CN210338268U - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
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- CN210338268U CN210338268U CN201920957280.3U CN201920957280U CN210338268U CN 210338268 U CN210338268 U CN 210338268U CN 201920957280 U CN201920957280 U CN 201920957280U CN 210338268 U CN210338268 U CN 210338268U
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- aerial vehicle
- unmanned aerial
- motor
- rotor
- rotor assembly
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Abstract
The disclosed embodiment relates to an unmanned aerial vehicle, include: the aircraft comprises an aircraft body, wings, an empennage and a flight controller, wherein a first rotor wing assembly is arranged behind the empennage and comprises a motor, a blade connected with a rotating shaft of the motor and a tilting mechanism for driving the motor and the blade to tilt together; the blade of the first rotor assembly is initially positioned below the horizontal of the fuselage in a first position; the flight controller is connected with the motor and the tilting mechanism; wherein, flight controller for the paddle of control first rotor subassembly is rotatory at initial first position, for provide lift when unmanned aerial vehicle takes off, and control the paddle of first rotor subassembly and vert to the second position after taking off, for unmanned aerial vehicle provides at least partial power when taking off flatly. The blades in the first rotor assembly of the disclosed embodiment provide upward lift for the drone during the takeoff phase of the drone; the paddle of the first rotor subassembly provides forward thrust for unmanned aerial vehicle at the stage of the flat flight for unmanned aerial vehicle's horizontal flight speed.
Description
Technical Field
The embodiment of the disclosure relates to the technical field of aircrafts, in particular to an unmanned aerial vehicle.
Background
Current unmanned aerial vehicle is provided with the tail rotor usually, and the tail rotor setting is at the organism afterbody and in the top of afterbody, at the unmanned aerial vehicle vertical takeoff phase, and the tail rotor work produces ascending air current, provides ascending lift for unmanned aerial vehicle. When the unmanned aerial vehicle ascends to the required height and enters a level flight stage, the tail rotor stops working.
With regard to the above technical solutions, the inventors have found that at least some of the following technical problems exist: after unmanned aerial vehicle got into the flat stage of flying, the tail rotor stop work, the weight of tail rotor has increased a burden for the organism, has increased the air resistance that receives when unmanned aerial vehicle flies, influences unmanned aerial vehicle's dynamic behavior.
Accordingly, there is a need to ameliorate one or more of the problems with the related art solutions described above.
It is noted that this section is intended to provide a background or context to the embodiments of the disclosure that are recited in the claims. The description herein is not admitted to be prior art by inclusion in this section.
SUMMERY OF THE UTILITY MODEL
It is an object of embodiments of the present disclosure to provide a drone, thereby overcoming, at least to some extent, one or more problems resulting from limitations and disadvantages of the related art.
The disclosed embodiment provides an unmanned aerial vehicle, which comprises a body, wings, an empennage and a flight controller, wherein a first rotor wing assembly is arranged behind the empennage, and comprises a motor, a blade connected with a rotating shaft of the motor and a tilting mechanism for driving the motor and the blade to tilt together;
the first rotor assembly has a blade initial first position below the horizontal of the fuselage; the flight controller is connected with the motor and the tilting mechanism;
the flight controller is used for controlling the blades of the first rotor assembly to rotate at an initial first position so as to provide lift force for the unmanned aerial vehicle during takeoff, and controlling the blades of the first rotor assembly to tilt to a second position after takeoff so as to provide at least part of power for the unmanned aerial vehicle during flat flight.
In an embodiment of the present disclosure, the empennage is provided with a connecting rod, and the first rotor assembly is arranged on the connecting rod.
In one embodiment of the disclosure, the tilting mechanism is a steering engine tilting mechanism.
In an embodiment of the present disclosure, the tilting angle between the initial first position and the second position is 0-90 °.
In an embodiment of the present disclosure, the wings are symmetrically provided with second rotor assemblies, each of which includes a motor, a blade connected to a rotating shaft of the motor, and a tilting mechanism for driving the motor and the blade to tilt together;
the flight controller is connected with a motor and a tilting mechanism of the second rotor assembly, and an initial first position of a blade of the second rotor assembly is positioned above the horizontal direction of the aircraft body;
the flight controller is used for controlling the blades of the second rotor assembly to rotate at an initial first position so as to provide lift force for the unmanned aerial vehicle during takeoff, and controlling the blades of the second rotor assembly to tilt to a third position after takeoff so as to provide at least part of power for the unmanned aerial vehicle during flat flight.
In an embodiment of the present disclosure, the tilt angle between the initial first position and the third position of the blade of the second rotor assembly is 0-90 °.
In an embodiment of the present disclosure, the tilting mechanism of the second rotor assembly is a steering engine tilting mechanism.
In an embodiment of the present disclosure, the unmanned aerial vehicle is a vertical take-off and landing unmanned aerial vehicle.
In an embodiment of the present disclosure, the fuselage, the wings, and the empennage of the unmanned aerial vehicle are all made of metal materials.
In an embodiment of the present disclosure, the motor is a servo motor.
The technical scheme provided by the embodiment of the disclosure can have the following beneficial effects:
the utility model provides an unmanned aerial vehicle, the initial first position of paddle in the first rotor subassembly at its fin rear is located below the fuselage horizontal direction, this paddle takes off the rotatory ascending lift that provides for unmanned aerial vehicle in the stage at unmanned aerial vehicle, and the paddle of the first rotor subassembly in the stage of flying to the tie rotates the second position like fuselage horizontal position, provides forward thrust for unmanned aerial vehicle, has promoted the dynamic property when unmanned aerial vehicle flies to a certain extent.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
Fig. 1 shows a takeoff state diagram of a drone in an exemplary embodiment of the present disclosure;
fig. 2 shows a flat flight state diagram of a drone in an exemplary embodiment of the present disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of embodiments of the disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repetitive description will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities.
In this example embodiment, there is first provided an unmanned aerial vehicle. Referring to fig. 1, the unmanned aerial vehicle may include a fuselage 100, a wing 200, an empennage 300, and a flight controller, a first rotor assembly 400 is disposed behind the empennage 300, the first rotor assembly 400 includes a motor 401, a blade 402 connected to a rotating shaft of the motor, and a tilting mechanism 403 for tilting the motor and the blade together; the first rotor assembly blade 402 is initially in a first position below the horizontal plane of the fuselage; the flight controller is connected to the motor 401 and the tilting mechanism 403.
The flight controller is used for controlling the blades of the first rotor assembly to rotate at an initial first position so as to provide lift force for the unmanned aerial vehicle during takeoff, and controlling the blades of the first rotor assembly to tilt to a second position after takeoff so as to provide at least part of power for the unmanned aerial vehicle during flat flight.
Through above-mentioned unmanned aerial vehicle, the operation of tilting mechanism and motor is controlled to flight control ware, and the spatial position of tilting mechanism control motor and paddle, the rotation of motor drive paddle. When unmanned aerial vehicle is in the stage of taking off, the paddle in the first rotor subassembly is in with fuselage vertically position under the control of the mechanism that verts, and the motor drives the paddle rotatory, provides ascending lift for unmanned aerial vehicle. At the flat stage of flying, the mechanism that verts takes place to vert and drives the paddle of first rotor subassembly and rotate horizontal position, and the motor drives the paddle and rotates and provide at least partial power for unmanned aerial vehicle this moment, and propulsive force forward promptly has accelerated unmanned aerial vehicle's horizontal flying speed.
Next, each part of the above-described unmanned aerial vehicle in the present exemplary embodiment will be described in more detail with reference to fig. 1 to 2.
In one embodiment, the fuselage, wings and empennage of the unmanned aerial vehicle are made of metal materials, such as composite materials, and the like, so as to meet the requirements of the unmanned aerial vehicle on strength, rigidity and the like. In one embodiment, the tail wing part 300 is provided with a connecting rod 500, and the first rotor assembly is arranged on the connecting rod 500. First rotor subassembly passes through the connecting rod to be installed on the fin.
In one embodiment, the tilting mechanism is a steering engine tilting mechanism, and the motor is a servo motor. The steering wheel mechanism of verting drives first rotor subassembly and rotates in good time under flight controller's control, changes the position of paddle in the first rotor subassembly, provides corresponding power for unmanned aerial vehicle's flight. Servo motor rotates for the paddle and provides more accurate control, makes the paddle can provide more accurate power in unmanned aerial vehicle flight.
In one embodiment, the tilting angle between the initial first position and the second position is 0-90 °. According to the flight needs, utilize flight controller to adjust the angle of verting of mechanism of verting, and then control the paddle from initial primary importance with the angle of verting between the second position makes the paddle be in and does benefit to the ascending or flat favourable spatial position that flies of unmanned aerial vehicle, provides corresponding lift and thrust. When the tilting angle is 90 degrees, the second position is located in the horizontal direction of the machine body.
More specifically, in the first position, the rotation direction of the paddle is parallel to the horizontal direction of the fuselage; and when the second position is in the second position, the rotating direction of the paddle is vertical to the horizontal direction of the machine body.
In one embodiment, the wing 200 is symmetrically provided with a second rotor assembly 600, and the second rotor assembly 600 includes a motor, a blade connected to a rotating shaft of the motor, and a tilting mechanism for driving the motor and the blade to tilt together; flight controller with the motor and the tilting mechanism of second rotor subassembly are connected, the initial first position of paddle of second rotor subassembly is located on the fuselage horizontal direction.
The flight controller is used for controlling the blades of the second rotor assembly to rotate at an initial first position so as to provide lift force for the unmanned aerial vehicle during takeoff, and controlling the blades of the second rotor assembly to tilt to a third position after takeoff, wherein the third position is a position where the rotating direction of the blades of the second rotor assembly is vertical to the horizontal direction of the unmanned aerial vehicle so as to provide at least part of power for the unmanned aerial vehicle during flat flight.
In one embodiment, the tilt angle between the initial first position and the third position of the blades of the second rotor assembly is 0-90 °. According to the flight needs, utilize flight controller to adjust the angle of verting of mechanism of verting, and then control the paddle from initial primary importance with the angle of verting between the third position makes the paddle be in and does benefit to the ascending or flat favourable spatial position that flies of unmanned aerial vehicle, provides corresponding lift and thrust.
In an embodiment, unmanned aerial vehicle is VTOL unmanned aerial vehicle, and after VTOL unmanned aerial vehicle set up first rotor subassembly or the second rotor subassembly in the above-mentioned embodiment, flight controller control rotor subassembly's operation, the spatial position of the paddle that the adjustment corresponds, for unmanned aerial vehicle take-off stage's lift and the forward thrust of stage of flying flat, accelerate unmanned aerial vehicle's airspeed.
It is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," and the like in the foregoing description are used for indicating or indicating the orientation or positional relationship illustrated in the drawings, merely for the convenience of describing the disclosed embodiments and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and therefore should not be considered limiting of the disclosed embodiments.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the embodiments of the present disclosure, "a plurality" means two or more unless specifically limited otherwise.
In the embodiments of the present disclosure, unless otherwise specifically stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present disclosure can be understood by those of ordinary skill in the art as appropriate.
In the embodiments of the present disclosure, unless otherwise expressly specified or limited, the first feature "on" or "under" the second feature may comprise the first and second features being in direct contact, or may comprise the first and second features being in contact, not directly, but via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (10)
1. An unmanned aerial vehicle comprises a body, wings, an empennage and a flight controller, and is characterized in that a first rotor wing assembly is arranged behind the empennage, the first rotor wing assembly comprises a motor, a blade connected with a rotating shaft of the motor and a tilting mechanism for driving the motor and the blade to tilt together;
the first rotor assembly has a blade initial first position below the horizontal of the fuselage; the flight controller is connected with the motor and the tilting mechanism;
the flight controller is used for controlling the blades of the first rotor assembly to rotate at an initial first position so as to provide lift force for the unmanned aerial vehicle during takeoff, and controlling the blades of the first rotor assembly to tilt to a second position after takeoff so as to provide at least part of power for the unmanned aerial vehicle during flat flight.
2. The unmanned aerial vehicle of claim 1, wherein a connecting rod is disposed at the tail wing, and the first rotor assembly is disposed on the connecting rod.
3. The drone of claim 1, wherein the tilting mechanism is a steering engine tilting mechanism.
4. The drone of claim 1, wherein the tilt angle between the initial first position and the second position is 0-90 °.
5. The unmanned aerial vehicle of any one of claims 1-4, wherein the wings are symmetrically provided with second rotor assemblies, and the second rotor assemblies comprise motors, blades connected with rotating shafts of the motors, and tilting mechanisms for driving the motors and the blades to tilt together;
the flight controller is connected with a motor and a tilting mechanism of the second rotor assembly, and an initial first position of a blade of the second rotor assembly is positioned above the horizontal direction of the aircraft body;
the flight controller is used for controlling the blades of the second rotor assembly to rotate at an initial first position so as to provide lift force for the unmanned aerial vehicle during takeoff, and controlling the blades of the second rotor assembly to tilt to a third position after takeoff so as to provide at least part of power for the unmanned aerial vehicle during flat flight.
6. The drone of claim 5, wherein the tilt angle between the initial first position and the third position of the blades of the second rotor assembly is 0-90 °.
7. The drone of claim 5, wherein the tilt mechanism of the second rotor assembly is a steering engine tilt mechanism.
8. The drone of claim 5, wherein the drone is a vertical take-off and landing drone.
9. The unmanned aerial vehicle of claim 5, wherein the fuselage, wings and empennage of the unmanned aerial vehicle are made of metal materials.
10. The drone of claim 5, wherein the motor is a servo motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920957280.3U CN210338268U (en) | 2019-06-25 | 2019-06-25 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920957280.3U CN210338268U (en) | 2019-06-25 | 2019-06-25 | Unmanned plane |
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| Publication Number | Publication Date |
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| CN210338268U true CN210338268U (en) | 2020-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920957280.3U Expired - Fee Related CN210338268U (en) | 2019-06-25 | 2019-06-25 | Unmanned plane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329492A (en) * | 2019-06-25 | 2019-10-15 | 李海刚 | Unmanned plane |
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2019
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329492A (en) * | 2019-06-25 | 2019-10-15 | 李海刚 | Unmanned plane |
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| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200417 Termination date: 20210625 |
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| CF01 | Termination of patent right due to non-payment of annual fee |