CN115924058B - Composite material wing stiffened wall panel and rear beam trailing edge integrated structure and manufacturing method - Google Patents
Composite material wing stiffened wall panel and rear beam trailing edge integrated structure and manufacturing methodInfo
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- CN115924058B CN115924058B CN202211620930.8A CN202211620930A CN115924058B CN 115924058 B CN115924058 B CN 115924058B CN 202211620930 A CN202211620930 A CN 202211620930A CN 115924058 B CN115924058 B CN 115924058B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
本发明公开了一种复合材料机翼加筋壁板与后梁后缘一体化结构及制作方法，涉及航空技术领域，包括一体固化成型的机翼上壁板蒙皮、机翼后缘蒙皮、壁板长桁和槽型后梁，所述机翼上壁板蒙皮的后缘设置所述机翼后缘蒙皮，所述机翼上壁板蒙皮的下翼面一侧设置所述壁板长桁，所述壁板长桁上设置长桁立筋，所述长桁立筋中间设置长桁立筋夹层，所述壁板长桁靠近后缘的一端设置所述槽型后梁，所述槽型后梁位于所述机翼后缘蒙皮内侧，所述槽型后梁与所述机翼后缘蒙皮构成的后缘空间内填充后缘内填充物。本发明复合材料结构一体化程度高，机翼结构重量轻，能够保证机翼类结构具有良好的水密特性，保证了机翼内设备及后缘内填充物性能的稳定。
The present invention discloses an integrated structure of a composite wing stiffened wall panel and a rear beam trailing edge and a manufacturing method thereof, relating to the field of aviation technology, comprising an integrally solidified wing upper wall panel skin, a wing trailing edge skin, a wall panel long stringer, and a grooved rear beam, wherein the trailing edge of the wing upper wall panel skin is provided with the wing trailing edge skin, the wall panel long stringer is provided on the lower wing surface side of the wing upper wall panel skin, long stringer vertical ribs are provided on the wall panel long stringer, a long stringer vertical rib sandwich is provided in the middle of the long stringer vertical ribs, the grooved rear beam is provided at one end of the wall panel long stringer close to the trailing edge, the grooved rear beam is located on the inner side of the wing trailing edge skin, and the trailing edge space formed by the grooved rear beam and the wing trailing edge skin is filled with a trailing edge filler. The composite material structure of the present invention has a high degree of integration, a light weight of the wing structure, can ensure that the wing-like structure has good watertightness, and ensures the stability of the performance of the wing internal equipment and the trailing edge filler.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a composite material wing reinforced wallboard and rear edge integrated structure of a rear beam and a manufacturing method thereof.
Background
Advanced composite materials have been widely used in the aviation field because of their high specific strength, specific stiffness, corrosion resistance, fatigue resistance, and designability. In particular in the development of aviation products in the last decade, the composite materials of advanced passenger aircraft structures have been used in amounts of more than 50%. The composite material also develops from secondary bearing structures such as ailerons, flaps, elevators, rudders and the like to primary bearing structures such as wings, fuselages and the like at the use positions of the aircraft structure.
With the rapid development of aviation technology, the application of composite materials to aircraft wing structures is increasing. While aviation products are very sensitive to weight, new ideas are continuously applied to pursue higher performance of the aircraft, and new structural forms are created to reduce the structural weight. Meanwhile, the aircraft is in service in various atmospheric environments for a long time, faces the test of rain and snow weather, and has higher requirements on watertight performance while reducing the weight of the structure. The advantage of simultaneous molding of composite materials and structures is urgently needed to be exerted, new manufacturable structural forms are continuously innovated while the weight of the structure is reduced, and the watertight characteristic of the wing structure is improved.
Disclosure of Invention
The invention aims to provide a composite material wing reinforcement wallboard and rear beam trailing edge integrated structure and a manufacturing method thereof, which are used for solving the problems in the prior art, reducing the weight of the composite material wing structure, ensuring that the wing structure has good watertight characteristics and ensuring the stability of the performance of equipment in the wing and filler in the rear edge.
In order to achieve the above object, the present invention provides the following solutions:
The invention provides a composite material wing reinforcement wallboard and trailing edge integrated structure, which comprises an integrally cured and formed wing upper wallboard skin, a wing trailing edge skin, a wallboard stringer and a groove-shaped trailing edge, wherein the wing trailing edge skin is arranged at the trailing edge of the wing upper wallboard skin, the wallboard stringer is arranged at one side of the lower airfoil of the wing upper wallboard skin, a stringer stud is arranged on the wallboard stringer, a stringer stud interlayer is arranged in the middle of the stringer stud, the groove-shaped trailing edge is arranged at one end of the wallboard stringer close to the trailing edge, the groove-shaped trailing edge is positioned at the inner side of the wing trailing edge skin, and a trailing edge space formed by the groove-shaped trailing edge and the wing trailing edge skin is filled with a trailing edge filler.
The invention also provides a manufacturing method of the composite material wing reinforced wallboard and rear beam trailing edge integrated structure, which comprises the following steps:
S1, paving an upper wing panel skin and an upper wing surface skin of a rear edge of a wing on the surface of a first die by adopting wet prepreg, and reserving prepreg required by paving a lower wing surface skin of the rear edge of the wing;
S2, paving a front stringer edge strip and the stringer studs of the panel stringer on the inner side of the wing upper panel skin paved in S1 by adopting wet prepreg, and placing a second die on the inner side of the front stringer edge strip to assist in paving the front stringer edge strip and the stringer studs;
s3, placing the stringer stud interlayer in the middle of the stringer studs laid in the S2;
S4, continuously paving a rear stringer edge strip of the wallboard stringer and an upper airfoil plate of the groove-type back beam at the inner side of the wing upper wallboard skin paved in S1 and behind the stringer studs paved in S2, reserving prepregs required for paving a web plate and a lower airfoil plate of the groove-type back beam, and placing a third die at the inner side of the rear stringer edge strip to assist in paving the rear stringer edge strip;
s5, placing a groove-shaped back beam die on the inner side of an upper wing surface plate of the groove-shaped back beam, and reversely paving the reserved web plate and the lower wing surface plate of the groove-shaped back beam above the groove-shaped back beam die with prepreg required for paving;
S6, placing the rear edge inner filler inside the upper wing surface skin of the wing trailing edge paved in S1 and behind the groove-shaped back beam paved in S5, and reversely paving the reserved prepreg required by paving the lower wing surface skin of the wing trailing edge on the rear edge inner filler and the lower wing panel of the groove-shaped back beam;
S7, integrally curing the prepreg laid in the S6, the first die, the second die, the third die, the groove-type back beam die, the stringer vertical rib interlayer and the rear edge inner filler to form an integrated structure;
S8, taking down the second die, the third die and the groove-shaped back beam die, and taking down the solidified part from the first die;
And S9, polishing the edge of the solidified part, coating sealant, and finishing the preparation of the composite material wing reinforced wallboard and rear edge integrated structure after nondestructive detection.
Preferably, the thickness of the prepreg paved on the upper panel skin and the trailing edge skin of the wing is 0.5-3 mm.
Preferably, the thickness of the prepreg paved by the front stringer edge strip, the stringer studs, the rear stringer edge strip and the groove-type back beam is 0.5-4 mm.
Preferably, the trailing edge inner filler is made of foam or honeycomb material.
Preferably, the stringer stud sandwich is a composite prepreg, foam or honeycomb material, and the laying thickness is 1-3 mm.
Preferably, before curing, the prepreg laid in S6, the first mold, the second mold, the third mold, the channel back beam mold, the stringer sandwich, and the trailing edge inner filler are integrally placed in a vacuum bag, the vacuum bag is vacuumized, and then the curing process is performed together with the vacuum bag.
Preferably, in the step S7, curing is performed in an autoclave, the curing temperature is 120-180 ℃, the curing heat preservation time is 120-180 min, and the pressure in the autoclave is 0.6MPa.
Compared with the prior art, the invention has the following technical effects:
According to the composite material wing reinforcement wallboard and rear edge integrated structure and the manufacturing method thereof, provided by the invention, the wing upper wallboard skin, the wing rear edge skin, the wallboard stringer and the groove-shaped rear beam are manufactured in an integrated mode, no structure separation surface exists, the mechanical connection between the groove-shaped rear beam and the wing rear edge and the upper wallboard structure is reduced, fasteners or adhesives used for connection are reduced, the structural weight is effectively reduced, meanwhile, the wing structure is ensured to have good watertight characteristics, the watertight characteristics of the wing integral structure are ensured under rainy and snowy weather, and the stability of the performance of equipment in the wing and fillers in the rear edge is further ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a method of manufacturing a composite wing stiffened panel and trailing edge integrated structure according to the present invention;
FIG. 2 is a schematic structural view of a composite wing stiffened panel and trailing edge integrated structure of a trailing beam according to the present invention;
In the figure, 1-wing upper panel skin, 2-wing trailing edge skin, 3-panel stringer, 4-channel back beam, 5-stringer stud, 6-stringer stud sandwich, 7-trailing edge inner filler, 8-first mold, 9-wing trailing edge upper wing skin, 10-wing trailing edge lower wing skin, 11-front stringer edge strip, 12-second mold, 13-rear stringer edge strip, 14-upper wing panel, 15-web, 16-lower wing panel, 17-third mold, 18-channel back beam mold
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a composite material wing reinforcement wallboard and rear edge integrated structure and a manufacturing method thereof, which are used for solving the problems existing in the prior art, reducing the weight of a composite material wing structure, ensuring that the wing structure has good watertight characteristics and ensuring the stability of the performance of equipment in the wing and filler in the rear edge.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1-2, this embodiment provides a composite material wing stiffened panel and trailing edge integrated structure, including an integrally cured and formed wing upper panel skin 1, a wing trailing edge skin 2, a panel stringer 3 and a groove-shaped trailing beam 4, wherein the wing trailing edge of the wing upper panel skin 1 is provided with the wing trailing edge skin 2, one side of the lower wing surface of the wing upper panel skin 1 is provided with the panel stringer 3, the panel stringer 3 is provided with a stringer stud 5, a stringer stud interlayer 6 is arranged between the two stringer studs 5, one end of the panel stringer 3 close to the trailing edge is provided with the groove-shaped trailing beam 4, the groove-shaped trailing beam 4 is positioned on the inner side of the wing trailing edge skin 2, and a trailing edge space formed by the groove-shaped trailing beam 4 and the wing trailing edge skin 2 is filled with a trailing edge inner filler 7.
The upper wall plate skin 1, the rear edge skin 2, the wall plate stringers 3 and the groove-shaped rear beams 4 of the wing are integrally cured and molded and manufactured, no structural separation surface exists, the groove-shaped rear beams, the rear edge of the wing and the upper wall plate structure are mechanically connected, fasteners or adhesives used for connection are reduced, the structural weight is effectively reduced, meanwhile, the wing structure is guaranteed to have good watertight characteristics, the watertight characteristics of the whole structure of the wing are guaranteed under rainy and snowy days, and further the stability of the performance of equipment in the wing and the filler 7 in the rear edge is guaranteed. The wing trailing edge skin 2 comprises an integrally cured wing trailing edge upper wing surface skin 9 and a wing trailing edge lower wing surface skin 10.
The manufacturing method of the composite material wing reinforcement wallboard and rear beam trailing edge integrated structure comprises the following steps of:
s1, paving an upper wing panel skin 1 and an upper wing surface skin 9 of the trailing edge of a wing on the surface of a first die 8 by adopting wet prepreg, and reserving a lower wing surface skin 10 of the trailing edge of the wing for paving required prepreg;
S2, paving a front stringer edge strip 11 and stringer studs 5 of a wallboard stringer 3 on the inner side of the wing upper panel skin 1 paved in S1 by adopting wet prepreg, and placing a second die 12 on the inner side of the front stringer edge strip 11 to assist paving the front stringer edge strip 11 and the stringer studs 5;
s3, placing a stringer stud interlayer 6 in the middle of the stringer studs 5 paved in the S2;
S4, continuously paving a rear stringer edge strip 13 of a wallboard stringer 3 and an upper wing panel 14 of a groove-type back beam 4 on the inner side of the wing upper wallboard skin 1 paved in S1 and behind the stringer studs 5 paved in S2, reserving a web 15 and a lower wing panel 16 of the groove-type back beam 4 for paving required prepregs, and placing a third mould 17 on the inner side of the rear stringer edge strip 13 to assist paving of the rear stringer edge strip 13;
S5, placing a groove-shaped back beam mould 18 on the inner side of the upper wing panel 14 of the groove-shaped back beam 4, and reversely paving the reserved web 15 and the lower wing panel 16 of the groove-shaped back beam 4 above the groove-shaped back beam mould 18 with the prepreg required for paving;
S6, placing a trailing edge inner filler 7 at the inner side of the upper wing surface skin 9 of the trailing edge of the wing paved in S1 and behind the slotted back beam 4 paved in S5, and reversely paving the reserved prepreg required for paving the lower wing surface skin 10 of the trailing edge on the trailing edge inner filler 7 and the lower wing panel 16 of the slotted back beam 4;
S7, integrally curing the prepreg, the first die 8, the second die 12, the third die 17, the groove-shaped back beam die 18, the stringer vertical rib interlayer 6 and the rear edge inner filler 7 which are paved in the S6 to form an integrated structure;
S8, taking down the second die 12, the third die 17 and the groove-shaped back beam die 18, and taking down the solidified part from the first die 8;
And S9, polishing the edge of the solidified part, coating a sealant, and finishing the preparation of the composite material wing reinforced wallboard and rear edge integrated structure after nondestructive detection.
The thickness of the prepreg paved on the upper panel skin 1 and the trailing edge skin 2 of the wing is 0.5-3 mm, preferably 1mm.
The thickness of the prepreg paved by the front long truss edge strip 11, the long truss stud 5, the rear long truss edge strip 13 and the groove-shaped back beam 4 is 0.5-4 mm, preferably 2mm.
The trailing edge inner filler 7 is made of foam or honeycomb material.
The stringer studs sandwich 6 is a composite prepreg, foam or honeycomb material laid to a thickness of 1-3 mm, preferably 1mm.
Before curing, the prepreg, the first mold 8, the second mold 12, the third mold 17, the groove-type back beam mold 18, the stringer-sandwich 6 and the rear-edge inner filler 7 which are laid in the step S6 are integrally placed in a vacuum bag, the vacuum bag is vacuumized, and then the curing treatment is carried out together with the vacuum bag.
In the step S7, curing is carried out in an autoclave, the curing temperature is 120-180 ℃, the curing heat preservation time is 120-180 min, and the pressure in the autoclave is 0.6MPa.
The technical scheme of the invention is described in detail below by specific examples.
The invention relates to a manufacturing method of a composite material wing reinforced wallboard and rear beam trailing edge integrated structure, which specifically comprises the following steps:
Step 1, cleaning the surface of a first die 8, coating a release agent, paving an upper wing panel skin 1 and an upper wing surface skin 9 of the rear edge of the wing by adopting carbon fiber resin matrix composite prepreg, wherein the thicknesses of the upper wing panel skin 1 and the upper wing surface skin 9 of the rear edge of the wing are preferably 0.5-3 mm, more preferably 1mm, the paving sequence is preferably [45/-45/0/90] s, and paving the required prepreg by reserving a lower wing surface skin 10 of the rear edge of the wing.
Step 2, paving front stringer edge strips 11 and stringer studs 5 of the wallboard stringers 3 on the inner side of the prepreg of the wing upper panel skin 1 paved in the step 1 by adopting carbon fiber resin matrix composite prepreg, and after coating a release agent on the surface of a second die 12, placing the second die 12 to assist paving of the stringer studs 5 and the front stringer edge strips 11, wherein the thickness of the front stringer edge strips 11 is preferably 0.5-4 mm, more preferably 2mm, the height of the stringer studs 5 is preferably 20-40 mm, more preferably 26mm, and the paving sequence is preferably [45/-45/0/90] 2s.
And 3, placing a stringer vertical rib interlayer 6 in the middle of the stringer vertical ribs 5 paved in the step 2, wherein the stringer vertical rib interlayer 6 is preferably a composite prepreg, foam or honeycomb material, the thickness of the composite prepreg is preferably 1-3 mm, more preferably 1mm, and the layering sequence is preferably [45/-45/0/90] s.
And 4, continuously paving the rear stringer edge strips 13 of the panel stringers 3 and the upper wing panel 14 of the groove-type back beams 4 on the inner side of the prepreg of the wing upper panel skin 1 paved in the step 1 and behind the stringer studs 5 paved in the step 2, and reserving the web 15 and the lower wing panel 16 of the groove-type back beams 4 for paving required prepregs. A third mold 17 coated with a release agent is placed behind the stringer studs 5, the surface of the groove-shaped back beam mold 18 is coated with the release agent, after the groove-shaped back beam mold 18 is placed, the web 15 and the prepreg of the lower airfoil plate 16 of the reserved groove-shaped back beam 4 are reversely paved above the groove-shaped back beam mold 18, the paving thickness is preferably 0.5-4 mm, more preferably 2mm, and the paving sequence is preferably [45/-45/0/90] 2s. The spacing of the stringer studs 5 from the channel back beam 4 is preferably 100 to 200mm, more preferably 115mm.
And 5, placing a trailing edge inner filler 7, which is preferably made of foam or honeycomb material, more preferably made of foam, on the inner side of the prepreg of the wing surface skin 9 on the trailing edge paved in the step 1 and behind the groove-shaped back beam 4 paved in the step 4.
And 6, reversely paving the prepreg required for paving the reserved trailing edge lower airfoil surface skin 10 in the step 1 on the trailing edge inner filler 7 finished in the step 5 and the lower airfoil panel 16 of the wing groove type back beam 4 finished in the step 4.
And 7, covering a vacuum bag above the finished product, adhering the sealing bag to the first die 8 by using sealant at the periphery above the first die 8, and vacuumizing the vacuum bag.
And 8, placing the workpiece and each die into an autoclave for curing, wherein the curing temperature is preferably 120-180 ℃, more preferably 180 ℃, and the heat preservation time is preferably 120-180 min, more preferably 180min. The pressure in the autoclave is preferably 0.6MPa.
And 9, taking out the solidified part, taking out the vacuum bag, sequentially taking out the second die 12, the third die 17 and the groove-shaped back beam die 18, and taking the part out of the first die 8.
And 10, polishing the edges of the parts, coating sealant, and finishing the preparation of the integrated structure of the reinforced wallboard of the composite wing and the rear edge of the rear beam after nondestructive testing. The structure of the finished product is shown in FIG. 2.
The composite material wing reinforcement wallboard and the rear edge integrated structure of the rear girder provided by the invention have the advantages that butt joint or lap joint materials are reduced, fasteners or adhesives used for connection are reduced, the structural weight is effectively reduced, compared with the traditional wing configuration, the rear girder and the upper and lower wing surface wallboard are respectively manufactured, the upper wing surface wallboard and the rear edge are respectively assembled after being manufactured by adopting the fasteners for connection, the structural weight of the composite material wing reinforcement wallboard and the rear edge integrated structure of the rear girder can be reduced by 1.06Kg in the wingspan direction, and compared with the traditional configuration, the weight is reduced by 10.8%, and the comprehensive performance of an airplane is improved.
The wing upper panel skin 1, the wing trailing edge skin 2, the panel stringers 3 and the groove-shaped back beams 4 are integrally molded and manufactured, and have no structure separation surface, so that the wing structure has good watertight characteristics, the watertight characteristics of the whole wing structure are ensured under rainy and snowy weather, and the stability of the performance of equipment in the wing and fillers in the trailing edge is further ensured.
According to the invention, the upper wing panel skin 1, the wing trailing edge skin 2, the panel stringers 3 and the groove-type back beams 4 are integrally cured and molded, and only one set of die is needed to be prepared, so that the occupation of multiple sets of dies and multiple curing processes on an autoclave required by the respective manufacturing of each part is reduced, the additional auxiliary tools and the connecting workload required during the assembly of the parts are reduced, the labor hour consumption and the processing and manufacturing cost are greatly reduced, and the manufacturing efficiency is improved.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided herein to facilitate understanding of the principles and embodiments of the present invention and to provide further advantages and practical applications for those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. The integrated structure is characterized by comprising an integrally cured wing upper panel skin, a wing trailing edge skin, a panel stringer and a groove-shaped trailing beam, wherein the wing trailing edge skin is arranged at the trailing edge of the wing upper panel skin, the panel stringer is arranged at one side of the lower airfoil of the wing upper panel skin, a stringer stud is arranged on the panel stringer, a stringer stud interlayer is arranged in the middle of the stringer stud, the groove-shaped trailing beam is arranged at one end of the panel stringer close to the trailing edge, the groove-shaped trailing beam is positioned at the inner side of the wing trailing edge skin, and a trailing edge space formed by the groove-shaped trailing beam and the wing trailing edge skin is filled with a trailing edge filler;
The panel stringers comprise a front stringer edge strip and a rear stringer edge strip, the joints of the front stringer edge strip and the rear stringer edge strip are respectively provided with a stringer stud, a stringer stud interlayer is arranged between the two stringer studs, the groove-shaped back beam comprises an upper wing panel, a web and a lower wing panel which are integrally cured and formed, the rear stringer edge strip and the upper wing panel of the groove-shaped back beam are integrally cured and formed, the wing trailing edge skin comprises an upper wing surface skin of the wing trailing edge and a lower wing surface skin of the wing trailing edge which are integrally cured and formed, and the lower wing surface skin of the wing trailing edge is downwards folded and overlapped on the lower surface of the lower wing panel of the groove-shaped back beam and is integrally cured and formed with the lower wing panel of the groove-shaped back beam.
2. A method of making a composite wing stiffened panel and trailing edge integrated structure of a trailing beam as defined in claim 1, comprising the steps of:
S1, paving an upper wing panel skin and an upper wing surface skin of a rear edge of a wing on the surface of a first die by adopting wet prepreg, and reserving prepreg required by paving a lower wing surface skin of the rear edge of the wing;
S2, paving a front stringer edge strip and the stringer studs of the panel stringer on the inner side of the wing upper panel skin paved in S1 by adopting wet prepreg, and placing a second die on the inner side of the front stringer edge strip to assist in paving the front stringer edge strip and the stringer studs;
s3, placing the stringer stud interlayer in the middle of the stringer studs laid in the S2;
S4, continuously paving a rear stringer edge strip of the wallboard stringer and an upper airfoil plate of the groove-type back beam at the inner side of the wing upper wallboard skin paved in S1 and behind the stringer studs paved in S2, reserving prepregs required for paving a web plate and a lower airfoil plate of the groove-type back beam, and placing a third die at the inner side of the rear stringer edge strip to assist in paving the rear stringer edge strip;
s5, placing a groove-shaped back beam die on the inner side of an upper wing surface plate of the groove-shaped back beam, and reversely paving the reserved web plate and the lower wing surface plate of the groove-shaped back beam above the groove-shaped back beam die with prepreg required for paving;
S6, placing the rear edge inner filler inside the upper wing surface skin of the wing trailing edge paved in S1 and behind the groove-shaped back beam paved in S5, and reversely paving the reserved prepreg required by paving the lower wing surface skin of the wing trailing edge on the rear edge inner filler and the lower wing panel of the groove-shaped back beam;
S7, integrally curing the prepreg laid in the S6, the first die, the second die, the third die, the groove-type back beam die, the stringer vertical rib interlayer and the rear edge inner filler to form an integrated structure;
S8, taking down the second die, the third die and the groove-shaped back beam die, and taking down the solidified part from the first die;
And S9, polishing the edge of the solidified part, coating sealant, and finishing the preparation of the composite material wing reinforced wallboard and rear edge integrated structure after nondestructive detection.
3. The method for manufacturing the composite material wing reinforcement wallboard and trailing edge integrated structure is characterized in that the thickness of the wing upper wallboard skin and the wing trailing edge skin laying prepreg is 0.5-3 mm.
4. The method for manufacturing the composite wing stiffened panel and trailing edge integrated structure of the trailing beam according to claim 2, wherein the thickness of the prepreg laid by the front stringer edge strip, the stringer stud, the rear stringer edge strip and the groove-type trailing beam is 0.5-4 mm.
5. The method for manufacturing the integrated structure of the reinforced wallboard of the composite wing and the trailing edge of the trailing beam according to claim 2, wherein the filler in the trailing edge is made of foam or honeycomb materials.
6. The method for manufacturing the composite wing reinforced wallboard and rear beam trailing edge integrated structure according to claim 2, wherein the stringer stud sandwich is made of composite prepreg, foam or honeycomb material, and the laying thickness is 1-3 mm.
7. The method of manufacturing a composite wing stiffened panel and trailing edge integrated structure of claim 2, wherein the prepreg, the first mold, the second mold, the third mold, the channel-shaped trailing edge mold, the stringer-sandwich, and the trailing edge inner filler laid in step S6 are integrally placed in a vacuum bag before curing, the vacuum bag is vacuumized, and then the composite wing stiffened panel and trailing edge integrated structure is cured together with the vacuum bag.
8. The method for manufacturing the integrated structure of the reinforced wallboard of the composite wing and the rear edge of the rear beam, which is disclosed in claim 2, is characterized in that in step S7, curing is carried out in an autoclave, the curing temperature is 120-180 ℃, the curing heat preservation time is 120-180 min, and the pressure in the autoclave is 0.6MPa.
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| CN104647771A (en) * | 2015-01-23 | 2015-05-27 | 南京航空航天大学 | K-cor foam sandwich enhanced composite material cap-shaped reinforcing rib wall plate structure and forming method thereof |
| CN110239112A (en) * | 2019-05-20 | 2019-09-17 | 宁波大学 | A processing method for composite hat-shaped reinforced wall panels |
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| CN202358297U (en) * | 2011-11-01 | 2012-08-01 | 哈尔滨飞机工业集团有限责任公司 | Wall plate of airplane wing |
| CN204399464U (en) * | 2014-12-12 | 2015-06-17 | 中国航天空气动力技术研究院 | Integrated composite controlsurface structure |
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| CN112406131B (en) * | 2020-10-30 | 2023-01-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A U-shaped co-cured long stringer, reinforced wall plate and forming method thereof |
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| CN104647771A (en) * | 2015-01-23 | 2015-05-27 | 南京航空航天大学 | K-cor foam sandwich enhanced composite material cap-shaped reinforcing rib wall plate structure and forming method thereof |
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