CN112406135B - Method for assisting forming of composite propeller blade by air bag blowing - Google Patents
Method for assisting forming of composite propeller blade by air bag blowing Download PDFInfo
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- CN112406135B CN112406135B CN202011231002.3A CN202011231002A CN112406135B CN 112406135 B CN112406135 B CN 112406135B CN 202011231002 A CN202011231002 A CN 202011231002A CN 112406135 B CN112406135 B CN 112406135B
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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
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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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
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a method for assisting the forming of a composite propeller blade by utilizing air bag blowing, which is characterized in that a skin shell of the propeller blade is blown by a flexible air bag, and then an internal core material is manufactured by adopting a foaming process. The method specifically comprises the steps of designing a forming tool, paving and pasting a skin prepreg, placing a flexible air bag, assembling and installing a die, blowing for curing, filling an inner core and the like. The method can uniformly and accurately transmit the pressure applied by the compressed air, ensures the uniform thickness of the skin structure, ensures the internal quality of the skin, and avoids the problem of sandwich pressure loss or insufficient filling in the mould pressing process; compared with the mould pressing and autoclave process, the method has the advantages of simple operation and lower equipment cost, and can be used for mass production. Moreover, the flexible air bag used by the method can be reused, the material is easy to purchase, the manufacturing process is simple, and the production cost and the manufacturing period are effectively reduced.
Description
Technical Field
The invention relates to a method for assisting the forming of a composite propeller blade by utilizing air bag inflation.
Background
The resin-based carbon fiber composite material has superior performances of high specific strength and specific stiffness, strong designability, good fatigue fracture resistance, corrosion resistance, good dimensional stability and the like, and is a high-performance structural material which is widely applied in the fields of aviation, aerospace, traffic and the like at present. With the development of composite material technology and the outstanding performance of mechanical property advantages thereof, the design and use of composite materials in propeller blades are paid extensive attention, various composite materials are used for designing propeller blades in various countries around the world since the 60 s of the 20 th century, and almost all developed advanced propeller blade airplanes are manufactured by adopting the composite materials.
Propeller blade structures are typically "sandwich structures formed of skin shells, foam core materials, and carbon beams. In various molding processes of the carbon fiber composite material, the hot press molding has uniform molding temperature and pressure, and has good adaptability to parts of different materials, shapes, sizes and structures, so that the hot press molding becomes one of the main process methods for researching and manufacturing aerospace high-quality composite material components. At present, the propeller blade is formed by a mould pressing process in a hot-press forming process. The method is characterized in that a mould pressing mould is used for heating and pressing through a hot press in an upper and lower mould closing mode, so that a workpiece is formed at high temperature and high pressure of a mould cavity, and finally the required blade product is obtained. The process has the following three main disadvantages: (1) The mould pressing technology is mainly transferred to the surface of a mould by virtue of pressing machine equipment, and then the mould pressing force is used for controlling a cavity, so that the requirement on the matching of the filler and the mould is very high, and if the filler is improper or the pressure is not transferred in place, the problems of poor glue, layering, fiber wrinkle and the like of a product are easily caused. (2) The heating mode of the mould pressing process mainly depends on the heat transfer of an upper mould and a lower mould of a mould, so that the problem of uneven heat conduction exists, the temperature rising rate of the surface of a workpiece is inconsistent with that of the interior of the workpiece, and the internal forming quality of the workpiece is influenced. (3) The mould pressing mould of the mould pressing process is generally made of steel materials, the precision requirement is high, the manufacturing and maintenance cost is extremely high, and the manufacturing period of repair or reworking is long.
Disclosure of Invention
Aiming at the existing problems, the invention provides a method for assisting the forming of the composite propeller blade by air bag blowing, which adopts a flexible air bag to blow to manufacture a skin shell of the propeller blade and then adopts a foaming process to manufacture an internal core material, thereby effectively solving the problems. The specific technical scheme is as follows:
a method for assisting in forming composite propeller blades by air bag inflation comprises the following steps:
1) Designing a forming tool: designing and processing a metal forming tool for manufacturing the propeller blade according to the external profile modeling of the propeller blade to be prepared; the propeller blade metal forming tool comprises an upper valve die body and a lower valve die body which can be matched and matched; after the upper valve die body and the lower valve die body are laminated, the inner cavity of the die body formed by the inner molded surface is matched with the outer molded surface of the propeller blade in shape;
2) Paving and pasting skin prepreg: respectively paving and adhering the inner profiles of the upper valve mould body and the lower valve mould body of the metal forming tool designed and processed in the step 1) to prepare a reinforced fiber prepreg of the propeller blade skin shell; the reinforced fiber prepreg layers on the upper die body and the lower die body are subjected to layer loss design;
3) Placing a flexible air bag: placing a flexible air bag on the reinforcing fiber prepreg paving layer of the lower die body which is paved in the step 2), and demolding and covering the reinforcing fiber prepreg paving layer on the upper die body on the flexible air bag; then folding the lost layer allowance of the reinforced fiber prepreg paving layer on the lower valve die body to the molding edge of the upper valve die body;
4) Assembling and installing: closing the upper mold body and the lower mold body which are demolded in the step 3), clamping the flexible air bag and the reinforced fiber prepreg for preparing the skin shell in the inner cavity of the mold body, and installing and fixing an air nozzle at the opening of the flexible air bag;
5) And (3) inflation and solidification: sending the device in the step 4) into a curing furnace, connecting an air nozzle with compressed air, carrying out inflation operation on the flexible air bag, slowly applying inflation pressure, and heating and curing after inflation is finished; after the curing is finished, closing the compressed air, removing the air nozzle, and taking out the flexible air bag to obtain a well-blown propeller blade skin shell;
6) Filling an inner core: vertically placing the well blown propeller blade skin shell in the step 5) together with a metal forming tool, pouring a foaming material mixed according to a ratio into the well blown propeller blade skin shell, standing and foaming for more than 2 hours to serve as an inner core of the propeller blade, and then detaching the metal forming tool to obtain the composite propeller blade.
As an optimal technical scheme, in the step 1), positioning guide pin holes and bolt holes for positioning and assembling dies and hoisting holes convenient to carry are correspondingly designed on the upper die body and the lower die body.
As a preferable technical scheme, in the step 2), the reinforced fiber prepreg for preparing the propeller blade skin shell is formed by combining a fabric of carbon fibers or glass fibers and a unidirectional tape; in the laying and pasting process, the vacuum bag process is adopted to compact each three layers of reinforced fiber prepreg, the vacuum degree of compaction is required to be more than or equal to 90kPa, and the compaction time is not less than 5min; the lost layer is designed in such a way that the boundary of the upper mold body layer is designed corresponding to the lower mold body, so that the continuity of the mold surface after mold assembly is ensured; the prepreg designed by the lost layer is at least three layers so as to ensure the strength of the front edge and the rear edge of the propeller blade, and the size requirement of the lost layer is 5-20 mm.
As a further preferable technical scheme, the layer on the lower die body is a decreasing layer, and the boundary of the first layer of the layer is required to extend at least 20mm outwards from the boundary of the lower die body; the layer on the upper valve die body is an incremental layer, and the distance between the first layer of layer and the boundary of the upper valve die body is not less than 15mm; the distance between the lost layers is 2-5 mm.
As a preferred technical scheme, in the step 3), the flexible air bag is made of flexible high-temperature-resistant rubber, and the outer molded surface of the flexible air bag is consistent with the structure of the molded surface of the inner cavity of the skin shell of the propeller blade; which is placed in a direction with the opening towards the root of the propeller blade.
Further preferably, the flexible air bag is made of silicon rubber, the lowest temperature resistance of the flexible air bag is 190 ℃, and the elongation is more than or equal to 300%.
Preferably, in step 4), the air tap is fixed with the opening of the flexible airbag through a flange device.
As a preferred technical solution, in the step 5), the process parameters of the inflation curing are as follows: the blowing pressure is 0.3-0.8 MPa, the curing temperature is 180 +/-6 ℃, and the curing time is 120-180 min.
Further preferably, the inflation pressure is gradually increased from 0.1MPa to the required pressure, and the stop is required to be carried out for at least 2min every time the inflation pressure is increased by 0.1MPa, so that the uneven inflation of the air bag caused by directly applying the pressure is prevented, and the heating curing is carried out after the inflation is finished.
As a preferred technical solution, in step 6), the hair is treatedThe foam material is light rigid foam, and comprises polyurethane foam, epoxy resin or phenolic resin; the density of the foaming material is 100-180 kg/m 3 The temperature resistance is 120-150 ℃.
Compared with the existing manufacturing method of the composite material propeller blade, the method has the following beneficial effects:
(1) The skin shell of the composite propeller blade is manufactured by blowing the flexible air bag, has the excellent performance of the pressure equalizing pad, can uniformly and accurately transmit the pressure applied by compressed air, ensures the uniform thickness of the skin structure and ensures the internal quality of the skin;
(2) The inner core material of the composite material propeller blade is manufactured by adopting a foaming process, the foam material can foam and fill the inner cavity, the distribution is uniform, the operating density is adjustable, and the problem of sandwich pressure loss or insufficient filling in a mould pressing process is avoided;
(3) The curing process of the composite propeller blade adopts the curing furnace for heat treatment, and compared with the die pressing and autoclave process, the curing process has the advantages of simple operation and lower equipment cost, and can be used for mass production;
(4) The flexible air bag used by the method can be repeatedly used, the material is easy to purchase, the manufacturing process is simple, and the production cost and the manufacturing period are effectively reduced.
Drawings
FIG. 1 is a schematic structural view of a composite propeller blade according to the present invention;
FIG. 2 is a schematic view of a mold closing structure of the metal forming tool of the present invention;
FIG. 3 is a schematic structural view of a longitudinal section of a mold assembly of the metal forming tool of the present invention;
FIG. 4 is a schematic structural view of a flexible airbag and a reinforcing fiber prepreg clamped in an inner cavity of a mold body according to the present invention;
FIG. 5 is a schematic view of the process of injecting the foaming material according to the present invention.
In the figure: 1. a propeller blade; 11. a skin shell; 12. an inner core; 2. a metal forming tool; 21. an upper valve mold body; 22. a lower die body; 23. positioning a guide pin hole; 24. bolt holes; 25. hoisting holes; 3. reinforcing fiber prepreg; 4. a flexible bladder; 5. an air tap; 6. a foam material; 7. a flange device.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the embodiments and the accompanying drawings, and it is to be understood that the described embodiments are merely preferred embodiments of the present invention, rather than all embodiments, and are not intended to limit the present invention in other forms, and that any person skilled in the art may make changes or modifications using the technical contents disclosed. However, any simple modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope of the technical solution of the present invention.
Example 1
The embodiment is a method for assisting the forming of a composite propeller blade by using air bag inflation, the structure of the composite propeller blade 1 is formed by filling an inner core 12 of a foaming material into a skin shell 11 of a composite material as shown in fig. 1, and the forming method comprises the following steps:
1) Designing a forming tool: according to the shape of the outer surface of the propeller blade 1 to be prepared, a metal forming tool 2 for manufacturing the propeller blade 1 is designed and processed in a machining mode, as shown in fig. 2 and 3; the metal forming tool 2 for the propeller blade 1 comprises an upper valve die body 21 and a lower valve die body 22 which can be matched and matched; after the upper valve die body 21 and the lower valve die body 22 are laminated, a die body inner cavity 20 formed by the inner molded surface is matched with the outer molded surface of the propeller blade 1 in shape; and the upper die body 21 and the lower die body 22 are correspondingly provided with a positioning guide pin hole 23 and a bolt hole 24 for positioning and assembling dies and a hoisting hole 25 convenient to carry.
2) Paving and pasting skin prepreg: respectively paving and adhering the inner profiles of an upper valve die body 21 and a lower valve die body 22 of the metal forming tool 2 designed and processed in the step 1 to prepare a reinforced fiber prepreg 3 of the skin shell 11 of the propeller blade 1; and the reinforced fiber prepreg 3 layers on the upper die body 21 and the lower die body 22 are designed to be lost; the reinforced fiber prepreg 3 for preparing the skin shell 11 of the propeller blade 1 is formed by combining a fabric of carbon fiber or glass fiber and a unidirectional tape; during the laying and pasting process, the vacuum bag process is adopted to compact each three layers of the reinforced fiber prepreg 3, the vacuum degree is required to be more than or equal to 90kPa, and the compacting time is not less than 5min. The lost layer is designed in such a way that the layer laying boundary of the upper die body 21 is designed to correspond to the lower die body 22, so that the continuity of the die surface after die assembly is ensured. The prepreg which needs to be subjected to layer loss design is at least three layers so as to ensure the strength of the front edge and the rear edge of the propeller blade 1, and the size of the layer loss is required to be 5-20 mm. In this embodiment, the ply on the lower valve body 22 is a decreasing ply, and the first ply boundary of the decreasing ply is required to extend at least 20mm outwards from the boundary of the lower valve body 22; the layer on the upper valve die body 21 is an incremental layer, and the distance between the first layer of layer and the boundary of the upper valve die body 21 is not less than 15mm; the distance between the lost layers is 2-5 mm.
3) Placing a flexible air bag: placing a flexible air bag 4 on the reinforcing fiber prepreg 3 layer of the lower die body 22 which is paved in the step 2, and demoulding the reinforcing fiber prepreg 3 layer on the upper die body 21 to cover the flexible air bag 4; then folding the lost layer allowance of the reinforced fiber prepreg 3 layer on the lower die body 22 to the molding edge of the upper die body 21; the flexible air bag 4 is made of flexible high-temperature-resistant rubber materials, is preferably supported by silicon rubber materials, has the minimum temperature resistance requirement of 190 ℃ and has the elongation requirement of more than or equal to 300 percent. The outer profile of the flexible air bag 4 is consistent with the inner cavity profile structure of the skin shell 11 of the propeller blade 1; which is placed in a direction opening towards the root of the propeller blade 1.
4) Die assembly and installation: and (3) closing the upper die body 21 and the lower die body 22 which are demolded in the step (3), screwing the bolt 24, clamping the flexible air bag 4 and the reinforced fiber prepreg 3 for preparing the skin shell 11 in the inner cavity 20 of the die bodies, as shown in fig. 4, installing an air nozzle 5 at the opening of the flexible air bag 4, and fixing the air nozzle 5 and the opening of the flexible air bag 4 together through the flange device 7.
5) And (3) blowing and curing: sending the device in the step 4 into a curing furnace, connecting an air nozzle 5 with compressed air, carrying out blowing operation on the flexible air bag 4, slowly increasing the blowing pressure from 0.1MPa to 0.6MPa when the blowing pressure is applied, and requiring at least 2min for each increase of 0.1MPa, so as to prevent the air bag from blowing unevenly due to direct application of pressure, and carrying out heating curing after blowing is finished, wherein the curing process parameters are as follows: the curing temperature is 180 +/-6 ℃, and the curing time is 120-180 min. And after the curing is finished, closing the compressed air, dismantling the air nozzle 5, and taking out the flexible air bag 4 to obtain the well-blown propeller blade skin shell 11.
6) Filling an inner core: vertically placing the well-blown propeller blade skin shell 11 and the metal forming tool 2 in the step 5 together, mixing the well-mixed foaming material 6 according to the proportion at a stirring speed of 2000 r/min, fully mixing for 30s, pouring the mixture into the well-blown propeller blade skin shell 11 through a propeller root joint, standing and foaming for more than 2h to serve as an inner core 12 of the propeller blade as shown in figure 5, and then removing the metal forming tool 2, so that the composite propeller blade 1 can be obtained. In this embodiment, the foaming material 6 is a light rigid foam, and includes polyurethane foam, epoxy resin or phenolic resin; the density of the foaming material 6 is 100-180 kg/m 3 The temperature resistance is 120-150 ℃.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. A method for assisting the forming of a composite propeller blade by air bag blowing is characterized in that: the method comprises the following steps:
1) Designing a forming tool: designing and processing a metal forming tool (2) for manufacturing the propeller blade (1) according to the external profile modeling of the propeller blade (1) to be prepared; the metal forming tool (2) for the propeller blade (1) comprises an upper valve die body (21) and a lower valve die body (22) which can be matched and matched; after the upper valve die body (21) and the lower valve die body (22) are combined, a die body inner cavity (20) formed by the inner profile of the upper valve die body is matched with the outer profile of the propeller blade (1) in shape;
2) Paving and pasting skin prepreg: respectively paving and preparing reinforced fiber prepreg (3) of a skin shell (11) of the propeller blade (1) on the inner profile surfaces of an upper flap die body (21) and a lower flap die body (22) of the metal forming tool (2) designed and processed in the step 1); and the reinforced fiber prepreg (3) layers on the upper die body (21) and the lower die body (22) are designed to be lost; the lost layer is designed in such a way that the layer boundary of the upper die body (21) is designed to correspond to the lower die body (22), so that the continuity of the die surface after die assembly is ensured; the prepreg designed by the lost layer is at least three layers so as to ensure the strength of the front edge and the rear edge of the propeller blade (1), and the size of the lost layer is required to be 5-20 mm; specifically, the layer on the lower valve die body (22) is a decreasing layer, and the boundary of the first layer of the layer is required to extend at least 20mm outwards from the boundary of the lower valve die body (22); the layer on the upper valve die body (21) is an incremental layer, and the distance between the first layer of layer and the boundary of the upper valve die body (21) is required to be not less than 15mm; the distance between the lost layers is 2-5 mm;
3) Placing a flexible air bag: placing a flexible air bag (4) on the reinforcing fiber prepreg (3) layer of the lower die body (22) which is paved in the step 2), and demoulding and covering the reinforcing fiber prepreg (3) layer on the upper die body (21) on the flexible air bag (4); then, folding lost layer allowance of the reinforced fiber prepreg (3) laying on the lower die body (22) to the forming edge of the upper die body (21);
4) Assembling and installing: closing the upper die body (21) and the lower die body (22) which are demolded in the step 3), clamping the flexible air bag (4) and the reinforced fiber prepreg (3) for preparing the skin shell (11) in an inner cavity (20) of the die bodies, and installing and fixing an air nozzle (5) at an opening of the flexible air bag (4);
5) And (3) inflation and solidification: sending the device in the step 4) into a curing furnace, connecting an air nozzle (5) with compressed air, carrying out inflation operation on the flexible air bag (4), slowly applying inflation pressure, and heating and curing after inflation is finished; after solidification is finished, the compressed air is closed, the air nozzle (5) is removed, the flexible air bag (4) is taken out, and a rotor blade skin shell (11) which is well blown is obtained; the technological parameters of the inflation and solidification are as follows: the blowing pressure is 0.3-0.8 MPa, the curing temperature is 180 +/-6 ℃, and the curing time is 120-180 min; when the inflation pressure is applied, the pressure is slowly increased from 0.1MPa to the required pressure, and the stop is required to be carried out for at least 2min every time the pressure is increased by 0.1MPa, so that the uneven inflation of the air bag caused by directly applying the pressure is prevented;
6) Filling an inner core: vertically placing the well blown propeller blade skin shell (11) and the metal forming tool (2) in the step 5), pouring the foaming material (6) mixed according to the proportion into the well blown propeller blade skin shell (11), standing and foaming for more than 2h to serve as an inner core (12) of the propeller blade, and then detaching the metal forming tool (2) to obtain the composite propeller blade (1).
2. The method of assisting in the formation of a composite propeller blade using airbag inflation as set forth in claim 1, wherein: in the step 1), positioning guide pin holes (23) and bolt holes (24) for positioning and closing the dies and hoisting holes (25) convenient to carry are correspondingly designed on the upper die body (21) and the lower die body (22).
3. The method of assisting in the formation of composite propeller blades using airbag inflation of claim 1, wherein the method further comprises the steps of: in the step 2), the reinforced fiber prepreg (3) for preparing the skin shell (11) of the propeller blade (1) is formed by combining a fabric of carbon fiber or glass fiber and a unidirectional tape; during the laying and pasting process, the vacuum bag process is adopted to compact each three layers of the reinforced fiber prepreg (3), the vacuum degree of compaction is required to be more than or equal to 90kPa, and the compaction time is not less than 5min.
4. The method of assisting in the formation of composite propeller blades using airbag inflation of claim 1, wherein the method further comprises the steps of: in the step 3), the flexible air bag (4) is made of flexible high-temperature-resistant rubber, and the outer molded surface of the flexible air bag is consistent with the structure of the inner cavity molded surface of the skin shell (11) of the propeller blade (1); the direction of placement is such that the opening is towards the root of the propeller blade (1).
5. The method of assisting in the formation of a composite propeller blade using airbag inflation of claim 4, wherein: the flexible air bag (4) is made of silicon rubber, the lowest temperature resistance is 190 ℃, and the elongation is more than or equal to 300%.
6. The method of assisting in the formation of a composite propeller blade using airbag inflation as set forth in claim 1, wherein: in the step 4), the air tap (5) is fixed with the opening of the flexible air bag (4) through the flange device (7).
7. The method of assisting in the formation of composite propeller blades using airbag inflation of claim 1, wherein the method further comprises the steps of: in the step 6), the foaming material (6) is light rigid foam, and comprises polyurethane foam, epoxy resin or phenolic resin; the density of the foaming material (6) is 100-180 kg/m 3 The temperature resistance is 120-150 ℃.
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| CN113478865A (en) * | 2021-07-12 | 2021-10-08 | 重庆泛锐科技有限公司 | Foam board forming method |
| CN114378986A (en) * | 2021-12-10 | 2022-04-22 | 昌河飞机工业（集团）有限责任公司 | Telescopic paddle die assembly |
| CN114889786B (en) * | 2022-05-17 | 2023-03-28 | 中国人民解放军海军工程大学 | Composite propeller blade |
| CN115056510B (en) * | 2022-07-06 | 2024-02-13 | 航天海鹰(镇江)特种材料有限公司 | Method for forming propeller blade by using double yellow bags to assist autoclave |
| CN116512639A (en) * | 2023-06-26 | 2023-08-01 | 北京玻钢院复合材料有限公司 | Composite material hand lay-up forming anti-drop tool and use method thereof |
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| US5042968A (en) * | 1989-11-02 | 1991-08-27 | United Technologies Corporation | Propeller blade subassembly and method for making a propeller blade subassembly |
| CN100385114C (en) * | 2005-04-01 | 2008-04-30 | 同济大学 | Wind machine's laminae made from composite material and preparation method |
| WO2009078871A1 (en) * | 2007-12-18 | 2009-06-25 | Bell Helicopter Textron Inc. | Rotor blade and method of making same |
| CN104669642A (en) * | 2015-01-13 | 2015-06-03 | 哈尔滨飞机工业集团有限责任公司 | Method for molding tail blades of composite material by using airbag |
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