CN210047615U - Longitudinal folding fixed wing assembled on vertical take-off and landing unmanned aerial vehicle - Google Patents
Longitudinal folding fixed wing assembled on vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN210047615U CN210047615U CN201920753430.9U CN201920753430U CN210047615U CN 210047615 U CN210047615 U CN 210047615U CN 201920753430 U CN201920753430 U CN 201920753430U CN 210047615 U CN210047615 U CN 210047615U
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- unmanned aerial
- aerial vehicle
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- fixed wing
- wing plates
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Abstract
A fixed wing which is longitudinally folded and assembled on a vertical take-off and landing unmanned aerial vehicle belongs to an aircraft; the fixed wing is formed by sequentially and transversely arranging and connecting 2-N strip wing plates, servo motors are fixedly arranged on the inner side parts of the 1 st to the N-1 st strip wing plates respectively, single-plate hinges are fixedly arranged on the inner side parts of the 2 nd to the N th strip wing plates respectively, a motor shaft of each servo motor is fixedly connected with the corresponding single-plate hinge, a double-plate combined hinge is fixedly arranged on the outer side part of the adjacent strip wing plate, and the double-plate combined hinge connects the adjacent strip wing plates into a whole through hinges which can rotate relatively; the fixed wing can meet and adapt to different flight mode requirements by changing the shape of the fixed wing under different flight modes, and has the characteristics of reasonable and simple structure, simplicity and convenience in operation and control, reliability in use, reduction of the lifting and descending resistance of the VTOL unmanned aerial vehicle, reduction of energy consumption and flexibility in flight maneuver.
Description
Technical Field
The invention belongs to the aircraft technology, and mainly relates to a fixed wing capable of being installed on a vertical take-off and landing unmanned aerial vehicle.
Background
With the development of science and technology, unmanned aerial vehicles are widely applied in various fields such as aerial photography, meteorological environment monitoring and agricultural production operation. At present, the existing fixed-wing vertical take-off and landing unmanned aerial vehicle is designed in a mode of combining multiple rotors and fixed wings, so that the unmanned aerial vehicle has the capabilities of vertical take-off and landing and hovering of a common helicopter and high-speed cruising flight of a turboprop. However, because the existing fixed wing adopts the structural design that the whole body is not foldable, the wide and non-foldable fixed wing can generate larger air resistance in the vertical take-off and landing and the horizontal flight of the vertical take-off and landing unmanned aerial vehicle and the flexible maneuvering flight, the take-off and landing capacity and the flying speed of the aircraft are reduced, and the energy consumption is increased.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and designs a longitudinal folding fixed wing assembled on a vertical take-off and landing unmanned aerial vehicle by combining the actual requirements of the vertical take-off and landing unmanned aerial vehicle in operation, so that the aims of reducing the lifting, descending and flat flying resistance of the vertical take-off and landing unmanned aerial vehicle, improving the flying flexibility and reducing the energy consumption are fulfilled.
The purpose of the invention is realized as follows: the fixed wing is formed by sequentially and transversely arranging and connecting 2-N strip wing plates, servo motors are fixedly installed on the inner side parts of the 1 st to N-1 st strip wing plates respectively, single plate hinges are fixedly installed on the inner side parts of the 2 nd to N th strip wing plates respectively, and motor shafts of the servo motors are fixedly connected with the corresponding single plate hinges; the outer sides of the adjacent strip-shaped wing plates are fixedly provided with double-plate combined hinges, and the double-plate combined hinges connect the adjacent strip-shaped wing plates into a whole by relative rotating hinges, so that the longitudinal folding fixed wing assembled on the vertical take-off and landing unmanned aerial vehicle is formed.
The invention has novel, reasonable and simple structural design, simple and convenient operation and control, reliable use, can greatly reduce the lifting, landing and flat flying resistance of the vertical take-off and landing unmanned aerial vehicle, reduces the flying energy consumption and improves the flexibility of the unmanned aerial vehicle.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a longitudinally-folded fixed wing mounted on a VTOL UAV;
FIG. 2 is a partial sectional view taken along line A-A of FIG. 1;
fig. 3 is a partial sectional view taken along line B-B in fig. 1.
Description of part numbers in the figures:
1. strip wing plate, 2, single-plate hinge, 3, servo motor, 4, double-plate combination hinge.
Detailed Description
The following detailed description of the inventive embodiments is provided in connection with the accompanying drawings. A longitudinal folding fixed wing assembled on a vertical take-off and landing unmanned aerial vehicle is formed by sequentially and transversely arranging and connecting 2-N strip wing plates 1, servo motors 3 are fixedly installed on the inner side parts of the 1 st to N-1 th strip wing plates 1 respectively, single plate hinges 2 are fixedly installed on the inner side parts of the 2 nd to N-th strip wing plates 1 respectively, and motor shafts of the servo motors 3 are fixedly connected with the corresponding single plate hinges 2; the outer side parts of the adjacent strip-shaped wing plates 1 are fixedly provided with double-plate combined hinges 4, and the double-plate combined hinges 4 can relatively rotatably connect the adjacent strip-shaped wing plates 1 into a whole.
①, when the fixed wing composed of 2-N strip wing plates 1 is completely unfolded, the vertical take-off and landing unmanned aerial vehicle obtains maximum buoyancy, the dead time is effectively prolonged, and the unmanned aerial vehicle is suitable for a cruise mode, ②, when the unmanned aerial vehicle is in a vertical take-off or landing state mode or a rapid maneuvering flight state mode, the servo motors 3 can be respectively controlled to rotate through a remote controller according to the mode requirements, the unmanned aerial vehicle passes through the single-plate hinges 2, and longitudinal folding between the adjacent strip wing plates 1 is completed under the matching of the double-plate combined hinges 4, so that the overall shape, the windward area and the overall dimension of the fixed wing are reduced, the air resistance is reduced, the good maneuvering performance of the aircraft is ensured, and the energy consumption is saved.
Claims (1)
1. The utility model provides a join in marriage dress and vertically fold fixed wing on VTOL unmanned aerial vehicle which characterized in that: the fixed wing is formed by sequentially and transversely arranging and connecting 2-N strip wing plates (1), servo motors (3) are fixedly arranged on the inner side parts of the 1 st to N-1 th strip wing plates (1), single plate hinges (2) are fixedly arranged on the inner side parts of the 2 nd to N-th strip wing plates (1), and motor shafts of the servo motors (3) are fixedly connected with the corresponding single plate hinges (2); the outer side parts of the adjacent strip-shaped wing plates (1) are fixedly provided with double-plate combined hinges (4), and the double-plate combined hinges (4) connect the adjacent strip-shaped wing plates (1) into a whole in a relatively rotatable hinge mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920753430.9U CN210047615U (en) | 2019-05-14 | 2019-05-14 | Longitudinal folding fixed wing assembled on vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920753430.9U CN210047615U (en) | 2019-05-14 | 2019-05-14 | Longitudinal folding fixed wing assembled on vertical take-off and landing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210047615U true CN210047615U (en) | 2020-02-11 |
Family
ID=69395932
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920753430.9U Expired - Fee Related CN210047615U (en) | 2019-05-14 | 2019-05-14 | Longitudinal folding fixed wing assembled on vertical take-off and landing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210047615U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104165A (en) * | 2019-05-14 | 2019-08-09 | 三亚学院 | It is fitted in longitudinal folding fixed wing in vertical take-off and landing drone |
-
2019
- 2019-05-14 CN CN201920753430.9U patent/CN210047615U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104165A (en) * | 2019-05-14 | 2019-08-09 | 三亚学院 | It is fitted in longitudinal folding fixed wing in vertical take-off and landing drone |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200211 Termination date: 20210514 |