Axial flow unmanned aerial vehicle

Abstract

The axial flow unmanned aerial vehicle comprises a body assembly and a plurality of rotor wing assemblies, the rotor wing assemblies are symmetrically arranged on the periphery of the body assembly, a flow guide cavity is formed in the middle of the body assembly, and an air outlet of the flow guide cavity is axially formed relative to the ground. An axial flow fan assembly is arranged in the flow guide cavity in a matched mode, and airflow formed in the axial flow fan assembly can be output in an axial and relatively concentrated mode relative to the ground along the flow guide cavity. According to the scheme, the axial flow fan is matched with the flow guide cavity, airflow formed by the axial flow fan in the flow guide cavity can be axially and relatively intensively output relative to the ground along the flow guide cavity, and therefore large thrust can be formed to drive the body assembly provided with materials to fly; and the unmanned aerial vehicle can be assembled with materials with a certain weight for transportation during rescue.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle manufacturing, in particular to an axial flow unmanned aerial vehicle. Background Art

[0002] With the development of society, the existing transportation of materials can be carried out by unmanned aerial vehicles instead of manual labor. By using unmanned aerial vehicles for transportation, it can save time and effort. At the same time, it can also achieve paths that cannot be carried out manually.

[0003] In the Chinese patent with the publication number of CN 112929072 B, "Relay system, method, device, medium and electronic equipment for unmanned aerial vehicle communication" is disclosed. See Figure 1 , which realizes the flight and hovering of the unmanned aerial vehicle by symmetrically arranging a plurality of multi-rotors 2 around the main unmanned aerial vehicle 1 and cooperating with an inflatable balloon 3.

[0004] This unmanned aerial vehicle can realize the rapid flight of the unmanned aerial vehicle through multiple groups of rotors 2. However, the airflow generated by the rotation of the multi-rotors 2 symmetrically arranged around it is dispersed, and it has a low lifting force while realizing rapid flight. Then, when transporting materials during rescue or construction, there will be certain limitations on the weight of the materials. If the weight exceeds a certain limit, this unmanned aerial vehicle cannot fly.

[0005] Therefore, the existing unmanned aerial vehicle has the technical problem of low practicality due to its low lifting force. It can be seen that how to improve the practicality of the unmanned aerial vehicle is a problem to be solved in this field. Summary of the Utility Model

[0006] Aiming at the technical problem of low practicality existing in the existing unmanned aerial vehicle, the purpose of the utility model is to provide an axial flow unmanned aerial vehicle, which can solve the technical problem of low lifting force of the unmanned aerial vehicle, enable it to be fully applied to the field of material transportation, improve the practicality of the unmanned aerial vehicle, and effectively overcome the problems existing in the prior art.

[0007] To achieve the above purpose, the utility model provides an axial flow unmanned aerial vehicle, which includes a body component and a plurality of groups of rotor components. The plurality of groups of rotor components are symmetrically arranged on the periphery of the body component. A diversion cavity is formed in the middle of the body component. The air outlet of the diversion cavity is axially arranged relative to the ground. An axial flow fan component is cooperatively arranged inside the diversion cavity. The airflow formed by the axial flow fan component can be axially and relatively concentratedly output along the diversion cavity relative to the ground.

[0008] Further, the cross-section of the diversion cavity is an annular structure.

[0009] Further, the axial flow fan component includes a second driving component and a second blade, and the second driving component is drivingly connected to the second blade.

[0010] Furthermore, the axial flow UAV is equipped with a power supply assembly, which includes a charger and several wires. One end of the several wires is connected to the charger, and the other end is connected to the axial flow UAV.

[0011] Furthermore, the power supply assembly is a chemical power source, and the chemical power sources are symmetrically distributed inside the body assembly.

[0012] Furthermore, assembly components are symmetrically arranged at the bottom of the body assembly.

[0013] The axial flow UAV provided by the present utility model, through the cooperation of the axial flow fan and the diversion cavity, the airflow formed by the axial flow fan in the diversion cavity can be axially and relatively concentratedly output relative to the ground along the diversion cavity. Thus, a relatively large thrust can be formed to drive the body assembly equipped with materials to fly, meeting the requirement that this UAV can be equipped with a certain weight of materials for transportation during rescue. Description of the Drawings

[0014] The following further describes the present utility model in conjunction with the drawings and specific embodiments.

[0015] Figure 1 is a schematic diagram of the overall structure of an existing UAV;

[0016] Figure 2 is a schematic diagram of the overall structure of this axial flow UAV;

[0017] Figure 3 is a three-dimensional diagram of the overall structure of this axial flow UAV;

[0018] Figure 4 is a side view of the overall structure of this axial flow UAV;

[0019] Figure 5 is a schematic diagram of the structure of the body assembly in this axial flow UAV.

[0020] The following is the component labeling description in the drawings:

[0021] 100. Body assembly 110. Mounting surface 120. Diversion cavity 200. Rotor assembly 210. First drive assembly 220. First blade 230. Connecting rod 300. Axial flow fan assembly 310. Second drive assembly 320. Second blade Specific Embodiments

[0022] In order to make the technical means, creative features, achieved purposes and effects of the present utility model easy to understand, the present utility model is further described below in conjunction with specific illustrations.

[0023] Example 1:

[0024] SeeFigure 2 , the axial-flow drone provided by the present utility model is composed of a body component 100, several groups of rotor components 200 and an axial-flow fan component 300 in cooperation. The formed axial-flow drone can increase the lifting force of the drone through the driving force of the axial flow, and meet the transportation of heavier materials in rescue operations.

[0025] Among them, referring to Figure 3 , the periphery of the body component 100 is the installation surface 110 of several groups of rotor components, and the middle is a cavity for installing the axial-flow fan component 300, which cooperates with the axial-flow fan component 300 to form a diversion cavity 120.

[0026] At the same time, the cross-section of the diversion cavity 120 in the middle of the body component 100 is an annular structure. When the body is flying, the two air outlets of the diversion cavity 120 are axially arranged relative to the opposite surfaces respectively. The airflow formed by the axial-flow fan component 300 inside can be axially and relatively concentratedly output along the diversion cavity 120 relative to the ground. Thus, a relatively large thrust can be formed to drive the body component equipped with materials to fly.

[0027] It should be noted here that, however, the peripheral structure of this solution is not limited in this solution. This solution is preferably a cylinder. When flying in the air, using a cylinder can reduce the resistance of a certain wind direction. At the same time, it is an absolutely axisymmetric structure, which can ensure the stability of the body during flight.

[0028] However, the structure of the periphery of the body in this solution is not limited to the above-mentioned cylinder structure, and it can be determined according to the actual situation specifically.

[0029] Referring to Figure 3 - Figure 4 , several groups of rotor components 200 are symmetrically distributed on the periphery of the body component 100. By symmetrically distributing several groups of rotor components 200 on the periphery of the body component 100, the balance of the body component 100 during flight can be ensured.

[0030] Several groups of rotor components 200 respectively include a first driving component 210, a first blade 220 and a connecting rod 230. The first blade 220 is connected to the body component 100 through the connecting rod 230, and the first driving component 210 is drivingly connected to the first blade 220. The first driving component 210 provides driving force for the rotation of the first blade 220.

[0031] This solution preferably symmetrically arranges four groups of rotor components 200 on the periphery of the body component 100. The four groups of rotor components 200 can assist the axial-flow fan component 300 to provide a certain amount of power for the body component 100. At the same time, by respectively adjusting the rotation speeds of the first blades 220 in the four groups of rotor components 200, the flight orientation of the body component 100 can be realized.

[0032] The number of blades of the first blade 220 is not limited in this solution and can be two blades, three blades, etc., and can be specifically determined according to the actual situation.

[0033] At the same time, the technical principle of adjusting the orientation of the drone by different rotation speeds of the rotor assembly 200 is well known to those skilled in the art and will not be elaborated in detail here.

[0034] The axial flow fan assembly 300 is arranged inside the diversion cavity 120, and the airflow formed by the axial flow fan assembly 300 in the diversion cavity 120 can be axially and relatively concentratedly output relative to the ground along the diversion cavity 120.

[0035] The axial flow fan assembly 300 includes a second drive assembly 310 and a second blade 320. The second drive assembly 310 is drivingly connected to the second blade 320 to provide driving force for the rotation of the second blade 320 through the second drive assembly 310.

[0036] The number of blades of the second blade 320 is not limited in this solution and can be four blades, six blades, etc., and can be specifically determined according to the actual situation.

[0037] The airflow formed by the rotation of the axial flow fan assembly 300 in the diversion cavity 120 blows out relative to the ground along the diversion cavity 120 in a concentrated manner, and can form a large axial thrust to drive the body assembly equipped with materials to fly.

[0038] The axial flow drone composed of the above solution, through the cooperation of the axial flow fan and the diversion cavity body, the airflow formed by the axial flow fan in the diversion cavity can be axially and relatively concentratedly output relative to the ground. Thus, a large thrust can be formed to drive the body assembly equipped with materials to fly, meeting the requirement that this drone can be equipped with a certain weight of materials for transportation during rescue.

[0039] Embodiment 2:

[0040] Based on the axial flow drone provided in Embodiment 1, a power supply component is further provided on the axial flow drone in this embodiment to supply power to the axial flow drone.

[0041] The composition of the power supply component is not limited in this solution. This solution preferably adopts wired charging. By adopting wired charging, the stable battery life of the axial flow robot can be guaranteed, and at the same time, the long working cycle of the axial flow robot can also be satisfied.

[0042] One end of the wire during limited charging is connected to the charger, and the other end is connected to the axial flow robot. To ensure aesthetics and prevent the wire from being wound around the propeller blades during flight, the wire can be introduced through the inside of the connecting rod of the rotor assembly to provide power for the components that require power in the axial flow UAV. Thus, the appearance can be made simple and the wire mess can be avoided, preventing safety issues.

[0043] Meanwhile, the circuit can also be distributed inside the body assembly, and the circuit can be led from inside the body assembly to the components that require power supply.

[0044] This solution does not limit the circuit distribution for wired charging, and it can be determined according to the actual situation specifically.

[0045] Meanwhile, the power supply component in this solution can also be charged using a chemical power source. If a chemical power source is used for power supply, refer to Figure 5 then the body assembly 100 can be divided into a first housing 130 and a second housing 140, and the first housing 130 and the second housing 140 can be assembled and connected.

[0046] Among them, the inside of the second housing 140 is a cavity body, configured to form a placement cavity for the chemical power source. The chemical power sources are symmetrically distributed inside the second housing 140, and the wiring is carried out inside it. Then, the second housing 140 and the first housing 130 are assembled together to achieve power supply for the axial flow UAV. Thus, setting the first housing 130 and the second housing 140 into a detachable assembly structure can facilitate the replacement of the power source.

[0047] It should be noted here that the chemical power sources need to be symmetrically distributed inside the body assembly 100 to ensure the balance of the body assembly during flight.

[0048] Embodiment 3:

[0049] Based on the axial flow robot provided in Embodiment 1, several assembly components are symmetrically distributed at the bottom of the body assembly 100 for assembling materials during rescue.

[0050] The structure of the assembly components in this solution is not limited. As an example, a hanging basket can be correspondingly arranged at the bottom of the body assembly 100, or several hooks can be symmetrically arranged at the bottom of the body assembly 100. The specific structure of the assembly components can be determined according to the actual situation.

[0051] Embodiment 4:

[0052] Based on Embodiment 1, spiral flow guiding grooves are arranged on the inner wall of the flow guiding cavity 120 inside the body assembly 100 according to the rotation direction of the second propeller 320.

[0053] The flow guiding groove is arranged along the inner wall of the cavity of the flow guiding cavity 120, and the spiral angle thereof corresponds to the air flow transmission path formed by the second blade dimension 320. The air flow formed by the second blade 320 can be output along the spiral flow guiding groove, ensuring the concentration of the air flow output, and further ensuring the magnitude of the axial thrust formed by the axial flow fan.

[0054] Embodiment 5:

[0055] Based on Embodiment 1, in this embodiment, a wear-resistant layer is coated on the entire outer layer of the body assembly 100 to protect the outer layer of the body assembly 100, so as to ensure that the body assembly 100 of the unmanned aerial vehicle is scratched during a collision during flight, and the service life of the body assembly 100 is extended.

[0056] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and the descriptions in the specification only illustrate the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. An axial flow drone, comprising a body assembly and a plurality of rotor assemblies, wherein the plurality of rotor assemblies are symmetrically arranged on the periphery of the body assembly, characterized in that: A guide cavity is formed in the middle of the main body component, and the air outlet of the guide cavity is axially arranged relative to the ground. An axial flow fan assembly is arranged inside the guide cavity. The airflow formed by the axial flow fan assembly can be output axially and relatively concentratedly along the guide cavity relative to the ground.

2. The axial flow UAV according to claim 1, characterized in that: The cross section of the flow guide cavity is an annular structure.

3. The axial flow UAV according to claim 1, characterized in that: The axial flow fan assembly includes a second driving assembly and a second blade, and the second driving assembly is drivingly connected to the second blade.

4. The axial flow UAV according to claim 1, characterized in that: The axial flow drone is equipped with a power supply assembly, which includes a charger and a plurality of wires, one end of the plurality of wires is connected to the charger, and the other end is connected to the axial flow drone.

5. The axial flow UAV according to claim 4, characterized in that: The power source component is a chemical power source, and the chemical power source is symmetrically distributed inside the body component.

6. The axial flow UAV according to claim 1, characterized in that: The bottom of the body component is symmetrically provided with assembly components.

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