CN112722233A - Unmanned aerial vehicle composite material fuselage and preparation method thereof - Google Patents
Unmanned aerial vehicle composite material fuselage and preparation method thereof Download PDFInfo
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- CN112722233A CN112722233A CN202011534758.5A CN202011534758A CN112722233A CN 112722233 A CN112722233 A CN 112722233A CN 202011534758 A CN202011534758 A CN 202011534758A CN 112722233 A CN112722233 A CN 112722233A
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- fiber layer
- aerial vehicle
- unmanned aerial
- fuselage
- carbon fiber
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- 239000002131 composite material Substances 0.000 title claims abstract description 32
- 238000002360 preparation method Methods 0.000 title abstract description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 45
- 239000004917 carbon fiber Substances 0.000 claims abstract description 45
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 44
- 229920006231 aramid fiber Polymers 0.000 claims abstract description 29
- 239000003365 glass fiber Substances 0.000 claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 claims abstract description 4
- 239000004744 fabric Substances 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 12
- 239000011152 fibreglass Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 abstract description 15
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000011157 advanced composite material Substances 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000003513 alkali Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
- B32B2262/0261—Polyamide fibres
- B32B2262/0269—Aromatic polyamide fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Abstract
An unmanned aerial vehicle composite fuselage and a method of making the same, the fuselage comprising: the glass fiber layer, carbon fiber layer and aramid fiber layer, wherein, carbon fiber layer set up in on the glass fiber layer, aramid fiber layer set up in on the carbon fiber layer. The unmanned aerial vehicle fuselage structure performance that this application provided is excellent for unmanned aerial vehicle combined material fuselage and preparation method, and the unmanned aerial vehicle fuselage structure performance who designs is excellent, has sufficient intensity and rigidity, has lighter weight simultaneously, make full use of combined material's designability characteristics to and utilize combined material's selection material and layer to realize fuselage structure's optimal design, excellent performance.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle fuselages, and particularly relates to an unmanned aerial vehicle composite fuselage and a preparation method thereof.
Background
At present, the application range of the composite material in the unmanned aerial vehicle is wider and wider, the application of a reasonably designed composite material structure is an effective means for light weight design of the unmanned aerial vehicle, and meanwhile, the performance index of the unmanned aerial vehicle can be effectively improved. The purpose of the composite material unmanned aerial vehicle body is to effectively reduce the weight of the unmanned aerial vehicle body under the condition of ensuring the load.
The unmanned aerial vehicle fuselage mainly is frame roof beam structural design form and whole crust structural style, and frame roof beam structure need design the roof beam of very strong intensity, and nevertheless the structure opening needs the convenience, and whole crust structural design intensity and rigidity are all higher, but are more sensitive to the opening. But the unmanned aerial vehicle combined material fuselage at present can't satisfy above-mentioned requirement simultaneously.
Disclosure of Invention
In view of the above, the present invention provides a composite fuselage for a drone and a method for making the same that overcome or at least partially solve the above-mentioned problems.
In order to solve the technical problem, the invention provides an unmanned aerial vehicle composite material fuselage, which comprises: the glass fiber layer, carbon fiber layer and aramid fiber layer, wherein, carbon fiber layer set up in on the glass fiber layer, aramid fiber layer set up in on the carbon fiber layer.
Preferably, the areal density of the glass fibre layer is 100g/m 2.
Preferably, the thickness of the glass fiber layer is 0.08mm to 0.12 mm.
Preferably, the carbon fiber layer is carbon fiber cloth.
Preferably, the carbon fiber cloth is 3K carbon fiber cloth.
Preferably, the 3K carbon fiber cloth is 1 or 2 layers.
Preferably, the aramid fiber layer has an areal density of 100g/m 2.
Preferably, the thickness of the aramid fiber layer is 0.15mm to 0.19 mm.
The invention also provides a preparation method of the composite material fuselage of the unmanned aerial vehicle, wherein the composite material fuselage of the unmanned aerial vehicle comprises the composite material fuselage of the unmanned aerial vehicle, and the method comprises the following steps:
forming a glass fiber layer with a preset shape;
forming a carbon fiber layer on the glass fiber layer;
and forming an aramid fiber layer on the carbon fiber layer.
One or more technical solutions in the embodiments of the present invention have at least the following technical effects or advantages: the application provides a this application provides an unmanned aerial vehicle combined material fuselage and preparation method thereof, and the unmanned aerial vehicle fuselage structural performance who designs is excellent, has sufficient intensity and rigidity, has lighter weight simultaneously, make full use of combined material's designability characteristics to and utilize combined material's selection material and layer to realize fuselage structure's optimal design, excellent performance.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
Fig. 1 is a schematic view of a composite fuselage of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic view of a composite fuselage of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic view of a composite fuselage of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 4 is a schematic view of a composite fuselage of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 5 is a schematic view of a composite fuselage of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 6 is a schematic view of a composite fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail below with reference to specific embodiments and examples, and the advantages and various effects of the present invention will be more clearly apparent therefrom. It will be understood by those skilled in the art that these specific embodiments and examples are for the purpose of illustrating the invention and are not to be construed as limiting the invention.
Throughout the specification, unless otherwise specifically noted, terms used herein should be understood as having meanings as commonly used in the art. Accordingly, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. If there is a conflict, the present specification will control.
Unless otherwise specifically stated, various raw materials, reagents, instruments, equipment and the like used in the present invention are commercially available or can be prepared by existing methods.
As shown in fig. 1-6, in an embodiment of the present application, the present invention provides a composite fuselage of an unmanned aerial vehicle, including: the glass fiber layer 10, the carbon fiber layer 20 and the aramid fiber layer 30, wherein the carbon fiber layer 20 is arranged on the glass fiber layer 10, and the aramid fiber layer 30 is arranged on the carbon fiber layer 20.
In this application embodiment, glass fiber layer 10 lays carbon fiber layer 20 as the basic layer of unmanned aerial vehicle fuselage on glass fiber layer 10, lays aramid fiber layer 30 on carbon fiber layer 20. Wherein, glass fiber layer 10 and aramid fiber layer 30 are all along the whole settings in fuselage surface, and carbon fiber layer 20 only need as required in fuselage surface local setting can.
The glass fiber (Fibreglass) is an inorganic non-metallic material with excellent performance, has the advantages of good insulation, strong heat resistance, good corrosion resistance and high mechanical strength, and can be used as a basic layer of a machine body.
The carbon fiber has the characteristics of high temperature resistance, friction resistance, electric conduction, heat conduction, corrosion resistance and the like, is fibrous and soft in appearance, can be processed into various fabrics, and has high strength and modulus along the fiber axis direction. The carbon fibers have a low density and thus a high specific strength and a high specific modulus. The carbon fiber is mainly used as a reinforcing material to be compounded with resin, metal, ceramic, carbon and the like to manufacture an advanced composite material. The specific strength and the specific modulus of the carbon fiber reinforced epoxy resin composite material are the highest in the existing engineering materials.
The aramid fiber has excellent performances of ultrahigh strength, high modulus, high temperature resistance, acid and alkali resistance, light weight and the like, the strength of the aramid fiber is 5-6 times that of a steel wire, the modulus of the aramid fiber is 2-3 times that of the steel wire or glass fiber, the toughness of the aramid fiber is 2 times that of the steel wire, the weight of the aramid fiber is only about 1/5 times that of the steel wire, and the aramid fiber is not decomposed or melted at the temperature of 560 ℃. The composite material has good insulativity and ageing resistance, has a long life cycle, and can be used as a material of the outermost surface of a machine body.
In the present example, the areal density of the glass fibre layer 10 is 100g/m 2.
In the present example, the fiberglass layer 10 is disposed along the entire surface of the fuselage with an areal density of 100g/m 2.
In the embodiment of the present application, the thickness of the glass fiber layer 10 is 0.08mm to 0.12 mm.
In the embodiment of the present application, the thickness of the glass fiber layer 10 is 0.08mm to 0.12mm, and can be selectively used within this range. Preferably, the glass fiber layer 10 has a thickness of 0.1 mm.
In the embodiment of the present application, the carbon fiber layer 20 is a carbon fiber cloth, and the carbon fiber cloth is a 3K carbon fiber cloth.
In the embodiment of the present application, the carbon fiber layer 20 is disposed along the surface of the fuselage portion, and the specific position can be used according to the choice, for example, as shown in fig. 2, 1 layer of 3K carbon fiber cloth can be laid at the opening of the fuselage; as shown in fig. 3, 2 layers of 3K carbon fiber cloth can be laid on the upper and lower sides of the fuselage; as shown in fig. 4 and 5, 1 layer of 3K carbon fiber cloth can be laid on the upper and lower side corners of the fuselage.
In the embodiment of the present application, the surface density of the aramid fiber layer 30 is 100g/m 2.
In the present example, the aramid fiber layer 30 has an areal density of 100g/m 2.
In the embodiment of the present application, the thickness of the aramid fiber layer 30 is 0.15mm to 0.19 mm.
In the embodiment of the present application, the thickness of the aramid fiber layer 30 is 0.15mm to 0.19mm, and may be selectively used within this range. Preferably, the aramid fiber layer 30 has a thickness of 0.17 mm.
In an embodiment of the present application, the present invention provides a method for manufacturing a composite fuselage of an unmanned aerial vehicle, the composite fuselage of the unmanned aerial vehicle comprising the composite fuselage of the unmanned aerial vehicle as described in fig. 1 to 6, the method comprising the steps of:
forming a glass fiber layer 10 in a predetermined shape;
forming a carbon fiber layer 20 on the glass fiber layer 10;
an aramid fiber layer 30 is formed on the carbon fiber layer 20.
In the embodiment of the present application, a glass fiber layer 10 (as shown in fig. 1) with a preset shape can be formed according to the shape requirement of the fuselage, for example, an injection molding machine can be used to inject glass fibers into the fuselage with the preset shape, and then a carbon fiber layer 20 (as shown in fig. 2-5) is laid on a local position on the glass fiber layer 10; then, the aramid fiber layer 30 is laid on the carbon fiber layer 20 (see fig. 6).
The unmanned aerial vehicle fuselage structure performance that this application provided is excellent for unmanned aerial vehicle combined material fuselage and preparation method, and the unmanned aerial vehicle fuselage structure performance who designs is excellent, has sufficient intensity and rigidity, has lighter weight simultaneously, make full use of combined material's designability characteristics to and utilize combined material's selection material and layer to realize fuselage structure's optimal design, excellent performance.
It is noted that, in this document, relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element. The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
In short, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An unmanned aerial vehicle composite fuselage, comprising: the glass fiber layer, carbon fiber layer and aramid fiber layer, wherein, carbon fiber layer set up in on the glass fiber layer, aramid fiber layer set up in on the carbon fiber layer.
2. The unmanned aerial vehicle composite fuselage of claim 1, wherein the fiberglass layer has an areal density of 100g/m 2.
3. The airframe of claim 1 or 2, wherein the fiberglass layer has a thickness of 0.08mm to 0.12 mm.
4. The unmanned aerial vehicle composite fuselage of claim 1, wherein the carbon fiber layer is carbon fiber cloth.
5. The unmanned aerial vehicle composite fuselage of claim 4, wherein the carbon fiber cloth is 3K carbon fiber cloth.
6. The unmanned aerial vehicle composite fuselage of claim 5, wherein the 3K carbon fiber cloth is 1 or 2 plies.
7. The unmanned aerial vehicle composite fuselage of claim 1, wherein the aramid fiber layer has an areal density of 100g/m 2.
8. The airframe of claim 1 or 7 wherein the aramid fiber layer is 0.15mm to 0.19mm thick.
9. A method of making a composite fuselage for an unmanned aerial vehicle, the fuselage comprising the composite fuselage according to any one of claims 1 to 8, the method comprising the steps of:
forming a glass fiber layer with a preset shape;
forming a carbon fiber layer on the glass fiber layer;
and forming an aramid fiber layer on the carbon fiber layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011534758.5A CN112722233A (en) | 2020-12-23 | 2020-12-23 | Unmanned aerial vehicle composite material fuselage and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011534758.5A CN112722233A (en) | 2020-12-23 | 2020-12-23 | Unmanned aerial vehicle composite material fuselage and preparation method thereof |
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| Publication Number | Publication Date |
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| CN112722233A true CN112722233A (en) | 2021-04-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011534758.5A Pending CN112722233A (en) | 2020-12-23 | 2020-12-23 | Unmanned aerial vehicle composite material fuselage and preparation method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114536908A (en) * | 2022-02-15 | 2022-05-27 | Oppo广东移动通信有限公司 | Manufacturing method of shell, shell and electronic equipment |
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| CN208216970U (en) * | 2018-05-30 | 2018-12-11 | 山东龙翼航空科技有限公司 | Fixed-wing unmanned plane shell ply angles |
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2020
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Application publication date: 20210430 |