CN218477647U - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
- Publication number
- CN218477647U CN218477647U CN202222488732.2U CN202222488732U CN218477647U CN 218477647 U CN218477647 U CN 218477647U CN 202222488732 U CN202222488732 U CN 202222488732U CN 218477647 U CN218477647 U CN 218477647U
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- upper wing
- rotor
- unmanned aerial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The utility model discloses an unmanned aerial vehicle, this unmanned aerial vehicle include fuselage, a plurality of rotor, go up wing and lower wing. Wherein: the upper wing and the lower wing are both foldable wings; the upper wing and the lower wing at least partially overlap in the vertical direction when unfolded; the rotor wing is arranged on the fuselage and/or the upper wing. This unmanned aerial vehicle has a plurality of rotors and collapsible wing, can realize big load, but vertical lift, the purpose of convenient transportation.
Description
Technical Field
The utility model relates to an aerospace technical field, in particular to unmanned aerial vehicle.
Background
In recent years, traditional agricultural unmanned aerial vehicle is mostly rotor type unmanned aerial vehicle, and this type unmanned aerial vehicle can't carry out long distance operation usually, and flying speed is also relatively slower.
The existing agricultural fixed wing unmanned aerial vehicle is mainly man-machine, can not take off and land vertically, can not be folded by wings in the transportation process, or can be assembled after the airplane is disassembled to be transported to a destination, and a large amount of time can be spent in the process.
Under the condition of the same load, the single-wing fixed-wing unmanned aerial vehicle needs a larger wing span, the wing can not be placed on the existing agricultural vehicle after being folded, and the rigidity of the wing is influenced by the longer wing span.
Therefore, how to design an unmanned aerial vehicle, can realize big load, but the purpose of vertical lift, convenient transportation, be the technical problem that technical staff in the field awaits a urgent need to solve at present.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at providing an unmanned aerial vehicle has a plurality of rotors and collapsible wing, can realize big load, but the purpose of vertical lift, convenient transportation.
In order to achieve the above purpose, the utility model provides a following technical scheme:
an unmanned aerial vehicle, includes fuselage, a plurality of rotors, goes up wing and lower wing, wherein:
the upper wing and the lower wing are foldable wings;
the upper wing and the lower wing at least partially overlap in a vertical direction when deployed;
the rotor is arranged on the fuselage and/or the upper wing.
Optionally, in the above drone, the upper wing includes a first upper wing unit and a second upper wing unit, wherein:
the first upper wing unit is hinged with the fuselage through a first hinge part;
the second upper wing unit is hinged with the fuselage through a second hinge part;
the body is provided with a protruding structure for limiting the first upper wing unit and the second upper wing unit at a rotation end point.
Optionally, in the above unmanned aerial vehicle, the first upper wing unit is detachably connected to the main body through a first clamping portion, and the first clamping portion is located in front of the first hinge portion;
the second upper wing unit is detachably connected with the body through a second clamping portion, and the second clamping portion is located in front of the second hinged portion.
Optionally, in the above drone, the lower wing includes a first lower wing element and a second lower wing element, wherein:
the first lower wing unit is hinged to the fuselage by a third hinge;
the second lower wing unit is hinged to the fuselage by a fourth hinge.
Optionally, in the above unmanned aerial vehicle, the first lower wing unit is detachably connected to the fuselage through a third clamping portion, and the third clamping portion is located in front of the third hinge portion;
the second lower wing unit is detachably connected with the fuselage through a fourth clamping portion, and the fourth clamping portion is located in front of the fourth hinged portion.
Optionally, in the above drone, the rotor includes a leading rotor and a trailing rotor;
the both sides of fuselage all are provided with leading rotor with rearmounted rotor.
Optionally, in the above unmanned aerial vehicle, further includes:
the first tilting steering engine is used for adjusting the pulling direction of the front rotor wing;
and/or a second tilting steering engine for adjusting the pulling direction of the rear rotor wing.
Optionally, in the above unmanned aerial vehicle, further includes:
one end of the first support rod is provided with the front rotor, and the other end of the first support rod is hinged with the front side edge of the upper wing;
and the rear rotor wing is arranged on the fuselage through the second supporting rod and is positioned at the rear of the upper wing and the lower wing.
Optionally, in the above drone, the upper wing, the lower wing, and the first strut are all in a folded state:
the front rotor and the rear rotor are arranged on two sides of a folding mechanism consisting of the fuselage, the upper wing and the lower wing;
the heights of the front rotor, the upper wing, the rear rotor and the lower wing are reduced in sequence.
Optionally, in above-mentioned unmanned aerial vehicle, the fuselage includes fuselage main frame and middle mounting, middle mounting is: a medical kit for holding the pesticide, or be used for holding the seed case of seed, or be used for the camera mount pad.
The utility model provides an unmanned aerial vehicle during operation, if upper and lower wing is in the expansion state, then the structure through its upper and lower overlapping layout can effectively improve unmanned aerial vehicle's load capacity, also is favorable to improving unmanned aerial vehicle's remote navigation ability moreover. Moreover, because a plurality of rotors are arranged in the unmanned aerial vehicle, and the upper wing and the lower wing can be folded, the unmanned aerial vehicle can be vertically lifted and landed, and can be conveniently transported on a vehicle.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is an expanded axonometric view of an unmanned aerial vehicle provided in an embodiment of the present invention;
fig. 2 is a folded state axonometric view of the unmanned aerial vehicle provided by the embodiment of the present invention;
fig. 3 is a folded state top view of the unmanned aerial vehicle provided in the embodiment of the present invention;
fig. 4 is a partial wing axonometric view of an unmanned aerial vehicle provided by an embodiment of the present invention;
fig. 5 is the embodiment of the utility model provides an unmanned aerial vehicle's transition state axonometric drawing is provided.
Detailed Description
The embodiment of the utility model provides an unmanned aerial vehicle has a plurality of rotors and collapsible wing, can realize big load, but the purpose of vertical lift, convenient transportation.
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The embodiment of the utility model provides an unmanned aerial vehicle has a plurality of rotors and collapsible wing, specifically is a two-wing fixed wing unmanned aerial vehicle, can be used for the pesticide to spray, the seed is sowed, also can be used to take photo by plane certainly, other fields such as electric power patrol and examine, environmental monitoring, forest fire prevention and disaster condition patrol and survey.
Referring to fig. 1 to 5, the drone includes a fuselage, a plurality of rotors, an upper wing 4 and a lower wing 3, wherein: the upper wing 4 and the lower wing 3 are both foldable wings; the upper wing 4 and the lower wing 3 are at least partially overlapped in the vertical direction when unfolded; multiple rotors may be mounted to the fuselage and to the upper wing 4, or alternatively, some rotors may be provided on the fuselage and some rotors may be provided on the upper wing 4.
This unmanned aerial vehicle during operation, if upper and lower wing is in the expansion state, then the structure through its upper and lower overlapping layout can effectively improve unmanned aerial vehicle's load-carrying capacity, also is favorable to improving unmanned aerial vehicle's televoyage ability moreover. Moreover, because a plurality of rotors are arranged in the unmanned aerial vehicle, and the upper wing and the lower wing can be folded, the unmanned aerial vehicle can be vertically lifted and landed, and can be conveniently transported on a vehicle.
In specific implementation, the upper wing 4 includes a first upper wing unit and a second upper wing unit, wherein: the first upper wing unit is hinged with the fuselage through a first hinge (see the rear lug 502 and the second rotating shaft 402 in fig. 3 and 4); the second upper wing unit is hinged with the fuselage through a second hinge part; the body is provided with a protruding structure 503 for limiting the first upper wing unit and the second upper wing unit at the rotation end point. Therefore, referring to fig. 3, when the first upper wing unit and the second upper wing unit are folded, the first upper wing unit and the second upper wing unit can be positioned by the protruding structure 503 without being turned over excessively.
Further, in order to ensure that the upper and lower wings can have a stable unfolding state, the first upper wing unit is detachably connected with the fuselage through a first clamping part (see a front lug 501 and a first rotating shaft 401 in fig. 3 and 4), and the first clamping part is located in front of the first hinge part; the second upper wing unit is detachably connected with the body through a second clamping portion, and the second clamping portion is located in front of the second hinged portion.
Similarly, the lower wing 3 comprises a first lower wing element and a second lower wing element, wherein: the first lower wing unit is hinged with the fuselage through a third hinge part; the second lower wing unit is hinged to the fuselage by a fourth hinge. The first lower wing unit is detachably connected with the fuselage through a third clamping part, and the third clamping part is positioned in front of the third hinging part; the second lower wing unit is detachably connected with the fuselage through a fourth clamping portion, and the fourth clamping portion is located in front of the fourth hinged portion.
Therefore, when the upper wing and the lower wing are in the unfolding state, each wing unit can be positioned through the first clamping part, the second clamping part, the third clamping part and the fourth clamping part respectively to keep stable unfolding; when the upper wing and the lower wing are folded, the clamping parts are respectively disassembled, and all the wing units rotate to the folding positions around the hinging parts.
In specific implementation, please refer to fig. 1 and 5, the rotor of the drone includes a front rotor and a rear rotor. And the two sides of the machine body are provided with a front rotor and a rear rotor.
Preferably, still include in this unmanned aerial vehicle: a first tilting steering engine 203 for adjusting the pulling direction of the front rotor wing; and/or a second tilt steering engine 602 for adjusting the pull-up direction of the rear rotor. Tilting of the front rotor and the rear rotor can effectively shorten the round trip time of the unmanned aerial vehicle and ensure the operation efficiency.
Specifically, as shown in fig. 1 to 5, a first strut and a second strut are also provided in the drone. Wherein: one end of the first support rod is provided with a front rotor, and the other end of the first support rod is hinged with the front side edge of the upper wing 4 through a horn folding mechanism 201; the rear rotor wing is arranged on the fuselage through a second support rod and is positioned behind the upper wing 4 and the lower wing 3.
Preferably, as shown in fig. 2, when the upper wing 4, the lower wing 3 and the first strut are all in a folded state: a front rotor and a rear rotor are arranged on both sides of a folding mechanism consisting of the fuselage, the upper wing 4 and the lower wing 3; the heights of the front rotor, the upper wing 4, the rear rotor and the lower wing 3 are sequentially reduced.
During the concrete implementation, please refer to fig. 1, this unmanned aerial vehicle's fuselage includes fuselage main frame 1 and intermediate fixing spare 5, and intermediate fixing spare 5 is: a medical kit for holding the pesticide, or be used for holding the seed case of seed, or be used for the camera mount pad. Preferably, the intermediate fixing member 5 is detachably coupled to the main body 1, so that the intermediate fixing member 5 having different load capacities can be replaced according to different needs.
The following description specifically describes an unmanned aerial vehicle for spraying pesticides as an example. Referring to fig. 1 to 5, the unmanned aerial vehicle mainly includes a main frame 1 of a metal framework type fuselage, a front rotor system 2, a lower wing 3, an upper wing 4, a medicine box 5, a rear rotor system 6, a vertical tail 7, a horizontal tail 8, a spray nozzle 9, a landing gear 10, a battery 11, and a radar 12.
Referring to fig. 1, an unfolding schematic view of the unmanned aerial vehicle is shown, the unfolded state of the unmanned aerial vehicle is a hovering operation state of the unmanned aerial vehicle, when wings of the unmanned aerial vehicle are unfolded, a front rotor system 2 and an upper wing 4 are in a vertical state, and a spraying system 9 and a rear rotor system 6 are in a downward vertical state. The shape of the upper surface of the medicine chest 5 is the same as that of the upper wing 4, so that the lift force of the unmanned aerial vehicle is effectively improved.
Referring to fig. 2 to 4, the medicine box 5 includes a front lug 501, a rear lug 502, and a rear projection 503. The upper wing 4 comprises a rotating shaft 401 and a rotating shaft 402, and the lower wing comprises a rotating shaft 301 and a rotating shaft 302. The upper wing 4 is connected with a front lug 501 and a rear lug 502 through a first rotating shaft 401 and a second rotating shaft 402; the lower wing 3 is connected with the fuselage main frame 1 through a third rotating shaft 301 and a fourth rotating shaft 302, and the rotating shaft 302 and the rotating shaft 402 are on the same rotating shaft. The upper wing and the lower wing are fixedly connected through a Z-shaped connecting piece 14, and the upper wing 4 is supported through a supporting piece 13;
when the wing is unfolded, the rotating shaft 401 and the rotating shaft 402 are respectively hinged with the front lug 501 and the rear lug 502, and the rotating shaft 301 and the rotating shaft 302 are respectively hinged with the fuselage;
when the wing is folded, the upper wing 4 and the lower wing 3 rotate backwards through the rotating shaft 402 and the rotating shaft 302 respectively, at this time, the rotating shaft 401 is separated from the front lug 501, the rotating shaft 301 is separated from the fuselage, and the inclined support 13 rotates backwards around the rotating shaft 302 under the driving of the upper wing 4. The upper back wing 4 is folded backwards for a certain position and limited by the medicine box bulge 503.
Referring to fig. 1-5, the front power system 2 includes a front rotor power system 202 and a tilting steering engine 203, the rear rotor system 6 includes a rear motor propeller 601 and a tilting steering engine 602, when flying in front, the front motor propeller 202 is driven by the tilting steering engine 203 to tilt forward by a certain angle, and at the same time, the rear motor propeller 601 is driven by the tilting steering engine 602 to tilt forward by a certain angle, so as to achieve the purpose of flying forward and operating quickly, and effectively shorten the round trip time.
Referring to fig. 4 and 5, the front rotor system includes a boom folding mechanism 201, a right front rotor power system 221, a left front rotor power system 222, a right front tilt steering engine 231, and a left front tilt steering engine 232
The embodiment of the utility model provides an unmanned aerial vehicle can be applicable to the pesticide and spray, the seed is sowed, and other fields such as photography by plane, electric power patrol and examine, environmental monitoring, forest fire prevention and disaster condition patrol and examine also can be used to certainly.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
In the present specification, the embodiments are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. An unmanned aerial vehicle, comprising a fuselage, a plurality of rotors, an upper wing (4) and a lower wing (3), wherein:
the upper wing (4) and the lower wing (3) are both foldable wings;
the upper wing (4) and the lower wing (3) are at least partially overlapped in the vertical direction when unfolded;
the rotor is arranged on the fuselage and/or the upper wing (4).
2. A drone according to claim 1, characterised in that the upper wing (4) comprises a first upper wing unit and a second upper wing unit, wherein:
the first upper wing unit is hinged with the fuselage through a first hinge part;
the second upper wing unit is hinged with the fuselage through a second hinge part;
the fuselage is provided with a protruding structure (503) for limiting the first upper wing unit and the second upper wing unit at the rotation end point.
3. The drone of claim 2, wherein the first upper wing unit is removably connected to the fuselage by a first snap-in portion located forward of the first hinge portion;
the second upper wing unit is detachably connected with the body through a second clamping portion, and the second clamping portion is located in front of the second hinge portion.
4. A drone according to claim 1, characterised in that the lower wing (3) comprises a first lower wing element and a second lower wing element, wherein:
the first lower wing unit is hinged to the fuselage by a third hinge;
the second lower wing unit is hinged to the fuselage by a fourth hinge.
5. The unmanned aerial vehicle of claim 4, wherein the first lower wing unit is detachably connected to the fuselage by a third joint, the third joint being located forward of the third hinge;
the second lower wing unit is detachably connected with the fuselage through a fourth clamping portion, and the fourth clamping portion is located in front of the fourth hinged portion.
6. The drone of claim 1, wherein the rotors include a leading rotor and a trailing rotor;
the both sides of fuselage all are provided with leading rotor with rearmounted rotor.
7. The drone of claim 6, further comprising:
a first tilting steering engine (203) for adjusting the pulling direction of the front rotor wing;
and/or a second tilting steering engine (602) for adjusting the pulling-up direction of the rear rotor wing.
8. A drone according to claim 6, characterized in that it further comprises:
one end of the first support rod is provided with the front rotor, and the other end of the first support rod is hinged with the front side edge of the upper wing (4);
the rear rotor wing is installed on the fuselage through the second supporting rod and located behind the upper wing (4) and the lower wing (3).
9. Unmanned aerial vehicle according to claim 8, characterized in that the upper wing (4), the lower wing (3) and the first strut are all in a folded state:
the front rotor and the rear rotor are arranged on two sides of a folding mechanism consisting of the fuselage, the upper wing (4) and the lower wing (3);
the height of the front rotor, the upper wing (4), the rear rotor and the lower wing (3) is reduced in sequence.
10. Unmanned aerial vehicle according to claim 1, wherein the fuselage comprises a fuselage main frame (1) and an intermediate fixing (5), the intermediate fixing (5) being: a medical kit for holding the pesticide, or be used for holding the seed case of seed, or be used for the camera mount pad.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222488732.2U CN218477647U (en) | 2022-09-20 | 2022-09-20 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222488732.2U CN218477647U (en) | 2022-09-20 | 2022-09-20 | Unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218477647U true CN218477647U (en) | 2023-02-14 |
Family
ID=85166961
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222488732.2U Active CN218477647U (en) | 2022-09-20 | 2022-09-20 | Unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218477647U (en) |
-
2022
- 2022-09-20 CN CN202222488732.2U patent/CN218477647U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP4101694A1 (en) | A uav take-off and landing platform | |
| US6224012B1 (en) | Roadable aircraft combined vehicle for practical use | |
| CN104743110B (en) | A kind of collapsible air-drop unmanned plane | |
| CN205499328U (en) | Unmanned aerial vehicle with linkage beta structure | |
| CN108832258A (en) | A kind of folding device of the motor-driven large-scale antenna front radar of vehicle-mounted height | |
| CN213057495U (en) | Portable four-rotor unmanned aerial vehicle | |
| CN211001843U (en) | Unmanned aerial vehicle | |
| CN218477647U (en) | Unmanned plane | |
| CN219008166U (en) | Unmanned aerial vehicle wheeled undercarriage and unmanned aerial vehicle | |
| CN216969996U (en) | Multi-rotor unmanned aerial vehicle | |
| CN210191813U (en) | Unmanned aerial vehicle of collapsible rotor | |
| CN207826537U (en) | A kind of dynamic rotor structure of new type foldable oil | |
| CN217374894U (en) | Folding fixed wing unmanned aerial vehicle | |
| CN110654535A (en) | Many rotors unmanned aerial vehicle collection system that horn can be folded automatically | |
| CN209719892U (en) | A kind of wing folding unmanned plane | |
| CN115771606A (en) | Collapsible wing of big aspect ratio unmanned aerial vehicle of formula of puting in | |
| CN211969736U (en) | Many rotor crafts's organism and many rotor crafts | |
| CN210284608U (en) | Dual-mode switching unmanned aerial vehicle | |
| CN209905038U (en) | Four folding rotor crafts | |
| CN109911196B (en) | Drag-reduction foldable flapping-wing micro air vehicle | |
| CN110775273A (en) | Unmanned aerial vehicle | |
| CN110001924A (en) | A kind of wing folding unmanned plane | |
| CN213862660U (en) | Unmanned aerial vehicle's collapsible rotor, unmanned aerial vehicle and collapsible rotor protection device | |
| CN208102332U (en) | A kind of novel double-layer multi-rotor unmanned aerial vehicle | |
| CN208498782U (en) | Connection and self-locking mechanism for unmanned plane foldable structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |