CN204998762U - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN204998762U CN204998762U CN201520574460.5U CN201520574460U CN204998762U CN 204998762 U CN204998762 U CN 204998762U CN 201520574460 U CN201520574460 U CN 201520574460U CN 204998762 U CN204998762 U CN 204998762U
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- unmanned plane
- horn
- fuselage
- centre
- lift
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Abstract
The utility model discloses an unmanned aerial vehicle, unmanned aerial vehicle includes: the organism, the organism includes fuselage and storing device, two at least preceding horns about axis symmetry setting, the one end of preceding horn with the front end of fuselage links to each other and extends forward, the motor is with the drive before being equipped with on the other end of preceding horn unmanned aerial vehicle, two at least back horns about axis symmetry setting, the one end of back horn with the rear end of fuselage links to each other and extends backwards, be equipped with the back motor on the other end of back horn with the drive unmanned aerial vehicle, wherein reaching of back horn the orientation of preceding horn the extension line of fuselage with the intersection region of axis is located centre of lift the place ahead of unmanned aerial vehicle, just preceding motor with back motor is right unmanned aerial vehicle's the application point of making a concerted effort does the centre of lift, unmanned aerial vehicle's focus is neighbouring the centre of lift. The utility model discloses an unmanned aerial vehicle, the control degree of difficulty is low, and has a smooth flight.
Description
Technical field
The utility model belongs to vehicle technology field, in particular to a kind of unmanned plane.
Background technology
Existing unmanned plane is the agricultural unmanned plane of multimachine arm particularly, the crossover location of the extended line of its horn overlaps with the centre of lift of unmanned plane, the parts of unmanned plane are installed in above or below fuselage, and parts thereof tired folded installation on gravity direction, when the goods that unmanned plane loads is laid down, the center of gravity of unmanned plane can have greatly changed, and increases the control difficulty of unmanned plane, there is room for improvement.
Utility model content
The utility model is intended to solve one of technical matters in correlation technique at least to a certain extent.For this reason, an object of the present utility model is to propose a kind of unmanned plane being convenient to manipulate.
According to unmanned plane of the present utility model, comprising: body, described body comprises fuselage and is located at the article-storage device of rear for lade of described fuselage; Symmetrically arranged at least two the front horns in axis about described fuselage fore-and-aft direction, one end of described front horn is connected with the front end of described fuselage and extends forward, and the other end of described front horn is provided with front motor to drive described unmanned plane; About horn behind symmetrically arranged at least two of described axis, one end of described rear horn is connected with the rear end of described fuselage and extends backwards, and the other end of described rear horn is provided with rear motor to drive described unmanned plane; The extended line towards described fuselage of wherein said rear horn and described front horn and the intersection region of described axis are positioned at the centre of lift front of described unmanned plane, and described front motor and the point of action of making a concerted effort of described rear motor to described unmanned plane are described centre of lift, the contiguous described centre of lift of center of gravity of described unmanned plane.
According to unmanned plane of the present utility model, the impact of the center-of-gravity position on unmanned plane of the goods that unmanned plane loads is less, and be conducive to controlling unmanned plane more reposefully, the control difficulty of unmanned plane is low.
In addition, above-mentioned according to the utility model unmanned plane can also have following additional technical characteristic:
Preferably, the geometric centre of the contiguous described article-storage device of described centre of lift.
Alternatively, the geometric centre of the center of gravity of described unmanned plane, described centre of lift and described article-storage device overlaps.
Preferably, described front horn and described rear horn are two.
Further, the angle of two described front horns is greater than the angle of two described rear horns.
Further, the length of described rear horn is greater than the length of described front horn.
Further, the described other end of two described front horns and the described other end of two described rear horns are positioned on four summits of a rectangle.
Preferably, the described other end of two described front horns and the described other end of two described rear horns are positioned on foursquare four summits.
Alternatively, described rear horn is configured to linear or arc.
Alternatively, the front end of described fuselage comprises front panel, and described front panel is provided with the control module of described unmanned plane, detection module and auxiliary device; The battery of described unmanned plane is located in described article-storage device.
Accompanying drawing explanation
Above-mentioned and/or additional aspect of the present utility model and advantage will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1 is the structural representation of the unmanned plane according to the utility model embodiment;
Fig. 2 is the partial enlarged drawing at D place in Fig. 1.
Reference numeral:
Unmanned plane 100,
Body 110, fuselage 111, front panel 1111, article-storage device 112,
Front horn 120,
Rear horn 130,
Front motor 142, rear motor 143,
First intersection point A, the second intersection points B, centre of lift C,
Angle α after two between horn, the angle β between two front horns.
Detailed description of the invention
Be described below in detail embodiment of the present utility model, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.
In description of the present utility model, it will be appreciated that, term " " center ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.
In the utility model, unless otherwise clearly defined and limited, the term such as term " installation ", " being connected ", " connection ", " fixing " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or integral; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals or the interaction relationship of two elements, unless otherwise clear and definite restriction.For the ordinary skill in the art, the concrete meaning of above-mentioned term in the utility model can be understood as the case may be.
In the utility model, unless otherwise clearly defined and limited, fisrt feature second feature " on " or D score can be that the first and second features directly contact, or the first and second features are by intermediary indirect contact.And, fisrt feature second feature " on ", " top " and " above " but fisrt feature directly over second feature or oblique upper, or only represent that fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " below " and " below " can be fisrt feature immediately below second feature or tiltedly below, or only represent that fisrt feature level height is less than second feature.
Below with reference to the accompanying drawings and describe the utility model in detail in conjunction with the embodiments.
As described in Figure 1, the fore-and-aft direction of the utility model embodiment refers to the heading of unmanned plane, and unmanned plane flies forward, and the afterbody of unmanned plane is positioned at rear.
Describe the unmanned plane 100 according to the utility model embodiment in detail referring to Fig. 1-Fig. 2, as depicted in figs. 1 and 2, unmanned plane 100 comprises body 110, front horn 120 and rear horn 130.
Wherein, body 110 comprises fuselage 111 and article-storage device 112, and article-storage device 112 is for lade, and article-storage device 112 is located at the rear of fuselage 111.
Front horn 120 is at least two, one end of front horn 120 is connected with the front end of fuselage 111, front horn 120 extends forward, and front horn 120 is symmetrical arranged about the axis being parallel to fuselage 111 fore-and-aft direction, the other end of front horn 120 is provided with front motor 142, and front motor 142 is for driving unmanned plane 100.
Rear horn 130 is at least two, one end of rear horn 130 is connected with the rear end of fuselage 111, rear horn 130 extends backwards, and rear horn 130 is symmetrical arranged about the axis being parallel to fuselage 111 fore-and-aft direction, the other end of rear horn 130 is provided with rear motor 143, and rear motor 143 is also for driving unmanned plane 100.
Front motor 142 is the centre of lift C of unmanned plane 100 with the point of action of making a concerted effort of rear motor 143 pairs of unmanned planes 100, and in other words, the point of action of making a concerted effort of the propulsive effort (comprising buoyancy) that unmanned plane 100 is subject to is the centre of lift C of unmanned plane 100.
As depicted in figs. 1 and 2, the extended line towards fuselage 111 of front horn 120 and the extended line towards fuselage 111 of rear horn 130 and the above-mentioned axis of fuselage 111 intersect at intersection region, and intersection region is positioned at the front of the centre of lift C of unmanned plane 100.
In other words, as depicted in figs. 1 and 2, the extended line towards fuselage 111 of rear horn 130 and the above-mentioned axis of fuselage 111 meet at the first intersection point A, the extended line towards fuselage 111 of front horn 120 and the above-mentioned axis of fuselage 111 meet at the second intersection points B, in Fig. 1 right abaft to the extended line towards fuselage 111 of rear horn 130 and Fig. 1 in left front to before the extended line towards fuselage 111 of horn 120 is approximate coincides together, in Fig. 1 left back to the extended line towards fuselage 111 of rear horn 130 and Fig. 1 in right front to before the extended line towards fuselage 111 of horn 120 is approximate coincides together, the extended line towards fuselage 111 of rear horn 130 and the extended line towards fuselage 111 of front horn 120 intersect at the midpoint of the first intersection point A and the second intersection points B substantially, the mid point of the first intersection point A and the second intersection points B is positioned at the front of the centre of lift C of unmanned plane 100.Alternatively, the first intersection point A and the second intersection points B are all positioned at the centre of lift C front of unmanned plane 100.
Be understandable that, rear horn 130 and the junction of fuselage 111 are positioned at the middle part of body 110, are equivalent to rear horn 130 to move forward, and front horn 120 and the junction of fuselage 111 are positioned at the front portion of body 110, and front horn 120 is also towards reach.Thus, the installing space of article-storage device 112 is left in position to the rear, the middle part of body 110, the centre of lift C of unmanned plane 100 is positioned at position to the rear, the middle part of body 110, that is, and the centre of lift C of the contiguous unmanned plane 100 of position of the goods in article-storage device 112.The contiguous centre of lift C of center of gravity of unmanned plane 100, is conducive to front motor 142 and drives unmanned plane 100 with rear motor 143.
The unmanned plane 100 of zero load is defined as constant weight module, the goods that unmanned plane 100 loads is defined as variable weight module, the centre of lift C of the contiguous unmanned plane 100 of center of gravity of constant weight module, the center of gravity of variable weight module is also close to the centre of lift C of unmanned plane 100, the unmanned plane 100 of lade is after unloading goods, and the center-of-gravity position change of unmanned plane 100 is less.
According to the unmanned plane 100 of the utility model embodiment, move forward by making the front horn of unmanned plane 100 120 and rear horn 130, goods (variable weight module) impact on the center-of-gravity position of unmanned plane 100 of loading in unmanned plane 100 can be reduced, be convenient to control unmanned plane 100 more reposefully, reduce the control difficulty of unmanned plane 100.
Alternatively, front motor 142 and rear motor 143 can be the motor of same model to reduce the parts kind of unmanned plane 100, the production procedure of simplification unmanned plane 100, the productive costs of reduction unmanned plane 100.
Alternatively, as depicted in figs. 1 and 2, the fuselage 111 of unmanned plane 100 can be provided with multiple engraved structure, to reduce the weight of unmanned plane 100, contribute to the lightweight realizing unmanned plane 100.
In preferred embodiments more of the present utility model, as described in Figure 1, the centre of lift C of unmanned plane 100 can be close to the geometric centre of article-storage device 112.
Be understandable that, the geometric centre of the contiguous article-storage device 112 of center of gravity of the goods (variable weight module) loaded in article-storage device 112, particularly for the goods of liquid or powdery type, its center of gravity overlaps substantially with the geometric centre of article-storage device 112.The geometric centre of article-storage device 112 is located at the position contiguous with the centre of lift C of unmanned plane 100, be conducive to alleviating the impact of goods on the center of gravity of unmanned plane 100, be convenient to manipulate unmanned plane 100 better when the weight of unmanned plane 100 is in and dynamically (such as, lays down goods gradually).
Preferably, the geometric centre of the center of gravity of unmanned plane 100, the centre of lift C of unmanned plane 100 and article-storage device 112 can overlap.In other words, the center of gravity of the center of gravity of the constant weight module of unmanned plane 100, centre of lift C and variable weight module can overlap, to reduce the impact of variable weight module on the center of gravity of unmanned plane 100.
In a concrete example of the present utility model, the front end of fuselage 111 can comprise front panel 1111, front panel 1111 can be provided with the control module of unmanned plane 100, detection module and auxiliary device, and the battery of unmanned plane 100 can be located in article-storage device 112.
Be understandable that, the constant weight module of unmanned plane 100 can comprise body 110, front horn 120, rear horn 130, control module, detection module, auxiliary device and battery, by the control module by lighter in weight, detection module, auxiliary device is located at the front end of body 110, battery larger for weight is located at the rear end of fuselage 111, the center of gravity of the constant weight module of unmanned plane 100 can be made to drop on position to the rear, the middle part of body 110, be conducive to the balance of unmanned plane 100 and the layout of variable weight module, and constant weight module and variable weight module can in fore-and-aft direction tiled arrangements, be conducive on gravity direction, make the center of gravity of unmanned plane 100 maintain near fuselage 111, the center of gravity of unmanned plane 100 is avoided to rise on gravity direction or decline, and the position of variable weight module is unobstructed, be conducive to the loading and unloading of variable weight module.
Alternatively, at least part of battery can be located at the rear end of article-storage device 112, in other words, at least part of battery can be located at the rear of variable weight module, with when laying down goods (variable weight module), the impact that the center of gravity alleviating unmanned plane 100 is subject to, the control of unmanned plane 100 is simpler and easy.
In some optional embodiments, front horn 120 can be two, and rear horn 130 can be four, and after four, horn 130 symmetry can be located at the both sides of axis between two.In other optional embodiments, front horn 120 can be four, and rear horn 130 can be four, and four front horns 120 symmetry can be located at the both sides of axis between two, and after four, horn 130 symmetry can be located at the both sides of axis between two.Certainly, front horn 120 is not limited thereto with the quantity of rear horn 130.
Preferably, as shown in Figure 1, front horn 120 can be two, and two front horns 120 symmetrical can be located at the both sides of axis, and rear horn 130 can be two, and after two, horn 130 symmetrical can be located at the both sides of axis.Can provide sufficient propulsive effort for unmanned plane 100 thus, and the structure of unmanned plane 100 is simple.
As Figure 1-Figure 2, because horn 130 after two is symmetrical arranged about axis, after two, the extended line towards fuselage 111 of horn 130 and axis meet at same point---the first intersection point A, the intersection point of the extended line towards fuselage 111 of two front horns 120 is the second intersection points B, and the second intersection points B can between the centre of lift C of unmanned plane 100 and the first intersection point A.
That is, the position relationship of above-mentioned 3 is: the first intersection point A can be positioned at forefront, and the first intersection point A and the second intersection points B all can be positioned at the centre of lift C front of unmanned plane 100.Thus, contribute to vacating a large amount of spaces for lade near the centre of lift C of unmanned plane 100, make the center of gravity next-door neighbour unmanned plane 100 centre of lift C of goods, to alleviate the impact of variable weight module on the center of gravity of unmanned plane 100, the operation of unmanned plane 100 is simpler and easy.
On the other hand, by arranging said structure, be equivalent on unmanned plane 100, add two triangular structures (the first intersection point A and the second intersection points B are the summit that these two triangles have), the structure of unmanned plane 100 is more firm.
As shown in Figure 2, the angle after two between horn 130 is α, and the angle between two front horns 120 is β, and α and β can meet: α < β.After two front horns 120, two, horn 130 towards the direction adduction near axis, thus, can move after can making the centre of lift C of unmanned plane 100.
Alternatively, the first intersection point A can be arranged with the second intersection points B is contiguous, and in other words, the first intersection point A can overlap substantially with the second intersection points B, can increase the middle part of unmanned plane 100 and the space at rear portion thus.
Further, as shown in Figure 1, the length of rear horn 130 can be greater than the length of front horn 120.In other words, the other end (being provided with one end of rear motor 143) of rear horn 130 can be greater than the distance of the other end (being provided with one end of front motor 142) to the second intersection points B of front horn 120 to the distance of the first intersection point A.Move forward because rear horn 130 and front horn 120 are all relative with the junction of fuselage 111, making the balance of unmanned plane 100 better by arranging said structure, being convenient to manipulation.
In embodiment more of the present utility model, as shown in Figure 1, rear horn 130 can be configured to linear.
In other embodiment of the present utility model, rear horn 130 can be configured to arc.
Certainly, the shape of rear horn 130 is not limited to above-mentioned two kinds, such as, can also be fold-line-shaped.
Preferably, two front horns 120 the other end (being provided with one end of front motor 142) with two after the other end (being provided with one end of rear motor 143) of horn 130 can be positioned on four summits of a rectangle.In other words, for being positioned at the front horn of axis homonymy 120 and rear horn 130, being arranged on the front motor 142 on this front horn 120 and being arranged on the line of the rear motor 143 on this rear horn 130 and above-mentioned axis parallel.
In a concrete example of the present utility model, as shown in Figure 1, two front horns 120 the other end (being provided with one end of front motor 142) with two after the other end (being provided with one end of rear motor 143) of horn 130 can be positioned on foursquare four summits.
Be understandable that, the centre of lift C of unmanned plane 100 under plateau is above-mentioned foursquare center, and the center of gravity of the constant weight module of unmanned plane 100 and variable weight module all can be positioned at above-mentioned foursquare immediate vicinity, thus, the structure of unmanned plane 100 is simple, symmetry and balance good, be easy to control.
Can be agricultural unmanned plane according to the unmanned plane 100 of the utility model embodiment, correspondingly, the goods (variable weight module) that unmanned plane 100 loads can be agricultural chemicals, because the constant weight module of unmanned plane 100 and variable weight module are tiled arrangements in the longitudinal direction, the loading of agricultural chemicals and unloading are all more for convenience, in unmanned plane 100 flight course, agricultural chemicals can be gone out from article-storage device 112 by flexible pipe progressive spraying, reduce in the process of (weight of variable weight module changes) at agricultural chemicals, the center of gravity of unmanned plane 100 is positioned near the centre of lift C of unmanned plane 100 all the time, thus, the control of unmanned plane 100 is comparatively simple and easy and steady.
In sum, according to the unmanned plane 100 of the utility model embodiment, comprise two symmetrically arranged front horns 120 and two symmetrically arranged rear horns 130, after one end being provided with front motor 142 of two front horns 120 and two, one end being provided with rear motor 143 of horn 130 can be positioned on foursquare four summits, by the junction of horn after moving forward 130 with fuselage 111, make the first intersection point A, the centre of lift C of the second intersection points B and unmanned plane 100 is arranged in turn from front to back on the fore-and-aft direction of unmanned plane 100, and the position that the middle part of unmanned plane 100 is to the rear is provided with article-storage device 112, the center of gravity of the constant weight module of unmanned plane 100 and the center of gravity of variable weight module is made all to be adjacent to the centre of lift C of unmanned plane 100.Thus, the impact of variable weight module on the center of gravity of whole unmanned plane 100 can be reduced, to simplify the control of unmanned plane 100, unmanned plane 100 is made to fly more steady, and by the constant weight module of unmanned plane 100 and variable weight module tiled arrangements, can prevent unmanned plane 100 from obtaining the lifting of center of gravity at gravity direction, article-storage device 112 is unobstructed, is convenient to loading and the unloading of variable weight module.
In the description of this specification sheets, specific features, structure, material or feature that the description of reference term " embodiment ", " some embodiments ", " example ", " concrete example " or " some examples " etc. means to describe in conjunction with this embodiment or example are contained at least one embodiment of the present utility model or example.In this manual, to the schematic representation of above-mentioned term not must for be identical embodiment or example.And the specific features of description, structure, material or feature can combine in one or more embodiment in office or example in an appropriate manner.In addition, when not conflicting, the feature of the different embodiment described in this specification sheets or example and different embodiment or example can carry out combining and combining by those skilled in the art.
Although illustrate and described embodiment of the present utility model above, be understandable that, above-described embodiment is exemplary, can not be interpreted as restriction of the present utility model, those of ordinary skill in the art can change above-described embodiment, revises, replace and modification in scope of the present utility model.
Claims (10)
1. a unmanned plane, is characterized in that, comprising:
Body, described body comprises fuselage and is located at the article-storage device of rear for lade of described fuselage;
Symmetrically arranged at least two the front horns in axis about described fuselage fore-and-aft direction, one end of described front horn is connected with the front end of described fuselage and extends forward, and the other end of described front horn is provided with front motor to drive described unmanned plane;
About horn behind symmetrically arranged at least two of described axis, one end of described rear horn is connected with the rear end of described fuselage and extends backwards, and the other end of described rear horn is provided with rear motor to drive described unmanned plane; Wherein
The extended line towards described fuselage of described rear horn and described front horn and the intersection region of described axis are positioned at the centre of lift front of described unmanned plane, and described front motor and the point of action of making a concerted effort of described rear motor to described unmanned plane are described centre of lift, the contiguous described centre of lift of center of gravity of described unmanned plane.
2. unmanned plane according to claim 1, is characterized in that, the geometric centre of the contiguous described article-storage device of described centre of lift.
3. unmanned plane according to claim 2, is characterized in that, the geometric centre of the center of gravity of described unmanned plane, described centre of lift and described article-storage device overlaps.
4. unmanned plane according to claim 2, is characterized in that, described front horn and described rear horn are two.
5. unmanned plane according to claim 4, is characterized in that, the angle of two described front horns is greater than the angle of two described rear horns.
6. unmanned plane according to claim 5, is characterized in that, the length of described rear horn is greater than the length of described front horn.
7. the unmanned plane according to any one of claim 4-6, is characterized in that, the described other end of the described other end of two described front horns and two described rear horns is positioned on four summits of a rectangle.
8. unmanned plane according to claim 7, is characterized in that, the described other end of the described other end of two described front horns and two described rear horns is positioned on foursquare four summits.
9. unmanned plane according to claim 2, is characterized in that, described rear horn is configured to linear or arc.
10. unmanned plane according to claim 2, is characterized in that, the front end of described fuselage comprises front panel, and described front panel is provided with the control module of described unmanned plane, detection module and auxiliary device; The battery of described unmanned plane is located in described article-storage device.
Priority Applications (8)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520574460.5U CN204998762U (en) | 2015-07-31 | 2015-07-31 | Unmanned aerial vehicle |
| ES16832251T ES2807923T3 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle |
| PCT/CN2016/091932 WO2017020763A1 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle |
| AU2016303994A AU2016303994B2 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
| US15/523,897 US10526087B2 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
| EP16832251.9A EP3202662B1 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle |
| KR1020177012662A KR101989258B1 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
| JP2017527807A JP6463841B2 (en) | 2015-07-31 | 2016-07-27 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520574460.5U CN204998762U (en) | 2015-07-31 | 2015-07-31 | Unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204998762U true CN204998762U (en) | 2016-01-27 |
Family
ID=55155663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520574460.5U Withdrawn - After Issue CN204998762U (en) | 2015-07-31 | 2015-07-31 | Unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN204998762U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173068A (en) * | 2015-07-31 | 2015-12-23 | 广州极飞电子科技有限公司 | Unmanned plane |
| WO2017020763A1 (en) * | 2015-07-31 | 2017-02-09 | 广州极飞科技有限公司 | Unmanned aerial vehicle |
| CN106394884A (en) * | 2015-07-31 | 2017-02-15 | 广州极飞科技有限公司 | Unmanned aerial vehicle |
| CN107031841A (en) * | 2016-04-07 | 2017-08-11 | 广州极飞科技有限公司 | Aircraft |
-
2015
- 2015-07-31 CN CN201520574460.5U patent/CN204998762U/en not_active Withdrawn - After Issue
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173068A (en) * | 2015-07-31 | 2015-12-23 | 广州极飞电子科技有限公司 | Unmanned plane |
| WO2017020763A1 (en) * | 2015-07-31 | 2017-02-09 | 广州极飞科技有限公司 | Unmanned aerial vehicle |
| CN106394884A (en) * | 2015-07-31 | 2017-02-15 | 广州极飞科技有限公司 | Unmanned aerial vehicle |
| US10526087B2 (en) | 2015-07-31 | 2020-01-07 | Guangzhou Xaircraft Technology Co., Ltd. | Unmanned aerial vehicle and unmanned aerial vehicle body configured for unmanned aerial vehicle |
| CN107031841A (en) * | 2016-04-07 | 2017-08-11 | 广州极飞科技有限公司 | Aircraft |
| CN107031827A (en) * | 2016-04-07 | 2017-08-11 | 广州极飞科技有限公司 | Aircraft |
| CN107031841B (en) * | 2016-04-07 | 2024-02-13 | 广州极飞科技股份有限公司 | Aircraft with a plurality of aircraft body |
| CN107031827B (en) * | 2016-04-07 | 2024-02-13 | 广州极飞科技股份有限公司 | Aircraft with a plurality of aircraft body |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 510000 Guangdong, Guangzhou, Tianhe District Cheng Cheng Road, No. 3A01, 1 Patentee after: Guangzhou flying Technology Co., Ltd. Address before: 510000 Guangdong, Guangzhou, Tianhe District Cheng Cheng Road, No. 3A01, 1 Patentee before: GUANGZHOU XAIRCRAFT ELECTRONIC TECHNOLOGY CO., LTD. |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20160127 Effective date of abandoning: 20180921 |
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| AV01 | Patent right actively abandoned |