Unmanned aerial vehicle with RTK positioning function

Abstract

The utility model discloses an unmanned aerial vehicle with an RTK positioning function. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, a spiral propeller transmission part, a supporting arm, an RTK spiral antenna and a buffering assembly. The support arms are mounted on the periphery of the unmanned aerial vehicle body; the propeller transmission parts are installed at the ends, away from the unmanned aerial vehicle body, of the supporting arms. The RTK helical antenna is installed on the side, away from the propeller transmission part, of the supporting arm. The buffering assembly is installed at the bottom of the unmanned aerial vehicle body and used for improving buffering and vibration during emergency landing. Wherein the buffer assembly comprises a first buffer part and a second buffer part; the first buffer part is mounted at the bottom of the unmanned aerial vehicle body and is used for primarily and indirectly buffering vibration; the second buffering part is installed on the first buffering part and is in direct contact with the forced landing ground for buffering, the unmanned aerial vehicle is reasonable in structure, when emergency forced landing occurs, the first buffering part and the second buffering part conduct multiple vibration reduction buffering on the unmanned aerial vehicle body, and economic losses and the damage degree are reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a unmanned aerial vehicle with RTK positioning. Background Art

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. Compared with manned aircraft, they have the advantages of small size, low cost, easy use, low requirements for combat environment, and strong battlefield survivability. In recent years, with the advancement of technology, the UAV industry has also developed rapidly, and it has gradually been applied to many fields such as aerial photography and mapping, police work, and firefighting and disaster relief.

[0003] When a drone malfunctions, it needs to make an emergency landing. The forced landing of a drone after an accident often causes large-scale damage, resulting in a large amount of economic losses. A solution is proposed below to the above problem. Utility Model Content

[0004] The utility model aims to provide a UAV with RTK positioning, which can minimize the damage degree and economic cost loss of the UAV body in case of emergency landing through a first buffer part and a second buffer part.

[0005] The above technical objectives of the utility model are achieved through the following technical solutions:

[0006] A drone with RTK positioning comprises a drone body, a propeller transmission part, a support arm, an RTK helical antenna and a buffer assembly; the support arm is mounted on the four sides of the drone body; the propeller transmission part is mounted on the end of each support arm away from the drone body; the RTK helical antenna is mounted on the side of the support arm away from the propeller transmission part; the buffer assembly is mounted on the bottom of the drone body to improve buffering and vibration during emergency landing; wherein the buffer assembly comprises a first buffer part and a second buffer part; the first buffer part is mounted on the bottom of the drone body to provide preliminary indirect buffering of vibration; the second buffer part is mounted on the first buffer part to provide direct contact and buffering with the ground for emergency landing.

[0007] By adopting the above technical solution, the UAV will inevitably encounter some special situations or failures during flight, which may cause the UAV to make an emergency landing. When making an emergency landing on the ground, the second buffer part on the UAV body will preferentially contact and collide with the ground. The second buffer part can play a good role in buffering and vibration reduction. At the same time, the first buffer part and the second buffer part are opened synchronously, and the first buffer part will push the second buffer part to contact the ground to reduce the degree of collision and wear between the ground and the UAV body. The double buffering and vibration reduction will effectively minimize the damage to the UAV body, and the first buffer part and the second buffer part will not affect the UAV body during normal flight. The propeller transmission part has a propeller and a drive motor. The drive motor is installed inside the UAV body and drives the propeller under the control of the drive motor.

[0008] Preferably, the first buffer part includes a chassis, an air pump, an airbag and a ventilation tube, the chassis is mounted on the bottom of the drone body, the air pump is mounted on the chassis, the output end of the air pump is connected to the ventilation tube, and the airbag is mounted on the chassis.

[0009] By adopting the above technical solution, the air inlet end of the ventilation pipe is connected to the air pump, and there are four air outlet ends of the ventilation pipe, which are respectively connected to each airbag on the base frame. After the air pump is turned on, the air pump inflates the air inlet end of the ventilation pipe and transports it to each airbag along four channels, so that the airbag changes from a deflated state to a bulged state.

[0010] Preferably, the chassis includes a frame and legs, the frame is mounted on the drone body, the legs are mounted around the frame, and channels are passed through the legs, and the airbags are arranged in the channels of the legs.

[0011] By adopting the above technical solution, the frame is used as a supporting part to position the ventilation tube, and the supporting legs are used as the storage area of ​​the deflated airbag.

[0012] Preferably, the second buffer portion comprises a spring and a buffer pad, two ends of the spring are respectively connected to the airbag and the buffer pad, and the buffer pad is snap-fitted with the channel on the leg.

[0013] By adopting the above technical solution, the spring and the buffer pad are pushed out into the supporting leg by the inflation of the airbag, the spring and the buffer pad are in direct contact with the ground, and the spring and the buffer pad perform repeated vibration rebound motion outside the supporting leg.

[0014] Preferably, a pressure relief hole is installed on the airbag, and a plug is installed on the pressure relief hole.

[0015] By adopting the above technical solution, when testing whether the air bag is airtight, the air pump is used to inflate the vent pipe into the air bag, changing the deflated state into an inflated state. After the test is completed, the plug is opened to manually deflate.

[0016] Preferably, the ventilation pipe is tied to the surrounding frame by cable ties.

[0017] By adopting the above technical solution, the ventilation pipe is tied to the frame to prevent the ventilation pipe from being messy or deviating and disturbing the normal flight of the UAV.

[0018] Preferably, the spring is arranged on the buffer pad in a triangular shape, and the cross-section of the spring is small at the top and large at the bottom.

[0019] By adopting the above technical solution, there are three springs, which are smaller at the top and larger at the bottom, so that they are convenient for vibration and buffering in the vertical direction when subjected to external force.

[0020] Beneficial effect: When the drone body is hit by a sudden external accident or failure, the first buffer first pushes the second buffer part to directly contact the ground, avoiding the destructive force of wear and tear caused by direct collision between the drone and the road surface. Combined with the first and second buffer parts in continuous vibration buffering, the damage to the drone body and the economic cost loss during emergency landing are minimized. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of an embodiment;

[0022] Figure 2 This is a schematic diagram of the structure of the embodiment for demonstrating observation from the back side;

[0023] Figure 3 For example, the Figure 2 A-direction enlarged view;

[0024] Figure 4 The embodiment is a schematic structural diagram of the first buffer portion and the second buffer portion for displaying another viewing angle.

[0025] Figure numerals: 1. UAV body; 2. propeller transmission part; 3. support arm; 4. RTK spiral antenna; 5. buffer assembly; 6. first buffer part; 7. second buffer part; 8. chassis; 9. air pump; 10. airbag; 11. ventilation pipe; 12. frame; 13. support leg; 14. spring; 15. buffer pad; 16. plug. Implementation

[0026] The technical solution of the utility model will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0027] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0028] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0030] This embodiment provides a drone with RTK positioning. Figures 1 to 4 As shown, it includes a drone body 1, a propeller transmission part, an arm 3, an RTK helical antenna 4 and a buffer component 5; the arm 3 is installed on the four sides of the drone body; the propeller transmission part 2 is installed on the end of each arm 3 away from the drone body 1; the RTK helical antenna 4 is installed on the side of the arm 3 away from the propeller transmission part 2; the buffer component 5 is installed at the bottom of the drone body 1, and is used to improve buffering and vibration during emergency landing; wherein, the buffer component 5 includes a first buffer part 6 and a second buffer part 7; the first buffer part 6 is installed on the bottom of the drone body 1, and is used for preliminary indirect buffering of vibration; the second buffer part 7 is installed on the first buffer part 6, and is in direct contact with the ground for emergency landing for buffering.

[0031] RTK (Real-time kinematic) carrier phase differential technology is a differential method for real-time processing of carrier phase observations of two measuring stations. The carrier phase collected by the base station is sent to the user receiver to calculate the coordinates. This is a new and commonly used satellite positioning measurement method. The previous static, fast static, and dynamic measurements all required post-calculation to obtain centimeter-level accuracy. RTK is a measurement method that can obtain centimeter-level positioning accuracy in real time in the field. It uses a carrier phase dynamic real-time differential method and is a major milestone in GPS applications. Its appearance has brought new measurement principles and methods to engineering layout, topographic mapping, and various control measurements, greatly improving work efficiency. The RTK helical antenna 4 is used as a bridge for signal transmission. The use of RTK positioning drones is more accurate when conducting surveys and positioning.

[0032] During the flight of the drone, it is inevitable that some special situations or failures will occur, which may cause the drone to make an emergency landing. When making an emergency landing on the ground, the second buffer part 7 on the drone body 1 will first contact and collide with the ground. The second buffer part 7 can play a good role in buffering and reducing vibration. At the same time, the first buffer part 6 and the second buffer part 7 are opened synchronously. The first buffer part 6 will push the second buffer part 7 to contact the ground, reducing the degree of collision and wear between the ground and the drone body 1. The double buffering and vibration reduction will effectively minimize the damage to the drone body 1, and the first buffer part 6 and the second buffer part 7 will not affect the drone body 1 during normal flight.

[0033] The first buffer part 6 includes a base frame 8, an air pump 9, an airbag 10 and a ventilation tube 11. The base frame 8 is installed on the bottom of the drone body 1, the air pump 9 is installed on the base frame 8, the output end of the air pump 9 is connected to the ventilation tube 11, and the airbag 10 is installed on the base frame 8.

[0034] The air inlet end of the ventilation pipe 11 is connected to the air pump 9. The ventilation pipe 11 has four air outlet ends, which are respectively connected to each air bag 10 on the base frame 8. After the air pump 9 is turned on, the air pump 9 inflates the air inlet end of the ventilation pipe 11 and transports it to each air bag 10 along four channels, so that the air bag 10 changes from a deflated state to a bulged state.

[0035] The chassis 8 includes a frame 12 and legs 13. The frame 12 is mounted on the drone body 1. The legs 13 are mounted around the frame 12. A channel is passed through the legs 13. The airbag 10 is arranged in the channel of the legs 13. The frame 12 serves as a support for the ventilating tube 11 to rely on and position, and the legs 13 are used as a storage area for the deflated airbag 10.

[0036] The second buffer part 7 includes a spring 14 and a buffer pad 15, the two ends of the spring 14 are connected to the airbag 10 and the buffer pad 15 respectively, and the buffer pad 15 is engaged with the channel on the leg 13. The spring 14 and the buffer pad 15 are pushed out into the leg 13 by the inflation of the airbag 10, and the spring 14 and the buffer pad 15 are in direct contact with the ground, and the spring 14 and the buffer pad 15 perform repeated vibration rebound motion outside the leg 13.

[0037] The airbag 10 is provided with a pressure relief hole, and the pressure relief hole is provided with a plug 16. When the air tightness of the airbag 10 is tested, the vent pipe 11 is inflated by the air pump 9 to reach the airbag 10, and the air is changed from a deflated state to a bulged state. After the test is completed, the plug 16 is opened for manual deflation.

[0038] The vent pipe 11 is tied to the surrounding frame 12 by cable ties. The vent pipe 11 is tied to the frame 12 to prevent the vent pipe 11 from being messy or eccentric and disturbing the normal flight of the drone.

[0039] The spring 14 is arranged on the buffer pad 15 in a triangular shape, and the cross section of the spring 14 is small at the top and large at the bottom. There are three springs 14, and the springs 14 are small at the top and large at the bottom, which is convenient for vibration and buffering in the vertical direction when subjected to external force.

[0040] When the drone body 1 is hit by a sudden external accident or failure, the first buffer first pushes the second buffer part 7 to directly contact the ground, avoiding the destructive force of wear caused by direct collision between the drone and the road surface. Combined with the first and second buffer parts 7, the continuous vibration buffering can minimize the damage to the drone body 1 and the economic cost loss during emergency landing, and protect the shooting lens from being broken and reduce the damage to the parts on the drone as much as possible.

[0041] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention of the utility model.

Claims

1. A drone with RTK positioning, characterized in that: It comprises a drone body (1), a propeller transmission part, a support arm (3), an RTK helical antenna (4) and a buffer component (5); The support arm (3) is installed on the four sides of the drone body; The propeller transmission part (2) is mounted on the end of each support arm (3) away from the drone body (1); The RTK helical antenna (4) is installed on a side of the support arm (3) away from the propeller transmission part (2); The buffer component (5) is installed at the bottom of the drone body (1) and is used to improve buffering and vibration during emergency landing; Wherein, the buffer assembly (5) comprises a first buffer portion (6) and a second buffer portion (7); The first buffer part (6) is installed on the bottom of the drone body (1) and is used for preliminary indirect vibration buffering; The second buffer part (7) is installed on the first buffer part (6) and directly contacts the ground where the vehicle is forced to land for buffering.

2. The UAV with RTK positioning according to claim 1, characterized in that: The first buffer part (6) comprises a base frame (8), an air pump (9), an air bag (10) and a ventilation pipe (11); the base frame (8) is mounted on the bottom of the drone body (1); the air pump (9) is mounted on the base frame (8); the output end of the air pump (9) is connected to the ventilation pipe (11); and the air bag (10) is mounted on the base frame (8).

3. The UAV with RTK positioning according to claim 2, characterized in that: The base frame (8) comprises a frame (12) and legs (13), wherein the frame (12) is mounted on the drone body (1), and the legs (13) are mounted on the four sides of the frame (12), and a channel runs through the legs (13), and the airbag (10) is arranged in the channel of the legs (13).

4. The UAV with RTK positioning according to claim 3, characterized in that: The second buffer portion (7) comprises a spring (14) and a buffer pad (15), the two ends of the spring (14) are respectively connected to the airbag (10) and the buffer pad (15), and the buffer pad (15) is snap-fitted with the channel on the supporting leg (13).

5. The UAV with RTK positioning according to claim 2, characterized in that: The air bag (10) is provided with a pressure relief hole, and a plug (16) is provided on the pressure relief hole.

6. The UAV with RTK positioning according to claim 3, characterized in that: The ventilation pipe (11) is tied to the surrounding frame (12) by means of cable ties.

7. The UAV with RTK positioning according to claim 4, characterized in that: The spring (14) is arranged on the buffer pad (15) in a triangular shape, and the cross section of the spring (14) is small at the top and large at the bottom.

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