CN112210192A - Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof - Google Patents

Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof Download PDF

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CN112210192A
CN112210192A CN202011193120.XA CN202011193120A CN112210192A CN 112210192 A CN112210192 A CN 112210192A CN 202011193120 A CN202011193120 A CN 202011193120A CN 112210192 A CN112210192 A CN 112210192A
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carbon fiber
unmanned aerial
aerial vehicle
composite material
fiber composite
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CN112210192B (en
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刘向
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Dalian Jiaotong University
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Dalian Jiaotong University
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    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/24—Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
    • 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
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • 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
    • B29L2031/3076—Aircrafts
    • B29L2031/3085—Wings
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J2363/00—Characterised by the use of epoxy resins; Derivatives of epoxy resins
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J2383/00—Characterised by the use of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing silicon with or without sulfur, nitrogen, oxygen, or carbon only; Derivatives of such polymers
    • C08J2383/04—Polysiloxanes
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J2463/00—Characterised by the use of epoxy resins; Derivatives of epoxy resins
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J2483/00—Characterised by the use of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing silicon with or without sulfur, nitrogen, oxygen, or carbon only; Derivatives of such polymers
    • C08J2483/04—Polysiloxanes
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/02—Elements
    • C08K3/04—Carbon
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K5/00—Use of organic ingredients
    • C08K5/04—Oxygen-containing compounds
    • C08K5/15—Heterocyclic compounds having oxygen in the ring
    • C08K5/151—Heterocyclic compounds having oxygen in the ring having one oxygen atom in the ring
    • C08K5/1515—Three-membered rings
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K7/00—Use of ingredients characterised by shape
    • C08K7/02—Fibres or whiskers
    • C08K7/04—Fibres or whiskers inorganic
    • C08K7/06—Elements
    • 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

Abstract

The invention discloses a carbon fiber composite material, an unmanned aerial vehicle wing and a preparation method thereof, wherein the carbon fiber composite material comprises carbon fiber prepreg, carbon powder, liquid epoxy resin, a curing agent and a surfactant, the mass ratio of the carbon powder to the carbon fiber prepreg is 1 (50-78), the mass ratio of the sum of the mass of the liquid epoxy resin and the curing agent to the mass of the carbon fiber prepreg is 1 (10-22), and the mass of the surfactant is 1-5% of the sum of the mass of the carbon fiber prepreg, the carbon powder, the liquid epoxy resin and the curing agent; the unmanned aerial vehicle wing made of the carbon fiber composite material and the preparation method of the unmanned aerial vehicle wing are further included. The preparation method provided by the invention has the characteristic of one-step molding, the condition that the joint is easy to break due to the traditional carbon fiber multiple splicing process is overcome, and the obtained carbon fiber composite material unmanned aerial vehicle wing has the advantages of good surface uniformity, high surface flatness, no obvious bubbles and pores and better overall impact resistance.

Description

Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof
Technical Field
The invention relates to the field of novel material processing, in particular to a carbon fiber composite material, an unmanned aerial vehicle wing and a preparation method thereof.
Background
Unmanned aerial vehicle has light in weight, uses extensively, characteristics such as energy consumption low, is being applied to each field such as military affairs, agriculture, pipeline inspection, geological exploration, forest fire prevention, ocean remote sensing more and more now. Because the wing is the most vulnerable part in the unmanned aerial vehicle, the wing not only needs to ensure that the weight of the wing is light enough, but also needs to have good strength and can bear strong pressure and impact resistance in rotation. A large number of facts prove that more than 90% of unmanned aerial vehicles are worn at the wing part. The unmanned aerial vehicle wing prepared from the carbon fiber composite material has the advantages of small density, high specific strength, good collision energy absorption performance and the like due to the carbon fiber, and is widely applied to the field of unmanned aerial vehicles at present.
Traditional carbon fiber unmanned aerial vehicle wing mainly adopts carbon cloth wet process hand to paste or compression molding process, compares with traditional wing shaping mode, and the fashioned combined material of preimpregnation material has mechanical properties and environmental suitability advantages such as the gel content is even, weight is lighter. Simultaneously, the structure forming technology of present unmanned aerial vehicle wing adopts shaping many times and concatenation forming mode, uses two halves mould to splice after shaping respectively, and it can produce the impact fracture easily at seam crossing to be inevitable like this. Patent document CN110193957A discloses a forming process method of composite aileron of small-sized unmanned aerial vehicle, which is an effective one-step forming method in the aspect of increasing the strength performance of carbon fiber unmanned aerial vehicle aileron. However, the solution of patent CN110193957A is limited to the aileron part of the wing of the drone, and is effective in smaller sizes (30 cm and below), and is difficult to be integrally formed in the size of the whole wing (60 to 120 cm) because of the multiple baffles. Still have the impact fracture risk, easily cause the problem of surface unevenness moreover.
Disclosure of Invention
Aiming at the problems, the invention researches and designs the carbon fiber composite material, the unmanned aerial vehicle wing and the preparation method thereof to solve the defects that the traditional carbon fiber composite material unmanned aerial vehicle wing is difficult to integrally form and has low surface flatness. The technical means adopted by the invention are as follows:
a carbon fiber composite material comprises carbon fiber prepreg, carbon powder, liquid epoxy resin, a curing agent and a surfactant, wherein the mass ratio of the carbon powder to the carbon fiber prepreg is 1 (50-78), the mass ratio of the sum of the liquid epoxy resin and the curing agent to the carbon fiber prepreg is 1 (10-22), and the mass of the surfactant is 1-5% of the sum of the carbon fiber prepreg, the carbon powder, the liquid epoxy resin and the curing agent;
the K number of the carbon fiber prepreg is 1-8K, and the particle size of the carbon powder is 10-50 mu m.
Preferably, the surfactant is a glycidyl ether surfactant.
Preferably, the glycidyl ether surfactant is C12-C14 alkyl glycidyl ether.
A method for preparing an unmanned aerial vehicle wing by applying the carbon fiber composite material comprises the following steps:
s1, taking the carbon fiber prepreg, the carbon powder, the liquid epoxy resin, the curing agent and the surfactant according to the mass ratio, and mixing the carbon powder, the liquid epoxy resin and the curing agent to obtain a first mixture;
s2, uniformly coating the obtained first mixture on the surface of the carbon fiber prepreg, and then paving a second layer of carbon fiber prepreg on the surface;
s3, uniformly coating a surfactant on the surface of the second layer of carbon fiber prepreg, and flattening the surface;
s4, cutting the two layers of carbon fiber prepregs obtained in the step S3 to a proper size, laying the two layers of carbon fiber prepregs close to the inner side of the mold, flattening the surface, shearing the excess carbon fiber prepregs along the edge of the mold, aligning and fixing the upper and lower half molds firmly, injecting a liquid silicone rubber material into the mold, and sealing the mold;
and S5, placing the mold in a vacuum environment, heating and curing, and demolding to obtain the carbon fiber composite material unmanned aerial vehicle wing.
Preferably, in step S4, the liquid silicone rubber is any two or three of methyl vinyl dipyrrolidone silane, polydimethylsiloxane, dibenzoyl peroxide and di-tert-butyl peroxy hexane.
Preferably, in step S6, the vacuum degree of vacuum curing is not less than 102Pa。
Preferably, in step S6, the temperature of vacuum curing is 90-120 ℃ for 1-4 hours.
An unmanned aerial vehicle wing prepared by any one of the above methods.
Compared with the prior art, the carbon fiber composite material, the unmanned aerial vehicle wing and the preparation method thereof have the beneficial effects that: the manufacturing process has the characteristics of integration and one-step forming, overcomes the defects that the bonding force at the joint is not tight enough due to the traditional carbon fiber multi-splicing process, and the impact resistance force is easy to break in the joint when external force is applied, and the obtained carbon fiber composite material unmanned aerial vehicle wing has the characteristics of good surface uniformity, high surface flatness, no obvious bubbles and pores, and good overall impact resistance force, and has wide application prospect in the field of unmanned aerial vehicle wings.
Drawings
FIG. 1 is a surface relief map (500 times Leica DMi8A microscope) of a carbon fiber composite material prepared in an example of the present invention;
FIG. 2 is a surface stereograph (500 times Leica DMi8A microscope) of the carbon fiber composite material prepared in the comparative example of the present invention;
Detailed Description
Example (b):
an integrated forming process for wings of an unmanned aerial vehicle made of carbon fiber composite materials comprises the following steps:
(1) mixing carbon powder with the particle size of 20 mu m, liquid epoxy resin and a curing agent according to the mass ratio of 1: 2: 1 and mixing.
(2) Uniformly coating the mixture of carbon powder, liquid epoxy resin and curing agent on the surface of the carbon fiber prepreg, and then paving a second layer of carbon fiber prepreg on the surface, wherein the K number of the selected carbon fiber prepreg is 3K. Wherein the mass ratio of the carbon powder to the carbon fiber prepreg is 1: 60.
(3) and (3) uniformly coating a surfactant material (C12-C14 alkyl glycidyl ether) with the mass ratio of 1.7% on the inner surface of the second layer of carbon fiber prepreg, and flattening the surface.
(4) Cutting the two layers of carbon fiber prepregs obtained in the step (3) to a proper size, laying the two layers of carbon fiber prepregs tightly close to the inner side of the mold, flattening the surface, shearing the surfaces of the two layers of carbon fiber prepregs along the edge of the mold to remove redundant carbon fiber prepregs, aligning and firmly fixing the upper and lower half molds, injecting a liquid silicon rubber material into the mold, and sealing the mold;
(5) putting the integral structure of the mould into a vacuum bag, then inserting a vacuum tube and sealing the vacuum tube with vacuum sealing mud; continuously vacuumizing and heating at 90 ℃ for 4 hours by a vacuum pump connected with a vacuum tube; and separating the mold from the carbon fiber finished product to obtain the carbon fiber composite material unmanned aerial vehicle wing.
Comparative example:
a preparation method of a carbon fiber unmanned aerial vehicle wing comprises the following steps:
(1) liquid epoxy resin and a curing agent are mixed according to the mass ratio of 2: 1 and mixing.
(2) And uniformly coating the mixture of the liquid epoxy resin and the curing agent on the surface of the carbon fiber, and then paving a second layer of carbon fiber on the mixture, wherein the K number of the selected carbon fiber is 3K.
(3) And (3) cutting the two layers of carbon fibers obtained in the step (2) and then respectively placing the cut two layers of carbon fibers into an upper mold and a lower mold.
(4) Putting the two half moulds into a vacuum bag, then inserting a vacuum tube and sealing by using vacuum mud sealing; continuously vacuumizing and heating at 90 ℃ for 4 hours by a vacuum pump connected with a vacuum tube; and separating the mold from the carbon fiber finished product.
(5) And splicing the upper half carbon fiber finished product and the lower half carbon fiber finished product along the seam, and bonding and curing. And grinding and polishing the joint to obtain the carbon fiber unmanned aerial vehicle wing.
The surface morphology (magnification 500 times, scale bar 100 μm) of the carbon fiber unmanned aerial vehicle wing prepared in the embodiment is observed by an inverted metallographic microscope of Leica DMi8A in germany, and compared with a carbon fiber wing part obtained by a traditional carbon fiber material and a method:
fig. 1 is a surface three-dimensional topography view of a carbon fiber unmanned aerial vehicle wing prepared according to an embodiment of the present invention, and fig. 2 is a surface three-dimensional topography view of a carbon fiber structural component obtained by a conventional carbon fiber material and process in a comparative example. The figure shows that the carbon fiber composite unmanned aerial vehicle wing obtained in the embodiment has good surface appearance uniformity, carbon fiber wires are not obviously exposed, the surface flatness is high, and obvious bubbles and pores are avoided; a small amount of carbon fiber tows are exposed on the surface of the wing of the carbon fiber unmanned aerial vehicle obtained by the traditional carbon fiber material and method, and the surface uniformity is poor. The comparison of the figures can show that the surface flatness and uniformity of the carbon fiber composite material unmanned aerial vehicle wing prepared by the embodiment are obviously improved.
On the basis of the design and preparation of the carbon fiber composite material, the integrated forming process method of the stainless steel outer die and the elastic high polymer material inner die is adopted, so that the obtained unmanned aerial vehicle wing has the advantages of good surface uniformity, no layering, high surface flatness and no obvious bubbles and pores. The carbon fiber unmanned aerial vehicle wing obtained by the process has the characteristic of integrated forming, and the defect that the joint is not tight enough in binding force due to the traditional carbon fiber multiple splicing process and is easy to break in the joint when external force comes is overcome. The invention has the other characteristic that the elastic material (liquid silicon rubber material) in the structure which is formed at one time has a supporting function, the elastic material can be easily demoulded, and the formed wing structure can be taken out from the mould after the process is finished.
The above-mentioned embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solution of the present invention by those skilled in the art should fall within the protection scope defined by the claims of the present invention without departing from the spirit of the present invention.

Claims (8)

1. A carbon fiber composite characterized by: the carbon fiber prepreg comprises carbon fiber prepreg, carbon powder, liquid epoxy resin, a curing agent and a surfactant, wherein the mass ratio of the carbon powder to the carbon fiber prepreg is 1 (50-78), the mass ratio of the sum of the liquid epoxy resin and the curing agent to the carbon fiber prepreg is 1 (10-22), and the mass of the surfactant is 1-5% of the sum of the carbon fiber prepreg, the carbon powder, the liquid epoxy resin and the curing agent;
the K number of the carbon fiber prepreg is 1-8K, and the particle size of the carbon powder is 10-50 mu m.
2. A carbon fiber composite material according to claim 1, characterized in that: the surfactant is glycidyl ether surfactant.
3. A carbon fiber composite material according to claim 2, characterized in that: the glycidyl ether surfactant is C12-C14 alkyl glycidyl ether.
4. A method of manufacturing an unmanned aerial vehicle wing using the carbon fiber composite material of any one of claims 1-3, wherein: the method comprises the following steps:
s1, mixing the carbon fiber prepreg, the carbon powder, the liquid epoxy resin, the curing agent and the surfactant according to the mass ratio of any one of claims 1 to 3 to obtain a first mixture;
s2, smearing the obtained first mixture on the surface of the carbon fiber prepreg, and then paving a second layer of carbon fiber prepreg on the surface;
s3, coating a surfactant on the surface of the second layer of carbon fiber prepreg, and flattening the surface;
s4, placing two layers of carbon fiber prepregs into a mold, injecting a liquid silicone rubber material into the mold, and closing the mold;
and S5, placing the mold in a vacuum environment, heating and curing, and demolding to obtain the carbon fiber composite material unmanned aerial vehicle wing.
5. The method for manufacturing the wing of the unmanned aerial vehicle by using the carbon fiber composite material is characterized in that: in step S4, the liquid silicone rubber is any combination of two or three of methyl vinyl dipyrrolidone silane, polydimethylsiloxane, dibenzoyl peroxide, and di-tert-butyl peroxy hexane.
6. The method for manufacturing the wing of the unmanned aerial vehicle by using the carbon fiber composite material is characterized in that: in step S6, the vacuum degree of vacuum solidification is not less than 102Pa。
7. The method for manufacturing the wing of the unmanned aerial vehicle by using the carbon fiber composite material is characterized in that: in step S6, the temperature of vacuum curing is 90-120 ℃ and the time is 1-4 h.
8. An unmanned aerial vehicle wing, its characterized in that: prepared by the process of any one of claims 4 to 7.
CN202011193120.XA 2020-10-30 2020-10-30 Carbon fiber composite material, unmanned aerial vehicle wing and preparation method thereof Active CN112210192B (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113211823A (en) * 2021-05-19 2021-08-06 江苏博实碳纤维科技有限公司 Forming method of carbon fiber composite material unmanned aerial vehicle wing
CN115194830A (en) * 2022-07-11 2022-10-18 浙江佳鹏电脑科技股份有限公司 Application of new carbon fiber knife cylinder material on transverse cutting machine

Citations (5)

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Publication number Priority date Publication date Assignee Title
US20170349720A1 (en) * 2015-01-21 2017-12-07 Toray Industries, Inc. Sizing agent coated carbon fiber bundle, method for manufacturing same, prepreg, and carbon fiber reinforced composite material
CN107932931A (en) * 2017-12-20 2018-04-20 大连交通大学 A kind of efficient carbon fiber cladding process of large area
CN108016054A (en) * 2017-11-20 2018-05-11 刘长喜 Carbon fibre composite is molded membranous disc manufacturing process
CN109795133A (en) * 2018-12-30 2019-05-24 镇江顺龙新材料技术开发有限公司 A kind of automobile polypropylene nitrile Carbon fibe/epoxy resin chair framework preparation method
CN111361180A (en) * 2020-02-14 2020-07-03 大连交通大学 Carbon fiber fine structure component and preparation method thereof

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170349720A1 (en) * 2015-01-21 2017-12-07 Toray Industries, Inc. Sizing agent coated carbon fiber bundle, method for manufacturing same, prepreg, and carbon fiber reinforced composite material
CN108016054A (en) * 2017-11-20 2018-05-11 刘长喜 Carbon fibre composite is molded membranous disc manufacturing process
CN107932931A (en) * 2017-12-20 2018-04-20 大连交通大学 A kind of efficient carbon fiber cladding process of large area
CN109795133A (en) * 2018-12-30 2019-05-24 镇江顺龙新材料技术开发有限公司 A kind of automobile polypropylene nitrile Carbon fibe/epoxy resin chair framework preparation method
CN111361180A (en) * 2020-02-14 2020-07-03 大连交通大学 Carbon fiber fine structure component and preparation method thereof

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113211823A (en) * 2021-05-19 2021-08-06 江苏博实碳纤维科技有限公司 Forming method of carbon fiber composite material unmanned aerial vehicle wing
CN115194830A (en) * 2022-07-11 2022-10-18 浙江佳鹏电脑科技股份有限公司 Application of new carbon fiber knife cylinder material on transverse cutting machine

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