Split type turning device for undercarriage of unmanned aerial vehicle

Abstract

The invention provides a split type turning device for an unmanned aerial vehicle undercarriage, and belongs to the technical field of unmanned aerial vehicle structural design, the split type turning device comprises a split type control panel, an upper shell and a lower shell, and the split type control panel and the upper shell are fixedly connected to form a transmission containing cavity; the protective cover is mounted on the upper shell and used for protecting the motor and / or the angular displacement sensor; 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 to the fourth gear shaft and the first gear shaft to the fourth gear shaft are sequentially meshed, the first gear shaft is meshed with a motor gear, one end of the fourth gear shaft is provided with an angular displacement sensor, the angular displacement sensor is connected to the split type control panel through an aviation plug, and the other end of the fourth gear shaft is connected with an undercarriage main structure; the motor is controlled to rotate through the split type control panel, then the undercarriage main structure is driven 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 split turning device for a UAV landing gear. Background Art

[0002] Turning devices are widely used in drone landing gear systems 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 as small as possible to better fit the drone's space and layout while reducing wind resistance.

[0003] The available space for drones is very small, and the existing turning device integrates motors, mechanical structures, split control panels, etc. to achieve the turning function. However, the turning device is large in size and high in mass. It is not only easy to interfere with the fuselage during the retraction and extension of the landing gear, but also easy to increase the power consumption of the drone due to its excessive mass and size.

[0004] Therefore, a compact, lightweight, fully functional, and lightweight turning device is needed to solve the above problems. Summary of the invention

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

[0006] The technical solution of the present application is: a split turning device for a UAV landing gear, comprising:

[0007] A split control panel, the remote end of which is integrated on the overall flight control panel of the UAV; an upper shell and a lower shell, wherein the upper shell and the lower shell are fixedly connected to form a transmission cavity;

[0008] A protective cover, which is mounted on the upper housing and is used to protect the motor and / or the angular displacement sensor;

[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] 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 split control board through an aviation plug. The other end of the fourth gear shaft is connected to the main structure of the landing gear. The rotation of the motor is controlled by the split control board, thereby driving 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.

[0011] In the present application, the split turning device actuator is separated from the split control panel, and the split control panel of the turning servo is partially integrated into the overall control box.

[0012] In an optional embodiment of the present application, the upper shell and the lower shell are detachably connected via a connecting piece.

[0013] In an optional embodiment of the present application, the protective cover is detachably mounted on the upper shell via a connecting piece.

[0014] 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.

[0015] 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.

[0016] 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.

[0017] The turning device provided by the present application separates the split control panel from the mechanical structure part, and is distributed as a separate part in the overall control box of the drone, which can not only realize the control and turning of the drone landing gear, but also facilitate the maintenance of the staff. The present application cleverly solves the shortcomings of the existing turning device in terms of volume and mass by adjusting the installation position of the split control panel of the turning device, and provides conditions for the drone to achieve high space utilization, reduce wind resistance, and have long endurance, high speed, and reliable flight, which promotes the future development of drones. The solution is simple, the implementation cost is low, and the effect is significant. 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 1This is a schematic diagram of the appearance of the turning device of this application.

[0020] Figure 2 This is an internal cross-sectional view of the turning device of the present application.

[0021] Reference numerals:

[0022] 11- Protective cover

[0023] 12-Upper shell

[0024] 13-Lower housing

[0025] 21-Motor

[0026] 22-Angular displacement sensor

[0027] 23-Aviation plug

[0028] 24-Motor gear

[0029] 31-First gear shaft

[0030] 32-Second gear shaft

[0031] 33-Third gear shaft

[0032] 34-Fourth gear shaft DETAILED DESCRIPTION

[0033] 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.

[0034] The present application proposes a split turning device for a UAV landing gear, which simply and conveniently solves the problems of difficulty in selecting a turning device for an existing UAV landing gear and the interference of the turning device with the fuselage during the retraction and extension process, thereby improving the space utilization rate of the UAV and the maintenance efficiency.

[0035] like Figure 1 and Figure 2 As shown, the split turning device 100 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.

[0036] The upper housing 12 and the lower housing 13 are detachably connected by connecting members such as screws or bolts, and a transmission cavity is formed between the two. The motor 11 and the angular displacement sensor 22 are arranged on the outside of the upper housing 12, which are protected by the protective cover 11, and the protective cover 11 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 provided 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.

[0037] The end of the motor 11 extends into the transmission cavity, and the motor gear 24 can be fixed to the end of the transmission shaft of the motor 11 by a pin shaft 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 (large gear) of the second gear shaft 32, the second gear (small gear) of the second gear shaft 32 meshes with the first gear (large gear) of the third gear shaft 33, 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 set at one end of the fourth gear shaft 34, and is connected to the split control panel through an aviation plug 23 (because the turning servo has universality, and its split control panel part has certain differences due to the different overall split control panel structures of the aircraft, so a separate schematic diagram is not listed here), and 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.

[0038] The motor 21 serves as a driving mechanism. It and the angular displacement sensor 22 receive the transmission signal from the split control board through the aviation plug 23, and transmit the motion to the large gear of the first gear shaft 31 through the motor gear 24, and 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, and at the same time feeds back the position signal to the split control board through the angular displacement sensor 22, so as to realize the landing gear turning function together.

[0039] 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.

[0040] 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.

[0041] The turning device provided by the present application separates the split control panel from the mechanical structure part, and is distributed as a separate part in the overall control box of the drone, which can not only realize the control and turning of the drone landing gear, but also facilitate the maintenance of the staff. The present application cleverly solves the shortcomings of the existing turning device in terms of volume and mass by adjusting the installation position of the split control panel of the turning device, and provides conditions for the drone to achieve high space utilization, low wind resistance, long endurance, high speed, and reliable flight, which promotes the future development of drones, has a simple solution, low implementation cost, and significant effect.

[0042] 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 split turning device for a drone landing gear, characterized in that: include: Split control panel, remotely integrated into the overall flight control panel of the drone; 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 housing and is used to protect the motor and / or the angular displacement sensor; 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 split control board through an aviation plug. The other end of the fourth gear shaft is connected to the main structure of the landing gear. The rotation of the motor is controlled by the split control board, thereby driving 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.

2. The split 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 split 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 split turning device for a drone landing gear according to 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 split turning device for the landing gear of a UAV 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 split 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.

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