CN210852909U - Unmanned aerial vehicle's horn and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle's horn and unmanned aerial vehicle Download PDFInfo
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- CN210852909U CN210852909U CN201921750569.4U CN201921750569U CN210852909U CN 210852909 U CN210852909 U CN 210852909U CN 201921750569 U CN201921750569 U CN 201921750569U CN 210852909 U CN210852909 U CN 210852909U
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- horn
- aerial vehicle
- unmanned aerial
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- lining
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- 239000003365 glass fiber Substances 0.000 claims abstract description 47
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 41
- 239000004917 carbon fiber Substances 0.000 claims abstract description 41
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 41
- 239000000463 material Substances 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 4
- 239000004593 Epoxy Substances 0.000 claims description 3
- 239000004744 fabric Substances 0.000 description 62
- 238000000034 method Methods 0.000 description 13
- 238000004804 winding Methods 0.000 description 13
- 239000003822 epoxy resin Substances 0.000 description 12
- 229920000647 polyepoxide Polymers 0.000 description 12
- 238000010438 heat treatment Methods 0.000 description 11
- 239000002994 raw material Substances 0.000 description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 10
- 229910052799 carbon Inorganic materials 0.000 description 10
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 8
- 229910052782 aluminium Inorganic materials 0.000 description 8
- 238000001035 drying Methods 0.000 description 4
- 238000003754 machining Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000002791 soaking Methods 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- 238000009941 weaving Methods 0.000 description 4
- 239000004411 aluminium Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 238000003856 thermoforming Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000013329 compounding Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle's horn and unmanned aerial vehicle, unmanned aerial vehicle's horn, include: the inner liner is of a hollow structure, and the inner liner is a glass fiber piece; the outer lining wraps the outer side of the inner lining, and the outer lining is a carbon fiber piece. According to the utility model discloses unmanned aerial vehicle's horn through setting up the inside lining into glass fiber spare, has alleviateed the weight of horn effectively, has improved the intensity of horn to the vibrations of horn have been reduced.
Description
Technical Field
The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to an unmanned aerial vehicle's horn and unmanned aerial vehicle are related to.
Background
Unmanned aerial vehicle includes the frame usually, a plurality of horn that link to each other with the frame, set up the power component who is used for driving this unmanned aerial vehicle flight on the horn and be used for controlling this unmanned aerial vehicle's control system. However, in the related art, the horn is heavy, low in strength, and large in vibration.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides an unmanned aerial vehicle's horn, the horn light in weight, intensity are big and vibrations are little.
The utility model discloses still provide an unmanned aerial vehicle of horn with above-mentioned unmanned aerial vehicle.
According to the utility model discloses unmanned aerial vehicle's horn, include: the lining is of a hollow structure and is a glass fiber piece; the outer lining is wrapped on the outer side of the inner lining and is a carbon fiber piece.
According to the utility model discloses unmanned aerial vehicle's horn through setting up the inside lining into glass fiber spare, has alleviateed the weight of horn effectively, has improved the intensity of horn to the vibrations of horn have been reduced.
According to some embodiments of the invention, the thickness of the inner liner is a1, the thickness of the outer liner is a2, and the ratio of the thickness a1 of the inner liner to the thickness a2 of the outer liner satisfies: A1/A2 is more than or equal to 1 and less than or equal to 2.
According to some embodiments of the invention, a ratio of the thickness a1 of the inner liner to the thickness a2 of the outer liner satisfies: a1/a2 equals 1.5.
According to some embodiments of the present invention, the outer diameter of the inner liner is D1, the outer diameter of the horn is D2, the ratio of the outer diameter D1 of the inner liner to the outer diameter D2 of the horn satisfies: D1/D2 is more than or equal to 0.7 and less than or equal to 0.99.
Further, the ratio of the outer diameter D1 of the inner liner to the outer diameter D2 of the horn satisfies 0.9 ≤ D1/D2 ≤ 0.95.
According to some embodiments of the invention, the inner lining is connected to the outer lining by epoxy bonding.
According to some embodiments of the invention, the inner lining with be equipped with the shock-absorbing shell between the outer lining.
According to some embodiments of the invention, the shock absorbing layer is a nano rubber material.
According to the utility model discloses unmanned aerial vehicle of second aspect embodiment, include according to the utility model discloses unmanned aerial vehicle's of above-mentioned first aspect embodiment horn.
According to the utility model discloses unmanned aerial vehicle of second aspect embodiment is through setting up according to the utility model discloses unmanned aerial vehicle's of above-mentioned first aspect embodiment horn has alleviateed unmanned aerial vehicle's weight effectively, has improved unmanned aerial vehicle's intensity to unmanned aerial vehicle's vibrations have been reduced.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a side view of an arm of an unmanned aerial vehicle according to an embodiment of the present invention;
figure 2 is a cross-sectional view of an arm of an unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 3 is an enlarged view of portion A of FIG. 2;
fig. 4 is a schematic diagram of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 5 is a flowchart of a method of manufacturing a horn of a drone according to an embodiment of the invention.
Reference numerals:
the arm (100) is provided with a mechanical arm,
the outer and inner liners 1, 2,
an unmanned aerial vehicle (1000) is provided,
a frame 200 and a propeller 300.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "inside", "outside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
The horn 100 of the drone 1000 according to an embodiment of the invention is described below with reference to fig. 1-3.
As shown in fig. 1 and 3, according to the utility model discloses unmanned aerial vehicle 1000's horn 100 includes: an inner liner 1 and an outer liner 2. The lining 1 is a hollow structure, and the lining 1 is a glass fiber piece. In particular, the liner 1 may be machined from fiberglass material. The outer lining 2 wraps the outer side of the inner lining 1, and the outer lining 2 is a carbon fiber piece. In particular, the outer liner 2 may be machined from a carbon fiber material.
The horn 100 in the related art generally employs a carbon-clad aluminum process, i.e., an inner layer is an aluminum layer and an outer layer is a carbon fiber layer. Utility model people find that the main problems of this process are: aluminium lamination and carbon fiber layer are at thermoforming to the in-process of recovering the normal atmospheric temperature, and the shrinkage ratio of the two is great, leads to recovering the normal atmospheric temperature back, and great space appears between outer lining 2 and the inside lining 1, influences the quality of horn 100, has hidden danger such as easy book, easy breach that appears. Meanwhile, the horn 100 produced by the carbon-coated aluminum process is heavy in weight and large in vibration.
And the shrinkage of the glass fiber and the carbon fiber is relatively close, and after the heating is recovered to normal temperature, the gap between the outer lining 2 and the inner lining 1 is small or basically has no gap, so that the hidden troubles are reduced to a great extent. The problem that the connection strength is reduced due to pulling after the outer lining 2 and the inner lining 1 are restored to normal temperature due to the fact that the contraction ratios of the two are inconsistent is also solved, and the strength of the horn 100 is effectively improved. Meanwhile, the glass fiber has a high elastic modulus, so that the toughness of the horn 100 can be improved, and the vibration of the horn 100 can be reduced.
According to the utility model discloses unmanned aerial vehicle 1000's horn 100 through setting up inside lining 1 into glass fiber spare, has alleviateed the weight of horn effectively, has improved the intensity of horn to the vibrations of horn have been reduced.
In some embodiments of the present invention, the thickness of the inner liner 1 is a1, the thickness of the outer liner 2 is a2, and the ratio of the thickness a1 of the inner liner 1 to the thickness a2 of the outer liner 2 satisfies: A1/A2 is more than or equal to 1 and less than or equal to 2. For example, the thickness a1 of the inner liner 1 and the thickness a2 of the outer liner 2 may further satisfy: a1/a2 ═ 1.1, a1/a2 ═ 1.2, a1/a2 ═ 1.3, a1/a2 ═ 1.4, a1/a2 ═ 1.5, a1/a2 ═ 1.6, a1/a2 ═ 1.7, a1/a2 ═ 1.8, a1/a2 ═ 1.9, and the like. Therefore, the entire weight of the horn 100 can be effectively reduced, and the strength of the horn 100 can be effectively increased and the vibration of the horn 100 can be reduced.
According to some embodiments of the present invention, the ratio of the thickness a1 of the inner liner 1 to the thickness a2 of the outer liner 2 satisfies: a1/a2 equals 1.5. Because the glass fiber has higher elastic modulus, set the ratio of thickness A1 of inside lining 1 and thickness A2 of outer lining 2 as A1/A2 1.5, can reduce the vibrations of horn 100 effectively on the basis of guaranteeing that horn 100 has lighter weight and great intensity, improve unmanned aerial vehicle 1000's security performance. Meanwhile, the machining process of the horn 100 can be simplified, and the machining cost and the material cost of the horn 100 can be reduced.
According to some embodiments of the utility model, the external diameter of inside lining 1 is D1, and the external diameter of horn 100 is D2, and the ratio of the external diameter D1 of inside lining 1 and the external diameter D2 of horn 100 satisfies: D1/D2 is more than or equal to 0.7 and less than or equal to 0.99. For example, the ratio of the outer diameter D1 of the liner 1 to the outer diameter D2 of the horn 100 may further satisfy: D1/D2 is 0.75, D1/D2 is 0.8, D1/D2 is 0.85, D1/D2 is 0.9, D1/D2 is 0.95, and the like. This can further reduce the vibration of the horn 100, reduce the weight of the horn 100, and increase the strength of the horn 100.
Further, the ratio of the outer diameter D1 of the liner 1 to the outer diameter D2 of the horn 100 satisfies 0.9 ≤ D1/D2 ≤ 0.95. Therefore, the machining process of the horn 100 can be simplified, and the machining cost and the material cost of the horn 100 can be reduced.
According to some embodiments of the present invention, the inner liner 1 and the outer liner 2 are bonded together by epoxy resin. This improves the strength of the joint between the inner liner 1 and the outer liner 2, and reduces the gap between the outer liner 2 and the inner liner 1 after the heating to return to normal temperature.
According to some embodiments of the present invention, a damping layer is provided between the inner liner 1 and the outer liner 2. For example, the shock absorbing layer may be a nano rubber material piece. Thereby, the vibration of the horn 100 can be further reduced, thereby further improving the safety performance of the horn 100.
According to the utility model discloses unmanned aerial vehicle 1000 of second aspect embodiment, include according to the utility model discloses the horn 100 of unmanned aerial vehicle 1000 of above-mentioned first aspect embodiment.
Specifically, referring to fig. 4, the drone 1000 may include: frame 200, horn 100, screw 300 and control module, horn 100 distribute in frame 200 around and with frame 200 fixed connection, screw 300 is fixed in horn 100 and keeps away from the tip of frame 200, and screw 300 provides lift for unmanned aerial vehicle 1000 flight, and control module is fixed in the flight posture that is used for controlling unmanned aerial vehicle 1000 on the frame 200.
According to the utility model discloses unmanned aerial vehicle 1000 of second aspect embodiment is through setting up according to the utility model discloses the unmanned aerial vehicle 1000's of above-mentioned first aspect embodiment horn 100 has alleviateed unmanned aerial vehicle 1000's weight effectively, has improved unmanned aerial vehicle 1000's intensity to unmanned aerial vehicle 1000's vibrations have been reduced.
Referring to fig. 5, a method for manufacturing the horn 100 of the unmanned aerial vehicle 1000 according to the embodiment of the present invention includes the following steps:
step S1: winding the glass fiber cloth into a tubular shape to form a lining 1;
step S2: and winding carbon fiber cloth on the outer side of the inner liner 1 to form the outer liner 2.
For example, the glass fiber cloth may be wound around a tubular mold during the process, whereby the glass fiber cloth may be conveniently wound in a tubular shape. Wherein, glass fiber cloth can be woven into through the glass fiber raw materials, and carbon fiber cloth can be woven into through carbon fiber raw materials.
The horn 100 in the related art generally employs a carbon-clad aluminum process, i.e., an inner layer is an aluminum layer and an outer layer is a carbon fiber layer. Utility model people find that the main problems of this process are: aluminium lamination and carbon fiber layer are at thermoforming to the in-process of recovering the normal atmospheric temperature, and the shrinkage ratio of the two is great, leads to recovering the normal atmospheric temperature back, and great space appears between outer lining 2 and the inside lining 1, influences the quality of horn 100, has hidden danger such as easy book, easy breach that appears. Meanwhile, the horn 100 produced by the carbon-coated aluminum process is heavy in weight and large in vibration.
And the shrinkage of the glass fiber and the carbon fiber is relatively close, and after the heating is recovered to normal temperature, the gap between the outer lining 2 and the inner lining 1 is small or basically has no gap, so that the hidden troubles are reduced to a great extent. The problem that the connection strength is reduced due to pulling after the outer lining 2 and the inner lining 1 are restored to normal temperature due to the fact that the contraction ratios of the two are inconsistent is also solved, and the strength of the horn 100 is effectively improved. Meanwhile, the glass fiber has a high elastic modulus, so that the toughness of the horn 100 can be improved, and the vibration of the horn 100 can be reduced.
According to the utility model discloses unmanned aerial vehicle 1000's horn 100's manufacturing method has alleviateed the weight of horn 100 effectively, has improved the intensity of horn 100 to the vibrations of horn 100 have been reduced.
According to some embodiments of the present invention, before winding the glass fiber cloth into a tube, the glass fiber cloth is impregnated in the epoxy resin, and the impregnated glass fiber cloth is half dried. Therefore, the glass fiber cloth layers are bonded through the epoxy resin, and the connection strength of the glass fiber cloth layers is improved.
According to the utility model discloses a some embodiments, before winding carbon cloth in the inside lining 1 outside, impregnate carbon cloth in epoxy to will pass through impregnated carbon cloth and half dry. Therefore, the carbon fiber cloth layers are bonded through the epoxy resin, and the connection strength of the carbon fiber cloth layers is improved.
Here, the term "half-baking" as used in the present application means baking until the epoxy resin does not flow.
According to some embodiments of the present invention, before the carbon fiber cloth is wound around the outer side of the inner liner 1, the glass fiber cloth layers are tightly connected and cured to form the inner liner 1 by heating and pressurizing; after winding carbon cloth in inside lining 1 outside, through the mode of heating and pressurizing complex, with each layer carbon cloth zonulae occludens for carbon cloth solidification moulding wraps up in inside lining 1 outside. From this, earlier with glass fiber cloth heating and pressurization so that each layer glass fiber cloth zonulae occludens and solidification shaping, twine carbon fiber cloth in the outside of inside lining 1 again to with carbon fiber cloth heating and pressurization so that each layer carbon fiber cloth zonulae occludens and solidification shaping, can greatly reduce carbon fiber cloth's the winding degree of difficulty.
According to the utility model discloses a further other embodiments, after winding carbon cloth in the inside lining 1 outside, through the compound mode of pressurization of heating, with each layer glass fiber cloth and each layer carbon cloth zonulae occludens and solidification moulding. Therefore, after the carbon fiber cloth is wound on the outer side of the lining 1, the glass fiber cloth and the carbon fiber cloth are heated and pressurized simultaneously, the processing technology is simplified, and the processing cost is reduced.
Two specific manufacturing methods of the horn 100 of the drone 1000 according to embodiments of the present invention are described below.
The method comprises the following steps:
selecting a glass fiber raw material;
weaving glass fiber raw materials into glass fiber cloth;
soaking glass fiber cloth in epoxy resin;
semi-drying the impregnated glass fiber cloth;
directly winding the glass fiber cloth into a tubular shape or winding the glass fiber cloth on a tubular mold, so that the glass fiber cloth layers are bonded and connected through epoxy resin;
tightly connecting and curing each layer of glass fiber cloth to form the lining 1 in a pressurizing and heating composite mode;
selecting a carbon fiber raw material;
weaving carbon fiber raw materials into carbon fiber cloth;
soaking the carbon fiber cloth in epoxy resin;
semi-drying the impregnated carbon fiber cloth;
winding the carbon fiber cloth on the lining 1, so that the carbon fiber cloth layers are bonded and connected through epoxy resin;
through the mode of pressurization and heating compounding, each layer of carbon fiber cloth is tightly connected so that the carbon fiber cloth is cured, molded and wrapped on the lining 1.
The second method comprises the following steps:
selecting a glass fiber raw material;
weaving glass fiber raw materials into glass fiber cloth;
soaking glass fiber cloth in epoxy resin;
semi-drying the impregnated glass fiber cloth;
directly winding the glass fiber cloth into a tubular shape or winding the glass fiber cloth on a tubular mold, so that the glass fiber cloth layers are bonded and connected through epoxy resin;
selecting a carbon fiber raw material, namely selecting a carbon fiber raw material,
weaving carbon fiber raw materials into carbon fiber cloth;
soaking the carbon fiber cloth in epoxy resin;
semi-drying the impregnated carbon fiber cloth;
tightly winding the carbon fiber cloth on the outer side of the glass fiber cloth formed into a tubular shape;
the carbon fiber cloth and the glass fiber cloth are tightly connected in a pressurizing and heating composite mode, so that the carbon fiber cloth is solidified, molded and wrapped on the glass fiber cloth.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (9)
1. An unmanned aerial vehicle's horn, its characterized in that includes:
the lining is of a hollow structure and is a glass fiber piece;
the outer lining is wrapped on the outer side of the inner lining and is a carbon fiber piece.
2. The drone horn of claim 1, wherein the inner liner has a thickness of a1, the outer liner has a thickness of a2, and the ratio of the thickness of the inner liner a1 to the thickness of the outer liner a2 is such that: A1/A2 is more than or equal to 1 and less than or equal to 2.
3. The drone of claim 2, wherein the ratio of the thickness a1 of the inner liner to the thickness a2 of the outer liner satisfies: a1/a2 equals 1.5.
4. The drone horn of claim 1, wherein the inner liner has an outer diameter of D1, the horn has an outer diameter of D2, and the ratio of the inner liner outer diameter D1 to the horn outer diameter D2 is such that: D1/D2 is more than or equal to 0.7 and less than or equal to 0.99.
5. The arm of the drone of claim 4, wherein the ratio of the outer diameter D1 of the liner to the outer diameter D2 of the arm satisfies 0.9 ≦ D1/D2 ≦ 0.95.
6. The drone horn of claim 1, wherein the inner liner and the outer liner are adhesively attached by epoxy.
7. The drone horn of claim 1, wherein a shock absorbing layer is disposed between the inner liner and the outer liner.
8. The drone arm of claim 7, wherein the shock absorbing layer is a nano-rubber material.
9. A drone, characterized in that it comprises a horn of a drone according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921750569.4U CN210852909U (en) | 2019-10-17 | 2019-10-17 | Unmanned aerial vehicle's horn and unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921750569.4U CN210852909U (en) | 2019-10-17 | 2019-10-17 | Unmanned aerial vehicle's horn and unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN210852909U true CN210852909U (en) | 2020-06-26 |
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| CN201921750569.4U Active CN210852909U (en) | 2019-10-17 | 2019-10-17 | Unmanned aerial vehicle's horn and unmanned aerial vehicle |
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| CN (1) | CN210852909U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588968A (en) * | 2019-10-17 | 2019-12-20 | 广州极飞科技有限公司 | Unmanned aerial vehicle arm, unmanned aerial vehicle and manufacturing method of arm |
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2019
- 2019-10-17 CN CN201921750569.4U patent/CN210852909U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588968A (en) * | 2019-10-17 | 2019-12-20 | 广州极飞科技有限公司 | Unmanned aerial vehicle arm, unmanned aerial vehicle and manufacturing method of arm |
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Address after: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee after: XAG Co., Ltd. Address before: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee before: Guangzhou Xaircraft Technology Co.,Ltd. |
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