A coaxial multi-rotor unmanned aerial vehicle

Abstract

This utility model discloses a coaxial multi-rotor unmanned aerial vehicle (UAV), belonging to the field of UAVs. It includes an avionics module, a motor module, and a jamming module arranged vertically in sequence; it also includes two wing structures. The wing structures are respectively positioned between the motor module and the avionics module and the jamming module; and the motor module is a dual-head motor, with its two output ends respectively connected to the two wing structures to drive the wing structures to rotate. This coaxial multi-rotor UAV, through improvements to the connection structure between the wing structures and the motor module, and optimization of the overall aerodynamic layout, effectively improves flight speed and wind resistance, thereby enhancing the stability of the UAV during flight, making power transmission more direct and efficient, reducing the complexity of the transmission system, and lowering the risk of failure.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicles (UAVs), specifically relating to a coaxial multi-rotor UAV. Background Technology

[0002] With the continuous development of technology, drones have been widely used in various fields, including military and civilian sectors. In the military field, drones can be used for reconnaissance, surveillance, and jamming missions; in the civilian field, drones can be used for aerial photography, logistics delivery, and agricultural plant protection. However, existing drones still have some shortcomings in terms of structural design and functional implementation.

[0003] In terms of structure, traditional multi-rotor drones typically use a single motor to drive multiple rotors. This structure suffers from problems such as low power transmission efficiency and poor structural stability. Independent driving of multiple rotors requires complex transmission systems and control mechanisms, increasing the drone's weight and the risk of failure. Furthermore, existing wing structures are relatively simple in design, making them prone to deformation and damage during flight, affecting the drone's flight performance and safety.

[0004] In terms of functionality, existing jamming modules are not well-designed for some UAVs that need to perform jamming missions. Their antenna modules have poor performance and limited signal processing capabilities, making them unable to effectively jam target signals. Furthermore, the avionics systems of UAVs also suffer from low precision 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 UAV is needed to address the structural and functional shortcomings of existing UAVs and improve their flight performance, stability, and interference resistance. Utility Model Content

[0006] To address one or more of the aforementioned deficiencies or improvement needs in existing technologies, this utility model provides a coaxial multi-rotor unmanned aerial vehicle (UAV). Through improvements to the connection structure between the wing structure and the motor module, it significantly enhances the stability of the device during flight, making power transmission more direct and efficient, reducing the complexity of the transmission system, lowering the risk of failure, and resulting in smoother flight. Simultaneously, the helical antenna module employing a planar helical antenna structure provides better signal reception and transmission performance, enabling more effective detection of external signals.

[0007] To achieve the above objectives, this utility model provides a coaxial multi-rotor unmanned aerial vehicle (UAV), which includes an avionics module, a motor module, and an interference module arranged vertically in sequence.

[0008] It also includes two wing structures; the wing structures are respectively located between the motor module, the avionics module and the jamming module; and the motor module is a dual-head motor, whose two output ends are respectively connected to the two wing structures to drive the wing structures to rotate.

[0009] The wing structure includes two support units. The two support units are provided with protrusions and connecting parts spaced apart along the width direction on the side close to each other. The protrusion of one support unit is embedded in the connecting part of the other support unit to form a stable frame structure. The end of the connecting part away from the protrusion is provided with a support structure.

[0010] A through hole is provided in the center of the frame structure for the output shaft of the motor module to pass through. Transmission components are respectively provided at the positions where the two output ends of the motor module pass through the through hole. The two transmission components are respectively connected to the two bracket structures to realize the power transmission connection between the motor module and the wing structure.

[0011] Meanwhile, a clamping member is provided on the side of the two support units that are far apart from each other, and an wing unit is assembled in the clamping member.

[0012] As a further improvement of this utility model, the avionics module includes a support, and a first detection sensor and a second detection sensor are provided on the support for detecting parameters in the flight attitude of the UAV.

[0013] As a further improvement of this utility model, the support foot placed at the bottom of the support is connected to the wing structure.

[0014] As a further improvement of this utility model, the wing structure also includes a mounting base, which is assembled on the motor module;

[0015] The bracket structure is assembled on the mounting base.

[0016] As a further improvement of this utility model, the transmission component 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 respectively disposed on both sides of the connecting seat, with one end assembled on the connecting seat and the other end assembled on the bracket structure.

[0017] As a further improvement of this utility model, the interference module includes a housing and an assembly block mounted on the outer periphery of the housing, and a helical antenna module is provided on the assembly block.

[0018] As a further improvement of this utility model, a partition plate is provided inside the housing, which divides the internal space into a first accommodating space and a second accommodating space.

[0019] As a further improvement of this utility model, the spiral antenna module is a planar spiral antenna structure.

[0020] As a further improvement of this utility model, a signal processing module is also provided in the first accommodating space inside the housing. It is communicatively connected to the helical antenna module and is used to receive external signals detected by the planar helical antenna and send interference signals to the detected signals after processing.

[0021] As a further improvement of this utility model, a power supply module is also provided in the second accommodating space of the housing, which is electrically connected to the helical antenna module, the signal processing module, the motor module, and the avionics module.

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

[0023] In summary, the beneficial effects of the above-described technical solutions conceived by this utility model compared with the prior art include:

[0024] (1) The coaxial multi-rotor UAV of this utility model improves the flight speed and wind resistance by improving the connection structure between the wing structure and the motor module, and optimizing the aerodynamic layout of the whole machine. This improves the stability of the UAV during flight, makes the power transmission more direct and efficient, reduces the complexity of the transmission system, and reduces the risk of failure. At the same time, with the optimization of the UAV tilting disk, the control effect of the UAV's variable pitch distance is effectively improved, the manufacturing cost is effectively reduced, and the service life is improved.

[0025] (2) The coaxial multi-rotor UAV of this utility model forms a stable frame structure through the nested design of the protruding parts and connecting parts of the two support units of the wing structure. This structural design enhances the overall strength and rigidity of the wing, effectively resists the external forces during flight, reduces wing deformation and damage, and improves the flight safety of the UAV.

[0026] (3) The coaxial multi-rotor UAV of this utility model has a helical antenna module with a planar helical antenna structure in its jamming module, which has better signal reception and transmission performance. It can more effectively detect external signals and accurately transmit the signals to the signal processing module. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall three-dimensional structure of the coaxial multi-rotor UAV in this embodiment of the present invention;

[0028] Figure 2 This is a three-dimensional cross-sectional view of the interference module in the coaxial multi-rotor UAV in this embodiment of the present invention;

[0029] Figure 3 This is a three-dimensional cross-sectional schematic diagram of the overall structure of the interference module in the coaxial multi-rotor UAV in this embodiment of the present invention from another perspective.

[0030] Figure 4 yes Figure 1 Enlarged structural diagram at point a;

[0031] Figure 5 A three-dimensional structural diagram of the avionics module in the coaxial multirotor UAV in this embodiment of the present invention.

[0032] In all the accompanying drawings, the same reference numerals denote 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. Connecting part; 204. Clamping component; 205. Wing unit; 206. Mounting component; 207. Transmission component; 208. Mounting base;

[0035] 300. Interference module; 301. Housing; 302. First accommodating space; 303. Second accommodating space; 304. Separator; 305. Assembly block; 306. Helical antenna module;

[0036] 400. Motor module. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments.

[0038] It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the scope of the invention. Furthermore, 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 see Figures 1-5 The coaxial multi-rotor UAV in the preferred embodiment of this utility model significantly improves the stability of the device during flight by improving the connection structure between the wing structure and the motor module. This makes power transmission more direct and efficient, reduces the complexity of the transmission system, lowers the risk of failure, and makes the UAV more stable during flight. Simultaneously, the helical antenna module, employing a planar helical antenna structure, has better signal reception and transmission performance, enabling more effective detection of external signals.

[0040] Specifically, the coaxial multi-rotor UAV in the preferred embodiment of this utility model includes an avionics module 100, a motor module 400, and a jamming module 300 arranged vertically in sequence; it also includes two wing structures 200; the wing structures 200 are respectively positioned between the motor module 400 and the avionics module 100 and the jamming module 300; and the motor module 400 is a dual-head motor, with its two output ends respectively connected to the two wing structures 200 to drive the wing structures 200 to rotate; the wing structure 200 includes two support units, and the two support units are provided with protrusions 202 and connecting parts 203 spaced apart along the width direction on the side close to each other; one of the support units... The protrusion 202 of the unit is embedded in the connecting part 203 of another support unit to form a stable frame structure. The end of the connecting part 203 away from the protrusion 202 is provided with a support structure 201. A through hole is left in the center of the frame structure for the output shaft of the motor module 400 to pass through. Transmission members 207 are respectively provided at the positions where the two output ends of the motor module 400 pass through the through hole. The two transmission members 207 are respectively connected to the two support 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 provided on the side of the two support units that are far apart from each other, and the wing unit 205 is assembled in the clamping member 204.

[0041] It is worth noting that, such as Figure 1 and Figure 4 As shown, the top view projection of its 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. The center of the frame structure has a through hole through which the output shaft of the motor module 400 can pass, and the transmission connection between the output shaft of the motor module 400 and the wing is realized through the transmission component 207.

[0042] In actual use, the wing structure 200 also includes a mounting base 208, which is assembled onto the motor module 400; the support structure 201 is assembled onto the mounting base 208. The transmission component 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 respectively located on both sides of the connecting seat, with one end assembled onto the connecting seat and the other end assembled onto the support structure 201. It is worth noting that a notch is left at the position of the arc-shaped rods on the support structure 201, and a mounting component 206 is provided in the notch. The end of the arc-shaped rod is connected to the mounting component 206.

[0043] This improvement to the connection structure between the wing structure 200 and the motor module 400 significantly enhances the stability of the equipment during flight, makes power transmission more direct and efficient, reduces the complexity of the transmission system, lowers the risk of failure, and makes the UAV more stable during flight.

[0044] More specifically, in a preferred embodiment of the present invention, the avionics module 100 includes a support 101, on which a first detection sensor 102 and a second detection sensor 103 are disposed for detecting parameters in the flight attitude of the UAV. The avionics module 100 also includes a support leg 104 disposed at the bottom of the support 101, which is 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 UAV in real time, providing precise data support for the flight control system. This enables the UAV to adjust its flight attitude in a timely manner according to different flight environments and mission requirements, improving its flight flexibility and adaptability.

[0046] In practical use, 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 acceleration, and can sense the acceleration changes of the UAV in three axes, thereby obtaining the changes in the UAV's motion state. The gyroscope is used to measure the angular velocity of the object, monitor the rotational motion of the UAV in real time, determine the rate of change of the UAV's attitude angle, and help the control system quickly sense the UAV's turning, rolling, and pitching actions.

[0047] Furthermore, such as Figure 2 and Figure 3 As shown, the interference module 300 in the preferred embodiment of this utility model includes a housing 301 and an assembly block 305 mounted on the outer periphery of the housing 301, with a helical antenna module 306 disposed on the assembly block 305. A partition plate 304 is disposed within the housing 301, dividing the internal space into a first accommodating space 302 and a second accommodating space 303. A signal processing module is also disposed within the first accommodating space 302 of the housing 301, which is communicatively connected to the helical antenna module 306. This module receives external signals detected by the planar helical antenna and, after processing, sends interference signals back to the detected signals. A power supply module is also disposed within the second accommodating space 303 of the housing 301, which is electrically connected to the helical antenna module 306, the signal processing module, the motor module, and the avionics module.

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

[0049] (1) The coaxial multi-rotor UAV of this utility model improves the flight speed and wind resistance by improving the connection structure between the wing structure and the motor module, and optimizing the aerodynamic layout of the whole machine. This improves the stability of the UAV during flight, makes the power transmission more direct and efficient, reduces the complexity of the transmission system, and reduces the risk of failure. At the same time, with the optimization of the UAV tilting disk, the control effect of the UAV's variable pitch distance is effectively improved, the manufacturing cost is effectively reduced, and the service life is improved.

[0050] (2) The coaxial multi-rotor UAV of this utility model forms a stable frame structure through the nested design of the protruding parts and connecting parts of the two support units of the wing structure. This structural design enhances the overall strength and rigidity of the wing, effectively resists the external forces during flight, reduces wing deformation and damage, and improves the flight safety of the UAV.

[0051] (3) The coaxial multi-rotor UAV of this utility model has a helical antenna module with a planar helical antenna structure in its jamming module, which has better signal reception and transmission performance. It can more effectively detect external signals and accurately transmit the signals to the signal processing module.

[0052] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A coaxial multi-rotor unmanned aerial vehicle, characterized in that, It includes an avionics module (100), an electric motor module (400), and an interference module (300) arranged vertically in sequence. It also includes two wing structures (200); the wing structures (200) are respectively located between the motor module (400), the avionics module (100), and the jamming module (300); and the motor module (400) is a dual-head motor, whose two output ends are respectively connected to the two wing structures (200) to drive the wing structures (200) to rotate; The wing structure (200) includes two support units. The two support units are provided with protrusions (202) and connecting parts (203) spaced apart along the width direction on the side close to each other. The protrusion (202) of one support unit is embedded in the connecting part (203) of the other support unit to form a stable frame structure. The end of the connecting part (203) away from the protrusion (202) is provided with a support structure (201). A through hole is provided in the center of the frame structure for the output shaft of the motor module (400) to pass through. Transmission components (207) are respectively provided at the positions where the two output ends of the motor module (400) pass through the through hole. The two transmission components (207) are respectively connected to the two support structures (201) to realize the power transmission connection between the motor module (400) and the wing structure (200). Meanwhile, a clamping member (204) is provided on the side of the two support units that are far apart from each other, and an wing unit (205) is assembled in the clamping member (204).

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

3. The coaxial multi-rotor UAV according to claim 2, characterized in that, The avionics module (100) also includes a support leg (104) disposed at the bottom of the support (101), which is connected to the wing structure (200).

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

5. The coaxial multi-rotor UAV according to claim 1, characterized in that, The transmission component (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 respectively located on both sides of the connecting seat, with one end mounted on the connecting seat and the other end mounted on the bracket structure (201).

6. The coaxial multi-rotor UAV according to claim 1, characterized in that, The interference module (300) includes a housing (301) and an assembly block (305) mounted on the outer periphery of the housing (301), and a helical antenna module (306) is provided on the assembly block (305).

7. The coaxial multi-rotor UAV according to claim 6, characterized in that, The housing (301) is provided with a partition plate (304), which divides the space inside the housing (301) 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 spiral antenna module (306) is a planar spiral antenna structure.

9. The coaxial multi-rotor UAV according to claim 7, characterized in that, A signal processing module is also provided in the first accommodating space (302) within the housing (301). It is communicatively connected to the spiral antenna module (306) and is used to receive external signals detected by the spiral antenna module (306) 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 module is also provided in the second accommodating space (303) of the housing (301), which is electrically connected to the helical antenna module (306), the signal processing module, the motor module (400), and the avionics module (100).

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