Lightweight unmanned aerial vehicle

Abstract

The utility model provides a lightweight unmanned aerial vehicle, which relates to an unmanned aerial vehicle and comprises a vehicle body, a plurality of vehicle arms and a plurality of propellers, one end of each vehicle arm is connected with the vehicle body, and the other end of each vehicle arm is connected with the corresponding propeller. The machine arm is of a porous structure formed by arraying extremely-small curved surface structure units in the length direction, the width direction and the height direction. The unmanned aerial vehicle has the advantages that the vehicle arm is of a porous structure formed by arraying the extremely small curved surface structure units in the length direction, the width direction and the height direction, the weight is reduced as much as possible while the strength is guaranteed through the porous structure lightweight design of the vehicle arm, and therefore the overall weight of the unmanned aerial vehicle is reduced, and the endurance time of the unmanned aerial vehicle is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle equipment, in particular to a lightweight unmanned aerial vehicle. Background Art

[0002] With the development of the market, the demand for drones is increasingly tending towards miniaturization and lightness. Therefore, when designing drones, it is necessary to maintain the performance of the structure itself while reducing the overall weight as much as possible. For the arm part of the current multi-rotor drone, which accounts for a large proportion of the weight, some current solutions are to simply punch holes or hollow out the arm. This method without optimized design can easily damage the strength of the drone and cause the frame structure to fail.

[0003] In addition, currently, the frames of multi-rotor drones are mainly manufactured by autoclave molding and vacuum bag molding. Among them, the use of autoclave molding will result in high processing costs and poor economic benefits. Vacuum bag manufacturing requires wet operation, which is easily interfered by human factors and cannot meet the needs of manufacturing complex structures such as arms. Utility Model Content

[0004] In view of this, in order to solve the problems that the arms of current multi-rotor drones are punched or hollowed out to damage the body strength of the drone, and the manufacturing process is complicated and costly, an embodiment of the utility model provides a lightweight drone.

[0005] An embodiment of the utility model provides a lightweight unmanned aerial vehicle, comprising a body, a plurality of arms and a plurality of propellers, wherein one end of each arm is connected to the body and the other end is connected to the propeller, the arm is in the shape of a flat plate, and the arm is a porous structure formed by an array of minimal curved surface structural units along three directions of length, width and height.

[0006] Furthermore, the minimal surface structural unit is a Gyroid surface.

[0007] Furthermore, the function expression of the minimal surface structure unit is as follows:

[0008] F Gyroid =sin(2πx)cos(2πy)+sin(2πy)cos(2πz)+sin(2πz)cos(2πx)-t;

[0009] Among them: t is the horizontal control parameter, x, y, z are the high-dimensional physical space coordinates, x∈[-a,a], y∈[-a,a], z∈[-a,a], a is the structure size control parameter, and the three-dimensional size of the minimal surface structure unit is 2a.

[0010] Furthermore, the width of the arm gradually decreases from both ends to the middle.

[0011] Furthermore, the machine body includes a fuselage and a circuit board arranged on the fuselage, a motor is provided at an outer end of each of the arms, the propeller is mounted on the motor, and the motor is connected to the circuit board.

[0012] Furthermore, the fuselage includes an upper panel, a lower panel and two landing gears, the upper panel and the lower panel overlap and are tightly connected, the two landing gears are respectively arranged at the bottom of the lower panel, and two connecting parts are provided at the bottom of the lower panel, each of the connecting parts includes an upper mounting seat and a lower inclined connecting tube, the upper end of the landing gear is inserted into the connecting tube and is tightly connected to the connecting tube, one end of the arm is provided with a triangular rear joint, and the other end is provided with a circular front joint, the motor is installed on the front joint, and the rear joint is inserted between the upper panel and the lower panel and is tightly connected.

[0013] Furthermore, the upper panel and the lower panel are both regular hexagons, each side of which is provided with an arc-shaped notch, the number of the arms is six, and one end of each arm is connected to one side of the lower panel.

[0014] Furthermore, the fuselage also includes a battery, two battery racks and two round tube brackets, the two battery racks are arranged opposite to each other, the upper end of each battery rack is fixedly connected to the lower surface of the lower panel, a rectangular mounting groove is provided in the middle of each battery rack, both ends of each battery rack pass through the two mounting grooves respectively and are fastened to the two battery racks, two through holes are provided at the bottom of the battery rack, the through holes of the two battery racks are arranged one by one, and each round tube bracket passes through the corresponding two through holes and is fastened.

[0015] Furthermore, the fuselage also includes an aerial photography device, and a connecting plate is installed at the bottom of the two battery racks. The two ends of the connecting plate are respectively attached to and fastened to the bottom of the two battery racks, and the aerial photography device is installed in the middle of the connecting plate.

[0016] Furthermore, the surfaces of the body, the arms and the propellers are coated with a magnetic lossy stealth coating containing ferrite.

[0017] The beneficial effects brought about by the technical solution provided by the embodiment of the utility model are:

[0018] 1. The utility model is a lightweight UAV, the arm of which adopts a porous structure formed by an array of extremely small curved surface structural units along the length, width and height directions. The porous structure lightweight design of the arm can reduce the weight as much as possible while ensuring the strength, thereby reducing the overall weight of the UAV and improving the UAV's endurance time.

[0019] 2. The utility model is a lightweight UAV, the arm of which is formed by an array of minimal curved surface structural units. The minimal curved surface structure adopts a Gyroid-type porous structure. The porous structure model can be changed by adjusting the function parameters of the minimal curved surface structure to construct a minimal curved surface three-dimensional body. Therefore, additive manufacturing technology can be directly used for rapid prototyping and manufacturing, which reduces the process flow and has low processing costs.

[0020] 3. The utility model provides a lightweight UAV, wherein the surfaces of the body, the arms and the propellers are coated with a magnetic loss stealth coating containing ferrite, and the UAV has a certain stealth performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a three-dimensional diagram of a lightweight UAV of the utility model;

[0022] Figure 2 This is a top view of a lightweight UAV of the utility model;

[0023] Figure 3 This is a bottom view of a lightweight UAV of the utility model;

[0024] Figure 4 It is a schematic diagram of the machine arm;

[0025] Figure 5 yes Figure 4 A partial enlarged view of the middle A;

[0026] Figure 6 yes Figure 4 A partial enlarged view of point B in the middle;

[0027] Figure 7 is a schematic diagram of the upper panel;

[0028] Figure 8 is a schematic diagram of the lower panel;

[0029] Fig. 9 is a schematic diagram of the connector;

[0030] Fig.10 is a schematic diagram of the connection plate;

[0031] Fig.11 The diagram of the battery rack is shown below.

[0032] In the figure: 1. Flight control system; 2. GPS module; 3. Arm; 4. Battery; 5. Connecting plate; 6. Aerial photography equipment; 7. Landing gear; 8. Battery rack; 9. Connector; 10. Round tube bracket; 11. Motor; 12. Propeller; 13. Upper panel; 14. Lower panel; 15. Rear joint; 16. Front joint; 17. Threaded hole; 18. Mounting groove; 19. Perforation; 20. Mounting seat; 21. Connecting tube; 22. Mounting hole. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the utility model clearer, the following will further describe the implementation of the utility model in conjunction with the accompanying drawings. The following is a preferred embodiment of the utility model among multiple possible embodiments, which is intended to provide a basic understanding of the utility model, but is not intended to confirm the key or decisive elements of the utility model or limit the scope of protection.

[0034] In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limiting. Therefore, other examples of the exemplary embodiments may have different values.

[0035] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered as part of the specification.

[0036] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further discussed in the subsequent drawings. At the same time, it should be understood that for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0037] In the description of the present utility model, it should be noted that the circuits, electronic components and modules involved in the present utility model are all prior art and can be fully implemented by those skilled in the art. Needless to say, the content protected by the present utility model does not involve improvements to the internal structure and methods.

[0038] It should be further explained that, unless otherwise clearly specified and limited, the terms "installation" and "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 a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this utility model can be understood according to specific circumstances.

[0039] Please refer to Figure 1-3 An embodiment of the utility model provides a lightweight UAV, which is a multi-rotor UAV, mainly including a body, a plurality of arms 3 and a plurality of propellers 12.

[0040] The body is the main part of the drone, and the arms 3 are used to install the propellers 12. One end of each arm 3 is connected to the body, and the other end is connected to the propeller 12, through which the drone can be driven to take off, land, hover, and other actions.

[0041] like Figure 4-6 As shown, the arm 3 is in the shape of a flat plate, and in this embodiment, the width of the arm 3 gradually decreases from both ends to the middle. The arm 3 is a porous structure formed by arraying minimal curved surface structural units along the length, width and height directions. The minimal curved surface structure can effectively reduce the mass of the arm 3 through the internal pores, and can also ensure the structural rigidity and strength of the arm 3.

[0042] Specifically, the minimal surface structure unit may be a Gyroid surface. In this embodiment, the function expression of the minimal surface structure unit is as follows:

[0043] F Gyroid =sin(2πx)cos(2πy)+sin(2πy)cos(2πz)+sin(2πz)cos(2πx)-t;

[0044] Wherein: t is the horizontal control parameter, x, y, z are high-dimensional physical space coordinates, x∈[-a,a], y∈[-a,a], z∈[-a,a], a is the structural size control parameter, the three-dimensional size of the minimal surface structural unit is 2a, where the minimal surface structural unit is a cubic unit cell structure, and 2a is the side length of the minimal surface structural unit. In this embodiment, a=2mm, then x, y, z∈[-1,1].

[0045] In this way, the arm 3 in this embodiment is formed by an array of Gyroid surfaces. The porous structure model can be changed by adjusting the function parameters of the minimal surface structure to construct a minimal surface three-dimensional body. Therefore, additive manufacturing technology can be directly used for rapid prototyping and manufacturing, such as using carbon fiber composite materials through FDM printing, which can reduce the process flow and reduce processing costs.

[0046] The body includes a fuselage and a circuit board arranged on the fuselage. Each of the arms 3 is provided with a motor 11 at one end thereof, and the motor 11 is a brushless motor 11. The propeller 12 is mounted on the motor 11, and the motor 11 is connected to the circuit board. The circuit board mainly integrates a flight control system 1 and a GPS module 2, etc., for controlling the flight of the drone. This is a prior art and will not be described in detail here.

[0047] Recombination Figure 7 and 8 As shown, the fuselage includes an upper panel 13, a lower panel 14 and two landing gears 7, the upper panel 13 and the lower panel 14 are both regular hexagons, each side of which is provided with an arc-shaped notch, and the number of the arms 3 is six, and one end of each arm 3 is connected to one side of the lower panel 14. In this way, multiple arms 3 are evenly distributed around the fuselage, which is convenient for controlling the UAV to achieve stable flight.

[0048] The upper panel 13 and the lower panel 14 overlap and are fastened together, and the two landing gears 7 are respectively arranged at the bottom of the lower panel 14. Fig. 9 As shown, two connecting members 9 are provided at the bottom of the lower panel 14, each of the connecting members 9 includes an upper mounting seat 20 and a lower inclined connecting tube 21, the upper end of the landing gear 7 is inserted into the connecting tube 21 and is tightly connected to the connecting tube 21, so that the two landing gears 7 are relatively divergent, forming a stable support for the UAV when it takes off and lands.

[0049] A triangular rear joint 15 is provided at one end of the arm 3, and a circular front joint 16 is provided at the other end, the motor 11 is mounted on the front joint 16, and the motor 11 and the propeller 12 are supported on the front joint 16. The rear joint 15 is inserted between the upper panel 13 and the lower panel 14 and is fastened and connected, and a threaded hole 17 is provided on the rear joint 15, and is fastened and connected to the upper panel 13 and the lower panel 14 at the same time by screws.

[0050] The fuselage also includes a battery 4, two battery racks 8 and two round tube brackets 10. The battery 4 is connected to the circuit board to supply power to the circuit board and the motor 11. Fig.11 As shown, the battery rack 8 is approximately a rectangular frame, and the two battery racks 8 are arranged opposite to each other. The upper end of each battery rack 8 is fixedly connected to the lower surface of the lower panel 14. A rectangular mounting groove 18 is provided in the middle of each battery rack 8. The two ends of each battery 4 pass through the two mounting grooves 18 and are fastened to the two battery racks 8. In addition, two through holes 19 are provided at the lower part of the battery rack 8. The through holes 19 of the two battery racks 8 are arranged one by one. Each round tube bracket 10 passes through the corresponding two through holes 19 and is fastened. The two battery racks 8 are connected by the two round tube brackets 10, which plays a reinforcing role, ensures the stability of the installation of the battery 4, and prevents the battery 4 from falling.

[0051] Recombination Fig.10 As shown, the fuselage also includes an aerial photography device 6, and a connecting plate 5 is installed at the bottom of the two battery racks 8. The two ends of the connecting plate 5 are respectively attached to and fastened to the bottom of the two battery racks 8. Here, both ends of the connecting plate 5 are provided with mounting holes 22, and the mounting holes 22 are used to fasten the battery rack 8 with screws. The aerial photography device 6 is installed in the middle of the connecting plate 5, and the aerial photography device 6 is connected to the circuit board. During the flight of the drone, the circuit board obtains the aerial photography data of the aerial photography device 6.

[0052] In addition, magnetic loss stealth coating containing ferrite can be sprayed on the surface of the body, the arm 3 and the propeller 12, so that the UAV has a certain stealth performance and can fly in a concealed manner.

[0053] The utility model provides a lightweight UAV, wherein the arm 3 adopts a porous structure formed by an array of extremely small curved surface structural units along the length, width and height directions. The porous structure lightweight design of the arm 3 reduces the weight as much as possible while ensuring the strength, thereby reducing the overall weight of the UAV and increasing the flight time of the UAV.

[0054] In this document, the directional words such as front, back, top, and bottom involved are defined by the positions of the parts in the drawings and the positions of the parts relative to each other, just for the clarity and convenience of expressing the technical solution. It should be understood that they are relative concepts and can change accordingly according to different ways of use and placement. The use of the directional words should not limit the scope of protection requested by this application. In the absence of conflict, the above embodiments and features in the embodiments can be combined with each other.

[0055] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. A lightweight drone, comprising a body, a plurality of arms and a plurality of propellers, wherein one end of each arm is connected to the body and the other end is connected to the propeller, characterized in that: The machine arm is in the shape of a flat plate, and is a porous structure formed by arraying extremely small curved surface structural units along the three directions of length, width and height; The minimal surface structural unit is a Gyroid surface; The function expression of the minimal surface structural unit is as follows: F Gyroid =sin(2πx)cos(2πy)+sin(2πy)cos(2πz)+sin(2πz)cos(2πx)-t; Among them: t is the horizontal control parameter, x, y, z are the high-dimensional physical space coordinates, x∈[-a,a], y∈[-a,a], z∈[-a,a], a is the structure size control parameter, and the three-dimensional size of the minimal surface structure unit is 2a.

2. A lightweight UAV as claimed in claim 1, characterized in that: The width of the machine arm gradually decreases from the two ends to the middle.

3. A lightweight UAV as claimed in claim 1, characterized in that: The machine body comprises a fuselage and a circuit board arranged on the fuselage, a motor is arranged at an outer end of each of the machine arms, the propeller is mounted on the motor, and the motor is connected to the circuit board.

4. A lightweight UAV as claimed in claim 3, characterized in that: The fuselage includes an upper panel, a lower panel and two landing gears, the upper panel and the lower panel overlap and are tightly connected, the two landing gears are respectively arranged at the bottom of the lower panel, and two connecting parts are provided at the bottom of the lower panel, each of the connecting parts includes an upper mounting seat and a lower inclined connecting tube, the upper end of the landing gear is inserted into the connecting tube and is tightly connected to the connecting tube, one end of the arm is provided with a triangular rear joint, and the other end is provided with a circular front joint, the motor is installed on the front joint, and the rear joint is inserted between the upper panel and the lower panel and is tightly connected.

5. A lightweight UAV as claimed in claim 4, characterized in that: The upper panel and the lower panel are both regular hexagons, each side of which is provided with an arc-shaped notch. The number of the machine arms is six, and one end of each of the machine arms is connected to one side of the lower panel.

6. A lightweight UAV as claimed in claim 4, characterized in that: The fuselage also includes a battery, two battery racks and two round tube brackets. The two battery racks are arranged opposite to each other. The upper end of each battery rack is fixedly connected to the lower surface of the lower panel. A rectangular mounting groove is provided in the middle of each battery rack. Both ends of each battery rack pass through the two mounting grooves respectively and are fastened to the two battery racks. Two through holes are provided at the lower part of the battery rack. The through holes of the two battery racks are arranged one by one. Each round tube bracket passes through the corresponding two through holes and is fastened.

7. A lightweight UAV as claimed in claim 6, characterized in that: The fuselage also includes an aerial photography device. A connecting plate is installed at the bottom of the two battery racks. The two ends of the connecting plate are respectively attached to and fastened to the bottom of the two battery racks. The aerial photography device is installed in the middle of the connecting plate.

8. A lightweight UAV as claimed in claim 1, characterized in that: The surfaces of the machine body, the machine arm and the propeller are all coated with magnetic loss stealth paint containing ferrite.

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