CN113427793B - High-strength high-temperature-resistant composite material air inlet channel and forming method thereof - Google Patents
High-strength high-temperature-resistant composite material air inlet channel and forming method thereof Download PDFInfo
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- CN113427793B CN113427793B CN202110565161.5A CN202110565161A CN113427793B CN 113427793 B CN113427793 B CN 113427793B CN 202110565161 A CN202110565161 A CN 202110565161A CN 113427793 B CN113427793 B CN 113427793B
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Classifications
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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
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
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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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/202—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC]
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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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- 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
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
The invention discloses a high-strength high-temperature-resistant composite material air inlet channel and a forming method thereof, belonging to the technical field of composite materials, wherein the wall surface is divided into a plurality of layers of profile modeling cloth layers according to the wall surface thickness of the air inlet channel to be formed; sequentially carrying out outward deviation of single-layer thickness according to the profile of the air inlet channel to obtain the outline shape of each layer of profiling cloth layer, and weaving each layer of profiling cloth by utilizing continuous fibers according to the outline shape of each layer; sequentially paving a plurality of layers of profile modeling cloth on the air inlet male die, and sewing and connecting the adjacent two layers by using continuous fiber bundles during paving; after the female die and the male die are assembled, resin is injected from a glue injection port of the die, and curing molding is carried out by utilizing a resin transfer molding process; and (4) cooling, demolding, and carrying out heat treatment to obtain the high-strength high-temperature-resistant composite material air inlet channel. The invention realizes the molding of the high-strength high-temperature-resistant air inlet channel by adopting the composite material, and solves the problems of material selection and limited molding process of the air inlet channel.
Description
Technical Field
The invention belongs to the technical field of composite materials, and particularly relates to a high-strength high-temperature-resistant composite material air inlet channel and a forming method thereof.
Background
The air inlet is divided into a subsonic air inlet and a supersonic air inlet according to the speed of the aircraft and the using condition. The subsonic aircraft has the advantages that the flying speed is generally 0.7-0.8 mach, incoming flow and force-heat conditions are not harsh, and low-temperature-resistant and low-strength composite materials such as glass fiber reinforced plastics are selected when the material is used for the air inlet channel. Along with the increase of the flying speed, the conditions of incoming flow and force heat become harsh, and particularly, the technical requirements of high temperature resistance and high strength need to be realized by the transonic and supersonic air inlet channels, so that the material selection of the transonic and supersonic air inlet channels can only be limited to titanium alloy and other high temperature resistance and high strength metal materials, and the aims of light structure of the projectile body and cost control are difficult to realize.
Disclosure of Invention
The invention aims to provide a high-strength high-temperature-resistant composite material air inlet and a forming method thereof.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a forming method of a high-strength high-temperature-resistant composite material air inlet channel comprises the following steps:
dividing the wall surface into a plurality of layers of profile cloth layers according to the wall surface thickness of the air inlet channel to be formed;
sequentially carrying out outward deviation of single-layer thickness according to the profile of the air inlet channel to obtain the outline shape of each layer of profiling cloth layer, and weaving each layer of profiling cloth by utilizing continuous fibers according to the outline shape of each layer;
sequentially paving a plurality of layers of profile modeling cloth on the air inlet male die, and sewing and connecting the adjacent two layers by using continuous fiber bundles during paving; the continuous fiber for weaving and the continuous fiber bundle adopt quartz fiber, aramid fiber or carbon fiber;
after the female die and the male die are assembled, resin is injected from a glue injection port of the die, and curing molding is carried out by utilizing a resin transfer molding process (RTM molding);
and (4) cooling, demolding, and carrying out heat treatment to obtain the high-strength high-temperature-resistant composite material air inlet channel.
Further, the air inlet is of an S-shaped pipe structure.
Furthermore, the number of the copying cloth layers is more than 3, because the whole fabric has high rigidity when the number of the copying cloth layers is small, and the copying cloth is not easy to stick to a mold.
Further, each layer of the woven profiling cloth is numbered to prevent confusion.
Further, the multiple layers of profile modeling cloth layers are equal in thickness or unequal in thickness, if the total thickness and the number of layers can be completely divided, the thicknesses of the layers are equal, otherwise, the thicknesses are allowed to be unequal.
Further, the profiling cloth is woven through a 2D or 2.5D weaving method, the 2D weaving method is that single-layer warp and single-layer weft are mutually interwoven, and the profiling cloth is suitable for a single-layer cloth layer with a thin thickness; the 2.5D weaving method is characterized in that single-layer warps and double-layer wefts are mutually interwoven, and the weaving method is suitable for a cloth layer with a single-layer thickness.
Further, resin is injected into a glue injection opening of the mold by using a reaction kettle.
Further, curing was performed using an oven.
Further, the resin is cyanate ester resin, phenolic resin or polyarylacetylene resin.
Further, the heat treatment adopts high-temperature curing, and the high-temperature curing is gradually increased to the highest temperature for using the resin, so that the product is kept for the longest time.
A high-strength high-temperature-resistant composite material air inlet channel is prepared by the method.
The density of the composite material in the invention is 1.4g/cm 3 Comparison with titanium alloy 4.5g/cm 3 The same product can achieve weight reduction 2/3. By applying the technical scheme, compared with a supersonic metal air inlet, the composite material is adopted to manufacture the air inlet, so that the weight of 1/3-1/2 can be reduced, and the temperature resistance of the composite material air inlet is improved by using high-performance fibers and resin in a matched manner. By means of profiling weaving of the fibers, handwork removal in the forming process is achieved, and the paving quality and uniformity of the fibers are guaranteed. The mechanical property of the composite material air inlet channel is improved by the interlayer sewing of the continuous fiber bundles. The forming method realizes the forming of the high-strength high-temperature-resistant air inlet duct by adopting the composite material, has high forming automation degree and good process stability, greatly improves the structural strength and the temperature resistance of the obtained product, meets the technical requirements of a transonic or supersonic aircraft on the air inlet duct, widens the application range of the composite material air inlet duct on the aircraft, and has good demonstration effect and popularization value.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic view of a typical structure of a profiled fabric layer;
in the figure: 1. 2, 3, 4-cloth layer, 5-air inlet inner type.
FIG. 2 is a flowchart of a method for forming a high-strength and high-temperature-resistant composite air inlet according to an embodiment of the invention.
Fig. 3 is a schematic view of the fiber orientation for a 2D weave.
Fig. 4 is a schematic view of the fiber orientation for a 2.5D weave.
Detailed Description
The following provides a detailed description of specific embodiments of the present invention. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the solution according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted, and the present invention is not described in detail as a part known to those skilled in the art.
Example 1
In this embodiment, the inlet duct made of the high-strength and high-temperature-resistant composite material shown in fig. 1 is manufactured, wherein the diameter of the outlet end is 300mm, the oval long circle part of the inlet end is 150mm, and the short circle part is 80 mm. The wall thickness of the air inlet channel is 4 mm. Wherein the composite material is quartz fiber/cyanate resin.
The forming process of the air inlet channel is shown in fig. 2, and the concrete steps are as follows:
the first step is as follows: according to the overall thickness d of the product General assembly And operation experience, the number of cloth layers is designed to be 4, and d is obtained by calculation Sheet 1 mm. Profile deflection d using three-dimensional models Sheet The distance of (a) gives the profile shape of each cloth layer. Designed to adopt asThe 2D knitting method shown in fig. 3, from the inner face to the outer face fabric layers are sequentially marked as fabric layers 1, 2, 3, 4;
the second step is that: preparing a set of profiling fabric, and brushing a release agent on the surface of a mould;
the third step: the cloth layer 1 is sleeved on the surface of the mould in sequence, then the cloth layer 2 is sleeved, after the position of the cloth layer is adjusted to be correct, the continuous quartz fiber is used for carrying out interlayer sewing along the whole molded surface. A cloth sleeving layer 3, sewing cloth layers 3 and 2, a cloth sleeving layer 4 and sewing cloth layers 4 and 3;
the fourth step: and (3) closing the die, putting the cyanate ester resin parked at room temperature into a reaction kettle, heating to melt and stirring at 50 ℃ for 0.5h, and injecting into the die under the pressure of 0.8-1.5 MPa. Curing at the speed of 120 ℃/2h +180 ℃/2h in a drying oven;
the fifth step: demolding;
and a sixth step: putting the product into an oven for heat treatment at 180 ℃/4h +250 ℃/5 min;
the seventh step: and cooling to obtain the high-strength high-temperature-resistant composite material air inlet channel.
The air inlet sampling test piece obtained in the embodiment is subjected to performance test at room temperature, and specific performance is shown in table 1.
The specific performance test method comprises the following steps: the tensile strength and the tensile modulus adopt GB/T1447-; the stamping shear strength adopts GB/T1450.2-2005 stamping shear strength test method of fiber reinforced plastics; the temperature resistance is tested by a heat resistance test.
Example 2
In the embodiment, the high-strength high-temperature-resistant composite material air inlet channel is manufactured, the diameter of the outlet end is 300mm, the oval long circle part of the inlet end is 150mm, and the short circle part is 80 mm. The wall thickness of the air inlet channel is 4 mm. Wherein the composite material is quartz fiber/polyarylacetylene resin.
The forming steps of the air inlet channel are as follows:
the first step is as follows: according to the overall thickness d of the product General assembly And operation experience, the number of cloth layers is designed to be 4, and d is obtained by calculation Sheet 1 mm. Profile deflection d using three-dimensional models Sheet The distance of (a) gives the profile shape of each cloth layer. Design adoptionKnitting with 2.5D knitting method as shown in FIG. 4, and sequentially marking from inner profile surface to outer profile surface cloth layers as cloth layers 1, 2, 3, 4;
the second step is that: preparing a set of profiling fabric, and brushing a release agent on the surface of a mould;
the third step: the cloth layer 1 is sleeved on the surface of the mould in sequence, then the cloth layer 2 is sleeved, after the position of the cloth layer is adjusted to be correct, the continuous quartz fiber is used for carrying out interlayer sewing along the whole molded surface. A cloth sleeving layer 3, sewing cloth layers 3 and 2, a cloth sleeving layer 4 and sewing cloth layers 4 and 3;
the fourth step: and (3) closing the die, putting the polyaryl acetylene resin parked at room temperature into a reaction kettle, heating to melt and stirring at 65 ℃ for 0.5h, and injecting into the die under the pressure of 0.8-1.5 MPa. Curing at the temperature of 120 ℃/10h +250 ℃/4h in a drying oven;
the fifth step: demolding;
and a sixth step: putting the product into an oven for heat treatment at 250 ℃/2h +400 ℃/5 min;
the seventh step: and cooling to obtain the high-strength high-temperature-resistant composite material air inlet channel.
The air inlet sampling test piece obtained in the embodiment is subjected to performance test at room temperature, and specific performance is shown in table 1.
Comparative example 1
The comparison example is used for manufacturing a glass fiber reinforced plastic composite material air inlet, the diameter of the outlet end is 300mm, the oval long circle position of the inlet end is 150mm, and the short circle position is 80 mm. The wall thickness of the air inlet channel is 4 mm. Wherein the composite material is glass fiber/epoxy resin.
The manufacturing process of the air inlet channel is as follows:
the first step is as follows: preparing 0.17mm of rear glass fiber cloth and epoxy resin, and brushing a release agent on the surface of a mold;
the second step is that: layering, namely soaking glass cloth with the thickness of 0.17mm with epoxy resin layer by layer and then surrounding the upper 20 layers of the molded surface of the air inlet channel mold;
the third step: and (4) feeding the air inlet channel which is parked for 8 hours at room temperature into an oven for curing at the temperature of 80 ℃/4 hours.
The fourth step: and (6) demolding.
The fifth step: and cooling to obtain the glass fiber reinforced plastic composite material air inlet channel.
The air inlet sampling test piece obtained in the comparative example is subjected to performance test at room temperature, and specific performance is shown in table 1.
Table 1 comparison of performance test data
As can be seen from Table 1, in the embodiment 1 of the cyanate ester resin, the tensile strength is up to 420MPa, and the temperature resistance is improved to 250 ℃ compared with that of a glass fiber reinforced plastic air inlet channel; in example 2 of the polyarylacetylene resin, the tensile strength is equivalent to that of a glass fiber reinforced plastic air inlet, but the temperature resistance is up to 400 ℃. At the same time, the density of the mixture is 4.5g/cm 3 Compared with the titanium alloy air inlet channel, the weight reduction 2/3 can be realized. The technical scheme provided by the invention can be selected according to the requirements of strength and temperature when in use.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The many features and advantages of these embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of these embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope of the invention as defined by the claims.
Claims (9)
1. A forming method of a high-strength high-temperature-resistant composite material air inlet channel is characterized by comprising the following steps:
dividing the wall surface into a plurality of layers of profile cloth layers according to the wall surface thickness of an air inlet channel to be formed, wherein the air inlet channel is of an S-shaped tubular structure;
sequentially carrying out outward deviation of single-layer thickness according to the profile of the air inlet channel to obtain the outline shape of each layer of profiling cloth layer, and weaving each layer of profiling cloth by utilizing continuous fibers according to the outline shape of each layer;
sequentially paving a plurality of layers of profile modeling cloth on the male die of the air inlet channel, and sewing and connecting adjacent two layers by using continuous fiber bundles when the profile modeling cloth is paved; the continuous fibers and the continuous fiber bundles for weaving each layer of the profiling cloth adopt quartz fibers, aramid fibers or carbon fibers;
after the female die and the male die are assembled, resin is injected from a glue injection port of the die, and curing molding is carried out by utilizing a resin transfer molding process;
and (4) cooling, demolding, and carrying out heat treatment to obtain the high-strength high-temperature-resistant composite material air inlet channel.
2. The method of claim 1, wherein the number of profiled plies is greater than 3.
3. The method of claim 1, wherein the plurality of profiled fabric layers are of equal or unequal thickness, and if the total thickness is divisible by the number of layers, the layers are of equal thickness, otherwise the layers are of unequal thickness.
4. The method of claim 1, wherein the profiled fabric is woven by a 2D or 2.5D weaving process, the 2D weaving process being a single layer of warp yarns interwoven with a single layer of weft yarns, and the 2.5D weaving process being a single layer of warp yarns interwoven with a double layer of weft yarns.
5. The method of claim 1, wherein the resin is injected into the mold gate using a reaction kettle.
6. The method of claim 1, wherein the curing is performed using an oven.
7. The method of claim 1, wherein the resin is a cyanate ester resin, a phenolic resin, or a polyarylacetylene resin.
8. The method of claim 1, wherein the heat treatment is a high temperature cure, the high temperature being the highest temperature at which the resin is used.
9. A high-strength high-temperature-resistant composite air inlet channel, characterized in that the air inlet channel is prepared by the method of any one of claims 1 to 8.
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|---|---|---|---|---|
| CN113954391B (en) * | 2021-10-13 | 2024-03-12 | 上海复合材料科技有限公司 | S-shaped composite material air inlet passage forming die and preparation method thereof |
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