 213891431 U CN213891431 U CN 213891431U
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- transverse strip
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- wing aircraft
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- 239000004568 cement Substances 0.000 claims abstract description 12
- 239000011521 glass Substances 0.000 claims abstract description 12
- 238000009434 installation Methods 0.000 claims abstract description 6
- 238000005086 pumping Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 239000000463 material Substances 0.000 abstract description 5
- 238000007493 shaping process Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 4
- 230000002349 favourable effect Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Abstract
The utility model discloses a novel fixed wing aircraft longeron mould. The device comprises transverse strips, a cylinder insert and a base, wherein the left transverse strip and the right transverse strip are parallel and level with the periphery of the base, and a plurality of vacuum holes and screw holes are distributed on each transverse strip, so that each transverse strip and the base can be conveniently positioned and installed. The base is a regular rectangular structure, is bonded with each transverse strip by glass cement firstly, is connected and fixed by a screw, and is bonded with the cylindrical insert by the glass cement. The utility model discloses compare in traditional whole machine addition type's wing mould, its installation and dismantlement are easier, and operating performance is good, is favorable to guaranteeing the assembly precision, improves assembly efficiency, alleviates workman intensity of labour to its shaping effect is better, and the gas tightness is better, has reduced the use of mould raw and other materials, has reduced mould cost of manufacture.
Description
Technical Field
The utility model relates to a fixed wing aircraft mould field especially relates to a novel fixed wing aircraft longeron mould.
Background
The development level of general aviation is a sign of the development level of the national science and technology and economy, and is also a sign of the development level of the national people. In recent years, with the continuous and rapid development of the economy of China and the great support of the national government policy, the yield of domestic light airplanes, particularly fixed wing airplanes, is increased year by year, and the fixed wing airplanes are one of the unique creations as the aviation technology in the 20 th century, thereby greatly expanding the application range of aircrafts. The fixed-wing aircraft is a typical civil product and can be widely applied to multiple fields of transportation, agriculture, tourism, rescue and the like.
The airplane longitudinal beam is an important part of an airplane structure, is usually connected with an airplane wing, and is an important ring for ensuring the stable connection of the parts of the fixed-wing airplane structure. The traditional airplane longitudinal beam mold is integrally formed by metal materials, the structure is difficult to meet the requirement of air tightness performance, the forming effect is poor, and the airplane mold is made of more materials, so that the mold is heavy and the manufacturing cost is high.
Disclosure of Invention
To above technical problem, the utility model aims to provide a simple structure, material saving, the gas tightness performance is good, and the product percent of pass is high, and the assembly precision is high, and satisfies the aircraft longeron mould of manufacturing requirement.
In order to solve the technical problem, the utility model adopts the following technical scheme:
a novel fixed wing aircraft longeron mould, includes: the left and right cross bars, the cylindrical insert and the base; the left and right cross bars are vertically distributed with the base and are flush with the periphery of the base; the base is of a regular rectangular structure.
Furthermore, a plurality of vacuum holes and screw holes are distributed on the left cross bar and the right cross bar.
Furthermore, the vacuum holes and the screw holes are uniformly distributed on the left cross bar and the right cross bar.
Furthermore, threaded holes and side vacuum holes matched with the left transverse strip and the right transverse strip are distributed on the base, so that subsequent positioning installation and side vacuum pumping are facilitated; the base, the left transverse strip and the right transverse strip are firstly bonded by glass cement and then are fixedly connected by screws; the base and the cylindrical insert are bonded by glass cement.
As above, the utility model provides a pair of novel fixed wing aircraft longeron mould has following advantage:
the left and right crossbands of the novel fixed wing aircraft longitudinal beam mould provided by the utility model are flush with the periphery of the base, a plurality of vacuum holes and screw holes are distributed on each crossband, which is convenient for positioning and mounting each crossband and the base, and five cylindrical inserts are additionally arranged in the middle of the mould for positioning the mould and shaping the shape of the product; the base is of a regular rectangular structure, threaded holes and side vacuum holes which are matched with the left transverse strip and the right transverse strip are distributed on the base, the base and each transverse strip are firstly bonded by glass cement and then are fixedly connected by screws, and the base and the middle cylinder insert are bonded by the glass cement; the corners of the whole die are in smooth transition connection. The utility model discloses compare in traditional integration aircraft mould, its installation and dismantlement are easier, and operating performance is good, is favorable to guaranteeing the assembly precision, improves assembly efficiency, alleviates workman intensity of labour to its shaping effect is better, and the gas tightness is better, has reduced the use of mould raw and other materials, has reduced mould cost of manufacture.
Drawings
Fig. 1 is a schematic view of the overall structure of a novel fixed-wing aircraft longitudinal beam mold.
Fig. 2 is a structural schematic diagram of a novel fixed wing aircraft longitudinal beam mold base.
Fig. 3 is a schematic structural diagram of a novel fixed-wing aircraft longitudinal beam product.
In the figure: 1. a left horizontal bar; 2. a right cross bar; 3. a cylindrical insert; 4. a base; 5. a vacuum hole; 6. screw holes; 7. a threaded hole; 8. side vacuum holes.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are only for illustrating and explaining the present invention, and are not intended to limit the present invention.
Example (b):
please refer to fig. 1, which shows a schematic structural diagram of a novel fixed-wing aircraft longitudinal beam mold according to the present invention, as shown in fig. 1, a fixed-wing aircraft longitudinal beam mold includes: the left and right transverse bars, the five cylindrical inserts and the base; each transverse strip is vertically distributed with the base and the periphery of each transverse strip is flush with the periphery of the base; the base is a regular rectangular structure.
The left cross bar and the right cross bar are uniformly distributed with a plurality of vacuum holes and screw holes; the vacuum holes and the screw holes are uniformly distributed on the left cross bar and the right cross bar; threaded holes and side vacuum holes matched with the left transverse strip and the right transverse strip are distributed on the base, so that subsequent positioning installation and side vacuum pumping are facilitated; the base, the left transverse strip and the right transverse strip are firstly bonded by glass cement and then are fixedly connected by screws; the base and the cylindrical insert are bonded by glass cement.
To sum up, the left and right crossbands of the novel fixed wing aircraft longitudinal beam mould provided by the utility model are flush with the periphery of the base, a plurality of vacuum holes and screw holes are distributed on each crossband, which is convenient for positioning and mounting each crossband and the base, and five cylindrical inserts are additionally arranged in the middle of the mould for positioning the mould and shaping the shape of the product; the base is of a regular rectangular structure, threaded holes and side vacuum holes which are matched with the left transverse strip and the right transverse strip are distributed on the base, the base and each transverse strip are firstly bonded by glass cement and then are fixedly connected by screws, and the base and the middle cylinder insert are bonded by the glass cement; the corners of the whole die are in smooth transition connection. The utility model discloses compare in traditional integration aircraft mould, its installation and dismantlement are easier, and operating performance is good, is favorable to guaranteeing the assembly precision, improves assembly efficiency, alleviates workman intensity of labour to its shaping effect is better, and the gas tightness is better, has reduced the use of mould raw and other materials, has reduced mould cost of manufacture. Therefore, the utility model effectively overcomes the defects of the traditional process and has high industrial utilization value.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the present invention, and any modifications, equivalents and improvements made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (4)
1. A novel fixed wing aircraft longitudinal beam die is characterized by comprising a left transverse strip (1), a right transverse strip (2), a cylindrical insert (3) and a base (4); the left transverse strip (1) and the right transverse strip (2) are vertically distributed with the base (4) and are parallel and level to the periphery; the base (4) is of a regular rectangular structure.
2. An aircraft stringer mould according to claim 1 wherein said left and right crossbars (1, 2) are each provided with vacuum holes (5) and screw holes (6).
3. The aircraft stringer mould according to claim 2, wherein the vacuum holes (5) and the screw holes (6) are evenly distributed on the left and right cross bars (1, 2).
4. The airplane stringer mould according to claim 1, wherein the base (4) is provided with a threaded hole (7) and a side vacuum hole (8) which are matched with the left cross bar (1) and the right cross bar (2) so as to facilitate subsequent positioning and installation and side vacuum pumping; the base (4) is bonded with the left transverse strip (1) and the right transverse strip (2) by glass cement and then is connected and fixed by screws; the base (4) and the cylindrical insert (3) are bonded by glass cement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022589977.5U CN213891431U (en) | 2020-11-11 | 2020-11-11 | Novel fixed wing aircraft longeron mould |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022589977.5U CN213891431U (en) | 2020-11-11 | 2020-11-11 | Novel fixed wing aircraft longeron mould |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213891431U true CN213891431U (en) | 2021-08-06 |
Family
ID=77118052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022589977.5U Expired - Fee Related CN213891431U (en) | 2020-11-11 | 2020-11-11 | Novel fixed wing aircraft longeron mould |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213891431U (en) |
-
2020
- 2020-11-11 CN CN202022589977.5U patent/CN213891431U/en not_active Expired - Fee Related
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210806 |