CN109109400B - Composite material and aircraft - Google Patents
Composite material and aircraft Download PDFInfo
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- CN109109400B CN109109400B CN201811078124.6A CN201811078124A CN109109400B CN 109109400 B CN109109400 B CN 109109400B CN 201811078124 A CN201811078124 A CN 201811078124A CN 109109400 B CN109109400 B CN 109109400B
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- 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
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- 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
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
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- 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
- B32B5/18—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 features of a layer of foamed material
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- 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
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
- B32B2260/023—Two or more layers
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- 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
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a composite material and an aircraft, and belongs to the technical field of unmanned aerial vehicles. The composite material comprises: a shaping foam, set up in the first fibre fabric layer of at least one deck of shaping foam upper surface and set up in the at least one deck second fibre fabric layer of shaping foam lower surface, first fibre fabric layer and second fibre fabric layer all are soaked with first colloid. According to the invention, the light composite material is used as the material of the propeller and/or the fuselage, so that the weight of the propeller and/or the fuselage can be greatly reduced, the cruising ability of the unmanned aerial vehicle is stronger, and the elastic characteristic of the foam can also increase the strength and toughness of the propeller and/or the fuselage; and first fibre fabric layer and second fibre fabric layer all are soaked with first colloid, and first colloid makes first fibre fabric layer and second fibre fabric layer solidification stiffening, changes the shaping more easily.
Description
The invention is a divisional application provided with an invention patent application with the application number of 201610422759.8 (application date: 2016-6-13, the name of the invention: propeller and fuselage).
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a composite material and an aircraft.
Background
Unmanned aerial vehicle has characteristics such as the portability is high, easy operation, use flexibility, obtains using widely in each field, and wherein the organism material technique is one of unmanned aerial vehicle's key technology, and the material that each part of unmanned aerial vehicle was used directly influences unmanned aerial vehicle's weight, structural strength and duration etc.. In order to guarantee the structural strength of the unmanned aerial vehicle, the materials used by the existing unmanned aerial vehicle are generally titanium alloy, aluminum alloy or carbon fiber, the materials are convenient to process, the forming method is simple, but the weight is large, and the cruising ability is seriously influenced.
Disclosure of Invention
The invention aims to provide a composite material structure applied to an aircraft, such as a propeller and a fuselage, which can reduce the weight of materials and enable the cruising ability of an unmanned aerial vehicle to be stronger.
In order to realize the purpose of the invention, the technical scheme is as follows:
the utility model provides a composite material, includes a shaping foam, set up in the first fibrous fabric layer of at least one deck of shaping foam upper surface and set up in the at least one deck second fibrous fabric layer of shaping foam lower surface, first fibrous fabric layer and second fibrous fabric layer all are soaked with first colloid.
The technical scheme is further explained as follows:
further, a cavity is formed between the first fiber fabric layer and the second fiber fabric layer, and the molded foam is arranged in the cavity.
Further, the thickness of the formed foam is larger than that of the cavity, and the formed foam and the cavity are in interference fit.
Furthermore, the composite material comprises a UD cloth layer, at least one UD cloth layer is arranged between the first fiber fabric layer and the formed foam and/or at least one UD cloth layer is arranged between the second fiber fabric layer and the formed foam, wherein the UD cloth layer is soaked with a first colloid.
Further, the composite material comprises two first fiber fabric layers or/and two second fiber fabric layers.
Furthermore, the composite material comprises three UD cloth layers, wherein the three UD cloth layers are arranged between the first fiber fabric layer and the formed foam, or/and the three UD cloth layers are arranged between the second fiber fabric layer and the formed foam.
Further, a first UD cloth layer is arranged on the bottom surface of the first fiber cloth layer, a second UD cloth layer is arranged on the bottom surface of the first UD cloth layer, a third UD cloth layer is arranged on the bottom surface of the second UD cloth layer, the bottom surface of the third UD cloth layer is adhered to the upper surface of the formed foam, the length of the first UD cloth layer is larger than that of the second UD cloth layer, and the length of the second UD cloth layer is larger than that of the third UD cloth layer.
Further, the length centers of the first UD cloth layer, the second UD cloth layer and the third UD cloth layer are overlapped.
Further, the first fiber fabric layer and the second fiber fabric layer are carbon fiber fabrics.
Further, the first colloid is epoxy resin.
The invention also provides an aircraft, the fuselage and/or the propeller of which comprise: a shaping foam, set up in the first fibre fabric layer of at least one deck of shaping foam upper surface and set up in the at least one deck second fibre fabric layer of shaping foam lower surface, first fibre fabric layer and second fibre fabric layer all are soaked with first colloid.
Further, the fuselage and/or the propeller of the aircraft comprise: two first fiber fabric layers or/and two second fiber fabric layers.
Further, the fuselage and/or the propeller of the aircraft comprise: and at least one UD cloth layer is arranged between the first fiber fabric layer and the formed foam, or/and at least one UD cloth layer is arranged between the second fiber fabric layer and the formed foam, wherein the UD cloth layer is soaked with a first colloid.
Further, a first UD cloth layer is arranged on the bottom surface of the first fiber cloth layer, a second UD cloth layer is arranged on the bottom surface of the first UD cloth layer, a third UD cloth layer is arranged on the bottom surface of the second UD cloth layer, the bottom surface of the third UD cloth layer is adhered to the upper surface of the formed foam, the length of the first UD cloth layer is larger than that of the second UD cloth layer, and the length of the second UD cloth layer is larger than that of the third UD cloth layer.
Further, the fiber fabric layer and the second fiber fabric layer are carbon fiber fabrics, and the first colloid is epoxy resin.
Further, the length centers of the first, second and third UD fabric layers overlap the length centers of the propeller and/or the fuselage.
Furthermore, the first fiber fabric layer, the UD fabric layer, the formed foam and the second fiber fabric layer of the machine body are bonded, and the first fiber fabric layer, the UD fabric layer, the formed foam and the second fiber fabric layer are combined and formed in a vacuum mode.
Further, the first fiber fabric layer and the second fiber fabric layer of the propeller are bonded to form a cavity, are in interference fit with the formed foam, and are formed in a compression molding mode.
Compared with the prior art, the invention has the following beneficial effects: the formed foam of the composite material is made of a foam material, the foam is light, the weight of the propeller and the weight of the unmanned aerial vehicle body can be greatly reduced, the cruising ability of the unmanned aerial vehicle is stronger, and the strength and the toughness of the propeller can be improved due to the elastic characteristic of the foam; the first fiber fabric layer and the second fiber fabric layer are both soaked with first colloid, and the first colloid enables the first fiber fabric layer and the second fiber fabric layer to be cured and hardened, so that the forming is easier; in addition, three UD cloth layers are arranged between the first fiber fabric layer and the forming foam and between the second fiber fabric layer and the forming foam, all the strengths of the UD cloth layers are in the first direction, the strength of the propeller and the machine body is increased, the UD cloth layers bonded with the fiber fabric layers are longest in length, and the UD cloth layers bonded with the forming foam are shortest in length.
Drawings
FIG. 1 is a schematic view of a composite material construction of a first embodiment of a propeller of the present invention;
FIG. 2 is a schematic view of a propeller according to a second embodiment of the present invention;
FIG. 3 is a schematic illustration of a composite structure for a first embodiment fuselage of the present invention;
fig. 4 is a schematic structural view of a second embodiment of the fuselage of the present invention.
Description of reference numerals:
10. the composite material comprises a forming foam, 20, a first fiber fabric layer, 30, a second fiber fabric layer, 40, a first colloid, 50, a UD fabric layer, 510, a first UD fabric layer, 520, a second UD fabric layer, 530, a third UD fabric layer and 60 of molding compound.
Detailed Description
Embodiments of the present invention are described in detail below with reference to the accompanying drawings:
the present invention provides an aircraft, such as a multi-rotor aircraft (not shown), that includes a propeller and a fuselage.
As shown in fig. 1, a propeller comprises a formed foam 10, at least one first fiber fabric layer 20 disposed on the upper surface of the formed foam 10, and at least one second fiber fabric layer 30 disposed on the lower surface of the formed foam 10, wherein the first fiber fabric layer 20 and the second fiber fabric layer 30 are both impregnated with a first colloid 40, and the formed foam 10 matches with the appearance of the propeller.
As shown in fig. 1, in the present embodiment, each of the first fiber fabric layer 20 and the second fiber fabric layer 30 is provided with only one layer, the first glue 40 is epoxy resin, the first fiber fabric layer 20 and the second fiber fabric layer 30 are carbon fiber fabrics, and the first glue 40, the first fiber fabric layer 20 and the second fiber fabric layer 30 may be arranged in other forms according to practical applications.
Further, as shown in fig. 1, mold closing glue 60 is adhered to the edges of the first fiber fabric layer 20, the molded foam 10 and the second fiber fabric layer 30, and the adhesion degree of the edges is improved by the mold closing glue, so that the propeller mold closing is facilitated. The first glue 40 can also be arranged as other glue according to the actual situation by impregnating the first fibre fabric layer 20 and the second fibre fabric layer 30 with the first glue 40 to achieve the adhesion between the fibre fabric layer and the formed foam and the curing of the fibre fabric.
In another embodiment, as shown in fig. 2, at least one UD fabric layer 50 is disposed between the first fibrous fabric layer 20 and the formed foam 10, and at least one UD fabric layer 50 is disposed between the second fibrous fabric layer 30 and the formed foam 10, and the UD fabric layer 50 is impregnated with the first glue 40. The UD material used for the UD fabric layer 50 is also referred to as organic fiber composite material, and is a material having all strength in the first direction, and UD materials are provided between the first fiber fabric layer 20 and the molded foam 10 and between the second fiber fabric layer 30 and the molded foam 10, so that the strength of the propeller is increased, and the propeller is light and has better comprehensive properties.
Further, as shown in fig. 2, in another embodiment, the first fibrous fabric layer 20 has two layers, the second fibrous fabric layer 30 has two layers, three UD fabric layers 50 are disposed between the first fibrous fabric layer 20 and the formed foam 10 and between the second fibrous fabric layer 30 and the formed foam 10, the first fibrous fabric layer 20 is provided with a first UD fabric layer 510 on a bottom surface thereof, the first UD fabric layer 510 is provided with a second UD fabric layer 520 on a bottom surface thereof, the second UD fabric layer 520 is provided with a third UD fabric layer 530 on a bottom surface thereof, the third UD fabric layer 530 is bonded to an upper surface of the formed foam 10 on a bottom surface thereof, a length of the first UD fabric layer is greater than a length of the second UD fabric layer, and a length of the second UD fabric layer is greater than a length of the third UD fabric layer. The second fibrous fabric layer 30 is provided with a first UD fabric layer 510 on the top, the first UD fabric layer 510 is provided with a second UD fabric layer 520 on the top, the second UD fabric layer 520 is provided with a third UD fabric layer 530 on the top, the third UD fabric layer 530 is adhered on the lower surface of the formed foam 10 on the top, the length of the first UD fabric layer is larger than that of the second UD fabric layer, and the length of the second UD fabric layer is larger than that of the third UD fabric layer. The length centers of the first UD cloth layer 510, the second UD cloth layer 520, and the third UD cloth layer 530 overlap with the length center of the propeller. The three UD cloth layers 50 are gradually decreased in length towards the center of the propeller, and further, the length of the first UD cloth layer is 1/3 longer than that of the second UD cloth layer, and the length of the second UD cloth layer is 1/3 longer than that of the third UD cloth layer, so that the strength of the propeller is improved, and meanwhile, the weight of the propeller is not greatly influenced.
When the propeller is manufactured, the first fiber fabric layer 20, the UD fabric layer 50, the formed foam 10 and the second fiber fabric layer 30 are tightly bonded in a compression molding mode, and the first fiber fabric layer 20 and the second fiber fabric layer 30 are bonded to form a cavity and are in interference fit with the formed foam 10 due to the fact that the foam is elastic, namely the thickness of the formed foam 10 is larger than that of the cavity, so that when the propeller is subjected to compression molding, the strength and toughness of the propeller are further improved through compression molding of the foam 10.
As shown in FIG. 3, the present invention further provides a fuselage, which comprises a formed foam 10, at least one first fiber fabric layer 20 disposed on the upper surface of the formed foam 10, and at least one second fiber fabric layer 30 disposed on the lower surface of the formed foam 10, wherein the first fiber fabric layer 20 and the second fiber fabric layer 30 are both impregnated with a first colloid 40, the formed foam 10 and the fuselage are combined
Further, the first glue 40 is epoxy resin, the first fiber fabric layer 20 and the second fiber fabric layer 30 are carbon fiber fabrics, and the first glue 40, the first fiber fabric layer 20 and the second fiber fabric layer 30 may be arranged in other forms according to the actual situation.
As shown in fig. 3, the first fiber fabric layer 20 in this embodiment has two layers, the second fiber fabric layer 30 has one layer, and the two first fiber fabric layers 20 are located at the outer side of the fuselage, and the one second fiber fabric layer 30 is located at the inner side of the fuselage, so that the fuselage is more stable during operation.
Further, the edges of the first fiber fabric layer 20, the molded foam 10 and the second fiber fabric layer 30 are all bonded with mold closing glue 60, and the adhesion degree of the edges is improved through the mold closing glue, so that the machine body is convenient to close the mold. In this embodiment, the mold compound 60 contains epoxy resin and carbon powder, and the adhesion degree is improved by the carbon powder.
In other embodiments, as shown in fig. 4, at least one UD fabric layer 50 is disposed between the first fibrous fabric layer 20 and the formed foam 10, and at least one UD fabric layer 50 is disposed between the second fibrous fabric layer 30 and the formed foam 10, and the UD fabric layer 50 is impregnated with the first glue 40. The UD material used for the UD fabric layer 50 is also referred to as organic fiber composite material, and is a material having all strength in the first direction, and the UD material is provided between the first fiber fabric layer 20 and the molded foam 10 and between the second fiber fabric layer 30 and the molded foam 10, so that the strength of the fuselage is increased, and the fuselage is light and has better overall properties.
As shown in fig. 4, three UD fabric layers 50 are provided between the first fibrous fabric layer 20 and the formed foam 10, and between the second fibrous fabric layer 30 and the formed foam 10. The first fiber fabric layer 20 is provided with a first UD fabric layer 510 at the bottom, a second UD fabric layer 520 at the bottom, a third UD fabric layer 530 at the bottom, the third UD fabric layer 530 is adhered to the upper surface of the molded foam 10 at the bottom, the length of the first UD fabric layer is longer than that of the second UD fabric layer, and the length of the second UD fabric layer is longer than that of the third UD fabric layer. The second fibrous fabric layer 30 is provided with a first UD fabric layer 510 on the top surface thereof, the first UD fabric layer 510 is provided with a second UD fabric layer 520 on the top surface thereof, the second UD fabric layer 520 is provided with a third UD fabric layer 530 on the top surface thereof, the third UD fabric layer 530 is adhered to the upper surface of the molded foam 10 on the top surface thereof, the length of the first UD fabric layer is greater than that of the second UD fabric layer, and the length of the second UD fabric layer is greater than that of the third UD fabric layer. The length of the three UD cloth layers 50 gradually decreases towards the center of the machine body, so that the strength of the machine body is improved, and the weight of the machine body cannot be greatly influenced.
In the manufacturing process of the fuselage, the first fiber fabric layer 20, the UD fabric layer 50, the formed foam 10 and the second fiber fabric layer 30 are bonded through the first colloid 40, and the first fiber fabric layer 20, the UD fabric layer 50, the formed foam 10 and the second fiber fabric layer 30 are combined through a vacuum pumping mode.
The invention has the advantages that the formed foam 10 of the propeller and the fuselage is made of foam material, the foam is light, the weight of the propeller and the fuselage can be greatly reduced, the cruising ability of the unmanned aerial vehicle is stronger, and the elastic characteristic of the foam can also increase the strength and toughness of the propeller; the first fiber fabric layer 20 and the second fiber fabric layer 30 are both soaked with the first glue body 40, and the first glue body 40 enables the first fiber fabric layer 20 and the second fiber fabric layer 30 to be cured and hardened, so that the forming is easier; and three UD cloth layers 50 are arranged between the first fiber fabric layer 20 and the formed foam 10 and between the second fiber fabric layer 30 and the formed foam 10, all the UD cloth layers 50 have the strength in the first direction, so that the strength of the propeller and the machine body is increased, the UD cloth layers 50 bonded with the fiber fabric layers have the longest length, and the UD cloth layers 50 bonded with the formed foam 10 have the shortest length, so that the strength of the propeller and the machine body is increased, the weight of the propeller and the machine body is not greatly influenced, and the comprehensive characteristics of the propeller and the machine body are better.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (7)
1. An aircraft comprising a propeller and a fuselage, characterized in that the propeller and the fuselage comprise a composite material comprising: the fabric comprises a molded foam, at least one first fiber fabric layer arranged on the upper surface of the molded foam, and at least one second fiber fabric layer arranged on the lower surface of the molded foam, wherein the first fiber fabric layer and the second fiber fabric layer are both soaked with a first colloid; the composite material further comprises: the three-layer UD cloth layer is soaked with a first colloid; three UD cloth layers are arranged between the first fiber fabric layer and the formed foam, and three UD cloth layers are arranged between the second fiber fabric layer and the formed foam; a first UD cloth layer is arranged on the bottom surface of the first fiber fabric layer, a second UD cloth layer is arranged on the bottom surface of the first UD cloth layer, a third UD cloth layer is arranged on the bottom surface of the second UD cloth layer, and the bottom surface of the third UD cloth layer is adhered to the upper surface of the formed foam; a first UD cloth layer is arranged on the top surface of the second fiber fabric layer, a second UD cloth layer is arranged on the top surface of the first UD cloth layer, a third UD cloth layer is arranged on the top surface of the second UD cloth layer, and the top surface of the third UD cloth layer is bonded to the lower surface of the formed foam; the first UD cloth layer length is 1/3 longer than the length of the second UD cloth layer, which is 1/3 longer than the length of the third UD cloth layer.
2. The aircraft of claim 1, wherein the composite material comprises: two of the first fiber fabric layers, and/or two of the second fiber fabric layers.
3. The aircraft of any of claims 1-2, wherein the first and second fiber fabric layers are carbon fiber fabrics.
4. The aircraft according to any one of claims 1 to 2, characterized in that said first glue is an epoxy.
5. The aircraft of claim 1 wherein a length center of the first, second, third UD cloth layers overlaps a length center of the propeller and/or fuselage.
6. The aircraft of claim 1 wherein the first fibrous fabric layer, the UD fabric layer, the shaped foam, and the second fibrous fabric layer of the fuselage are bonded and vacuum formed to bond the first fibrous fabric layer, the UD fabric layer, the shaped foam, and the second fibrous fabric layer together.
7. The vehicle of claim 1 wherein the first and second layers of fibrous fabric of the propeller are bonded to form a cavity and the shaped foam is an interference fit and is shaped by compression molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811078124.6A CN109109400B (en) | 2016-06-13 | 2016-06-13 | Composite material and aircraft |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811078124.6A CN109109400B (en) | 2016-06-13 | 2016-06-13 | Composite material and aircraft |
| CN201610422759.8A CN105904800B (en) | 2016-06-13 | 2016-06-13 | Propeller and fuselage |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610422759.8A Division CN105904800B (en) | 2016-06-13 | 2016-06-13 | Propeller and fuselage |
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| Publication Number | Publication Date |
|---|---|
| CN109109400A CN109109400A (en) | 2019-01-01 |
| CN109109400B true CN109109400B (en) | 2021-03-02 |
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| CN201811078124.6A Active CN109109400B (en) | 2016-06-13 | 2016-06-13 | Composite material and aircraft |
| CN201610422759.8A Active CN105904800B (en) | 2016-06-13 | 2016-06-13 | Propeller and fuselage |
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| CN206170762U (en) * | 2016-06-13 | 2017-05-17 | 亿航智能设备（广州）有限公司 | Screw and fuselage |
| CN106828865B (en) * | 2017-03-01 | 2019-04-02 | 山东长空雁航空科技有限责任公司 | Crossbeam and its forming method on fuselage |
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| CN102765361A (en) * | 2012-08-03 | 2012-11-07 | 南通南京大学材料工程技术研究院 | Auto front anti-collision beam made of carbon fiber/aramid fiber reinforced material |
| CN104527085A (en) * | 2014-12-05 | 2015-04-22 | 航天特种材料及工艺技术研究所 | Composite multi-closed-chamber thick-walled box beam and integral moulding method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5222297A (en) * | 1991-10-18 | 1993-06-29 | United Technologies Corporation | Composite blade manufacture |
| JP4278677B2 (en) * | 2006-11-30 | 2009-06-17 | 株式会社ジャムコ | Sandwich panel |
| CN101219587B (en) * | 2007-12-28 | 2010-06-02 | 同济大学 | Composite stressed-skin construction for fuselage and technique of preparing the same |
| KR101396290B1 (en) * | 2012-11-06 | 2014-05-19 | 한국항공우주산업 주식회사 | Blade of propeller for turboprop aircraft |
| CN203793632U (en) * | 2014-03-26 | 2014-08-27 | 重庆金泰航空工业有限公司 | Composite top cover opening and closing structure on agricultural unmanned aerial vehicle |
| CN206170762U (en) * | 2016-06-13 | 2017-05-17 | 亿航智能设备（广州）有限公司 | Screw and fuselage |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102765361A (en) * | 2012-08-03 | 2012-11-07 | 南通南京大学材料工程技术研究院 | Auto front anti-collision beam made of carbon fiber/aramid fiber reinforced material |
| CN104527085A (en) * | 2014-12-05 | 2015-04-22 | 航天特种材料及工艺技术研究所 | Composite multi-closed-chamber thick-walled box beam and integral moulding method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109109400A (en) | 2019-01-01 |
| CN105904800B (en) | 2018-10-02 |
| CN105904800A (en) | 2016-08-31 |
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