Propeller rectification structure and vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The application provides a propeller rectification structure and a vertical take-off and landing fixed-wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The propeller rectification structure comprises a cantilever, the two ends of the cantilever are respectively provided with motors, the output ends of the motors are provided with double-blade propellers, the two ends of the cantilever are respectively movably connected with rectification covers, a driving mechanism is arranged in the cantilever to drive the rectification covers to move up and down, the rectification covers movably cover the corresponding propellers, and an angle detection mechanism is arranged in the cantilever to detect the rotation angle of the propeller. The application has the following effects: the rectification cover is arranged at the upper end of the propeller, the driving mechanism drives the rectification cover to move away from the propeller during vertical take-off and landing, the angle detection mechanism is matched with the motor to align the double-blade propeller with the rectification cover during level flight and cruising, and then the driving mechanism drives the rectification cover to cover the propeller, so that the rectification of the propeller is realized, the level flight resistance is reduced, and the flight stability is improved.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a propeller rectification structure and a vertical take-off and landing fixed-wing UAV. Background Technology

[0002] Vertical takeoff and landing (VTOL) fixed-wing drones generally adopt a quadcopter + fixed-wing hybrid layout, where the quadcopter part is used for vertical takeoff and landing, and the fixed-wing part is used for cruise flight. This layout combines the advantages of multi-rotor drones, which allow for flexible takeoff and landing, and fixed-wing drones, which do not require runways, with the ability of fixed-wing drones to fly for extended periods of time.

[0003] For example, Chinese patent application number CN201920864921.0 discloses a vertical take-off and landing fixed-wing UAV. When this type of UAV is cruising, the quadcopter will generate a large drag, affecting the cruising speed and stability. Utility Model Content

[0004] To overcome the above deficiencies, this application provides a propeller rectification structure and a vertical take-off and landing fixed-wing UAV, which aims to improve the problems mentioned in the background art.

[0005] In a first aspect, embodiments of this application provide a propeller rectification structure, including a cantilever, with motors respectively disposed at both ends of the cantilever, and a double-bladed propeller disposed at the output end of the motors. A fairing is movably connected to both ends of the cantilever, and a driving mechanism is disposed inside the cantilever to drive the fairing to move up and down. The fairing is movably covered on the corresponding propeller, and an angle detection mechanism is disposed inside the cantilever for detecting the rotation angle of the propeller.

[0006] In one specific implementation, a mounting base is provided inside the cantilever, and the motor is mounted inside the mounting base.

[0007] In the above implementation process, the motor is embedded in the mounting base to reduce exposure and lower wind resistance.

[0008] In one specific implementation, the angle detection mechanism includes a reflective photoelectric sensor and a reflective sticker, the photoelectric sensor being installed inside the cantilever and the reflective sticker being attached to the rotor of the motor.

[0009] In the above implementation process, the reflective sticker rotates along with the motor, and the position of the reflective sticker corresponds to that of the propeller. When the light emitted by the photoelectric sensor returns through the reflective sticker, it indicates that the propeller is aligned with the fairing. At this time, the drive mechanism drives the fairing to fall onto the propeller. Specifically, when the aircraft transitions from takeoff and landing to cruise, the ESC sends a low-speed PWM signal to drive the brushless motor to rotate at a low speed, causing the propeller to rotate slowly. The photoelectric sensor begins to detect the angle of the motor. When the reflective sticker is below the photoelectric sensor, the motor stops rotating. At this time, the propeller is parallel to the cantilever, and the drive mechanism begins to drive the fairing to fall. In this embodiment, reflective stickers and light-absorbing stickers of the same mass are respectively attached to the centrally symmetrical positions on the rotor to maintain dynamic balance. The light-absorbing stickers do not reflect the light from the photoelectric sensor and are relatively inexpensive. In another embodiment, after attaching the reflective stickers, the rotor is re-balanced, which has a better effect but is more expensive.

[0010] In one specific implementation, a sliding rod is fixedly connected to the fairing, and a sliding groove adapted to the sliding rod is provided on the cantilever, with the sliding groove being inclined.

[0011] In the above implementation process, the slide bar is used to determine the movement trajectory of the fairing on the cantilever. When the slide bar moves along the slide groove, it manifests as the oblique extension and retraction of the fairing.

[0012] In one specific implementation, the fairing is U-shaped, and two slide rods are provided, both of which are fixedly connected to both sides of the opening of the fairing.

[0013] In the above implementation process, the U-shaped fairing is adapted to the cantilever, and the structural strength at the fairing opening is ensured by two sliding rods, which are also connected to the drive mechanism inside the cantilever.

[0014] In one specific implementation, the drive mechanism includes a double-headed electric telescopic rod, with the two ends of the electric telescopic rod respectively fixedly connected to the slide rod.

[0015] In the above process, the electric telescopic rod pushes the slide bar to move along the slide groove, thereby realizing the automatic extension and retraction of the fairing.

[0016] In one specific implementation, the drive mechanism includes a push rod and an adapter block. One end of the push rod is fixedly connected to the slide rod, and the other end of the push rod is fixedly connected to the telescopic end of the electric telescopic rod through the adapter block.

[0017] In the above implementation process, the electric telescopic rod itself is suspended in the air, and its telescopic ends are connected to the push rods at both ends of the cantilever through the adapter blocks. When the electric telescopic rod extends, the guide of the sliding rod by the inclined slide groove causes the fairing to leave the propeller, and the electric telescopic rod body moves upward to adapt to the extension action. Conversely, the fairing covers the propeller. The advantage of this setting is that one electric telescopic rod can drive the action of two fairings, and it is also convenient to set the electric telescopic rod in the slender cantilever.

[0018] Secondly, this application also provides a vertical take-off and landing fixed-wing unmanned aerial vehicle, including the aforementioned propeller rectification structure.

[0019] Compared with the prior art, the beneficial effects of this application are: a fairing is set on the upper end of the propeller. During vertical take-off and landing, the drive mechanism drives the fairing away from the propeller. During level flight cruise, the angle detection mechanism and the motor work together to align the two-bladed propeller with the fairing. Then the drive mechanism drives the fairing to cover the propeller, so as to rectify the propeller, reduce level flight drag, and improve flight stability. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the propeller rectification structure and vertical take-off and landing fixed-wing UAV structure provided in the embodiments of this application; Figure 2 A schematic cross-sectional view of the fairing in the propeller-free state provided in an embodiment of this application; Figure 3 A schematic cross-sectional view of the fairing covering the propeller, provided for an embodiment of this application; Figure 4 Provided for the implementation of this application Figure 1 A magnified view of the structure at point A in the middle; Figure 5 A schematic diagram illustrating the connection structure between the fairing and the drive mechanism provided in this embodiment of the application.

[0022] In the diagram: 10-Cantilever; 20-Motor; 30-Propeller; 40-Fairing; 41-Sliding rod; 50-Drive mechanism; 51-Electric telescopic rod; 52-Push rod; 53-Adapter block; 60-Angle detection mechanism; 61-Photoelectric sensor; 62-Reflective sticker. Detailed Implementation

[0023] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0024] Please see Figures 1-5 This application provides a propeller rectification structure, including a cantilever 10, with motors 20 at both ends of the cantilever 10. A two-bladed propeller 30 is mounted on the output end of each motor 20. A fairing 40 is movably connected to both ends of the cantilever 10. A drive mechanism 50 is located inside the cantilever 10 to drive the fairing 40 to move up and down. The fairing 40 movably covers the corresponding propeller 30. An angle detection mechanism 60 is located inside the cantilever 10 to detect the rotation angle of the propeller 30. Specifically, the fairing 40 is located on the upper end of the propeller 30. During vertical takeoff and landing, the drive mechanism 50 drives the fairing 40 away from the propeller 30. During level flight and cruise, the angle detection mechanism 60, in conjunction with the motors 20, aligns the two-bladed propeller 30 with the fairing 40, and then the drive mechanism 50 drives the fairing 40 to cover the propeller 30, thereby rectifying the propeller 30, reducing drag during level flight, and improving flight stability.

[0025] Please see Figures 1-5 The cantilever 10 has a mounting base inside, and the motor 20 is mounted inside the mounting base. The motor 20 is embedded in the mounting base to reduce exposure and lower wind resistance.

[0026] Please see Figures 1-5 The angle detection mechanism 60 includes a reflective photoelectric sensor 61 and a reflective sticker 62. The photoelectric sensor 61 is installed inside the cantilever 10, and the reflective sticker 62 is attached to the rotor of the motor 20. The reflective sticker 62 rotates along with the motor 20. The reflective sticker 62 corresponds to the position of the propeller 30. When the light emitted by the photoelectric sensor 61 returns through the reflective sticker 62, it indicates that the propeller 30 is aligned with the fairing 40. At this time, the drive mechanism 50 drives the fairing 40 to fall and cover the propeller. Specifically, when the aircraft transitions from takeoff and landing to cruise, the ESC sends a low-speed PWM signal to drive the brushless motor 20 to rotate at a low speed, causing the propeller 30 to rotate slowly. The photoelectric sensor 61 begins to detect the angle of the motor 20. When the reflective sticker 62 is below the photoelectric sensor 61, the motor 20 stops rotating. At this time, the propeller 30 is parallel to the cantilever 10, and the drive mechanism 50 begins to drive the fairing 40 to fall. In this embodiment, reflective stickers 62 and light-absorbing stickers of the same mass are respectively attached to the centrally symmetrical positions on the rotor to maintain dynamic balance. The light-absorbing stickers do not reflect the light of the photoelectric sensor 61 and are relatively inexpensive. In another embodiment, after attaching the reflective sticker 62, the rotor is re-balanced, which has a better effect but is more expensive.

[0027] Please see Figures 1-5A sliding rod 41 is fixedly connected to the fairing 40, and a sliding groove adapted to the sliding rod 41 is provided on the cantilever 10. The sliding groove is inclined. The sliding rod 41 is used to determine the movement trajectory of the fairing 40 on the cantilever 10. When the sliding rod 41 moves along the sliding groove, it manifests as the oblique extension and retraction of the fairing 40.

[0028] Please see Figures 1-5 The fairing 40 is U-shaped, and two slide rods 41 are provided. Both slide rods 41 are fixedly connected to both sides of the opening of the fairing 40. The U-shaped fairing 40 is adapted to the cantilever 10. The two slide rods 41 ensure the structural strength of the opening of the fairing 40, and are connected to the drive mechanism 50 inside the cantilever 10 through the slide rods 41.

[0029] Please see Figures 1-5 The drive mechanism 50 includes a double-headed electric telescopic rod 51, with each end of the electric telescopic rod 51 fixedly connected to a corresponding slide rod 41. The electric telescopic rod 51 pushes the slide rod 41 to move along the slide groove, thereby realizing the automatic extension and retraction of the fairing 40.

[0030] Please see Figures 1-5 The drive mechanism 50 includes a push rod 52 and an adapter block 53. One end of the push rod 52 is fixedly connected to the slide rod 41, and the other end of the push rod 52 is fixedly connected to the telescopic end of the electric telescopic rod 51 through the adapter block 53. The electric telescopic rod 51 itself is suspended in the air, and its telescopic ends are connected to the push rods 52 at both ends of the cantilever 10 through the adapter blocks 53. When the electric telescopic rod 51 extends, the guide of the slide rod 41 by the inclined slide groove causes the fairing 40 to move away from the propeller 30, and the electric telescopic rod 51 moves upward to adapt to the extension action. Conversely, the fairing 40 covers the propeller 30. The advantage of this arrangement is that one electric telescopic rod 51 can drive the action of two fairings 40, and it is also convenient to set the electric telescopic rod 51 inside the slender cantilever 10.

[0031] Please see Figures 1-5 This application also provides a vertical take-off and landing fixed-wing unmanned aerial vehicle, including the aforementioned propeller rectification structure.

[0032] The working principle of the propeller rectification structure is as follows: During takeoff, the four propellers 30 push the UAV to a designated height, and then the propeller at the tail end drives the UAV to fly horizontally. The four propellers 30 rotate at low speed, and the photoelectric sensor 61 starts to detect the angle of the motor 20. When the reflective sticker 62 is below the photoelectric sensor 61, the motor 20 stops rotating. At this time, the propeller 30 is parallel to the cantilever 10, the electric telescopic rod 51 retracts, and the slide rods 41 at both ends fall along the slide groove, so that the fairing 40 falls and covers the propeller 30, thereby rectifying the propeller 30.

[0033] In summary, a fairing 40 is installed on the upper end of the propeller 30. During vertical takeoff and landing, the drive mechanism 50 drives the fairing 40 away from the propeller 30. During level flight and cruise, the angle detection mechanism 60 works with the motor 20 to align the two-bladed propeller 30 with the fairing 40. Then, the drive mechanism 50 drives the fairing 40 to cover the propeller 30, thereby rectifying the propeller 30, reducing drag during level flight, and improving flight stability.

[0034] The motors, flight controllers, electronic speed controllers, photoelectric sensors, and other execution and detection equipment involved in this application are automatically controlled by a PLC. The patent specification fully discloses its control logic; those skilled in the art can implement the corresponding control program using ladder diagrams or structured text programming languages ​​based on the logical relationships. The related equipment is connected according to the IEC 61131-2 electrical standard, which is a common connection technology in the field of automation; therefore, redundant descriptions are not provided.

[0035] The above are merely embodiments of this application and are not intended to limit the scope of protection of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application. It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

Claims

1. A propeller rectification structure, characterized in that, The device includes a cantilever (10), with a motor (20) installed at each end of the cantilever (10). A double-bladed propeller (30) is installed at the output end of the motor (20). A fairing (40) is movably connected to each end of the cantilever (10). A drive mechanism (50) is installed inside the cantilever (10) to drive the fairing (40) to move up and down. The fairing (40) is movably covered on the corresponding propeller (30). An angle detection mechanism (60) is installed inside the cantilever (10) to detect the rotation angle of the propeller (30).

2. The propeller rectification structure according to claim 1, characterized in that, The cantilever (10) is provided with a mounting base, and the motor (20) is installed in the mounting base.

3. The propeller rectification structure according to claim 2, characterized in that, The angle detection mechanism (60) includes a reflective photoelectric sensor (61) and a reflective sticker (62). The photoelectric sensor (61) is installed inside the cantilever (10), and the reflective sticker (62) is attached to the rotor of the motor (20).

4. The propeller rectification structure according to claim 3, characterized in that, A slide rod (41) is fixedly connected to the fairing (40), and a slide groove adapted to the slide rod (41) is provided on the cantilever (10), with the slide groove being inclined.

5. The propeller rectification structure according to claim 4, characterized in that, The fairing (40) is U-shaped, and there are two slide rods (41). Both slide rods (41) are fixedly connected to both sides of the opening of the fairing (40).

6. The propeller rectification structure according to claim 5, characterized in that, The drive mechanism (50) includes a double-headed electric telescopic rod (51), with the two ends of the electric telescopic rod (51) respectively fixedly connected to the slide rod (41).

7. A propeller rectification structure according to claim 6, characterized in that, The drive mechanism (50) includes a push rod (52) and an adapter block (53). One end of the push rod (52) is fixedly connected to the slide rod (41), and the other end of the push rod (52) is fixedly connected to the telescopic end of the electric telescopic rod (51) through the adapter block (53).

8. A vertical takeoff and landing fixed-wing unmanned aerial vehicle, characterized in that, Includes the propeller rectification structure as described in any one of claims 1-7.

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