Unmanned aerial vehicle with foldable support

Abstract

The unmanned aerial vehicle comprises an unmanned aerial vehicle body and rotor wing assemblies arranged on the two sides of the unmanned aerial vehicle body, integrated aerodynamic assemblies are symmetrically arranged on the left side and the right side of the unmanned aerial vehicle body, and each assembly comprises a support mechanism, a folding mechanism and a folding mechanism, the flow guide mechanism comprises a flow guide bin fixedly connected with the unmanned aerial vehicle body, and first shark fin plates and second shark fin plates which are distributed in a matrix mode are arranged on the outer surface of the flow guide bin; the support mechanism comprises a first supporting rod and a second supporting rod which are pivoted in the flow guide bin and are rotationally connected through a shaft rod; the unmanned aerial vehicle with the foldable support is additionally provided with the support mechanism and the flow guide mechanism, the support mechanism eliminates an airflow interference source of a traditional support through the electric drive folding design, the flow guide mechanism achieves energy dissipation control through flow guide and structure optimization, the aerodynamic efficiency of the unmanned aerial vehicle is improved through cooperation of the support mechanism and the flow guide mechanism, and meanwhile the flight stability breaks through.

Description

Technical Field

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

[0002] A drone is an unmanned aerial vehicle controlled by radio remote control or autonomous program. It consists of a flight platform, power system, navigation control system, data communication link and mission payload. It has functions such as vertical take-off and landing, fixed-point hovering, route cruising and real-time obstacle avoidance. It is widely used in military reconnaissance, disaster relief, agricultural plant protection, logistics and transportation, and environmental monitoring. Its technical core lies in the integration of aerodynamics, intelligent algorithms and lightweight materials, and realizes environmental perception and decision-making through airborne sensors and edge computing. At the same time, it relies on 5G / satellite communications to ensure beyond-line-of-sight control and data feedback, and must comply with airworthiness certification, electromagnetic compatibility and airspace management regulations. It is a key carrier of the modern low-altitude economy.

[0003] Combining the existing drones with existing technologies, it was found that the open support structure of existing drones lacks aerodynamic design, which produces high-intensity turbulence during flight. This not only directly weakens the aerodynamic efficiency of the rotor, but the asymmetric vortex it induces will also form complex interference with the flow around the fuselage, forcing the flight control system to frequently correct its attitude, resulting in a surge in energy consumption and a reduction in control margin, and ultimately significantly reducing the drone's wind resistance and flight stability, becoming a core technical bottleneck restricting performance improvement. Utility Model Content

[0004] The purpose of the utility model is to provide a drone with a foldable bracket to solve the problems raised in the above background technology.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] A drone with a foldable support, comprising a drone body and rotor assemblies arranged on both sides thereof, wherein the left and right sides of the drone body are symmetrically provided with integrated aerodynamic assemblies, the assemblies comprising: a support mechanism, which realizes the conversion between the deployed state and the stored state through a double torsion spring linkage structure; a diversion mechanism, which comprises a diversion bin fixedly connected to the drone body, the outer surface of which is provided with a first shark fin plate and a second shark fin plate distributed in a matrix; the support mechanism comprises: a first support rod and a second support rod pivotally connected to the inside of the diversion bin, the two being rotationally connected through an axle; a first torsion spring body and a second torsion spring body symmetrically arranged at both ends of the axle, respectively acting on the reset movement of the second support rod and the first support rod; a support frame fixedly connected to the axle, and a connecting frame is provided on the upper part of the support frame, which is transmission-connected to an electric push rod body.

[0007] Optionally, a first rubber pad is provided at the bottom of the first support rod, a second rubber pad is provided at the bottom of the second support rod, and a buffer silicone layer is provided on the contact surface between the first rubber pad and the second rubber pad.

[0008] Optionally, the electric push rod body is fixed to the bottom of the diversion chamber through a rod body support plate, and the end of its push rod stroke is fixedly connected to the connecting frame.

[0009] Optionally, a guiding and limiting component is arranged on the inner wall of the diversion chamber, including: a limiting sleeve fixed to the inner wall, with a T-shaped sliding groove arranged inside; a limiting plate fixedly connected to the connecting frame, with a flange structure matching the T-shaped sliding groove arranged at its edge.

[0010] Optionally, the cross-section of the diversion chamber is in a flat diversion structure, the surface of the chamber body is subjected to mirror polishing, the long axis direction of the chamber body is parallel to the flight direction of the unmanned aerial vehicle, and the maximum thickness part corresponds to the storage space of the support mechanism.

[0011] Optionally, the support mechanism can be completely embedded in the storage cavity of the diversion chamber under the linear drive of the electric push rod body, and the flat outer surface of the diversion chamber is configured to form a continuous transition with the flow around boundary layer of the unmanned aerial vehicle body.

[0012] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0013] 1. In the present utility model, a support mechanism is provided, achieving the optimization of aerodynamic performance: through the linear folding mechanism driven by the electric push rod body, the support mechanism is hidden in the diversion chamber, eliminating the turbulence generation source of the traditional open-type support.

[0014] 2. In the present utility model, a diversion mechanism is provided, achieving the control of air flow: the matrix distribution of the first shark fin plate and the second shark fin plate forms a diversion system, suppressing the generation of asymmetric eddies, greatly improving the wind resistance, and the flat diversion structure of the diversion chamber forms a continuous transition with the flow around layer of the unmanned aerial vehicle body. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic structural diagram of the present utility model in a three-dimensional front view;

[0016] Figure 2 is a schematic structural diagram of the present utility model in a plan front view;

[0017] Figure 3 is a schematic structural diagram of the present utility model in a plan left view;

[0018] Figure 4 is a schematic structural diagram of the present utility model in a three-dimensional top view;

[0019] Figure 5 is a schematic cross-sectional structural diagram of the present utility model in a three-dimensional view Figure 1 ;

[0020] Figure 6 is a schematic cross-sectional structural diagram of the present utility model in a three-dimensional viewFigure 2 ;

[0021] Figure 7 Structural schematic diagram of the three-dimensional section of the present utility model Figure 3 ;

[0022] Figure 8 For the present utility model Figure 5 Structural schematic diagram of the three-dimensional enlarged view at position A in it.

[0023] In the figure: 1, unmanned aircraft body; 2, bracket mechanism; 201, first strut; 202, first rubber pad; 203, second strut; 204, second rubber pad; 205, shaft rod; 206, first torsion spring body; 207, second torsion spring body; 208, support frame; 209, connecting frame; 210, electric push rod body; 211, rod body support plate; 3, flow guiding mechanism; 301, flow guiding bin; 302, first shark fin plate; 303, second shark fin plate; 304, limit sleeve; 305, limit plate. Specific embodiments

[0024] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model 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 thus should not be construed as a limitation to the present utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present utility model, unless otherwise specified, the meaning of "a plurality" is two or more.

[0025] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", "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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood through specific situations.

[0026] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0027] Please refer to Figures 1 to 8 , in the embodiment of the present invention, a drone with a foldable bracket includes a drone body 1 and rotor assemblies arranged on both sides thereof. Integrated aerodynamic assemblies are symmetrically arranged on the left and right sides of the drone body 1. The assembly includes: a bracket mechanism 2, which realizes the conversion between the unfolded state and the retracted state through a double torsion spring linkage structure; a flow guiding mechanism 3, which includes a flow guiding chamber 301 fixedly connected to the drone body 1. The outer surface of the flow guiding chamber 301 is provided with first shark fin plates 302 and second shark fin plates 303 distributed in a matrix; a guiding and limiting assembly is arranged on the inner wall of the flow guiding chamber 301, including: a limiting sleeve 304 fixed to the inner wall, and a T-shaped sliding groove is arranged inside it; a limiting plate 305 fixedly connected to the connecting frame 209, and a flange structure matching the T-shaped sliding groove is arranged on the edge. The cross-section of the flow guiding chamber 301 is in a flat flow guiding structure, the surface of the chamber body is polished to a mirror finish, the long axis direction of the chamber body is parallel to the flight direction of the drone, and the maximum thickness part corresponds to the storage space of the bracket mechanism 2. The flat outer surface of the flow guiding chamber 301 is configured to form a continuous transition with the flow boundary layer of the drone body 1.

[0028] The first torsion spring body 206 and the second torsion spring body 207 inside the bracket mechanism 2 assist the reset movement of the bracket mechanism 2 during unfolding or folding through pre-tightening force. The first support rod 201 and the second support rod 203 penetrate through the shaft rod 205 and are integrally in a V shape. When the drone lands on the ground, the first rubber pads 202 and the second rubber pads 204 at the lower ends of the first support rod 201 and the second support rod 203 contact the ground. During this process, both the torsion spring body and the rubber pads play an elastic buffering role, which can not only prevent the drone from bumping against the ground, but also play a buffering effect.

[0029] The electric push rod body 210 inside the support mechanism 2 is divided into two parts as a whole. The lower end area is the driving part, and the upper end area is the transmission rod part. The transmission rod part is connected to the top end of the connecting frame 209. The specific operation process is as follows: The electric push rod body 210 pulls down the transmission rod part at the upper end, so that the connecting frame 209 drives the lower support frame 208, the second torsion spring body 207, the first torsion spring body 206, the shaft rod 205, the second rubber pad 204, the second support rod 203, the first rubber pad 202 and the first support rod 201 to move down synchronously. After the first support rod 201 and the second support rod 203 protrude from the inside of the diversion bin 301, the support part of this UAV can perform the traditional support function. During flight, the electric push rod body 210 is enabled again. The electric push rod body 210 pushes up the transmission rod part, thereby driving the connecting frame 209 and the support frame 208, the second torsion spring body 207, the first torsion spring body 206, the shaft rod 205, the second rubber pad 204, the second support rod 203, the first rubber pad 202 and the first support rod 201 below the connecting frame 209 to move up at the same time, so that the first support rod 201 and the second support rod 203 move back into the inside of the diversion bin 301, achieving the effect of storing the support part.

[0030] The support mechanism 2 includes: a first support rod 201 and a second support rod 203 pivotally connected inside the diversion bin 301, and the two are rotatably connected through a shaft rod 205; a first torsion spring body 206 and a second torsion spring body 207 symmetrically arranged at both ends of the shaft rod 205, respectively acting on the reset movement of the second support rod 203 and the first support rod 201; a support frame 208 fixedly connected to the shaft rod 205, and a connecting frame 209 is arranged on its upper part and is in transmission connection with the electric push rod body 210. A first rubber pad 202 is arranged at the bottom of the first support rod 201, and a second rubber pad 204 is arranged at the bottom of the second support rod 203. A buffer silicone layer is arranged on the contact surface of the first rubber pad 202 and the second rubber pad 204. The electric push rod body 210 is fixed to the bottom of the diversion bin 301 through a rod body support plate 211, and the end of its push rod stroke is fixedly connected to the connecting frame 209. The support mechanism 2 can be completely embedded in the storage cavity of the diversion bin 301 under the linear drive of the electric push rod body 210.

[0031] Flight mode: When the UAV starts the flight program, the electric push rod body 210 is fixed to the bottom of the diversion bin 301 through the rod body support plate 211, and its push rod contracts linearly upward, driving the connecting frame 209 and the support frame 208 to move synchronously. At this time, the first support rod 201 and the second support rod 203 move into the diversion bin 301 under the transmission action of the electric push rod body 210, and finally the support mechanism 2 is completely embedded in the closed storage cavity of the diversion bin 301.

[0032] Flow diversion control: The flat outer surface of the diversion chamber 301 is connected to the flow boundary layer of the unmanned aerial vehicle 1, and its long axis direction is parallel to the flight direction. The maximum thickness area wraps the folded support mechanism 2. During the flight, the first shark fin plate 302 serves as a primary diversion structure to delay the airflow separation point; the second shark fin plate 303 serves as a secondary diversion structure, and uses the trailing edge to implement secondary diversion on the residual vortex, thereby stabilizing the airflow and ensuring the stable flight of the unmanned aerial vehicle 1.

[0033] Landing mode: When the drone needs to land, the electric push rod body 210 extends in the opposite direction to push the connecting frame 209 downward. The T-shaped slide groove in the limiting sleeve 304 cooperates with the flange structure of the limiting plate 305 to ensure the precise control of the deployment angle of the bracket. After the first rubber pad 202 and the second rubber pad 204 touch the ground, the impact load is buffered by the silicone layer to achieve a stable landing. The first support rod 201 and the second support rod 203 and the corresponding torsion spring body play a buffering role.

[0034] The working principle of the utility model is as follows: the UAV realizes the folding and unfolding of the bracket mechanism 2 through the linear drive of the electric push rod body 210: during flight, the electric push rod body 210 contracts and drives the connecting frame 209 and the supporting frame 208 to link, so that the first support rod 201 and the second support rod 203 pivot around the shaft rod 205, and the first support rod 201 and the second support rod 203 are completely folded into the closed storage cavity of the guide compartment 301 with the assistance of the pre-tightening force of the first torsion spring body 206 and the second torsion spring body 207, effectively avoiding the bracket The structure generates airflow, ensuring the stable flight of the unmanned aerial vehicle 1; during flight, the first shark fin plate 302 and the second shark fin plate 303 distributed in a matrix on the surface of the guide chamber 301 guide the airflow to suppress the generation of turbulence, while the T-shaped slide groove of the limit sleeve 304 and the limit plate 305 cooperate to ensure the movement accuracy of the bracket; when landing, the electric push rod body 210 extends in the opposite direction to drive the bracket to unfold, and the buffer silicone layer of the first rubber pad 202 and the second rubber pad 204 absorbs the impact load, realizing closed-loop control of aerodynamic optimization and mechanical stability.

[0035] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A drone with a foldable frame, comprising a drone body (1) and rotor assemblies arranged on both sides thereof, characterized in that: The unmanned aerial vehicle (1) is symmetrically provided with an integrated aerodynamic component on the left and right sides, the component comprising: a support mechanism (2) which realizes the conversion between the unfolded state and the stowed state through a double torsion spring linkage structure; a flow guide mechanism (3) which comprises a flow guide chamber (301) fixedly connected to the unmanned aerial vehicle (1), the outer surface of the flow guide chamber (301) being provided with a first shark fin plate (302) and a second shark fin plate (303) distributed in a matrix; the support mechanism (2) comprising: a first support rod (201) and a second support rod (203) pivotally connected to the inside of the flow guide chamber (301), the two being rotationally connected through a shaft (205); a first torsion spring body (206) and a second torsion spring body (207) symmetrically arranged at both ends of the shaft (205), respectively acting on the reset movement of the second support rod (203) and the first support rod (201); a support frame (208) fixedly connected to the shaft (205), the upper part of which is provided with a connecting frame (209) which is transmission-connected to the electric push rod body (210).

2. The drone with a foldable support according to claim 1, characterized in that: A first rubber pad (202) is provided at the bottom of the first support rod (201), a second rubber pad (204) is provided at the bottom of the second support rod (203), and a buffer silicone layer is provided on the contact surface between the first rubber pad (202) and the second rubber pad (204).

3. The drone with a foldable support according to claim 1, characterized in that: The electric push rod body (210) is fixed to the bottom of the diversion chamber (301) via a rod body support plate (211), and the end of the push rod stroke is fixedly connected to the connecting frame (209).

4. The drone with a foldable support according to claim 1, characterized in that: The inner wall of the guide bin (301) is provided with a guide limit assembly, comprising: a limit sleeve (304) fixed to the inner wall of the guide bin (301), the interior of which is provided with a T-shaped slide groove; and a limit plate (305) fixed to the connecting frame (209), the edge of which is provided with a flange structure matching the T-shaped slide groove.

5. The UAV with a foldable support according to claim 1, characterized in that: The cross section of the guide chamber (301) is a flat guide structure, the chamber body surface is mirror-polished, the long axis direction of the chamber body is parallel to the flight direction of the UAV, and the maximum thickness portion corresponds to the storage space of the bracket mechanism (2).

6. The UAV with a foldable support according to claim 1, characterized in that: The support mechanism (2) can be completely embedded in the storage cavity of the flow guide chamber (301) under the linear drive of the electric push rod body (210), and the flat outer surface of the flow guide chamber (301) is configured to form a continuous transition with the flow boundary layer of the unmanned aerial vehicle body (1).

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