CN211994298U - Forming die for forming long and thin composite material I-shaped wall parts of airplane - Google Patents
Forming die for forming long and thin composite material I-shaped wall parts of airplane Download PDFInfo
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- CN211994298U CN211994298U CN201922143194.1U CN201922143194U CN211994298U CN 211994298 U CN211994298 U CN 211994298U CN 201922143194 U CN201922143194 U CN 201922143194U CN 211994298 U CN211994298 U CN 211994298U
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Abstract
The utility model relates to a forming die mould for forming slender composite material I-shaped wall parts of airplanes. In the prior art, in the actual manufacturing process, especially for slender walls, the deformation is easy during the forming, the wall is formed by adopting a die with a casting or aluminum alloy integral structure design, the heat dissipation and ventilation performance are poor during the forming of wall parts, and the influence on the parts is large when the die is heated and expanded. The utility model discloses an it is fixed with last die panel to go up the die frame, and lower die frame is fixed with lower die panel, and the equalizer plate passes through the fix with screw on last die panel, and the exhaust plate is inlayed in the recess of lower die panel, and lower die frame passes through the screw to be connected with the underframe, and the both ends of going up die frame and lower die frame all are equipped with the limit thick plate. The utility model discloses frame construction's mould is favorable to steam to flow wantonly in the middle of the frame and along profile sheet metal upper and lower surface to guarantee that combined material wall class part is heated evenly, shortened intensification and cooling time greatly, improved productivity and product quality.
Description
Technical Field
The utility model belongs to the technical field of the relevant technique of wall class combined material forming die and specifically relates to the moulded die utensil of the long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft.
Background
Wall parts are the main load bearing parts on an airplane, and in order to reduce the weight of the airplane, a large amount of composite materials are applied to all parts of the airplane. The composite material wall parts are generally formed by adopting an autoclave technology in the actual use process. In the actual manufacturing process, especially, the slender wall is easy to deform during the forming, the wall is formed by adopting a die designed by a casting or aluminum alloy integral structure in the past, the heat dissipation and ventilation performance of the wall part are poor during the forming, the thermal expansion coefficient of the die material is inconsistent with that of a composite material part, and the die has a large influence on the part when being heated and expanded. And because the former mould is made or cast by integral welding, the difficulty of later-stage mould maintenance is huge, and the labor cost is increased.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The utility model aims to mainly solve the technical problems and provide a forming die for forming the slender composite material I-shaped wall parts of the airplane.
(II) technical scheme
The technical scheme of the utility model: the forming die for forming the I-shaped wall part made of the slender composite material of the airplane comprises an upper die frame, a lower die frame and a bottom frame; wherein: the upper die frame is fixed with the upper die panel, the lower die frame is fixed with the lower die panel, the pressure equalizing plate is fixed on the upper die panel through screws, the exhaust plate is embedded in a groove of the lower die panel, the lower die frame is connected with the bottom frame through screws, the upper die panel is connected with the lower die panel through the guide block, the bottom frame is provided with a lifting lug, and the two ends of the upper die frame and the lower die frame are respectively provided with a limit plate.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: the upper die frame and the lower die frame are both provided with vent holes.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: and the upper die frame and the lower die frame are provided with vent grooves on the panels.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: the upper die frame and the lower die frame are made of INVAR steel.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: a U-shaped and slotted connection mode is adopted between the bottom frame and the lower die frame, and Q35-A steel is adopted for the bottom frame.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: the thickness of the thickness limiting plate is smaller than that of the web plate of the I-shaped wall part.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: the upper die panel and the lower die panel are both made of INVAR steel panels with the same thickness of 15 mm.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: the ventilation hole evenly distributed is in last mould frame and lower mould frame, under the circumstances of guaranteeing frame intensity, opens great ventilation hole as far as possible, guarantees the gaseous rapid flow of forming process.
The shaping die mould of long and thin combined material "worker" style of calligraphy wall class part of shaping aircraft, wherein: the air channel evenly distributed is on last mould frame and lower mould frame, and the diameter of single air channel is 50mm, and the margin distance of air channel and air channel is 100 mm.
(III) advantageous effects
The utility model has the advantages that: provides a forming die for forming an I-shaped wall part made of slender composite materials of an airplane. The forming die for forming the slender composite material wall part of the airplane can greatly reduce the deformation of the formed composite material wall part, and provides a frame type die with good heat dissipation and ventilation in the forming process of the composite material wall part. The mould with the frame structure is beneficial to the random flow of hot air in the middle of the frame and along the upper surface and the lower surface of the molded surface thin plate, thereby ensuring that composite material wall parts are uniformly heated, greatly shortening the time of temperature rise and temperature reduction, and improving the labor productivity and the product quality. And for later maintenance mould, the degree of difficulty greatly reduced has reduced time and labour cost.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further explained with reference to the drawings.
Drawings
Fig. 1 is a side view of the part shaft of the die of the present invention.
Fig. 2 is a perspective view of the mold structure of the present invention.
Fig. 3 is a front view of the mold structure of the present invention.
Fig. 4 is a top view of the mold structure of the present invention.
Fig. 5 is a structural diagram of the upper mold frame and the upper mold panel of the mold of the present invention.
Fig. 6 is the structure diagram of the lower mold frame, the lower mold panel and the bottom frame of the mold of the present invention.
Fig. 7 is a guide block diagram of the mold of the present invention.
Reference numerals: go up mould frame 01, lower mould frame 02, underframe 03, go up mould panel 1, guide block 2, lower mould panel 3, screw 4, lug 5, equalizer plate 6, exhaust plate 7, limit for thickness board 8, ventilation hole 9, air channel 10.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Embodiment 1, please refer to fig. 1-7, a forming mold for forming an "i" shaped wall part made of an elongated composite material of an airplane comprises an upper mold frame 01, a lower mold frame 02 and a bottom frame 03; wherein: go up mould frame 01 and last die panel 1 fixed, lower mould frame 02 and lower die panel 3 fixed, the equalizer plate 6 passes through the fix with screw on last die panel 1, and exhaust plate 7 is inlayed in the recess of lower die panel 3, and lower mould frame 02 passes through screw 4 and is connected with underframe 03, goes up die panel 1 and passes through guide block 2 and be connected with lower die panel 3, is equipped with lug 5 on the underframe 03, and the both ends of going up mould frame 01 and lower mould frame 02 all are equipped with limit for thickness board 8.
Example 2, please refer to fig. 3, a forming mold for forming an aircraft slender composite material i-shaped wall part, wherein: the upper mold frame 01 and the lower mold frame 02 are both provided with vent holes 9. The rest is the same as example 1.
Example 3, please refer to fig. 3, a forming die for forming an aircraft slender composite material i-shaped wall part, wherein: vent grooves 10 are provided on the top mold frame 01 and the bottom mold frame 02. The rest is the same as example 1.
Example 4, referring to fig. 1-6, a forming die for forming an "i" shaped wall part of an aircraft elongated composite material, wherein: the upper die frame 01 and the lower die frame 02 are both made of INVAR steel. The rest is the same as example 1.
Example 5, referring to fig. 1-6, a forming die for forming an "i" shaped wall part of an aircraft elongated composite material, wherein: a U-shaped slotting connection mode is adopted between the bottom frame 03 and the lower die frame 02, and Q35-A steel is adopted for the bottom frame 03. The rest is the same as example 1.
Example 6, referring to fig. 7, a forming die for forming an "i" shaped wall part of an aircraft elongate composite material, wherein: the thickness of the thickness limiting plate 8 is smaller than the thickness of the web plate of the I-shaped wall part. The rest is the same as example 1.
Example 7, referring to fig. 1-6, a forming die for forming an "i" shaped wall part of an aircraft elongate composite material, wherein: the upper die panel 1 and the lower die panel 3 are both made of INVAR steel panels with the same thickness of 15 mm. The rest is the same as example 1.
Example 8, referring to fig. 1-6, a forming die for forming an "i" shaped wall part of an aircraft elongate composite material, wherein: ventilation hole 9 evenly distributed is on last mould frame 01 and lower mould frame 02, under the circumstances of guaranteeing frame intensity, opens great ventilation hole as far as possible, guarantees the gaseous rapid flow among the forming process. The rest is the same as example 1 or 2.
Example 9, referring to fig. 1-6, a forming die for forming an "i" shaped wall part of an aircraft elongate composite material, wherein: the vent grooves 10 are uniformly distributed on the upper die frame 01 and the lower die frame 02, the diameter of a single vent groove is 50mm, and the side distance between the vent groove and the vent groove is 100 mm. The rest is the same as in example 1 or 3.
The utility model discloses the theory of operation:
the utility model discloses mainly constitute by triplex: an upper die frame 01, a lower die frame 02 and a bottom frame 03; because the thermal expansion coefficients of the composite material and the INVAR steel are close, the deformation condition of the die when the die expands under heat has little influence on the composite material wall parts, so that the upper die frame 01 and the lower die frame 02 both adopt the INVAR steel. In order to save economic cost, the bottom frame 03 is made of Q35-A steel, and a U-shaped slotted connection mode is adopted between the bottom frame 03 and the lower die frame 02, namely: the bottom frame 03 is connected with the lower die frame 02 through the screws 4, so that the expansion deformation of the two frames is inconsistent when heating is eliminated, the deformation of the die is caused to influence the forming quality of parts, and U-shaped grooves are formed in the bottom frame 03 at positions of 200mm at intervals. Go up the mould panel 1 and all adopt equal thickness 15 mm's INVAR steel panel with lower mould panel 3, go up and all open ventilation hole 9 on mould frame 01 and the lower mould frame 02, make things convenient for wall class part forming process in the steam circulation. The upper die frame 01 and the lower die frame 02 are provided with vent grooves 10 on their panels, which facilitates rapid air extraction during the molding process. Because wall part is slender, the mould work portion is also corresponding comparatively thin, goes up mould frame 01 and lower mould frame 02 and adopts the locating pin location and set up guide block 2 at the both ends of last mould frame 01 and lower mould frame 02 and carry out preliminary guiding orientation. In order to ensure that the molded surfaces on the two sides of the I-shaped wall part are uniform in thickness, an aluminum pressure equalizing plate is adopted to limit the thickness. Meanwhile, in order to ensure that the thickness of the middle molded surface of the I-shaped wall part is uniform, two ends of the upper die frame 01 and the lower die frame 02 are respectively provided with a limit thick plate 8, and the thickness of the limit thick plate 8 is smaller than that of a web plate of the I-shaped wall part; firstly, a lower die frame 01 and a bottom frame 03 are connected and positioned by screws 4, after the connection and the positioning are finished, the lower die frame 01 and the bottom frame 03 are respectively paved and pasted on an upper die panel 1 and a lower die panel 2 according to the paving requirement of an I-shaped wall part, after the paving and the pasting are finished, the lower die frame 02 is taken as a reference, the upper die frame 01 is turned over, the guide block 2 is used for preliminary positioning (as shown in figures 4 and 7), and after the preliminary positioning, the positioning pin is used for accurate positioning. After the upper die frame 01 and the lower die frame 02 are positioned, the whole die is conveyed to an autoclave for molding through the lifting lugs 5. The working environment is as follows: not less than 0.096MPa, 0.8MPa external pressure, 200 ℃ temperature, and heat preservation for 3 h.
It is to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The forming die for forming the I-shaped wall part made of the slender composite material of the airplane comprises an upper die frame (01), a lower die frame (02) and a bottom frame (03); the method is characterized in that: go up mould frame (01) and fixed with last die panel (1), lower mould frame (02) are fixed with lower die panel (3), it is fixed on last die panel (1) that equalizer plate (6) pass through the fix with screw, exhaust plate (7) are inlayed in the recess of lower die panel (3), lower mould frame (02) are connected with underframe (03) through screw (4), it is connected with lower die panel (3) through guide block (2) to go up die panel (1), be equipped with lug (5) on underframe (03), the both ends of going up mould frame (01) and lower mould frame (02) all are equipped with limit thick plate (8).
2. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 1, wherein: the upper die frame (01) and the lower die frame (02) are both provided with vent holes (9).
3. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 1, wherein: the upper die frame (01) and the lower die frame (02) are provided with vent grooves (10) on the panels.
4. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 1, wherein: the upper die frame (01) and the lower die frame (02) are both made of INVAR steel.
5. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 1, wherein: a U-shaped and slotted connection mode is adopted between the bottom frame (03) and the lower die frame (02), and Q35-A steel is adopted in the bottom frame (03).
6. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 1, wherein: the thickness of the thickness limiting plate (8) is smaller than the thickness of the web plate of the I-shaped wall part.
7. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 1, wherein: the upper die panel (1) and the lower die panel (3) are both made of INVAR steel panels with the same thickness of 15 mm.
8. A forming die for forming an "i" shaped wall part of an aircraft as claimed in claim 3, wherein: the vent grooves (10) are uniformly distributed on the upper die frame (01) and the lower die frame (02), the diameter of each vent groove is 50mm, and the side distance between each vent groove and each vent groove is 100 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922143194.1U CN211994298U (en) | 2019-12-04 | 2019-12-04 | Forming die for forming long and thin composite material I-shaped wall parts of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922143194.1U CN211994298U (en) | 2019-12-04 | 2019-12-04 | Forming die for forming long and thin composite material I-shaped wall parts of airplane |
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| Publication Number | Publication Date |
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| CN211994298U true CN211994298U (en) | 2020-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201922143194.1U Active CN211994298U (en) | 2019-12-04 | 2019-12-04 | Forming die for forming long and thin composite material I-shaped wall parts of airplane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116061464A (en) * | 2022-12-26 | 2023-05-05 | 江西洪都航空工业集团有限责任公司 | Multi-stringer forming device and forming method |
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2019
- 2019-12-04 CN CN201922143194.1U patent/CN211994298U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116061464A (en) * | 2022-12-26 | 2023-05-05 | 江西洪都航空工业集团有限责任公司 | Multi-stringer forming device and forming method |
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Address after: Nanchang high tech Industrial Development Zone, Jiangxi Province Patentee after: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. |