An unmanned aerial vehicle antenna support

Abstract

The utility model relates to the field of antenna support discloses an unmanned aerial vehicle antenna support including low shelter bionical support structure, low shelter bionical support structure includes support frame, the inner wall fixedly connected with support rod of support frame, the inner wall fixedly connected with mounting rod of support frame, the bottom outer wall rotationally connected with gyroscope structure of mounting rod, the gyroscope structure includes first ring, the inner wall rotationally connected with second ring of first ring, the inner wall rotationally connected with third ring of second ring, the inner wall rotationally connected with signal receiver of third ring through pivot. In the utility model, through setting up low shelter bionical support structure, reduce the support to the signal shelter, and reduce the weight of self, through setting up gyroscope structure, realize antenna real -time attitude compensation, make signal receiver always steady point to target, solve the problem that the antenna is easy to disconnect with ground because of fuselage attitude change.

Description

Technical Field

[0001] This utility model relates to the field of antenna brackets, and in particular to an antenna bracket for unmanned aerial vehicles (UAVs). Background Technology

[0002] The drone antenna bracket is a core supporting component of the drone signal transmission system. It is mainly used to fix various communication, image transmission and telemetry antennas to ensure stable signal transmission and reception during flight. Its applications cover various types of drones, including consumer and industrial drones.

[0003] When using existing drone antenna brackets, first select the corresponding interface according to the antenna type, and then use bolts, clips or adapter connectors to firmly install the antenna on the preset mounting surface of the bracket. After installation, it is assembled and debugged with the drone body to ensure that the antenna radiation direction is in line with the flight operation requirements, and to provide stable support for the transmission of signals such as image transmission, measurement and control and communication between the drone and the ground terminal.

[0004] Existing drone antenna brackets, as key support components for signal transmission, require matching the fuselage interface and antenna type for daily assembly. On the one hand, their structures are often complex or heavy, relying on multiple sets of bolts and reinforcements to ensure stability, and are mostly made of solid metal, which significantly increases the load on the drone fuselage, leading to a significant increase in power system energy consumption and a marked reduction in endurance. On the other hand, tilting, turning, and turbulence during drone flight can cause the antenna to deviate from the ground receiving end, making it easy to disconnect from the ground. Therefore, a drone antenna bracket is proposed to solve the above problems. Utility Model Content

[0005] To overcome the above shortcomings, this utility model provides a drone antenna bracket, which aims to improve the problems in the prior art where the complex and heavy structure of the drone antenna bracket leads to increased energy consumption, reduced battery life, and easy disconnection of the antenna from the ground receiver due to changes in the aircraft's attitude.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a drone antenna bracket, comprising a low-obstruction bionic support structure, the low-obstruction bionic support structure comprising a support frame, a support rod fixedly connected to the inner wall of the support frame, an mounting rod fixedly connected to the inner wall of the support frame, a gyroscope structure rotatably connected to the bottom outer wall of the mounting rod, the gyroscope structure comprising a first ring, a second ring rotatably connected to the inner wall of the first ring, a third ring rotatably connected to the inner wall of the second ring, a signal receiver rotatably connected to the inner wall of the third ring via a rotating shaft, and the gyroscope structure rotatably connected to the outer walls of the support rod and the mounting rod via a rotating shaft.

[0007] As a further description of the above technical solution:

[0008] The support frame is equipped with an air duct and an air-breaking head. The outer wall of the mounting rod is fixedly connected with a wing plate.

[0009] As a further description of the above technical solution:

[0010] The mounting rod is fixedly connected to the support frame, and the two sets of wing plates are arranged in a mirror symmetrical manner according to the central axis of the mounting rod.

[0011] As a further description of the above technical solution:

[0012] The support rod is a triangular truss structure, with one end connected to the support frame and the other end connected to the mounting rod.

[0013] As a further description of the above technical solution:

[0014] The first ring, the second ring, and the third ring are nested ring structures, and each ring can rotate relative to the other.

[0015] As a further description of the above technical solution:

[0016] The signal receiver is fixed at the center of the third ring.

[0017] As a further description of the above technical solution:

[0018] The airfoil is a streamlined airfoil structure with a rounded leading edge and a relatively thin trailing edge.

[0019] As a further description of the above technical solution:

[0020] The air duct is arranged along the extension direction of the support frame, and the air breaker head has a streamlined structure.

[0021] This utility model has the following beneficial effects:

[0022] 1. In this utility model, by setting a low-obstruction bionic support structure, the obstruction of the support to the signal is reduced, and the weight of the support is also reduced. By setting a gyroscope structure, real-time attitude compensation of the antenna is achieved, so that the signal receiver always points stably to the target, thus solving the problem that the antenna is easy to disconnect from the ground due to changes in the attitude of the aircraft.

[0023] 2. In this utility model, by setting up air ducts extending along the support frame and streamlined air-breaking heads, airflow is guided to reduce wind resistance, reduce the power consumption of the UAV, and improve energy efficiency. By setting up streamlined wing plates, the support frame is stabilized, and the aerodynamic performance is further optimized, thus solving the problem of increased energy consumption caused by the heavy structure of the existing support frame. Attached Figure Description

[0024] Figure 1This is a front side view of the overall structure of a drone antenna bracket proposed in this utility model;

[0025] Figure 2 This is a left-side view of the overall structure of a drone antenna bracket proposed in this utility model;

[0026] Figure 3 This is a front view schematic diagram of the overall structure of a drone antenna bracket proposed in this utility model;

[0027] Figure 4 This is a schematic diagram of the gyroscope structure of a drone antenna bracket proposed in this utility model;

[0028] Figure 5 This is a schematic diagram of the wing plate structure of a drone antenna support proposed in this utility model.

[0029] Legend:

[0030] 1. Support frame; 2. Air duct; 3. Air breaker head; 4. Mounting rod; 5. Support rod; 6. Wing plate; 7. First ring; 8. Second ring; 9. Third ring; 10. Signal receiver; 11. Low-obstruction bionic support structure; 12. Gyroscope structure. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0032] Reference Figures 2-4This utility model provides an embodiment of a drone antenna bracket, including a low-obstruction bionic support structure 11, which serves as the core load-bearing and optimization unit of the bracket. By integrating a lightweight structure and bionic design, it simultaneously achieves three core objectives: low signal obstruction, low load, and high stability. The low-obstruction bionic support structure 11 includes a support frame 1, which forms the basic framework of the entire bracket. It not only provides overall support but also integrates an air duct 2 and a windbreak head 3 through an integrated molding process, making the structure more compact. Furthermore, its hollowed-out main body design reduces the area obstructing the signal, ensuring signal reception. The radiation range of receiver 10 is not obstructed by the frame, leaving ample space for signal transmission. The inner wall of support frame 1 is fixedly connected to support rod 5, which is a triangular truss structure. This structure uses the geometric stability of triangles to distribute the force between support frame 1 and mounting rod 4 to three nodes. The layout of one end connecting to support frame 1 and the other end connecting to mounting rod 4 forms a stable force transmission path of "frame-truss-carrier". At the same time, the hollow characteristics greatly reduce the amount of material used, while enhancing the connection strength between support frame 1 and mounting rod 4 and maintaining lightweight to reduce the load on the UAV body.

[0033] Reference Figures 2-4The inner wall of the support frame 1 is fixedly connected to the mounting rod 4, which not only connects the support frame 1 to the gyroscope structure 12 and the wing plate 6, but also evenly transfers the dynamic load of the gyroscope structure 12 and the aerodynamic load of the wing plate 6 to the support frame 1. The pressure is distributed through the synergistic effect of the support rod 5. The bottom outer wall of the mounting rod 4 is rotatably connected to the gyroscope structure 12, which can sense the attitude changes such as tilt, turn, and turbulence of the UAV in real time. The built-in attitude sensor drives the mechanical structure to adjust, so that the signal receiver 10 always points stably to the ground receiving end. The gyroscope structure 12 includes a first ring 7, a second ring 8, and a third ring 9. The three are nested ring structures and each ring can rotate relative to the other, forming a "three-axis rotation compensation system". The first ring 7 corresponds to the pitch attitude adjustment of the UAV, the second ring 8 corresponds to the roll attitude adjustment, and the third ring 9 corresponds to the yaw attitude adjustment. Through the coordinated rotation of the three rings, 360° all-dimensional attitude compensation can be achieved. The compensation system provides a stable mounting reference for the signal receiver 10 regardless of whether the UAV is in a sharp turn, tilt, or dive, adapting to the attitude change requirements of complex operating scenarios. The inner wall of the third ring 9 is rotatably connected to the signal receiver 10 via a pivot, and the signal receiver 10 is fixed at the center of the third ring 9. This central mounting layout ensures that the center of gravity of the signal receiver 10 coincides with the rotation axis of the three rings, avoiding swaying caused by centrifugal force during rotation and ensuring the stability of signal reception. At the same time, the pivot connection method allows for fine adjustment of the signal receiver 10. Combined with the three-ring compensation system, it further improves pointing accuracy and ensures the continuity of signal transmission. The gyroscope structure 12 is rotatably connected to the outer wall of the support rod 5 and the mounting rod 4 via a pivot. This "dual-point support" design avoids the swaying of the gyroscope structure 12 caused by single-point force, enhances its structural stability in dynamic environments, and makes the attitude compensation action smoother and more accurate.

[0034] Reference Figures 1-2 , Figure 5 The support frame 1 is equipped with an air duct 2, which is set along the extension direction of the support frame 1. Its interior has a smoothly transitioned arc-shaped channel structure, which can guide the airflow to pass smoothly along the support frame 1, avoiding the wind resistance loss caused by the turbulence of the airflow on the support surface. At the same time, the direction of the air duct 2 is consistent with the flight direction of the UAV, so that the airflow enters from the front air breaker 3 and flows quickly through the support body along the air duct 2, effectively reducing the wind resistance coefficient, reducing the energy consumption of the UAV's power system, and improving the endurance. The support frame 1 is also equipped with an air breaker 3, which has a streamlined structure with a sharp arc at the front end and a smooth connection with the support frame 1 at the rear end. It can quickly divert the oncoming airflow to the air ducts 2 on both sides, avoiding the airflow directly impacting the support body and creating a high-pressure area. At the same time, the streamlined design reduces the phenomenon of airflow separation, forming an airflow path of "guidance-smooth passage" with the air duct 2, further reducing wind resistance, and achieving a drag reduction effect of "1+1>2" together with the air duct 2.

[0035] Reference Figures 1-3 The outer wall of the mounting rod 4 is fixedly connected to the wing plate 6. The wing plate 6 is fixedly connected to the support frame 1 through the mounting rod 4. The two sets of wing plates 6 are set in a mirror symmetrical arrangement according to the central axis of the mounting rod 4. This symmetrical layout can balance the aerodynamic forces on the wing plate 6 when the UAV is flying, and avoid the support offset caused by the force on one side. The wing plate 6 is a streamlined airfoil structure with a rounded arc at the leading edge to reduce airflow impact and a relatively thin trailing edge to accelerate airflow separation. This design can not only generate a weak and stable lift during flight to balance the sinking force brought by the weight of the support itself, but also enhance the support's anti-rollover ability in strong wind environments and help maintain support stability. At the same time, its thin structure will not block the signal, taking into account both aerodynamic performance and signal transmission requirements.

[0036] Working Principle: The support frame 1 in the low-obstruction bionic support structure 11 serves as the overall basic frame. Utilizing an integrated molding process, the air duct 2 and the air breaker 3 are integrated to form a compact structure. Its hollow design significantly reduces signal obstruction, reserving ample radiation space for the signal receiver 10. The triangular truss structure support rod 5 fixed to the inner wall of the support frame 1 uses the geometric stability of a triangle to distribute the force between the support frame 1 and the mounting rod 4 to three nodes. Through the stable force transmission path of "frame-truss-carrier," it enhances connection strength while reducing material usage through its hollow structure, achieving lightweighting and reducing the load on the drone's fuselage. The mounting rod 4 on the inner wall of the support frame 1 serves as the core connection. The hub not only connects the support frame 1, the gyroscope structure 12, and the wing plate 6, but also evenly transmits the dynamic load of the gyroscope structure 12 and the aerodynamic load of the wing plate 6 to the support frame 1. The pressure is then distributed through the support rod 5 to ensure balanced force transmission. The gyroscope structure 12, rotatably connected to the bottom outer wall of the mounting rod 4, provides crucial support for stable signal transmission. Its built-in attitude sensor can detect real-time attitude changes such as tilt, turn, and turbulence during UAV flight, driving the operation of a "three-axis rotation compensation system" composed of nested and relatively rotatable first ring 7, second ring 8, and third ring 9. The first ring 7 corresponds to pitch attitude adjustment, the second ring 8 to roll attitude adjustment, and the third ring 9 to... The heading and attitude adjustment achieves 360° all-dimensional attitude compensation through the coordinated rotation of the three rings, ensuring that the signal receiver 10, fixed at the center of the third ring 9, always points stably towards the ground receiver. The rotating shaft connection between the signal receiver 10 and the third ring 9 allows for fine-tuning, further improving pointing accuracy. The gyroscope structure 12, through a "dual-point support" design formed by the rotating shaft, support rod 5, and mounting rod 4, avoids single-point force swaying, ensuring stable and accurate attitude compensation. Regarding wind resistance and flight stability, the arc-shaped channel-like air duct 2 along the extension direction of the support frame 1, with its direction consistent with the UAV's flight direction, guides airflow smoothly to reduce turbulent wind resistance. This, combined with the sharp tip at the front of the support frame 1... The streamlined, curved, and smoothly connected rear end of the air-breaking head 3 can quickly divert the oncoming airflow to the side air ducts 2, reducing the high-pressure area generated by airflow separation and direct impact. The two work together to achieve a drag reduction effect of "1+1>2", reducing power consumption and improving range. The two sets of mirror-symmetrical wing plates 6 fixed to the outer wall of the mounting rod 4 generate a weak and stable lift in flight with a streamlined airfoil structure, balancing the sinking force of the support itself. At the same time, the symmetrical layout balances the aerodynamic forces, preventing the support from shifting and enhancing the anti-rollover capability under strong winds. Moreover, the thin structure does not obstruct the signal, taking into account both aerodynamic performance and signal transmission requirements, ultimately achieving stable support and efficient signal transmission of the support in complex flight scenarios.

[0037] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., 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 drone antenna support, comprising a low-obstruction biomimetic support structure (11), characterized in that: The low-obstruction bionic support structure (11) includes a support frame (1), a support rod (5) is fixedly connected to the inner wall of the support frame (1), an installation rod (4) is fixedly connected to the inner wall of the support frame (1), a gyroscope structure (12) is rotatably connected to the bottom outer wall of the installation rod (4), the gyroscope structure (12) includes a first ring (7), a second ring (8) is rotatably connected to the inner wall of the first ring (7), a third ring (9) is rotatably connected to the inner wall of the second ring (8), a signal receiver (10) is rotatably connected to the inner wall of the third ring (9) via a rotating shaft, and the gyroscope structure (12) is rotatably connected to the outer wall of the support rod (5) and the installation rod (4) via a rotating shaft.

2. The UAV antenna bracket according to claim 1, characterized in that: The support frame (1) is provided with an air duct (2), and the support frame (1) is also provided with an air breaker (3). The outer wall of the mounting rod (4) is fixedly connected with a wing plate (6).

3. The UAV antenna bracket according to claim 2, characterized in that: The wing plate (6) is fixedly connected to the support frame (1) by the mounting rod (4), and the two sets of wing plates (6) are arranged in a mirror symmetrical manner according to the central axis of the mounting rod (4).

4. The UAV antenna bracket according to claim 1, characterized in that: The support rod (5) is a triangular truss structure, with one end connected to the support frame (1) and the other end connected to the mounting rod (4).

5. The UAV antenna bracket according to claim 1, characterized in that: The first ring (7), the second ring (8), and the third ring (9) are nested ring structures, and each ring can rotate relative to the other.

6. The UAV antenna bracket according to claim 1, characterized in that: The signal receiver (10) is fixed at the center of the third ring (9).

7. The UAV antenna bracket according to claim 2, characterized in that: The airfoil (6) is a streamlined airfoil structure with a rounded arc at the leading edge and a relatively thin trailing edge.

8. The UAV antenna bracket according to claim 2, characterized in that: The air duct (2) is arranged along the extension direction of the support frame (1), and the air breaker (3) has a streamlined structure.

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