CN113619158A - Manufacturing process method of large-thickness high-chamfer honeycomb sandwich structure - Google Patents
Manufacturing process method of large-thickness high-chamfer honeycomb sandwich structure Download PDFInfo
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- CN113619158A CN113619158A CN202110878406.XA CN202110878406A CN113619158A CN 113619158 A CN113619158 A CN 113619158A CN 202110878406 A CN202110878406 A CN 202110878406A CN 113619158 A CN113619158 A CN 113619158A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
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- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to the technical field of manufacturing of aviation composite materials, and discloses a manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure. According to the invention, the honeycomb high chamfer angle area is replaced by the high-density honeycomb, and the high-density honeycomb and the sandwich low-density honeycomb are stabilized together, so that the lateral strength of the high-density honeycomb and the low-density honeycomb is enhanced together, the pressure resistance of the honeycomb high chamfer angle area is increased simultaneously, and the problems of sinking and sliding of the large-thickness honeycomb in the honeycomb inclined angle area in the honeycomb interlayer forming process are solved; the requirements of the large-thickness honeycomb and the large-thickness high-density honeycomb are designed in detail, and the requirement of the invention can be met; the method of the invention is detailed, delicate, easy to realize and low in manufacturing cost.
Description
Technical Field
The invention belongs to the technical field of manufacturing of aviation composite materials, relates to a manufacturing method of a honeycomb sandwich structure, and particularly relates to a manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure.
Background
In the preparation process of the civil aircraft wing body fairing, the honeycomb sandwich structure has the characteristics of high specific strength, high specific modulus, light weight and the like, and is a structural form commonly adopted by aircraft composite material parts. Along with the improvement of the requirements of the aircraft fairing on rigidity and weight reduction, the aircraft wing body fairing is designed to be in a large-thickness high-chamfer honeycomb sandwich structure form, and the structural form increases the rigidity of the fairing as much as possible while reducing the weight and reduces the deformation amount of the fairing in the flight process.
Since the honeycomb chamfer is large, and the honeycomb chamfer is larger than 60 degrees in a local area. If a female die is selected for forming the large-thickness high-chamfer honeycomb sandwich structure, the sufficient forming pressure applied to the honeycomb sandwich structure is difficult to confirm in a honeycomb inclined plane area, and the surface flatness of the prepared sandwich structure is poor. The pneumatic surface of a large-thickness high-chamfer composite material workpiece prepared by the male die is a film-sticking surface, so that the surface smoothness is better. The large-thickness high-chamfer honeycomb sandwich structure is based on weight reduction requirements, the volume weight of the honeycomb is low, and in the forming process, the inclined plane of the honeycomb is easy to dent, deform and shrink and slide. Specifically, in the forming process of the large-thickness high-chamfer honeycomb sandwich structure, a honeycomb slope area is pressed, and as the lateral compressive strength of a honeycomb is smaller than the pressure of a prepreg forming process, the honeycomb is sunken laterally and slides and deforms in the forming process of the sandwich structure, so that the honeycomb sandwich structure deforms, skin materials are folded and bent, and the application of the honeycomb sandwich structure is limited.
The sunken deformation of the honeycomb cannot be solved by adopting the conventional prepreg tying mode and the like.
Disclosure of Invention
In order to solve the problems, the invention provides a manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure, which comprises the steps of adopting high-density honeycombs as protection at the edges of the large-thickness honeycomb sandwich structure honeycombs, simultaneously adopting a stabilizing measure to enhance the anti-sliding and deformation capabilities of the large-thickness high-chamfer honeycombs, then preparing the honeycomb sandwich structure, and solving the phenomena of collapse and deformation sliding of the honeycombs in the inclined plane area in the preparation process of the large-thickness high-chamfer honeycomb sandwich structure.
The technical scheme of the invention is as follows:
a manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure comprises the steps of replacing a large-thickness honeycomb with a large-thickness high-density honeycomb within a certain range of a large-thickness honeycomb edge region, stabilizing the processed large-thickness honeycomb by using an adhesive film and prepreg, and then carrying out high chamfer processing on a honeycomb inclined plane.
Further, the method specifically comprises the following steps:
step one, according to the size of a required honeycomb core layer, cutting a large-thickness honeycomb into the size of a removed edge part, wherein the edge part is larger than a part needing chamfering;
cutting the large-thickness high-density honeycomb with the same size as the edge, and splicing the cut large-thickness honeycomb and the large-thickness high-density honeycomb;
thirdly, paving adhesive films and prepreg on the upper and lower surfaces of the spliced honeycomb for stabilization after splicing;
fourthly, high chamfering processing is carried out on the stabilized spliced honeycomb;
and fifthly, taking the spliced honeycomb subjected to high chamfer processing as a sandwich, paving an adhesive film and skin prepreg, covering the outer surface of the sandwich completely, and curing and molding to obtain the large-thickness high-chamfer honeycomb sandwich structure.
Further, in the second step, according to the range of the large-thickness honeycomb needing chamfering, 1 to 4 large-thickness high-density honeycombs are cut out, the thickness of each large-thickness high-density honeycomb is the same as that of each large-thickness honeycomb, the width of each large-thickness high-density honeycomb is slightly larger than the range needing chamfering, and the length of each large-thickness high-density honeycomb is ensured to be capable of being spliced with the large-thickness honeycomb to form the required honeycomb core layer length.
Further, in the step one, the large-thickness honeycomb is cut into a structure with the outer diameter smaller than the required chamfering range of the edge of the honeycomb core layer, in the step two, the large-thickness high-density honeycomb is cut to obtain a large-thickness high-density honeycomb ring, the size and the shape of the inner diameter of the ring are matched with the outer diameter of the cut large-thickness honeycomb, and the outer diameter of the ring is matched with the required outer diameter of the honeycomb core layer.
And further splicing the large-thickness honeycomb and the large-thickness high-density honeycomb by adopting a foaming adhesive film gluing or filling and splicing mode of the filling material.
Further, the bulk density of the high-thickness, high-density honeycomb is at least twice the bulk density of the high-thickness honeycomb.
Further, the stabilizing method in the third step is as follows: curing by adopting an oven or autoclave method, wherein the curing temperature is 120-190 ℃, and the curing time is as follows: 90-240 min, the curing pressure is as follows: 0.05MPa to 0.4 MPa.
Further, the curing and molding method of the fifth step is as follows: curing by adopting an oven or autoclave method, wherein the curing temperature is 120-190 ℃, and the curing time is as follows: 90-240 min, the curing pressure is as follows: 0.3MPa to 0.4 MPa.
The invention has the advantages that:
1. according to the invention, the honeycomb high chamfer angle area is replaced by the high-density honeycomb, and the high-density honeycomb and the sandwich low-density honeycomb are stabilized together, so that the lateral strength of the high-density honeycomb and the low-density honeycomb is enhanced together, the pressure resistance of the honeycomb high chamfer angle area is increased simultaneously, and the problems of sinking and sliding of the large-thickness honeycomb in the honeycomb inclined angle area in the honeycomb interlayer forming process are solved;
2. the invention designs the requirements of the large-thickness honeycomb and the large-thickness high-density honeycomb in detail, and can meet the requirement of the invention;
3. the method of the invention is detailed, delicate, easy to realize and low in manufacturing cost.
Drawings
FIG. 1 is a schematic view of stabilization of a large thickness high chamfer honeycomb of the present invention;
FIG. 2 is a schematic diagram of a honeycomb chamfer after stabilization of a large thickness high chamfer of the present invention;
FIG. 3 is a schematic view of a large thickness high chamfer honeycomb sandwich structure molding of the present invention;
the method comprises the following steps of 1-stabilized prepreg, 2-large-thickness honeycomb, 3-large-thickness high-density honeycomb, 4-splicing part, 5-high chamfer, 6-upper-layer skin prepreg and 7-lower-layer skin prepreg.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure comprises the steps of replacing a large-thickness honeycomb with a large-thickness high-density honeycomb within a certain range of a large-thickness honeycomb edge region, stabilizing the processed large-thickness honeycomb by using an adhesive film and prepreg, and then carrying out high chamfer processing on a honeycomb inclined plane.
The method specifically comprises the following steps:
step one, according to the size of a required honeycomb core layer, cutting a large-thickness honeycomb into the size of a removed edge part, wherein the edge part is larger than a part needing chamfering;
cutting the large-thickness high-density honeycomb with the same size as the edge, and splicing the cut large-thickness honeycomb and the large-thickness high-density honeycomb;
thirdly, paving adhesive films and prepreg on the upper and lower surfaces of the spliced honeycomb for stabilization after splicing;
fourthly, high chamfering processing is carried out on the stabilized spliced honeycomb;
and fifthly, taking the spliced honeycomb subjected to high chamfer processing as a sandwich, paving an adhesive film and skin prepreg, covering the outer surface of the sandwich completely, and curing and molding to obtain the large-thickness high-chamfer honeycomb sandwich structure.
And in the second step, 1 to 4 large-thickness high-density honeycombs are cut according to the range of the large-thickness honeycombs needing chamfering, the thickness of each large-thickness high-density honeycomb is the same as that of each large-thickness honeycomb, the width of each large-thickness high-density honeycomb is slightly larger than the range of the large-thickness high-density honeycomb needing chamfering, and the length of each large-thickness high-density honeycomb is ensured to be capable of being spliced with the large-thickness honeycomb to form the required honeycomb core layer length.
In the step two, the large-thickness high-density honeycomb is cut to obtain a large-thickness high-density honeycomb ring, the size and the shape of the inner diameter of the ring are matched with the outer diameter of the cut large-thickness honeycomb, and the outer diameter of the ring is matched with the outer diameter of the required honeycomb core layer.
And in the second step, splicing the large-thickness honeycomb and the large-thickness high-density honeycomb by adopting a foaming adhesive film gluing or filler filling splicing mode.
The high-thickness, high-density honeycomb has a volume weight at least twice that of the high-thickness honeycomb.
The stabilizing method of the third step is as follows: curing by adopting an oven or autoclave method, wherein the curing temperature is 120-190 ℃, and the curing time is as follows: 90-240 min, the curing pressure is as follows: 0.05MPa to 0.4 MPa.
The curing and forming method of the fifth step comprises the following steps: curing by adopting an oven or autoclave method, wherein the curing temperature is 120-190 ℃, and the curing time is as follows: 90-240 min, the curing pressure is as follows: 0.3MPa to 0.4 MPa.
The principle of the invention is as follows:
the invention provides a forming process method of a large-thickness high-chamfer honeycomb sandwich structure, which is characterized in that in the forming process of the large-thickness high-chamfer honeycomb sandwich structure, because of the weight reduction requirement, low-density honeycombs are adopted as sandwich materials, meanwhile, in order to increase the rigidity of the sandwich structure, the chamfer angle of a honeycomb inclined surface area is higher and is generally more than 60 degrees, the low-density honeycomb inclined surface area cannot resist the curing pressure of prepreg, and the honeycomb inclined surface area is sunken and shrinks and deforms. In the forming process of the large-thickness high-chamfer honeycomb sandwich structure, the honeycomb deforms or collapses to generate slippage and display, so that the large-thickness honeycomb sandwich structure generates defects of deformation or collapse and the like in the forming process.
In the process of forming the large-thickness high-chamfer honeycomb sandwich structure, the high-chamfer honeycomb inclined plane area generates a sinking phenomenon which cannot be eliminated by methods such as tying and the like.
To take a practical example:
the large-thickness high-chamfer honeycomb sandwich structure comprises the following components: the size of the honeycomb area is 650mm multiplied by 1000mm, the thickness of the honeycomb is 60mm, and the chamfer angle of the edge area of the honeycomb is 70 degrees. The manufacturing process of the large-thickness honeycomb sandwich structure is as follows:
step one, cutting a 60 mm-thick 3 honeycomb with the volume weight of 48g/cm into 540mm × 890mm, and cutting a 60 mm-thick 3 honeycomb with the volume weight of 128g/cm into: 2 pieces 890mm x 55mm and 2 pieces 550mm x 55 mm; splicing a high-density honeycomb and a middle low-density honeycomb by adopting a foaming adhesive film, respectively paving a layer of adhesive film and a layer of prepreg on the upper surface and the lower surface of the spliced honeycomb, and then curing in an autoclave, wherein the curing process is carried out according to the curing process conditions of the prepreg;
and step two, processing the edges of the solidified honeycomb to generate a honeycomb inclined plane chamfer angle, wherein the honeycomb inclined plane chamfer angle is 70 degrees.
And thirdly, paving and pasting a lower skin prepreg of the honeycomb sandwich structure on the surface of the mold, paving a layer of adhesive film, placing the honeycomb on the surface of the adhesive film, paving an upper surface adhesive film and an upper skin prepreg, placing an isolation film and an air-permeable felt auxiliary material after the prepreg is paved, sealing by adopting a vacuum bag film and a sealant strip, and then sending into an autoclave for curing the sandwich structure, wherein the curing process is carried out according to the curing process conditions of the prepreg.
Claims (8)
1. A manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure is characterized in that large-thickness honeycombs are replaced by large-thickness high-density honeycombs within a certain range of the edge area of the large-thickness honeycombs, and after the processed large-thickness honeycombs are stabilized by using an adhesive film and prepreg, high chamfer processing is carried out on the inclined surfaces of the honeycombs.
2. The manufacturing process method of the large-thickness high-chamfer honeycomb sandwich structure according to claim 1, characterized by comprising the following steps:
step one, according to the size of a required honeycomb core layer, cutting a large-thickness honeycomb into the size of a removed edge part, wherein the edge part is larger than a part needing chamfering;
cutting the large-thickness high-density honeycomb with the same size as the edge, and splicing the cut large-thickness honeycomb and the large-thickness high-density honeycomb;
thirdly, paving adhesive films and prepreg on the upper and lower surfaces of the spliced honeycomb for stabilization after splicing;
fourthly, high chamfering processing is carried out on the stabilized spliced honeycomb;
and fifthly, taking the spliced honeycomb subjected to high chamfer processing as a sandwich, paving an adhesive film and skin prepreg, covering the outer surface of the sandwich completely, and curing and molding to obtain the large-thickness high-chamfer honeycomb sandwich structure.
3. The manufacturing process method of the large-thickness high-chamfer honeycomb sandwich structure according to claim 2, characterized in that in the second step, according to the range of the large-thickness honeycomb to be chamfered, 1 to 4 large-thickness high-density honeycombs are cut, the thickness of each large-thickness high-density honeycomb is the same as that of the large-thickness honeycomb, the width of each large-thickness high-density honeycomb is slightly larger than the range of the large-thickness honeycomb to be chamfered, and the length of each large-thickness high-density honeycomb ensures that the required length of the honeycomb core layer can be spliced with the large-thickness honeycomb.
4. The manufacturing process method of the large-thickness high-chamfer honeycomb sandwich structure according to claim 2, characterized in that in the first step, the large-thickness honeycomb is cut into a structure with the outer diameter smaller than the required chamfer range of the edge of the honeycomb core layer, and in the second step, the large-thickness high-density honeycomb is cut to obtain a large-thickness high-density honeycomb ring, the inner diameter of the ring is matched with the outer diameter of the cut large-thickness honeycomb, and the outer diameter of the ring is matched with the required outer diameter of the honeycomb core layer.
5. The manufacturing process method of the large-thickness high-chamfer honeycomb sandwich structure according to claim 2, wherein in the second step, the large-thickness honeycomb and the large-thickness high-density honeycomb are spliced by adopting a foaming adhesive film bonding or filler filling splicing mode.
6. The manufacturing process method of the large-thickness high-chamfer honeycomb sandwich structure according to claim 2, characterized in that the stabilizing method of the third step is: curing by adopting an oven or autoclave method, wherein the curing temperature is 120-190 ℃, and the curing time is as follows: 90-240 min, the curing pressure is as follows: 0.05MPa to 0.4 MPa.
7. The manufacturing process method of the large-thickness high-chamfer honeycomb sandwich structure according to claim 2, wherein the curing and forming method of the step five is as follows: curing by adopting an oven or autoclave method, wherein the curing temperature is 120-190 ℃, and the curing time is as follows: 90-240 min, the curing pressure is as follows: 0.3MPa to 0.4 MPa.
8. The manufacturing process method of a large-thickness high-chamfer honeycomb sandwich structure according to claim 1, wherein the volume weight of the large-thickness high-density honeycomb is at least twice of the volume weight of the large-thickness honeycomb.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010000655A (en) * | 2008-06-19 | 2010-01-07 | Mitsubishi Electric Corp | Honeycomb sandwich panel and its manufacturing process |
| US20150151524A1 (en) * | 2012-12-19 | 2015-06-04 | Embraer S.A. | Methods for fabricating stabilized honeycomb core composite laminate structures |
| CN106275379A (en) * | 2015-06-05 | 2017-01-04 | 哈尔滨飞机工业集团有限责任公司 | A kind of composite big thickness deep camber honeycomb parts forming method |
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- 2021-07-30 CN CN202110878406.XA patent/CN113619158A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010000655A (en) * | 2008-06-19 | 2010-01-07 | Mitsubishi Electric Corp | Honeycomb sandwich panel and its manufacturing process |
| US20150151524A1 (en) * | 2012-12-19 | 2015-06-04 | Embraer S.A. | Methods for fabricating stabilized honeycomb core composite laminate structures |
| CN106275379A (en) * | 2015-06-05 | 2017-01-04 | 哈尔滨飞机工业集团有限责任公司 | A kind of composite big thickness deep camber honeycomb parts forming method |
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