CN114802704A - Wing folding structure for unmanned aerial vehicle - Google Patents
Wing folding structure for unmanned aerial vehicle Download PDFInfo
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- CN114802704A CN114802704A CN202210404607.0A CN202210404607A CN114802704A CN 114802704 A CN114802704 A CN 114802704A CN 202210404607 A CN202210404607 A CN 202210404607A CN 114802704 A CN114802704 A CN 114802704A
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- aerial vehicle
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- 230000007246 mechanism Effects 0.000 claims abstract description 20
- 238000005452 bending Methods 0.000 claims description 12
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses a wing folding structure for an unmanned aerial vehicle, which comprises: the unmanned aerial vehicle comprises a vehicle body and two wings symmetrically arranged on two sides of the vehicle body; every the one end of wing one side with the fuselage is articulated, and the other end is articulated with a many link mechanism, many link mechanism is articulated through a connecting axle and a straight-bar, be provided with an arc groove on the fuselage, the connecting axle can be followed the arc groove slides, the other end of straight-bar is provided with the driving piece, the driving piece with the straight-bar drive is connected, the direction of drive of driving piece is followed the length direction of fuselage sets up, the driving piece drive straight-bar linear motion, and then drive the homonymy the wing expandes or folds. The wing folding structure adopts a full connecting rod form to realize large-angle wing sweepback, and can be popularized to the unmanned aerial vehicle with a slightly large structure.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a wing folding structure for an unmanned aerial vehicle.
Background
The pilotless plane is called unmanned plane for short, and is one controlled by radio remote controller and self-contained program controller. Unmanned aerial vehicles have been widely used in military or civil fields, and the civil fields are rich in application scenes such as aerial photography, agriculture, express transportation, power routing inspection and the like. Nowadays, the Emotl concept of the big fire further expands the concept of the unmanned plane from the unmanned plane to the manned plane.
The flying mode of the unmanned aerial vehicle can be divided into a rotor wing and a fixed wing. Fixed wing aircraft, because of its aerodynamic performance advantages, have greater cruising speeds and cruising ranges than rotary wing aircraft, but the wings of drones are therefore designed to be slim for more excellent aerodynamic characteristics. The slender of the wing inevitably affects the transportation and parking of the machine body. In the future, the requirement of the unmanned aerial vehicle for the storage space of the unmanned aerial vehicle, such as going into a family of ordinary people like an automobile, needs to be solved necessarily, and therefore a reasonable folding mechanism capable of being used on the unmanned aerial vehicle needs to be designed.
Disclosure of Invention
To the above-mentioned problem that exists among the prior art, aim at providing a wing beta structure for unmanned aerial vehicle.
The specific technical scheme is as follows:
a wing beta structure for unmanned aerial vehicle mainly includes: the unmanned aerial vehicle comprises a vehicle body and two wings symmetrically arranged on two sides of the vehicle body;
every the one end of wing one side with the fuselage is articulated, and the other end is articulated with a many link mechanism, many link mechanism is articulated through a connecting axle and a straight-bar, be provided with an arc groove on the fuselage, the connecting axle can be followed the arc groove slides, the other end of straight-bar is provided with the driving piece, the driving piece with the straight-bar drive is connected, the direction of drive of driving piece is followed the length direction of fuselage sets up, the driving piece drive straight-bar linear motion, and then drive the homonymy the wing expandes or folds.
The wing folding structure for the unmanned aerial vehicle is characterized in that the multi-link mechanism comprises a first connecting rod, a second connecting rod and a bending rod, one end of the first connecting rod is hinged to the wing, the other end of the first connecting rod is hinged to the second connecting rod, the second connecting rod is hinged to the bending rod, and the bending rod is hinged to the straight rod through the connecting shaft.
The wing folding structure for the unmanned aerial vehicle is characterized in that a limiting rod is further arranged on the first connecting rod, one end of the limiting rod is hinged to the first connecting rod, and the other end of the limiting rod is hinged to a fixing block on the body.
In the wing folding structure for the unmanned aerial vehicle, the wing folding structure further has the characteristic that two lugs are arranged on the same side of the wing, namely a first lug and a second lug, the first lug is hinged with the fuselage, and the second lug is hinged with the multi-link mechanism.
In the wing-folding structure for the unmanned aerial vehicle, the fixing block is close to the second lug.
In foretell a wing beta structure for unmanned aerial vehicle, still have such characteristic, the driving piece is the actuator, the actuator is cylinder, pneumatic cylinder or electric putter.
In the wing folding structure for the unmanned aerial vehicle, the two straight rods on two sides share one driving piece or are respectively corresponding to one driving piece.
The positive effects of the technical scheme are as follows:
the wing folding structure for the unmanned aerial vehicle provided by the invention realizes large-angle wing sweepback by adopting a full connecting rod form, and can be popularized to the unmanned aerial vehicle with a slightly large structure.
Drawings
Fig. 1 is a schematic structural view of a first state of a wing folding structure for an unmanned aerial vehicle provided by the invention;
fig. 2 is a structural schematic diagram of a second state of the wing folding structure for the unmanned aerial vehicle provided by the invention.
In the drawings: 1. a body; 11. an arc groove; 2. an airfoil; 21. a first lug; 22. a second lug; 3. a multi-link mechanism; 31. a first link; 32. a second link; 33. a bending rod; 4. a connecting shaft; 5. a straight rod; 6. a drive member; 7. a limiting rod; 8. and fixing blocks.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below by way of embodiments with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The numbering of the components themselves, such as "first", "second", etc., is used herein only to distinguish between the objects depicted and not to have any sequential or technical meaning. The term "connected" and "coupled" when used in this application, unless otherwise indicated, includes both direct and indirect connections (couplings). In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
Referring to fig. 1 and 2, the present invention discloses a wing folding structure for an unmanned aerial vehicle, first, the unmanned aerial vehicle includes a vehicle body 1 and two wings 2 symmetrically disposed at two sides of the vehicle body 1. The fuselage 1 and wing 2 in fig. 1 and 2 are simplified.
One end of each wing 2 one side is articulated with fuselage 1, the other end is articulated with a many link mechanism 3, many link mechanism 3 is articulated with a straight-bar 5 through a connecting axle 4, be provided with an arc groove 11 on the fuselage 1, connecting axle 4 can slide along arc groove 11, the other end of straight-bar 5 is provided with driving piece 6, driving piece 6 and straight-bar 5 drive connection, the length direction along fuselage 1 of the drive direction of driving piece 6 sets up, 5 linear motion of driving piece 6 drive straight-bar, and then drive the wing 2 of homonymy and expand or fold.
Specifically, in the present embodiment, the wings 2 on both sides are symmetrically arranged in the same manner, and therefore, only the wing 2 on one side is described. The number of the wings 2, the multi-link mechanisms 3, the connecting shafts 4, the straight rods 5 and the driving pieces 6 is multiplied by 2, that is, the number of the wings 2, the multi-link mechanisms 3, the connecting shafts 4, the straight rods 5 and the driving pieces 6 is two, and the wings 2, the multi-link mechanisms 3, the connecting shafts 4, the straight rods 5 and the driving pieces 6 are symmetrically arranged on the fuselage 1.
Optionally, the multi-link mechanism 3 includes a first link 31, a second link 32 and a bending rod 33, the first link 31 has one end hinged to the wing 2 and the other end hinged to the second link 32, the second link 32 is hinged to the bending rod 33, and the bending rod 33 is hinged to the straight rod 5 through the connecting shaft 4. In particular, as shown in fig. 1 and 2, the bending direction of the bending bar 33 is away from the wing 2 of the respective side.
Further, still be provided with gag lever post 7 on the first connecting rod 31, gag lever post 7 one end is articulated with first connecting rod 31, and the other end is articulated with the fixed block 8 that sets up on fuselage 1.
Optionally, in this embodiment, two lugs are provided on the same side of the wing 2, namely a first lug 21 and a second lug 22, respectively, where the first lug 21 is hinged to the fuselage 1, and the second lug 22 is hinged to the multi-link mechanism 3. Optionally, the fixing block 8 is adjacent to the second lug 22.
Alternatively, the driving member 6 is an actuator, and the actuator is an air cylinder, a hydraulic cylinder or an electric push rod.
It should be noted that two straight rods 5 on two sides may share one driving member 6 or each driving member 6 corresponds to each other, and thus the number of the driving members 6 may be one or two.
Optionally, in this embodiment, the arc groove 11 uses a hinge point where the wing 2 is hinged to the fuselage 1 as a center of a circle, and the length of the arc groove 11 may control an opening or folding angle of the wing 2, for example, in this embodiment, each arc groove 11 is symmetrically disposed along a straight line where the hinge point on two sides is located, and the angle of the arc groove 11 is 90 degrees, and the angle of the wing 2 that is unfolded may be controlled from 0 to 90 degrees, and meanwhile, each link of the multi-link mechanism 3 and an angle between links are controlled.
The wing 2 is in a deployed condition, as shown in figure 1, with the actuators 6 in a retracted condition, and the wing 2 is in a collapsed condition, as shown in figure 2, with the actuators 6 in an extended condition.
The wing folding structure for the unmanned aerial vehicle provided by the invention adopts a full connecting rod form to realize large-angle wing sweepback, and can be popularized to the unmanned aerial vehicle with a slightly large structure.
The unfolding and folding functions of the wings on the two sides can be realized only by using one driving piece 6, so that unnecessary waste is saved.
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above examples only show some embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent should be subject to the appended claims.
Claims (7)
1. A wing beta structure for unmanned aerial vehicle, comprising: the unmanned aerial vehicle comprises a vehicle body and two wings symmetrically arranged on two sides of the vehicle body;
every the one end of wing one side with the fuselage is articulated, and the other end is articulated with a many link mechanism, many link mechanism is articulated through a connecting axle and a straight-bar, be provided with an arc groove on the fuselage, the connecting axle can be followed the arc groove slides, the other end of straight-bar is provided with the driving piece, the driving piece with the straight-bar drive is connected, the direction of drive of driving piece is followed the length direction of fuselage sets up, the driving piece drive straight-bar linear motion, and then drive the homonymy the wing expandes or folds.
2. The wing folding structure for unmanned aerial vehicle of claim 1, wherein the multi-link mechanism comprises a first link, a second link and a bending rod, the first link is hinged to the wing at one end, the second link is hinged to the second link at the other end, the second link is hinged to the bending rod, and the bending rod is hinged to the straight rod through the connecting shaft.
3. The wing folding structure for unmanned aerial vehicle of claim 2, wherein the first connecting rod is further provided with a limiting rod, one end of the limiting rod is hinged to the first connecting rod, and the other end of the limiting rod is hinged to a fixing block arranged on the fuselage.
4. A wing-fold-away structure for unmanned aerial vehicles according to claim 3, wherein two lugs are provided on the same side of the wing, respectively a first lug and a second lug, the first lug being hinged to the fuselage and the second lug being hinged to the multi-link mechanism.
5. The wing-fold structure for a drone of claim 4, wherein the fixing block is proximate to the second lug.
6. A wing-fold-structure for unmanned aerial vehicle as claimed in any one of claims 1 to 5, wherein the driving member is an actuator, and the actuator is a cylinder, a hydraulic cylinder or an electric push rod.
7. The wing-folding structure for unmanned aerial vehicles of claim 1, wherein two straight rods on two sides share one driving piece or each corresponds to one driving piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210404607.0A CN114802704A (en) | 2022-04-18 | 2022-04-18 | Wing folding structure for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210404607.0A CN114802704A (en) | 2022-04-18 | 2022-04-18 | Wing folding structure for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114802704A true CN114802704A (en) | 2022-07-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210404607.0A Pending CN114802704A (en) | 2022-04-18 | 2022-04-18 | Wing folding structure for unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN114802704A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2826464C1 (en) * | 2023-11-23 | 2024-09-11 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Method for mounting and fastening deployable wing of unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101028866A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with wing sweepback angle change |
| KR20110062088A (en) * | 2009-12-02 | 2011-06-10 | 국방과학연구소 | Deploying device of folding wing and aircraft having the same |
| CN103661919A (en) * | 2013-12-23 | 2014-03-26 | 北京理工大学 | Wing folding mechanism based on flex-wing aircraft |
| US20200148337A1 (en) * | 2017-07-01 | 2020-05-14 | Autel Robotics Co., Ltd. | Undercarriage and unmanned aerial vehicle (uav) having undercarriage |
| CN215399303U (en) * | 2021-04-02 | 2022-01-04 | 泉州中国兵器装备集团特种机器人研发中心 | Foldable unmanned aerial vehicle wing assembly capable of being unfolded and folded |
-
2022
- 2022-04-18 CN CN202210404607.0A patent/CN114802704A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101028866A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with wing sweepback angle change |
| KR20110062088A (en) * | 2009-12-02 | 2011-06-10 | 국방과학연구소 | Deploying device of folding wing and aircraft having the same |
| CN103661919A (en) * | 2013-12-23 | 2014-03-26 | 北京理工大学 | Wing folding mechanism based on flex-wing aircraft |
| US20200148337A1 (en) * | 2017-07-01 | 2020-05-14 | Autel Robotics Co., Ltd. | Undercarriage and unmanned aerial vehicle (uav) having undercarriage |
| CN215399303U (en) * | 2021-04-02 | 2022-01-04 | 泉州中国兵器装备集团特种机器人研发中心 | Foldable unmanned aerial vehicle wing assembly capable of being unfolded and folded |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2826464C1 (en) * | 2023-11-23 | 2024-09-11 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Method for mounting and fastening deployable wing of unmanned aerial vehicle |
| RU2826532C1 (en) * | 2023-12-25 | 2024-09-11 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Unmanned aerial vehicle folding wing modular system |
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