Low-wind-resistance turning device for undercarriage of unmanned aerial vehicle

Abstract

The invention provides a low-wind-resistance turning device for an undercarriage of an unmanned aerial vehicle, and belongs to the technical field of structural design of unmanned aerial vehicles, the turning device comprises an upper shell and a lower shell which are fixedly connected to form a transmission cavity; the protective cover is installed on the upper shell and used for protecting the motor and / or the angular displacement sensor, and the outlines of the protective cover and the windward side of the upper shell and the windward side of the lower shell are arranged to be circular; the motor is installed on the upper shell, the end of the motor extends into the transmission containing cavity, and a motor gear is fixed to the end of the motor; the first gear shaft, the second gear shaft, the third gear shaft and the fourth gear shaft are sequentially meshed, the first gear shaft is meshed with a motor gear, and an angular displacement sensor is installed at one end of the fourth gear shaft, connected to a control panel and connected with a flight controller through an aviation plug. The other end of the fourth gear shaft is connected with the undercarriage main structure, the motor is controlled to rotate through the control panel to drive the undercarriage main structure to move, and meanwhile the rotation angle of the undercarriage main structure is obtained through the angular displacement sensor.

Description

Technical Field

[0001] The present application belongs to the technical field of unmanned aerial vehicle (UAV) structural design, and in particular relates to a low wind resistance turning device for a UAV landing gear. Background Art

[0002] Turning devices are widely used in the landing gear system of drones to control the attitude and movement of drones. Turning devices should have the following characteristics: 1) have sufficient torque to control the movement of the drone's rudder or other mechanical parts; 2) have sufficient speed to quickly respond to the movement of the drone; 3) the weight should be as light as possible to reduce the burden on the drone; 4) the size should be suitable for the flight characteristics of the drone during flight and will not cause too much burden on the flight.

[0003] The existing turning device combines a motor, a mechanical mechanism, a control panel, etc. to achieve the turning function. However, the shape of the turning device is more of a square structure such as a cube. It is not only easy to interfere with the fuselage during the retraction of the landing gear, but also has high wind resistance when the UAV is flying at high speed, and its concealment and endurance performance are reduced.

[0004] Therefore, a small, lightweight, fully functional, and low wind resistance turning device is needed to improve the space utilization and flight efficiency of the UAV. Summary of the invention

[0005] The purpose of the present application is to provide a low wind resistance turning device for a UAV landing gear to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: a low wind resistance turning device for a drone landing gear, comprising:

[0007] An upper shell and a lower shell, wherein the upper shell and the lower shell are fixedly connected to form a transmission chamber;

[0008] A protective cover, which is mounted on the upper shell and is used to protect the motor and / or the angular displacement sensor, wherein the contours of the windward side of the protective cover, the upper shell and the lower shell are set to be circular;

[0009] A motor, wherein the motor is mounted on the upper housing and an end of the motor extends into the transmission cavity, and a motor gear is fixed to the end of the motor;

[0010] From the first gear shaft to the fourth gear shaft, the first gear shaft is meshed with the motor gear, the second gear shaft is meshed with the first gear shaft, the third gear shaft is meshed with the second gear shaft, and the fourth gear shaft is meshed with the third gear shaft. An angular displacement sensor is installed at one end of the fourth gear shaft, and the angular displacement sensor is connected to the internal control board of the turning servo, and the signal is transmitted to the flight control through the aviation plug. The other end of the fourth gear shaft is connected to the main structure of the landing gear, and the rotation of the motor is controlled by the control board to drive the main structure of the landing gear to move. At the same time, the rotation angle of the main structure of the landing gear is obtained by the angular displacement sensor to realize the turning control of the landing gear. Compared with other turning servo transmission structure distribution forms, the internal gear shaft distribution method is rearranged to reduce the space occupied.

[0011] In an optional embodiment of the present application, the upper shell and the lower shell are detachably connected via a connecting piece.

[0012] In an optional embodiment of the present application, the protective cover is detachably mounted on the upper shell via a connecting piece.

[0013] In an optional embodiment of the present application, a sealing structure is provided between the upper shell and the lower shell and / or between the upper shell and the protective cover.

[0014] In an optional implementation manner of the present application, the second gear shaft is coaxially arranged with the motor, the first gear shaft is coaxially arranged with the third gear shaft, and the fourth gear shaft is coaxially arranged with the angular displacement sensor.

[0015] In an optional embodiment of the present application, the first to fourth gear shafts are supported on the upper shell and / or the lower shell through bearings.

[0016] In an optional embodiment of the present application, the fourth gear shaft is connected to the landing gear main structure by a pin shaft connection.

[0017] This application rearranges the design of the contour distribution of the mechanical structure part and compactly arranges the gear shaft installation method within a certain space. This not only solves the problem of large windward surface and large wind resistance caused by the large square arrangement space occupancy of the existing turning device, but also provides conditions for reducing the weight of the UAV and achieving high-speed and reliable flight, which promotes the future development of UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0019] Figure 1 This is a schematic diagram of the appearance of the turning device of this application.

[0020] Figure 2This is a top view of the turning device of the present application.

[0021] Figure 3 This is a top view of the turning device of the present application (with the protective cover removed).

[0022] Figure 4 Based on Figure 2 AA section view.

[0023] Reference numerals:

[0024] 11- Protective cover

[0025] 12-Upper shell

[0026] 13-Lower housing

[0027] 21-Motor

[0028] 22-Angular displacement sensor

[0029] 23-Aviation plug

[0030] 24-Motor gear

[0031] 31-First gear shaft

[0032] 32-Second gear shaft

[0033] 33-Third gear shaft

[0034] 34-Fourth gear shaft

[0035] 40-Control Panel DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0037] The present application proposes a low wind resistance turning device for a UAV landing gear, which is used to solve the problem that the existing UAV landing gear turning device has high wind resistance and the fuselage is easy to interfere with the turning device during the retraction and extension process. It can improve the flight efficiency of the UAV and improve the flight reliability of the UAV.

[0038] like Figures 1 to 4 As shown, the low wind resistance turning device 100 for the landing gear of a UAV provided in the present application includes: a protective cover 11, an upper shell 12, a lower shell 13, a motor 21, an angular displacement sensor 22, an aviation plug 23, a motor gear 24 and a first gear shaft 31 to a fourth gear shaft 34 and a control board 40

[0039] The upper housing 12 and the lower housing 13 are detachably connected by means of screws or bolts, and a transmission cavity is formed between the two. The motor 11 and the angular displacement sensor 22 can be arranged outside the upper housing 12, and they are protected by the protective cover 11, which is fastened to the upper housing 12 by screws. In some embodiments of the present application, a sealing structure such as a sealing strip can be arranged between the upper housing 12 and the lower housing 13 and between the upper housing 12 and the protective cover 11 to prevent the external environment from affecting the inside of the device.

[0040] In addition, by rearranging the spatial layout of the gear shafts, the outer contours of the upper shell 12, the lower shell 13 and the protective cover 11 are set to be an outer circle on the windward side, which is used to effectively reduce the wind resistance during flight.

[0041] The end of the motor 11 extends into the transmission cavity, and the motor gear 24 can be fixed to the transmission shaft end of the motor 11 by a pin or a spline. The motor gear 24 meshes with the first gear (large gear) of the first gear shaft 31, the second gear (small gear) of the first gear shaft 31 meshes with the first gear of the second gear shaft 32 (large gear), the second gear (small gear) of the second gear shaft 32 meshes with the first gear of the third gear shaft 33 (large gear), and the second gear (small gear) of the third gear shaft 33 meshes with the fourth gear shaft 34. An angular displacement sensor 22 is arranged at one end of the fourth gear shaft 34, and is connected to the control board 40, and communicates with the flight control through the aviation plug 23. The other end of the fourth gear shaft 34 is connected to the main structure of the landing gear to control the turning of the landing gear. Among them, the lower end of the fourth gear shaft 34 is connected to the main structure of the landing gear by a pin connection, which can not only realize the lightweight of the mechanism, but also improve the reliability of the mechanism movement.

[0042] The motor 21 serves as a driving mechanism. It and the angular displacement sensor 22 receive the transmission signal from the control board, and transmit the motion to the large gear of the first gear shaft 31 through the motor gear 24. The small gear of the first gear shaft 31 rotates with the first gear shaft 31. The small gear of the first gear shaft 31 transmits the motion to the large gear of the second gear shaft 31, and the small gear of the second gear shaft 32 rotates with the second gear shaft. The small gear of the second gear shaft 32 transmits the motion to the large gear of the third gear shaft 33, and the small gear of the third gear shaft 33 rotates with the third gear shaft 33. The small gear of the third gear shaft 33 transmits the motion to the fourth gear shaft 34, and the fourth gear shaft 34 transmits the motion to the main structure of the landing gear. At the same time, the position signal is fed back to the control board through the angular displacement sensor 22, and the landing gear turning function is realized together.

[0043] The turning device of the present application realizes the transmission of the turning of the landing gear through the movement of multiple sets of gears, and the gear transmission has high precision, stable transmission and high efficiency.

[0044] In a preferred embodiment of the present application, the first gear shaft 31 and the third gear shaft 33 are coaxially arranged, the second gear shaft 32 is coaxially arranged with the motor 11, the fourth gear shaft 34 is arranged on the non-motor side of the first gear shaft 31 or the third gear shaft 33, and the fourth gear shaft 34 is coaxially arranged with the angular displacement sensor 22, and the first gear shaft 31 to the fourth gear shaft 34 are all installed in the transmission cavity through bearings.

[0045] The turning device provided in this application redesigns the contour distribution of the mechanical structure part, which solves the shortcomings of the existing turning device such as large wind resistance, large windward surface and low reliability, provides conditions for the UAV to achieve high-speed and reliable flight, and promotes the future development of UAVs.

[0046] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A low wind resistance turning device for a drone landing gear, characterized in that: include: An upper shell and a lower shell, wherein the upper shell and the lower shell are fixedly connected to form a transmission chamber; A protective cover, which is mounted on the upper shell and is used to protect the motor and / or the angular displacement sensor, wherein the contours of the windward side of the protective cover, the upper shell and the lower shell are set to be circular; A motor, wherein the motor is mounted on the upper housing and an end of the motor extends into the transmission cavity, and a motor gear is fixed to the end of the motor; The first gear shaft to the fourth gear shaft, the first gear shaft is meshed with the motor gear, the second gear shaft is meshed with the first gear shaft, the third gear shaft is meshed with the second gear shaft, and the fourth gear shaft is meshed with the third gear shaft. An angular displacement sensor is installed at one end of the fourth gear shaft, and the angular displacement sensor is connected to the internal control board of the servo, and transmits signals with the flight control through an aviation plug. The other end of the fourth gear shaft is connected to the main structure of the landing gear, and the rotation of the motor is controlled by the control board to drive the main structure of the landing gear to move. At the same time, the rotation angle of the main structure of the landing gear is obtained through the angular displacement sensor to realize the turning control of the landing gear.

2. The low wind resistance turning device for the landing gear of a UAV as claimed in claim 1, characterized in that: The upper shell and the lower shell are detachably connected via a connecting piece.

3. The low wind resistance turning device for the landing gear of a UAV as claimed in claim 1, characterized in that: The protective cover is detachably mounted on the upper shell through a connecting piece.

4. The low wind resistance turning device for a drone landing gear as claimed in claim 2 or 3, characterized in that: A sealing structure is provided between the upper shell and the lower shell and / or between the upper shell and the protective cover.

5. The low wind resistance turning device for a drone landing gear as claimed in claim 1, characterized in that: The second gear shaft is coaxially arranged with the motor, the first gear shaft is coaxially arranged with the third gear shaft, and the fourth gear shaft is coaxially arranged with the angular displacement sensor.

6. The low wind resistance turning device for the landing gear of a UAV as claimed in claim 5, characterized in that: The first to fourth gear shafts are supported on the upper housing and / or the lower housing via bearings.

7. The low wind resistance turning device for a drone landing gear as claimed in claim 1, characterized in that: The fourth gear shaft and the landing gear main structure are connected in a pin-shaft connection.

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