CN220682679U - Variable-pitch compound-wing unmanned aerial vehicle - Google Patents
Variable-pitch compound-wing unmanned aerial vehicle Download PDFInfo
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- CN220682679U CN220682679U CN202322084591.2U CN202322084591U CN220682679U CN 220682679 U CN220682679 U CN 220682679U CN 202322084591 U CN202322084591 U CN 202322084591U CN 220682679 U CN220682679 U CN 220682679U
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Abstract
The utility model relates to the technical field of compound wing unmanned aerial vehicles, and discloses a variable pitch compound wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, wherein a distance adjusting assembly is arranged on the front surface of the unmanned aerial vehicle body, the distance adjusting assembly comprises a wing fixedly arranged on the front surface of the unmanned aerial vehicle body, a U-shaped plate is fixedly arranged at the bottom of the wing, a sliding plate is connected with the inner bottom wall of the U-shaped plate in a sliding manner, a guide assembly is arranged at the bottom of the sliding plate, two rotating rods are rotatably connected with the inner bottom wall of the U-shaped plate, a transmission assembly is arranged on the outer sides of the two rotating rods, and mounting plates are fixedly arranged on the outer sides of the two rotating rods. This compound wing unmanned aerial vehicle of variable pitch can ensure unmanned aerial vehicle body hover and flight's stability in the vertical direction through setting up the roll adjustment subassembly, simultaneously, can also adjust the distance between two perpendicular power oar wings through the roll adjustment subassembly, makes things convenient for the stability of unmanned aerial vehicle body in the vertical direction in not co-altitude and different environment.
Description
Technical Field
The utility model relates to the technical field of compound wing unmanned aerial vehicles, in particular to a variable pitch compound wing unmanned aerial vehicle.
Background
The composite wing layout is a vertical take-off and landing aircraft solution combining the fixed wing layout and the multi-rotor wing layout, not only can the vertical take-off and landing, hovering, vertical climbing and descending and other flight functions be realized through a plurality of screw pull forces and aerodynamic drag forces like a multi-rotor wing aircraft, but also the gravity force can be overcome through aerodynamic lift forces like a fixed wing aircraft, and the power system overcomes the aerodynamic drag forces to realize high-speed cruising flight.
When the existing compound wing unmanned aerial vehicle is hovered or maneuvered, the propeller pitch of the compound wing unmanned aerial vehicle needs to be adjusted through a controller, the existing compound wing unmanned aerial vehicle is generally adjusted in a hydraulic mode, the reliability is poor during adjustment, and the synchronization efficiency during adjustment is low, so that the variable pitch compound wing unmanned aerial vehicle is provided to solve the problems.
Disclosure of Invention
(one) solving the technical problems
Aiming at the defects of the prior art, the utility model provides the variable-pitch compound wing unmanned aerial vehicle which has the advantages of being capable of stably adjusting the pitch and the like, and solves the problems that the existing variable-pitch compound wing unmanned aerial vehicle is poor in reliability during adjustment and low in synchronization efficiency during adjustment.
(II) technical scheme
In order to achieve the purpose of stably adjusting the pitch, the utility model provides the following technical scheme: the utility model provides a compound wing unmanned aerial vehicle of variable pitch, includes the unmanned aerial vehicle body, the front of unmanned aerial vehicle body is provided with the roll adjustment subassembly.
The pitch adjusting assembly comprises a wing fixedly arranged on the front face of the unmanned aerial vehicle body, a U-shaped plate is fixedly arranged at the bottom of the wing, a sliding plate is slidably connected to the inner bottom wall of the U-shaped plate, a guide assembly is arranged at the bottom of the sliding plate, two rotating rods are rotatably connected to the inner bottom wall of the U-shaped plate, transmission assemblies are arranged on the outer sides of the rotating rods, mounting plates are fixedly arranged on the outer sides of the rotating rods, vertical power paddles are fixedly arranged at the tops of the mounting plates, and a driving assembly is arranged inside the U-shaped plate.
Further, the drive assembly includes fixed mounting in the servo motor at U shaped plate back, servo motor's output shaft fixed mounting has one end to run through and extend to the inside threaded rod of U shaped plate, sliding plate threaded connection is in the outside of threaded rod.
Further, the right side fixed mounting of unmanned aerial vehicle body has horizontal power oar wing, the left side fixed mounting of unmanned aerial vehicle body has the fin.
Further, the guide assembly comprises two guide blocks fixedly mounted at the bottom of the sliding plate, and a guide groove in sliding connection with the guide blocks is formed in the inner bottom wall of the U-shaped plate.
Further, the tops of the two rotating rods are both rotationally connected with the bottom of the wing.
Further, the transmission assembly comprises transmission racks fixedly arranged on the left side and the right side of the sliding plate, and transmission gears meshed with the transmission racks are fixedly arranged on the outer sides of the two rotating rods.
Further, the front of threaded rod rotates with the preceding lateral wall of U shaped plate inner chamber to be connected.
Further, the distance adjusting assembly is provided with two groups, and the distance adjusting assemblies are respectively positioned on the front surface and the back surface of the unmanned aerial vehicle body and are uniformly distributed.
(III) beneficial effects
Compared with the prior art, the utility model provides a variable pitch compound wing unmanned aerial vehicle, which has the following beneficial effects:
this compound wing unmanned aerial vehicle of variable pitch can ensure the stability that unmanned aerial vehicle body hovered and fly in the vertical direction through setting up the roll adjustment subassembly, simultaneously, can also adjust the distance between two perpendicular power oar wings through the roll adjustment subassembly, makes things convenient for the stability of unmanned aerial vehicle body vertical direction in not co-altitude and different environment, has solved current compound wing unmanned aerial vehicle of variable pitch reliability when the adjustment poor, and synchronous efficiency lower problem during the adjustment.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is an enlarged view of A in FIG. 1, which is a structural view of the present utility model;
fig. 3 is a top view of a pitch assembly in accordance with the present utility model.
In the figure: 1. an unmanned aerial vehicle body; 2. a distance adjusting component; 201. a wing; 202. a U-shaped plate; 203. a sliding plate; 204. a guide assembly; 205. a rotating lever; 206. a transmission assembly; 207. a mounting plate; 208. vertical power paddles; 209. a drive assembly; 2091. a servo motor; 2092. a threaded rod; 3. horizontal power paddles; 4. and a tail wing.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Embodiment one: referring to fig. 1-3, a pitch-variable compound wing unmanned aerial vehicle in the present embodiment includes an unmanned aerial vehicle body 1, and a pitch adjusting assembly 2 is disposed on the front surface of the unmanned aerial vehicle body 1.
Wherein, unmanned aerial vehicle body 1's right side fixed mounting has horizontal power oar wing 3, can guarantee unmanned aerial vehicle body 1 stability when horizontal flight through horizontal power oar wing 3, and unmanned aerial vehicle body 1's left side fixed mounting has fin 4, can have the stability when further guaranteeing unmanned aerial vehicle body 1 and fly in the horizontal direction through fin 4.
Specifically, guarantee through pitch adjustment subassembly 2 that unmanned aerial vehicle body 1 can be at the vertical direction on the distraction, can adjust unmanned aerial vehicle body 1 pitch simultaneously, ensure unmanned aerial vehicle body 1 in the ascending stability of vertical direction.
Embodiment two: referring to fig. 1-3, on the basis of the first embodiment, the distance adjusting assembly 2 includes a wing 201 fixedly mounted on the front surface of the unmanned aerial vehicle body 1, a U-shaped plate 202 is fixedly mounted at the bottom of the wing 201, a sliding plate 203 is slidably connected to an inner bottom wall of the U-shaped plate 202, a guiding assembly 204 is provided at the bottom of the sliding plate 203, two rotating rods 205 are rotatably connected to the inner bottom wall of the U-shaped plate 202, a transmission assembly 206 is provided on the outer sides of the two rotating rods 205, mounting plates 207 are fixedly mounted on the outer sides of the two rotating rods 205, vertical power paddles 208 are fixedly mounted at the tops of the two mounting plates 207, and a driving assembly 209 is provided inside the U-shaped plate 202.
The driving assembly 209 includes a servo motor 2091 fixedly mounted on the back of the U-shaped plate 202, a threaded rod 2092 having one end penetrating and extending into the U-shaped plate 202 is fixedly mounted on an output shaft of the servo motor 2091, and the sliding plate 203 is in threaded connection with the outer side of the threaded rod 2092.
The front surface of the threaded rod 2092 is rotatably connected with the front side wall of the inner cavity of the U-shaped plate 202, so as to ensure the stability of the rotation of the threaded rod 2092, and when the servo motor 2091 is started, the output shaft of the servo motor 2091 drives the threaded rod 2092 to rotate.
In addition, the guide assembly 204 includes two guide blocks fixedly installed at the bottom of the sliding plate 203, a guide groove slidably connected with the guide block is formed in the inner bottom wall of the U-shaped plate 202, the sliding plate 203 can be guided through the guide block and the guide groove, and meanwhile, the sliding plate 203 is prevented from rotating, and because the sliding plate 203 is in threaded connection with the outer side of the threaded rod 2092, when the threaded rod 2092 rotates, the threaded rod 2092 can drive the sliding plate 203 to move forward under the action of a thread thrust.
It should be noted that, the transmission assembly 206 includes a transmission rack fixedly mounted on the left and right sides of the sliding plate 203, and transmission gears meshed with the transmission racks are fixedly mounted on the outer sides of the two rotation rods 205, when the sliding plate 203 moves forward, the sliding plate 203 drives the two transmission racks to move forward, the two transmission racks respectively drive the two transmission gears to rotate, and the two transmission gears respectively drive the two rotation rods 205 to rotate, so that the two rotation rods 205 can rotate through the transmission assembly 206.
Wherein the rotation amplitude of the two rotation levers 205 is kept identical and the rotation directions of the two rotation levers 205 are opposite.
In addition, the top of two dwang 205 all rotates with the bottom of wing 201 to be connected, ensures two dwang 205 pivoted stability, and when two dwang 205 rotated, two dwang 205 can drive two perpendicular power wing 208 respectively and rotate, and the rotation direction of two perpendicular power wing 208 is opposite, through the rotation of two perpendicular power wing 208, reaches the purpose of adjusting the distance between two perpendicular power wing 208.
It should be noted that, the distance adjusting assemblies 2 are two groups, and are respectively located on the front surface and the back surface of the unmanned aerial vehicle body 1 to be uniformly distributed, and the unmanned aerial vehicle body 1 can hover and fly in the vertical direction through the two groups of distance adjusting assemblies 2.
Specifically, the distance between the two vertical power paddles 208 can be adjusted by starting the servo motor 2091, so as to ensure the stability of the unmanned aerial vehicle body 1 in the vertical direction.
The working principle of the embodiment is as follows:
this compound wing unmanned aerial vehicle of variable pitch, when using, start servo motor 2091, servo motor 2091's output shaft can drive threaded rod 2092 and rotate, under the screw thread thrust effect, threaded rod 2092 can drive sliding plate 203 forward motion, sliding plate 203 can drive two drive rack forward motion, two drive rack can drive two drive gear respectively and rotate, two drive gear can drive two dwang 205 respectively and rotate, two dwang 205 can drive two perpendicular power wings 208 respectively and rotate the opposite direction of two perpendicular power wings 208, through the rotation of two perpendicular power wings 208, reach the purpose of adjusting the distance between two perpendicular power wings 208.
The electrical components appearing herein are all electrically connected with the master controller and the power supply, the master controller can be a conventional known device for controlling a computer and the like, and the prior art of power connection is not described in detail herein.
It should be noted that 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 phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The utility model provides a compound wing unmanned aerial vehicle of variable pitch, includes unmanned aerial vehicle body (1), its characterized in that: the front surface of the unmanned aerial vehicle body (1) is provided with a distance adjusting component (2);
the pitch adjusting assembly (2) comprises a wing (201) fixedly mounted on the front face of the unmanned aerial vehicle body (1), a U-shaped plate (202) is fixedly mounted at the bottom of the wing (201), a sliding plate (203) is slidably connected to the inner bottom wall of the U-shaped plate (202), a guide assembly (204) is arranged at the bottom of the sliding plate (203), two rotating rods (205) are rotatably connected to the inner bottom wall of the U-shaped plate (202), transmission assemblies (206) are arranged on the outer sides of the two rotating rods (205), mounting plates (207) are fixedly mounted on the outer sides of the two rotating rods (205), perpendicular power paddles (208) are fixedly mounted at the top of the two mounting plates (207), and a driving assembly (209) is arranged inside the U-shaped plate (202).
2. The pitch compound wing unmanned aerial vehicle of claim 1, wherein: the driving assembly (209) comprises a servo motor (2091) fixedly mounted on the back of the U-shaped plate (202), a threaded rod (2092) with one end penetrating through and extending to the inside of the U-shaped plate (202) is fixedly mounted on an output shaft of the servo motor (2091), and the sliding plate (203) is in threaded connection with the outer side of the threaded rod (2092).
3. The pitch compound wing unmanned aerial vehicle of claim 1, wherein: the unmanned aerial vehicle comprises an unmanned aerial vehicle body (1), wherein a horizontal power paddle wing (3) is fixedly installed on the right side of the unmanned aerial vehicle body (1), and a tail wing (4) is fixedly installed on the left side of the unmanned aerial vehicle body (1).
4. The pitch compound wing unmanned aerial vehicle of claim 1, wherein: the guide assembly (204) comprises two guide blocks fixedly mounted at the bottom of the sliding plate (203), and a guide groove which is in sliding connection with the guide blocks is formed in the inner bottom wall of the U-shaped plate (202).
5. The pitch compound wing unmanned aerial vehicle of claim 1, wherein: the tops of the two rotating rods (205) are rotatably connected with the bottom of the wing (201).
6. The pitch compound wing unmanned aerial vehicle of claim 1, wherein: the transmission assembly (206) comprises transmission racks fixedly arranged on the left side and the right side of the sliding plate (203), and transmission gears meshed with the transmission racks are fixedly arranged on the outer sides of the two rotating rods (205).
7. A pitch compound wing unmanned aerial vehicle as claimed in claim 2, wherein: the front surface of the threaded rod (2092) is rotationally connected with the front side wall of the inner cavity of the U-shaped plate (202).
8. The pitch compound wing unmanned aerial vehicle of claim 1, wherein: the distance adjusting assemblies (2) are two groups, and are respectively located on the front face and the back face of the unmanned aerial vehicle body (1) and are uniformly distributed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322084591.2U CN220682679U (en) | 2023-08-04 | 2023-08-04 | Variable-pitch compound-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322084591.2U CN220682679U (en) | 2023-08-04 | 2023-08-04 | Variable-pitch compound-wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220682679U true CN220682679U (en) | 2024-03-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322084591.2U Active CN220682679U (en) | 2023-08-04 | 2023-08-04 | Variable-pitch compound-wing unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN220682679U (en) |
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2023
- 2023-08-04 CN CN202322084591.2U patent/CN220682679U/en active Active
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