CN212603543U - Aviation composite part forming tool with blocking frame - Google Patents
Aviation composite part forming tool with blocking frame Download PDFInfo
- Publication number
- CN212603543U CN212603543U CN202021343983.6U CN202021343983U CN212603543U CN 212603543 U CN212603543 U CN 212603543U CN 202021343983 U CN202021343983 U CN 202021343983U CN 212603543 U CN212603543 U CN 212603543U
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- CN
- China
- Prior art keywords
- frame
- keep
- magnet
- magnetic block
- part forming
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 230000000903 blocking effect Effects 0.000 title claims description 20
- 239000002131 composite material Substances 0.000 title claims description 10
- 239000000463 material Substances 0.000 claims abstract description 15
- 230000005389 magnetism Effects 0.000 claims abstract description 13
- 238000007493 shaping process Methods 0.000 claims abstract description 9
- 239000002674 ointment Substances 0.000 abstract description 9
- 239000011505 plaster Substances 0.000 abstract description 9
- 238000007711 solidification Methods 0.000 abstract description 3
- 230000008023 solidification Effects 0.000 abstract description 3
- 239000011162 core material Substances 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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- Magnetic Treatment Devices (AREA)
Abstract
The utility model discloses an aviation combined material part shaping frock with keep off frame, including the frock body, keep off frame, magnetism inhale the structure on the work profile of frock body, be provided with along spreading to paste the edge keep off the frame, keep off the frame with between the frock body with magnetism inhales the structural connection, and preimpregnation material is spread and is pasted on the work profile, keep off frame preimpregnation material bearing edge. This shaping frock can control when applying ointment or plaster preimpregnation material and apply ointment or plaster the size, and the operation of being convenient for apply ointment or plaster is compared and is aligned, and then the fashioned part size of control solidification, and the setting that keeps off the frame can also prevent honeycomb core side direction pressurized and cause the edge shrink, connects the frock body and keeps off the frame through magnetism structure of inhaling, connects reliably, dismantles in a flexible way, convenient operation, frequent use is not fragile.
Description
Technical Field
The utility model relates to an aviation compound material part shaping frock.
Background
When the aviation composite material part is manufactured, prepreg is laid on a forming tool firstly, and then the part enters an autoclave for curing and forming. When the prepreg is paved, the paving size is basically controlled so as not to be too long or too short, which causes unqualified sizes of parts after curing and molding, and the honeycomb core material is required to prevent the defects of edge shrinkage and the like caused by lateral compression, but the existing molding tool has no such function and effect.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: to the problem, the utility model aims at providing an aviation compound material part shaping frock with keep off frame, steerable part size prevents the edge shrink.
The technical scheme is as follows: the utility model provides an aviation combined material part shaping frock with keep off frame, includes the frock body, keeps off frame, magnetism inhales the structure on the work profile of frock body, along paving pasting the edge and being provided with keep off the frame, keep off the frame with between the frock body with magnetism inhales the structural connection, and preimpregnation material is spread and is pasted on the work profile, keep off frame bearing preimpregnation material edge.
One specific structure of the magnetic attraction structure is as follows: including inlaying and locating magnet A on the frock body, and installing keep off the magnet locating pin on the frame, the magnet locating pin with magnet A connects, magnet A with magnet locating pin's connection face is provided with the heavy groove, the magnet locating pin with magnet A's connection face its shape with the heavy groove matches, inserts connect in the heavy groove.
Furthermore, the longitudinal section of the sinking groove is trapezoidal. The sinking groove is convenient for the baffle frame to be matched with the operation and position positioning on the connection through the magnet positioning pin.
Further, the magnetic block A and the tool body, the magnet positioning pin and the blocking frame are respectively fastened and connected through bolts.
Another kind of structure is inhaled to magnetism does: the fixture comprises a magnetic block B embedded on the fixture body and a magnetic block C embedded on the blocking frame, wherein the magnetic block B is connected with the magnetic block C.
Further, the magnetic block B and the tool body, and the magnetic block C and the blocking frame are respectively fastened and connected through bolts.
Furthermore, the magnetic attraction structure is provided with a plurality of magnetic attraction structures along the paving and pasting edge.
Furthermore, the blocking frame is of a strip-shaped structure and is continuously arranged or arranged at intervals along the paving edge.
Has the advantages that: compared with the prior art, the utility model has the advantages that: this shaping frock can control when applying ointment or plaster preimpregnation material and apply ointment or plaster the size, and the operation of being convenient for apply ointment or plaster is compared and is aligned, and then the fashioned part size of control solidification, and the setting that keeps off the frame can also prevent honeycomb core side direction pressurized and cause the edge shrink, connects the frock body and keeps off the frame through magnetism structure of inhaling, connects reliably, dismantles in a flexible way, convenient operation, frequent use is not fragile.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a longitudinal sectional view D-D of FIG. 1 at a magnetic attraction structure;
FIG. 3 is a schematic structural view of a first magnetic attraction structure;
fig. 4 is a schematic structural view of a second magnetic attraction structure.
Detailed Description
The invention will be further elucidated with reference to the drawings and the specific embodiments. These examples are provided only for illustrating the present invention and are not intended to limit the scope of the present invention.
The utility model provides an aviation combined material part shaping frock with keep off frame, as shown in attached 1, 2, includes frock body 1, keeps off frame 2, magnetism inhale structure 3.
Frock body 1 has depth length, is provided with work profile 11 on its surface, and preimpregnation material is spread and is pasted on work profile 11, keeps off frame 2 for bar structure, along spreading edge 12 department setting on work profile 11, can set up in succession or the interval sets up, and magnetism is inhaled structure 3 and is set up and be connected both between keeping off frame 2 and frock body 1, and magnetism is inhaled structure 3 and can be provided with a plurality ofly, makes and keeps off frame 2 and install on frock body 1, keeps off frame 2 bearing preimpregnation material edge.
As shown in fig. 3, the first specific structure of the magnetic attraction structure 3 is: comprises a magnetic block A31 and a magnetic positioning pin 32; the magnetic block A31 is embedded on the outer surface of the tool body 1, the outer surfaces of the magnetic block A31 and the tool body 1 are flush, a sunk groove 33 is formed in the outer surface of the magnetic block A31, the longitudinal section of the sunk groove 33 is trapezoidal, the lower bottom of the trapezoid is flush with the outer surface, and a bolt fastens and connects the magnetic block A31 and the tool body 1 from the sunk groove 33; the bottom of the magnet positioning pin 32 is tightly connected with the baffle frame 2 through a bolt extending from the outer surface of the baffle frame 2, the front end of the magnet positioning pin 32 protrudes out of the inner surface of the baffle frame 2, and the shape of the front end is matched with that of the sinking groove 33; when the blocking frame 2 is connected with the tool body 1, the front end of the magnet positioning pin 32 is inserted into the sinking groove 33 to be connected with the magnetic block A31 to form a connecting surface, the blocking frame 2 and the tool body 1 are fixedly installed by magnetic attraction, and at the moment, the outer surface of the tool body 1 and the outer surface of the magnetic block A31 are attached to the inner surface of the blocking frame 2. The countersunk groove 33 facilitates the operational and positional engagement of the bezel 2 with its attachment by the magnet positioning pin 32.
As shown in fig. 4, the second specific structure of the magnetic attraction structure 3 is: comprises a magnetic block B34 and a magnetic block C35; the magnetic block B34 is embedded on the outer surface of the tool body 1, the outer surfaces of the magnetic block B34 and the tool body 1 are flush, and the magnetic block B34 is fixedly connected with the tool body 1 through bolts; the magnetic block C35 is embedded on the inner surface of the blocking frame 2, the inner surfaces of the magnetic block C35 and the blocking frame 2 are flush, and a bolt extends into the blocking frame 2 from the outer surface of the blocking frame to fixedly connect the magnetic block B34 with the blocking frame 2; when the blocking frame 2 is connected with the tool body 1, the magnetic block B34 and the magnetic block C35 are opposite in position and attracted by magnetic force, so that the blocking frame 2 and the tool body 1 are fixedly installed, and at the moment, the outer surface of the tool body 1 and the outer surface of the magnetic block B34 are attached to the inner surface of the blocking frame 2 and the inner surface of the magnetic block C35.
This shaping frock can control when applying ointment or plaster preimpregnation material and apply ointment or plaster the size, and the operation of being convenient for apply ointment or plaster is compared and is aligned, and then the fashioned part size of control solidification, and the setting that keeps off the frame can also prevent honeycomb core side direction pressurized and cause the edge shrink, connects the frock body and keeps off the frame through magnetism structure of inhaling, connects reliably, dismantles in a flexible way, convenient operation, frequent use is not fragile.
Claims (8)
1. The utility model provides an aviation combined material part shaping frock with keep off frame which characterized in that: including frock body (1), keep off frame (2), magnetism inhale structure (3) on work profile (11) of frock body (1), along spreading to paste edge (12) department and be provided with keep off frame (2), keep off frame (2) with between frock body (1) with magnetism inhales structure (3) and connects, and prepreg spreads to paste on work profile (11), keep off frame (2) bearing prepreg edge.
2. The aviation composite part forming tool with the baffle frame as claimed in claim 1, wherein: magnetic structure (3) are including inlaying locate magnet A (31) on the frock body (1) and installing keep off magnet locating pin (32) on frame (2), magnet locating pin (32) with magnet A (31) are connected, magnet A (31) with be provided with heavy groove (33) on the face of being connected of magnet locating pin (32), magnet locating pin (32) with its shape of the face of being connected of magnet A (31) with heavy groove (33) match, insert connect in heavy groove (33).
3. The aviation composite part forming tool with the baffle frame as claimed in claim 2, wherein: the longitudinal section of the sinking groove (33) is trapezoidal.
4. The aviation composite part forming tool with the baffle frame as claimed in claim 2, wherein: the magnetic block A (31) is respectively and fixedly connected with the tool body (1), the magnet positioning pin (32) is respectively and fixedly connected with the baffle frame (2) through bolts.
5. The aviation composite part forming tool with the baffle frame as claimed in claim 1, wherein: the magnetic attraction structure (3) comprises a magnetic block B (34) embedded on the tool body (1) and a magnetic block C (35) embedded on the blocking frame (2), and the magnetic block B (34) is connected with the magnetic block C (35).
6. The aviation composite part forming tool with the baffle frame as claimed in claim 5, wherein: the magnetic block B (34) is fixedly connected with the tool body (1), and the magnetic block C (35) is fixedly connected with the blocking frame (2) through bolts.
7. The aviation composite part forming tool with the baffle frame as claimed in claim 1, wherein: the magnetic attraction structure (3) is provided with a plurality of magnetic attraction structures along the paving and pasting edge (12).
8. The aviation composite part forming tool with the baffle frame as claimed in claim 1, wherein: the blocking frame (2) is of a strip-shaped structure and is continuously arranged or arranged at intervals along the paving edge (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021343983.6U CN212603543U (en) | 2020-07-09 | 2020-07-09 | Aviation composite part forming tool with blocking frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021343983.6U CN212603543U (en) | 2020-07-09 | 2020-07-09 | Aviation composite part forming tool with blocking frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212603543U true CN212603543U (en) | 2021-02-26 |
Family
ID=74745103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021343983.6U Active CN212603543U (en) | 2020-07-09 | 2020-07-09 | Aviation composite part forming tool with blocking frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212603543U (en) |
-
2020
- 2020-07-09 CN CN202021343983.6U patent/CN212603543U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Forming fixture for aviation composite parts with retaining frames Granted publication date: 20210226 Pledgee: Bank of Jiangsu Limited by Share Ltd. Zhenjiang branch Pledgor: FESHER AVIATION COMPONENTS (ZHENJIANG) CO.,LTD. Registration number: Y2024980008283 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |