CN210126327U - Composite board of unmanned aerial vehicle organism - Google Patents
Composite board of unmanned aerial vehicle organism Download PDFInfo
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- CN210126327U CN210126327U CN201920865786.1U CN201920865786U CN210126327U CN 210126327 U CN210126327 U CN 210126327U CN 201920865786 U CN201920865786 U CN 201920865786U CN 210126327 U CN210126327 U CN 210126327U
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Abstract
The utility model discloses a composite board of an unmanned aerial vehicle body, which comprises a first glass fiber layer, a first epoxy resin glue layer, a balsa wood layer, a second epoxy resin glue layer and a second glass fiber layer from inside to outside in sequence; the first glass fiber layer and the balsa wood layer are fixedly bonded through a first epoxy resin glue layer, and the balsa wood layer and the second glass fiber layer are fixedly bonded through a second epoxy resin glue layer. The utility model discloses low in manufacturing cost, texture are light, easily shaping, specific strength and specific stiffness are high.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, in particular to composite board of unmanned aerial vehicle organism.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. Drones are in fact a generic term for unmanned aircraft.
Compared with an airplane driven by a pilot, the unmanned aerial vehicle has the characteristics of stronger maneuverability, smaller weight, small size, low manufacturing cost, convenience in use and the like. The unmanned aerial vehicle mainly has five key technologies, namely a machine body structure design technology, a machine body material technology, a flight control technology, a wireless communication remote control technology and a wireless image return technology. Airframe materials (including structural and non-structural materials), engine materials and paints, the most important of which are airframe and engine materials, should have high specific strength and specific stiffness to reduce the structural weight of the aircraft, improve flight performance or increase economic efficiency, and also should have good workability to facilitate the fabrication of the required parts.
Compared with metal materials, the resin-based composite material has the advantages of light structure weight, easy molding of complex or large-scale structures, large design space, high specific strength and specific stiffness, small thermal expansion coefficient and the like. The composite material is directly applied to the structure of the unmanned aerial vehicle, and has important effects of reducing the weight of the unmanned aerial vehicle body, increasing the effective load, and improving the safety and the stealth.
In the prior art, the manufacturing cost of the composite material is high, the non-military unmanned aerial vehicle does not need to use the composite material to manufacture the body of the unmanned aerial vehicle, but no matter what the unmanned aerial vehicle is used, the body of the unmanned aerial vehicle needs to have the characteristics of light weight, easiness in forming, high specific strength, high specific rigidity and the like.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is according to the not enough of above-mentioned prior art, provide a low in manufacturing cost, the texture is light, easily shaping, than intensity and than the high composite board of unmanned aerial vehicle organism of rigidity.
In order to solve the technical problem, the technical scheme of the utility model is that: a composite board of an unmanned aerial vehicle body sequentially comprises a first glass fiber layer, a first epoxy resin glue layer, a balsa wood layer, a second epoxy resin glue layer and a second glass fiber layer from inside to outside; the first glass fiber layer and the balsa wood layer are fixedly bonded through a first epoxy resin glue layer, and the balsa wood layer and the second glass fiber layer are fixedly bonded through a second epoxy resin glue layer.
As to the utility model discloses a further explanation:
preferably, the thickness of the first glass fiber layer is 0.035 mm-0.070 mm; the thickness of the first epoxy resin glue layer is 0.001 mm-0.01 mm; the thickness of the balsa blanket is 0.55 mm-1.00 mm; the thickness of the second epoxy resin glue layer is 0.001 mm-0.01 mm; the thickness of the second glass fiber layer is 0.035 mm-0.070 mm.
Preferably, the thickness of the first glass fiber layer is 0.05 mm; the thickness of the first epoxy resin glue layer is 0.003 mm-0.006 mm; the thickness of the balsa blanket is 0.8 mm; the thickness of the second epoxy resin glue layer is 0.003 mm-0.006 mm; the thickness of the second glass fiber layer is 0.05 mm.
Preferably, a third epoxy resin glue layer and a carbon fiber cloth layer are further arranged on the inner side of the position, used for mounting the wing, the landing gear and the engine, of the composite board, and the carbon fiber cloth layer and the first glass fiber layer are fixedly bonded through the third epoxy resin glue layer.
Preferably, the thickness of the third epoxy resin glue layer is 0.001 mm-0.01 mm; the thickness of the carbon fiber cloth layer is 0.85 mm-1.20 mm.
Preferably, the thickness of the third epoxy resin glue layer is 0.003 mm-0.006 mm; the thickness of carbon fiber cloth layer is 1.0 mm.
Preferably, the balsa blanket is formed by splicing at least two balsa wood sheets, and a plurality of groups of dovetail grooves and dovetail flanges which are mutually clamped are arranged at the splicing position of each two balsa wood sheets.
The utility model has the advantages that: one of the two layers is that the utility model comprises a first glass fiber layer, a first epoxy resin glue layer, a balsa wood layer, a second epoxy resin glue layer and a second glass fiber layer from inside to outside in sequence, the middle layer is the balsa wood layer, the balsa wood has low density and high strength, and the requirements of the unmanned aerial vehicle on the specific strength and the specific rigidity of the body are met; secondly, the utility model discloses from inside to outside be equipped with first glass fiber layer and second glass fiber layer, guarantee that unmanned aerial vehicle organism composite board has stronger intensity and has good machinability, through control glass first glass fiber layer and second glass fiber layer, the thickness of first epoxy glue layer and second epoxy glue layer, further guarantee that unmanned aerial vehicle organism composite board texture is light; the thickness of the first epoxy resin glue layer and the second epoxy resin glue layer is 0.001-0.01 mm, the first glass fiber layer and the balsa wood layer are fixedly bonded through the first epoxy resin glue layer, and the balsa wood layer and the second glass fiber layer are fixedly bonded through the second epoxy resin glue layer, so that the thin glue layer can not be seen when the bonding and fixing are ensured, and the light texture of the unmanned aerial vehicle body composite board is ensured; a third epoxy resin glue layer and a carbon fiber cloth layer are further arranged on the inner side of the plate position of the composite plate for mounting the wing, the undercarriage and the engine, and the carbon fiber cloth layer and the first glass fiber layer are fixedly bonded through the third epoxy resin glue layer, so that the specific strength and the specific rigidity of the plate position for mounting the wing, the undercarriage and the engine are further enhanced; fifthly, the balsa wood layer is formed by two piece at least balsa wood chip concatenations, and the concatenation position of per two balsa wood chips is equipped with forked tail recess and the forked tail flange of the mutual block of a plurality of groups for the vibrations are propagated to unmanned aerial vehicle organism composite board high efficiency, and durable prevents falling and prevent absolutely, the utility model discloses overall structure design is simple, low in manufacturing cost, the texture is light, easily the shaping.
Drawings
Fig. 1 is a schematic view of an overall structure of a first embodiment of the present invention.
Fig. 2 is a schematic view of an overall structure of a second embodiment of the present invention.
Fig. 3 is the utility model discloses unmanned aerial vehicle composite board mould structure sketch map.
In the figure: 1. a first fiberglass layer; 2. a first epoxy glue layer; 3. a balsa blanket; 4. a second epoxy glue layer; 5. a second fiberglass layer; 6. a third epoxy glue layer; 7. a carbon fiber cloth layer; 8. unmanned aerial vehicle composite board mould.
Detailed Description
The structure and operation of the present invention will be described in detail with reference to the accompanying drawings.
Example one
As shown in fig. 1, the utility model relates to a composite board of unmanned aerial vehicle body, which comprises a first glass fiber layer 1, a first epoxy resin glue layer 2, a balsa wood layer 3, a second epoxy resin glue layer 4 and a second glass fiber layer 5 from inside to outside in sequence; the first glass fiber layer 1 and the balsa wood layer 3 are fixedly bonded through a first epoxy resin glue layer 2, and the balsa wood layer 3 and the second glass fiber layer 5 are fixedly bonded through a second epoxy resin glue layer 4. The balsa wood is the lightest wood in the world, is produced in Yunnan and Guangxi provinces of America and China, is only 0.1 ton in weight per cubic meter, is one tenth of the weight of water with the same volume, is an excellent natural wood, is the lightest wood in the world, has low density but higher strength, and is commonly used in the fields of aviation, ships, transportation, buildings, wind energy and the like.
In the embodiment, the thickness of the first glass fiber layer 1 is 0.035 mm-0.070 mm; the thickness of the first epoxy resin glue layer 2 is 0.001 mm-0.01 mm; the thickness of the balsa blanket 3 is 0.55 mm-1.00 mm; the thickness of the second epoxy resin glue water layer 4 is 0.001 mm-0.01 mm; the thickness of the second glass fiber layer 5 is 0.035 mm-0.070 mm.
Preferably, the thickness of the first glass fiber layer 1 is 0.05 mm; the thickness of the first epoxy resin glue water layer 2 is 0.003 mm-0.006 mm; the thickness of the balsa blanket 3 is 0.8 mm; the thickness of the second epoxy resin glue water layer 4 is 0.003 mm-0.006 mm; the thickness of the second glass fiber layer 5 is 0.05 mm.
The balsa blanket 3 is formed by splicing at least two balsa wood sheets, and a plurality of groups of dovetail grooves and dovetail flanges which are mutually clamped are arranged at the splicing position of each two balsa wood sheets.
Example two
As shown in fig. 2, the utility model relates to a composite board of unmanned aerial vehicle body, which comprises a first glass fiber layer 1, a first epoxy glue layer 2, a balsa wood layer 3, a second epoxy glue layer 4 and a second glass fiber layer 5 from inside to outside in sequence; the first glass fiber layer 1 and the balsa wood layer 3 are fixedly bonded through a first epoxy resin glue layer 2, and the balsa wood layer 3 and the second glass fiber layer 5 are fixedly bonded through a second epoxy resin glue layer 4.
The thickness of the first glass fiber layer 1 is 0.035 mm-0.070 mm; the thickness of the first epoxy resin glue layer 2 is 0.001 mm-0.01 mm; the thickness of the balsa blanket 3 is 0.55 mm-1.00 mm; the thickness of the second epoxy resin glue water layer 4 is 0.001 mm-0.01 mm; the thickness of the second glass fiber layer 5 is 0.035 mm-0.070 mm.
In this embodiment, the thickness of the first glass fiber layer 1 is 0.05 mm; the thickness of the first epoxy resin glue water layer 2 is 0.003 mm-0.006 mm; the thickness of the balsa blanket 3 is 0.8 mm; the thickness of the second epoxy resin glue water layer 4 is 0.003 mm-0.006 mm; the thickness of the second glass fiber layer 5 is 0.05 mm.
The balsa blanket 3 is formed by splicing at least two balsa wood sheets, and a plurality of groups of dovetail grooves and dovetail flanges which are mutually clamped are arranged at the splicing position of each two balsa wood sheets.
According to the first embodiment, the first glass fiber layer 1, the first epoxy glue layer 2, the balsa wood layer 3, the second epoxy glue layer 4 and the second glass fiber layer 5 are sequentially attached to the inside of the groove of the unmanned aerial vehicle composite board die 8, the third epoxy glue layer 6 and the carbon fiber cloth layer 7 are further attached to the inner side of the position of the board where the composite board of the unmanned aerial vehicle body is used for installing wings, undercarriages and engines, and the carbon fiber cloth layer 7 and the first glass fiber layer 1 are fixedly bonded through the third epoxy glue layer 6, so that the composite board of the unmanned aerial vehicle body according to the second embodiment is obtained.
The thickness of the third epoxy resin glue layer 6 is 0.001 mm-0.01 mm; the thickness of the carbon fiber cloth layer 7 is 0.85 mm-1.20 mm.
In this embodiment, the thickness of the third epoxy glue layer 6 is 0.003mm to 0.006 mm; the thickness of the carbon fiber cloth layer 7 is 1.0 mm.
Experiments show that the specific strength and specific rigidity of the wings, the undercarriage and the engine part of the composite board of the unmanned aerial vehicle body manufactured by the method in the second embodiment are higher than those of the wings, the undercarriage and the engine part of the composite board of the unmanned aerial vehicle body manufactured in the first embodiment.
And compare with the unmanned aerial vehicle organism panel that traditional wooden material made, the utility model discloses an embodiment one and the composite board of the unmanned aerial vehicle organism that embodiment two made have than intensity with than the characteristics that rigidity is high, coefficient of thermal expansion is little, antifatigue ability and anti vibration ability are strong, compare the unmanned aerial vehicle that traditional wooden material made, the utility model discloses an unmanned aerial vehicle that embodiment one and embodiment two made can subtract heavy 25% ~ 30%.
Fig. 3 is a drawing illustrating an unmanned aerial vehicle composite board mold 8, the unmanned aerial vehicle composite board mold 8 is a concave body mold, and a second glass fiber layer 5, a second epoxy resin glue layer 4, a balsa layer 3, a first epoxy resin glue layer 2 and a first glass fiber layer 1 are sequentially attached to a groove of the unmanned aerial vehicle composite board mold 8; and sequentially attaching a third epoxy resin glue layer 6 and a carbon fiber cloth layer 7 to the wing, the undercarriage and the engine to obtain the composite board of the unmanned aerial vehicle body.
The above, only the utility model discloses preferred embodiment, all be according to the utility model discloses a technical scheme does any slight modification, the equivalent change and the modification to above embodiment, all belong to the utility model discloses technical scheme's within range.
Claims (7)
1. The utility model provides a composite board of unmanned aerial vehicle organism which characterized in that: the composite material sequentially comprises a first glass fiber layer, a first epoxy resin glue layer, a balsa wood layer, a second epoxy resin glue layer and a second glass fiber layer from inside to outside; the first glass fiber layer and the balsa wood layer are fixedly bonded through a first epoxy resin glue layer, and the balsa wood layer and the second glass fiber layer are fixedly bonded through a second epoxy resin glue layer.
2. The composite board of unmanned aerial vehicle organism of claim 1, characterized in that: the thickness of the first glass fiber layer is 0.035-0.070 mm; the thickness of the first epoxy resin glue layer is 0.001 mm-0.01 mm; the thickness of the balsa blanket is 0.55 mm-1.00 mm; the thickness of the second epoxy resin glue layer is 0.001 mm-0.01 mm; the thickness of the second glass fiber layer is 0.035 mm-0.070 mm.
3. The composite board of unmanned aerial vehicle organism of claim 2, characterized in that: the thickness of the first glass fiber layer is 0.05 mm; the thickness of the first epoxy resin glue layer is 0.003 mm-0.006 mm; the thickness of the balsa blanket is 0.8 mm; the thickness of the second epoxy resin glue layer is 0.003 mm-0.006 mm; the thickness of the second glass fiber layer is 0.05 mm.
4. The composite board of unmanned aerial vehicle organism of claim 1, characterized in that: the composite board is characterized in that a third epoxy resin glue layer and a carbon fiber cloth layer are further arranged on the inner side of the board position for mounting the wings, the landing gear and the engine, and the carbon fiber cloth layer is fixedly bonded with the first glass fiber layer through the third epoxy resin glue layer.
5. The composite board of unmanned aerial vehicle organism of claim 4, characterized in that: the thickness of the third epoxy resin glue layer is 0.001 mm-0.01 mm; the thickness of the carbon fiber cloth layer is 0.85 mm-1.20 mm.
6. The composite board of unmanned aerial vehicle organism of claim 4, characterized in that: the thickness of the third epoxy resin glue layer is 0.003 mm-0.006 mm; the thickness of carbon fiber cloth layer is 1.0 mm.
7. The composite board of unmanned aerial vehicle organism of any one of claims 1 ~ 6, characterized in that: the balsa wood layer is formed by splicing at least two balsa wood sheets, and a plurality of groups of dovetail grooves and dovetail flanges which are mutually clamped are arranged at the splicing position of each two balsa wood sheets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920865786.1U CN210126327U (en) | 2019-06-11 | 2019-06-11 | Composite board of unmanned aerial vehicle organism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920865786.1U CN210126327U (en) | 2019-06-11 | 2019-06-11 | Composite board of unmanned aerial vehicle organism |
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| Publication Number | Publication Date |
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| CN210126327U true CN210126327U (en) | 2020-03-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920865786.1U Active CN210126327U (en) | 2019-06-11 | 2019-06-11 | Composite board of unmanned aerial vehicle organism |
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| CN (1) | CN210126327U (en) |
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2019
- 2019-06-11 CN CN201920865786.1U patent/CN210126327U/en active Active
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Address after: 523000 Room 401, No.14, Xinhe Road, Xiaobian, Chang'an Town, Dongguan City, Guangdong Province Patentee after: DONGGUAN FLIGHT AVIATION TECHNOLOGY Co.,Ltd. Address before: No.10 Funing street, Lianhua Industrial Zone, Xian Xi, Chang'an Town, Dongguan City, Guangdong Province 523000 Patentee before: DONGGUAN FLIGHT AVIATION TECHNOLOGY Co.,Ltd. |
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