Coaxial multi-rotor unmanned aerial vehicle

Abstract

The invention discloses a coaxial multi-rotor unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicles and comprises an avionic module, a motor module and an interference module which are sequentially arranged in the vertical direction, the unmanned aerial vehicle further comprises two wing structures. The wing structures are respectively arranged at positions between the motor module and the avionics module and between the motor module and the interference module; the motor module is a double-head motor, and the two output ends of the motor module are in transmission connection with the two wing structures correspondingly so as to drive the wing structures to rotate; according to the coaxial multi-rotor unmanned aerial vehicle disclosed by the invention, by improving a connecting structure between the wing structure and the motor module and optimizing and adjusting the aerodynamic layout of the whole vehicle, the flight speed and the wind resistance are effectively improved, so that the stability of the unmanned aerial vehicle in the flight process is improved, and the power transmission is more direct and efficient; and the complexity of a transmission system is reduced, and the fault risk is reduced.

Description

Technical Field

[0001] The present invention belongs to the field of unmanned aerial vehicles, and particularly relates to a coaxial multi-rotor unmanned aerial vehicle. Background Art

[0002] With the continuous development of technology, unmanned aerial vehicles have been widely used in many fields such as military and civilian. In the military field, unmanned aerial vehicles can be used for tasks such as reconnaissance, surveillance, and interference; in the civilian field, unmanned aerial vehicles can be used for aerial photography, logistics distribution, agricultural plant protection, etc. However, there are still some deficiencies in the structural design and function implementation of existing unmanned aerial vehicles.

[0003] In terms of structure, traditional multi-rotor unmanned aerial vehicles usually use a single-head motor to drive multiple rotors. This structure has problems such as low power transmission efficiency and poor structural stability. The independent drive of multiple rotors requires a complex transmission system and control mechanism, increasing the weight and failure risk of the unmanned aerial vehicle. At the same time, the existing wing structure design is relatively simple and is prone to deformation and damage during flight, affecting the flight performance and safety of the unmanned aerial vehicle.

[0004] In terms of function, for some unmanned aerial vehicles that need to perform interference tasks, the existing interference module design is not reasonable, the performance of the antenna module is poor, and the signal processing ability is limited, making it unable to effectively interfere with target signals. In addition, the avionics system of the unmanned aerial vehicle also has problems with low accuracy in flight attitude detection and control, making it difficult to meet the flight requirements in complex environments.

[0005] Therefore, a new type of coaxial multi-rotor unmanned aerial vehicle is needed to solve the deficiencies of existing unmanned aerial vehicles in structure and function, and improve the flight performance, stability, and interference ability of the unmanned aerial vehicle. Summary of the Invention

[0006] In view of one or more of the above-mentioned defects or improvement requirements of the prior art, the present invention provides a coaxial multi-rotor unmanned aerial vehicle. By improving the connection structure between the wing structure and the motor module, the stability of the device during flight is greatly improved, the power transmission is more direct and efficient, the complexity of the transmission system is reduced, the failure risk is lowered, and the unmanned aerial vehicle is more stable during flight. At the same time, a spiral antenna module with a planar spiral antenna structure is adopted, which has better signal receiving and transmitting performance and can detect external signals more effectively.

[0007] To achieve the above object, the present invention provides a coaxial multi-rotor unmanned aerial vehicle, which includes an avionics module, a motor module, and an interference module arranged in sequence vertically.

[0008] It also includes two wing structures; the wing structures are respectively arranged at positions between the motor module, the avionics module and the interference module; and the motor module is a double-headed motor, and its two output ends are respectively connected to the two wing structures to drive the wing structures to rotate;

[0009] The wing structure comprises two bracket units, and a protrusion and a connection portion are arranged at intervals along the width direction on one side of the two bracket units close to each other; the protrusion of one of the bracket units is embedded in the connection portion of the other bracket unit to form a stable frame structure;

[0010] A through hole is reserved in the center of the frame structure for the output shaft of the motor module to pass through, and transmission members are respectively arranged at the positions where the two output ends of the motor module pass through the through hole, and the two transmission members are respectively connected to the two support structures to realize the power transmission connection between the motor module and the wing structure;

[0011] At the same time, a clamping piece is arranged on the side of the two bracket units which are away from each other, and a wing unit is assembled in the clamping piece.

[0012] As a further improvement of the present invention, the avionics module includes a support, and a first detection sensor and a second detection sensor are arranged on the support for detecting parameters in the flight attitude of the drone.

[0013] As a further improvement of the present invention, the support foot disposed at the bottom of the support is connected to the wing structure.

[0014] As a further improvement of the present invention, the wing structure further includes a mounting seat, which is assembled on the motor module;

[0015] The support structure is assembled on the mounting seat.

[0016] As a further improvement of the present invention, the transmission member includes a connecting seat and two arc-shaped rods, the connecting seat is sleeved on the output shaft of the motor module, and the two arc-shaped rods are arranged on both sides of the connecting seat, one end of which is assembled on the connecting seat, and the other end is assembled on the support structure.

[0017] As a further improvement of the present invention, the interference module includes a shell and an assembly block assembled on the outer periphery of the shell, and a helical antenna module is arranged on the assembly block.

[0018] As a further improvement of the present invention, a partition plate is arranged in the shell, and the partition plate divides the internal space into a first accommodating space and a second accommodating space.

[0019] As a further improvement of the present invention, the spiral antenna module is a planar spiral antenna structure.

[0020] As a further improvement of the present invention, a signal processing module is further provided in the first accommodation space within the housing. The signal processing module is communicatively connected to the spiral antenna module and is configured to receive external signals detected by the planar spiral antenna and send interference signals to the detected signals after processing.

[0021] As a further improvement of the present invention, a power module is further provided in the second accommodation space of the housing. The power module is electrically connected to the spiral antenna module, the signal processing module, the motor module, and the avionics module.

[0022] The above-described improved technical features can be combined with each other as long as they do not conflict with each other.

[0023] Generally speaking, compared with the prior art, the beneficial effects of the technical solutions conceived by the present invention include:

[0024] (1) For the coaxial multi-rotor unmanned aerial vehicle of the present invention, through the improvement of the connection structure between the wing structure and the motor module, and the optimization and adjustment of the overall aerodynamic layout of the whole machine, the flight speed and wind resistance performance are effectively improved, thereby improving the stability of the unmanned aerial vehicle during flight, making the power transmission more direct and efficient, reducing the complexity of the transmission system, and reducing the risk of failure; at the same time, in cooperation with the optimization of the swashplate of the unmanned aerial vehicle, the control effect of the pitch change distance of the unmanned aerial vehicle is effectively improved, the manufacturing cost is effectively reduced, and the service life is increased.

[0025] (2) For the coaxial multi-rotor unmanned aerial vehicle of the present invention, through the nested design of the protruding parts and the connecting parts of the two bracket units of the wing structure, a stable frame structure is formed. This structural design enhances the overall strength and stiffness of the wing, can effectively resist external forces during flight, reduce the deformation and damage of the wing, and improve the flight safety of the unmanned aerial vehicle.

[0026] (3) For the coaxial multi-rotor unmanned aerial vehicle of the present invention, the interference module adopts a spiral antenna module with a planar spiral antenna structure, which has better signal receiving and transmitting performance. It can more effectively detect external signals and accurately transmit the signals to the signal processing module. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is an overall three-dimensional structure schematic diagram of the coaxial multi-rotor unmanned aerial vehicle in an embodiment of the present invention;

[0028] Figure 2 is a three-dimensional sectional structure schematic diagram of the interference module in the coaxial multi-rotor unmanned aerial vehicle in an embodiment of the present invention;

[0029] Figure 3 It is a schematic diagram of the overall structure of the three-dimensional cross-section of another perspective of the interference module in the coaxial multi-rotor UAV in the embodiment of the present invention;

[0030] Figure 4 is Figure 1 the enlarged structural schematic diagram at position a in

[0031] Figure 5 Schematic diagram of the three-dimensional structure of the avionics module in the coaxial multi-rotor UAV in the embodiment of the present invention

[0032] In all the drawings, the same reference numerals represent the same technical features, specifically:

[0033] 100, avionics module; 101, support; 102, first detection sensor; 103, second detection sensor; 104, support leg;

[0034] 200, wing structure; 201, support structure; 202, protrusion; 203, connection part; 204, clamping part; 205, wing unit; 206, mounting part; 207, transmission part; 208, mounting seat;

[0035] 300, interference module; 301, housing; 302, first accommodation space; 303, second accommodation space; 304, partition board; 305, assembly block; 306, planar spiral antenna module;

[0036] 400, motor module. Detailed implementation manners

[0037] In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the drawings and embodiments.

[0038] It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0039] Please refer to Figures 1 to 5 , the coaxial multi-rotor UAV in the preferred embodiment of the present invention, through the improvement of the connection structure between the wing structure and the motor module, greatly improves the stability of the device during flight, makes the power transmission more direct and efficient, reduces the complexity of the transmission system, reduces the risk of failure, makes the UAV more stable during flight, and at the same time adopts a planar spiral antenna module with a planar spiral antenna structure, which has better signal reception and transmission performance. It can detect external signals more effectively.

[0040] Specifically, the coaxial multi-rotor UAV in the preferred embodiment of the present invention includes an avionics module 100, a motor module 400 and an interference module 300 arranged in sequence along the vertical direction; it also includes two wing structures 200; the wing structures 200 are respectively arranged at positions between the motor module 400 and the avionics module 100 and the interference module 300; and the motor module 400 is a double-headed motor, and its two output ends are respectively connected to the two wing structures 200 for driving the wing structures 200 to rotate; the wing structure 200 includes two bracket units, and the two bracket units are close to each other. The side is provided with a protrusion 202 at intervals along the width direction. and a connecting portion 203; the protrusion 202 of one of the bracket units is embedded in the connecting portion 203 of the other bracket unit to form a stable frame structure; and a through hole is reserved in the center of the frame structure for the output shaft of the motor module 400 to pass through, and transmission members 207 are respectively arranged at the positions where the two output ends of the motor module 400 pass through the through hole, and the two transmission members 207 are respectively connected to the two bracket structures 201 to realize the power transmission connection between the motor module 400 and the wing structure 200; at the same time, a clamping member 204 is arranged on the side where the two bracket units are away from each other, and a wing unit 205 is assembled in the clamping member 204.

[0041] It is worth noting that Figure 1 and Figure 4 As shown in the figure, the top projection surface of the protrusion 202 adopts an L-shaped structure, the protruding part is inserted into the connecting part 203, and then assembled by screws to form a frame structure, and a through hole is reserved in the center of the frame structure for the output shaft of the motor module 400 to pass through, and the transmission connection between the output shaft of the motor module 400 and the wing is realized by the transmission member 207.

[0042] In actual use, the wing structure 200 also includes a mounting seat 208, which is mounted on the motor module 400; the support structure 201 is mounted on the mounting seat 208. The transmission member 207 includes a connecting seat and two arc-shaped rods. The connecting seat is sleeved on the output shaft of the motor module 400, and the two arc-shaped rods are arranged on both sides of the connecting seat, one end of which is mounted on the connecting seat, and the other end is mounted on the support structure 201. It is worth noting that a gap is left at the position of the support structure 201 corresponding to the arc-shaped rod, and a mounting member 206 is arranged in the gap, and the end of the arc-shaped rod is connected to the mounting member 206.

[0043] By improving the connection structure between the wing structure 200 and the motor module 400, the stability of the device during flight is greatly improved, the power transmission is made more direct and efficient, the complexity of the transmission system is reduced, the risk of failure is reduced, and the UAV is more stable during flight.

[0044] More specifically, the avionics module 100 in the preferred embodiment of the present invention includes a support 101, and a first detection sensor 102 and a second detection sensor 103 are arranged on the support 101 for detecting parameters in the flight attitude of the drone. The avionics module 100 further includes feet 104 arranged at the bottom of the support 101, which are connected to the wing structure 200.

[0045] The first detection sensor 102 and the second detection sensor 103 in the avionics module 100 can accurately detect the flight attitude parameters of the drone in real time, providing precise data support for the flight control system. This enables the drone to timely adjust its flight attitude according to different flight environments and mission requirements, improving the flexibility and adaptability of flight.

[0046] In the actual use process, the first detection sensor 102 and the second detection sensor 103 are an accelerometer and a gyroscope respectively. The accelerometer measures acceleration by detecting the force generated by the mass block under the action of acceleration, and can sense the acceleration changes of the drone in three axes, thereby obtaining the changes in the motion state of the drone. The gyroscope is used to measure the angular velocity of an object, real-time monitor the rotational motion of the drone, determine the change rate of the attitude angle of the drone, and help the control system quickly sense the actions such as turning, rolling and pitching of the drone.

[0047] Furthermore, as Figure 2 and Figure 3 shown, the interference module 300 in the preferred embodiment of the present invention includes a housing 301 and an assembly block 305 assembled on the outer periphery of the housing 301, and a planar spiral antenna module 306 is arranged on the assembly block 305. At the same time, a partition plate 304 is arranged in the housing 301, and the partition plate 304 divides the internal space into a first accommodation space 302 and a second accommodation space 303. A signal processing module is further arranged in the first accommodation space 302 in the housing 301, which is communicatively connected with the planar spiral antenna module 306, for receiving the external signals detected by the planar spiral antenna and sending interference signals to the detected signals after processing. A power module is further arranged in the second accommodation space 303 of the housing 301, which is electrically connected to the planar spiral antenna module 306, the signal processing module, the motor module and the avionics module.

[0048] Preferably, the planar spiral antenna module 306 is a planar spiral antenna structure.

[0049] (1) The coaxial multi-rotor drone of the present invention effectively improves the flight speed and wind resistance performance through the improvement of the connection structure between the wing structure and the motor module, as well as the optimization and adjustment of the overall aerodynamic layout of the drone. Thereby, the stability of the drone during flight is improved, the power transmission is made more direct and efficient, the complexity of the transmission system is reduced, and the failure risk is lowered. At the same time, in cooperation with the optimization of the swashplate of the drone, the control effect of the pitch change distance of the drone is effectively improved, the manufacturing cost is effectively reduced, and the service life is increased.

[0050] (2) The coaxial multi-rotor drone of the present invention forms a stable frame structure through the nested design of the protruding parts and the connecting parts of the two support units of the wing structure. This structural design enhances the overall strength and stiffness of the wing, can effectively resist external forces during flight, reduce the deformation and damage of the wing, and improve the flight safety of the drone.

[0051] (3) The coaxial multi-rotor drone of the present invention uses a spiral antenna module with a planar spiral antenna structure for the interference module, which has better signal receiving and transmitting performance. It can more effectively detect external signals and accurately transmit the signals to the signal processing module.

[0052] Those skilled in the art can easily understand that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A coaxial multi-rotor drone, characterized in that: It comprises an avionics module (100), a motor module (400) and an interference module (300) which are arranged in sequence along the vertical direction; It also includes two wing structures (200); the wing structures (200) are respectively arranged at positions between the motor module (400), the avionics module (100) and the interference module (300); and the motor module (400) is a double-headed motor, and its two output ends are respectively connected to the two wing structures (200) in a transmission manner to drive the wing structures (200) to rotate; The wing structure (200) comprises two bracket units, and a protrusion (202) and a connection part (203) are arranged at intervals along the width direction on one side of the two bracket units that are close to each other; the protrusion (202) of one of the bracket units is embedded in the connection part (203) of the other bracket unit to form a stable frame structure; A through hole is reserved in the center of the frame structure for the output shaft of the motor module (400) to pass through, and transmission members (207) are respectively arranged at the positions where the two output ends of the motor module (400) pass through the through hole, and the two transmission members (207) are respectively connected to the two support structures (201) to achieve power transmission connection between the motor module (400) and the wing structure (200); At the same time, a clamping member (204) is provided on one side of the two bracket units that are away from each other, and a wing unit (205) is installed in the clamping member (204).

2. The coaxial multi-rotor UAV according to claim 1, characterized in that: The avionics module (100) comprises a support (101), and a first detection sensor (102) and a second detection sensor (103) are arranged on the support (101) for detecting parameters in the flight attitude of the drone.

3. The coaxial multi-rotor UAV according to claim 1, characterized in that: The avionics module (100) further comprises a support foot (104) arranged at the bottom of the support (101), which is connected to the wing structure (200).

4. The coaxial multi-rotor drone according to any one of claims 1 to 3, characterized in that: The wing structure (200) further includes a mounting seat (208) which is mounted on the motor module (400); The support structure (201) is assembled on the mounting seat (208).

5. The coaxial multi-rotor UAV according to claim 1, characterized in that: The transmission member (207) comprises a connecting seat and two arc-shaped rods, wherein the connecting seat is sleeved on the output shaft of the motor module (400), and the two arc-shaped rods are arranged on both sides of the connecting seat, one end of which is assembled on the connecting seat and the other end is assembled on the support structure (201).

6. The coaxial multi-rotor UAV according to any one of claims 1 to 5, characterized in that: The interference module (300) comprises a housing (301) and an assembly block (305) assembled on the outer periphery of the housing (301), and a helical antenna module (306) is arranged on the assembly block (305).

7. The coaxial multi-rotor UAV according to claim 6, characterized in that: A partition plate (304) is arranged inside the shell (301), and the partition plate (304) divides the internal space into a first accommodating space (302) and a second accommodating space (303).

8. The coaxial multi-rotor UAV according to claim 6, characterized in that: The helical antenna module (306) is a planar helical antenna structure.

9. The coaxial multi-rotor UAV according to claim 6, characterized in that: A signal processing module is also provided in the first accommodation space (302) in the shell (301), which is communicatively connected to the helical antenna module (306) and is used to receive external signals detected by the planar helical antenna and send interference signals to the detected signals after processing.

10. The coaxial multi-rotor UAV according to claim 9, characterized in that: A power supply module is also provided in the second accommodation space (303) of the shell (301), and is electrically connected to the helical antenna module (306) and the signal processing module, as well as the motor module and the avionics module.

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