Unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle which comprises a vehicle body, at least two linear supporting pieces connected to the vehicle body, a left main wing and a right main wing. Two propellers are arranged on each linear supporting piece. In this way, in the take-off process of the unmanned aerial vehicle, better lift force can be provided, and when any one of one or more propellers breaks down, the unmanned aerial vehicle can continue to work only by closing the corresponding broken-down propeller, so that built-in configuration redundancy is achieved, and the reliability of the unmanned aerial vehicle is improved. Therefore, the flight distance and the cruising ability of the unmanned aerial vehicle are remarkably improved.

Description

Technical Field

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

[0002] Unmanned aircraft, also known as drones, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. UAVs in the prior art are mainly divided into fixed-wing drones, multi-rotor drones and compound-wing drones. In actual use, fixed-wing drones and multi-rotor drones have their own advantages. Fixed-wing drones have the characteristics of long flight time and high-altitude flight, and are widely used in surveying and mapping, geology, petroleum, agriculture and forestry and other industries. Multi-rotor drones can take off and land vertically and hover in the air, and are mainly suitable for low-altitude, low-speed operations that require vertical take-off and landing and hovering.

[0003] With the rapid development of drone technology, the functions of drones have become more and more complete and have been deeply integrated into the actual operations of various industries. However, the complexity of drone application scenarios has also posed higher challenges to the performance of drones. At present, composite-wing drones have gradually become the focus of the drone field because they have the advantages of vertical take-off and landing capabilities and long flight time.

[0004] Although the drones of the prior art have both vertical take-off and landing and fixed-wing flight modes, they cannot provide sufficiently large lift in the vertical take-off and landing mode, that is, the existing drones are limited by the number of linear supports and the number of propellers, and during the high-speed flight of the drone, one of the propellers is very likely to malfunction. Therefore, it is necessary to improve the problems existing in the existing drones. Utility Model Content

[0005] One purpose of the utility model is to provide a drone with improved flight performance.

[0006] To achieve this purpose, the utility model adopts the following technical solutions:

[0007] A drone, comprising:

[0008] body;

[0009] at least two linear supports connected to the fuselage;

[0010] A left main wing and a right main wing, wherein the left main wing and the right main wing are connected to the fuselage;

[0011] Two propellers are arranged on each of the at least two linear supports;

[0012] Wherein, the propellers are arranged linearly;

[0013] Each of the at least two linear support members is spaced apart from each other and distributed on both sides of the fuselage;

[0014] The drone includes a first linear support, a second linear support, a third linear support and a fourth linear support;

[0015] The first linear support is provided with a first propeller and a second propeller, the second linear support is provided with a third propeller and a fourth propeller, the third linear support is provided with a fifth propeller and a sixth propeller, and the fourth linear support is provided with a seventh propeller and an eighth propeller;

[0016] The first propeller is located below the first linear support, and the second propeller is located above the first linear support; the third propeller is located above the second linear support, and the fourth propeller is located below the second linear support; the fifth propeller is located below the third linear support, and the sixth propeller is located above the third linear support; the seventh propeller is located above the fourth linear support, and the eighth propeller is located below the fourth linear support;

[0017] The drone also includes a tail wing connected to the rear of the fuselage, the tail wing includes a left tail wing piece abutting against the second linear support member and a right tail wing piece abutting against the third linear support member, and the left tail wing piece and the right tail wing piece together form an inverted V shape.

[0018] Preferably, the left main wing and the right main wing form a dihedral structure.

[0019] Preferably, each of the linear supports is parallel to the axis of the fuselage.

[0020] Preferably, each linear support has a cylindrical cross section.

[0021] Preferably, the left main wing is provided with a first folding portion that turns upward at an end away from the UAV fuselage, and the right main wing is provided with a second folding portion that turns upward at an end away from the UAV fuselage.

[0022] Beneficial effects of the utility model:

[0023] The utility model can provide better lift during the take-off of the UAV by configuring a total of four linear support members and eight lift propellers on both sides of the fuselage. At the same time, a total of eight propellers are configured on the linear support members, and the four propellers on the left and the four propellers on the right are arranged linearly to form four parallel arrays. In this way, when any one or more propellers fails, the UAV can continue to work by simply shutting down the corresponding faulty propeller, thereby realizing built-in configuration redundancy, thereby significantly improving the flight distance and endurance of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the UAV provided by the utility model;

[0025] Figure 2 It is a top view of the UAV provided by the utility model;

[0026] Figure 3 It is a schematic diagram of the UAV provided by the utility model;

[0027] Figure 4 It is a side view of the drone provided by the utility model;

[0028] Figure 5 It is a front view of the UAV provided by the utility model. DETAILED DESCRIPTION

[0029] The technical solution of the utility model is further described below in conjunction with the accompanying drawings and implementation methods. It is understood that the specific embodiments described herein are only used to explain the utility model, rather than to limit the utility model. It should also be noted that, for the convenience of description, only the parts related to the utility model are shown in the accompanying drawings, rather than all.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable 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 the present invention can be understood according to specific circumstances.

[0031] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0032] In the description of this embodiment, the terms "upper", "lower", "right", etc., are based on the directions or positions shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0033] like Figure 1 As shown, the utility model of the present application generally depicts the overall structure of a drone. Overall, the drone has a fuselage 100, and the fuselage 100 has an aerodynamic design, and its contour can be used to minimize air resistance during flight. A left main wing 210 is attached to the left side of the fuselage 100, and correspondingly, a right main wing 220 is attached to the right side of the fuselage 100. The left main wing 210 and the right main wing 220 are respectively attached to the two sides of the fuselage 100.

[0034] In one embodiment, the left main wing 210 and the right main wing 220 are respectively attached to the front end portion of both sides of the fuselage 100 , approximately located at a position about one third of the length of the entire fuselage 100 from the front end of the fuselage 100 , and are integrally formed with the fuselage 100 .

[0035] In another embodiment, the left main wing 210 and the right main wing 220 are respectively attached to the front end portion of both sides of the fuselage 100, approximately located at a position about one-third of the length of the entire fuselage 100 away from the front end of the fuselage 100, and are detachably connected to the fuselage 100, so that the wings and the fuselage 100 can be directly and quickly disassembled and installed.

[0036] In one embodiment, the left main wing 210 and the right main wing 220 are respectively attached to the middle part of both sides of the fuselage 100 , approximately located in the middle between the front end and the rear end of the fuselage 100 , and are integrally formed with the fuselage 100 .

[0037] In another embodiment, the left main wing 210 and the right main wing 220 are respectively attached to the middle part of both sides of the fuselage 100, approximately located in the middle position between the front end and the rear end of the fuselage 100, and are detachably connected to the fuselage 100, so that the wings and the fuselage 100 can be directly and quickly disassembled and installed.

[0038] In the drone provided in the present application, the left main wing 210 and the right main wing 220 are used to provide lift for the aircraft during the level flight of the aircraft. In the present application, the two main wings are fixed main wings, that is, the main wings cannot rotate relative to the fuselage 100, and the main wings are symmetrically arranged on both sides of the fuselage 100 along the longitudinal axis of the fuselage 100. As for the shape of the main wings, in the present embodiment, the two main wings are in the form of a straight wing structure, and in other embodiments, the two main wings are in the form of a delta wing structure, etc. The drone provided in the present application does not further limit the structure of the two main wings.

[0039] Now continue to refer to Figure 1 It can be found that in the drone provided in the present application, the left main wing 210 is provided with a first folding portion 201 that turns upward at the end away from the drone fuselage 100, and the first folding portion 201 is integrally formed with the left main wing 210. Correspondingly, the right main wing 220 is provided with a second folding portion 202 that turns upward at the end away from the drone fuselage 100, and the second folding portion 202 is integrally formed with the left main wing 210.

[0040] Furthermore, the drone fuselage 100 provided in the present application is preferably made of a carbon fiber material, which has certain ductility and toughness. While enhancing the strength of the fuselage 100, the carbon fiber material itself has certain toughness and ductility and can be used to resist part of the torque and air resistance applied to the fuselage 100 during flight.

[0041] Furthermore, the drone provided in the present application also includes two left linear supports, namely a first linear support 310 far away from the fuselage 100 and a second linear support 320 closer to the fuselage 100, each located at the left end of the drone fuselage 100. Correspondingly, the drone provided in the present application also includes two right linear supports, namely a third linear support 330 closer to the fuselage 100 and a fourth linear support 340 far away from the fuselage 100, each located at the right end of the drone fuselage 100.

[0042] In the drone provided in the present application, the first linear support 310 is fixedly attached to the end of the left main wing 210 away from the left side of the drone fuselage 100, the fourth linear support 340 is fixedly attached to the end of the right main wing 220 away from the right side of the drone fuselage 100, the second linear support 320 is located between the first linear support 310 and the left side of the drone fuselage 100, close to the left side of the drone fuselage 100, and correspondingly, the third linear support 330 is located between the fourth linear support 340 and the right side of the drone fuselage 100, close to the right side of the drone fuselage 100.

[0043] Preferably, each linear support member can be made of a suitable material to withstand the physical demands during flight and to resist distortion caused by various pressures generated during flight. Such materials include natural and synthetic polymers, various metals and metal alloys, natural materials, textile fibers, glass and ceramic materials, etc. Specifically, during flight, air will exert a distortion force on the drone fuselage 100 through the left main wing 210 and the right main wing 220, and the up and down movement of the left main wing 210 and the right main wing 220. Each linear support member can minimize this distortion force to provide a more complete structural force for the drone.

[0044] It is understandable that the main body shape of each linear support member can be a straight body and parallel to the longitudinal axis of the fuselage 100. The straight body structure shape can reduce aerodynamic drag during flight. In addition, the cross-sectional shape of each linear support member can also be circular, elliptical, square, rectangular or any other suitable shape, and the utility model of the present application does not impose further restrictions on this.

[0045] In one embodiment, each linear support member is arranged parallel to each other, and each linear support member is parallel to the longitudinal axis of the drone fuselage 100 provided in the present application.

[0046] In another embodiment, the first linear support member 310 and the fourth linear support member 340 are symmetrically arranged on both sides of the fuselage 100, the second linear support member 320 and the third linear support member 330 are symmetrically arranged on both sides of the fuselage 100, and the first linear support member 310 is parallel to the second linear support member 320, the third linear support member 330 is parallel to the fourth linear support member 340, and the center lines of each linear support member intersect with the front end of the longitudinal axis of the drone fuselage 100 provided in the present application and are arranged at a certain angle.

[0047] In another embodiment, the first linear support member 310 and the fourth linear support member 340 are symmetrically arranged on both sides of the fuselage 100, the second linear support member 320 and the third linear support member 330 are symmetrically arranged on both sides of the fuselage 100, and the first linear support member 310 is parallel to the second linear support member 320, the third linear support member 330 is parallel to the fourth linear support member 340, and the center lines of each linear support member intersect with the tail end of the longitudinal axis of the drone fuselage 100 provided in the present application and are arranged at a certain angle.

[0048] Now refer to Figure 2-Figure 5 It can be found that in the drone provided by the present application, a thrust propeller is arranged at the tail end of the drone fuselage 100. The thrust propeller has a rotation axis that is perpendicular to the rotation axis of each propeller on each linear support. During high-speed flight, the thrust propeller is used to propel the drone, and at this time, each propeller on each linear support is locked and does not rotate.

[0049] Further, in the drone provided in the present application, a tail 400 is provided at the rear of the drone fuselage 100. Specifically, the tail 400 includes a left tail piece 410 abutting against the second linear support member 320 and a right tail piece 420 abutting against the third linear support member 330, which together constitute the inverted V-shaped tail 400 of the drone provided in the present application. In this embodiment, the left tail piece 410 and the right tail piece 420 are designed in an inverted V shape and form an angle with each other, and the angle formed between the left tail piece 410 and the right tail piece 420 is an acute angle. The inverted V-shaped tail 400 has the functions of both a vertical tail and a horizontal tail, and can simultaneously play a role in longitudinal stability during vertical takeoff and lateral stability during horizontal flight. When the rudders on both sides are deflected in the same direction, the inverted V-shaped tail 400 acts as an elevator. On the contrary, when the drone is deflected in different directions, the inverted V-shaped tail 400 acts as a rudder. Therefore, in order for the inverted V-shaped tail 400 to have better controllability and structural strength, in this embodiment, the left tail piece 410 and the right tail piece 420 are respectively integrally formed between the second linear support member 320 and the third linear support member 330.

[0050] It is worth noting that in this embodiment, the portion where the left tail fin 410 and the right tail fin 420 are connected to each other is in an arc-shaped transition, and the cross-sectional thickness of the arc-shaped transition can be slightly thicker than the average cross-sectional thickness of the left tail fin 410 and the right tail fin 420 to increase the structural strength of the transition connection. The left tail fin 410 is attached to the left side of the UAV fuselage 100 through the second linear support 320, and correspondingly, the right tail fin 420 is attached to the right side of the UAV fuselage 100 through the third linear support 330. The connection portion where the left tail fin 410 and the right tail fin 420 abut against each other is higher than the tail end of the fuselage 100, so that the angle area enclosed by the left tail fin 410 and the right tail fin 420 is located above the thrust propeller at the tail end of the fuselage 100.

[0051] Now continue to refer to Figure 1-Figure 5 A left rudder is provided on the left tail wing 410, which is used to control the pitch and turn of the aircraft. Similarly, a right rudder is provided on the right tail wing 420, which is also used to control the pitch and turn of the aircraft. The left rudder and the right rudder have the functions of the rudder and the elevator provided by ordinary drones. Therefore, in the drone provided by this embodiment, the rudder and the elevator provided by ordinary drones are omitted, so the pitch and turn of the drone can be controlled more efficiently. During the flight of the drone, the left rudder and the right rudder can control the pitch and turn of the aircraft in the same direction at the same time, or in different directions, that is, in opposite directions.

[0052] Further, in the present application, each linear support is provided with a propeller so that the UAV has the ability to take off and land vertically. In the embodiment shown in the figure, two propellers are provided on the first linear support 310, namely the first propeller 301 and the second propeller 302, and at the same time, two propellers are provided on the second linear support 320, namely the third propeller 303 and the fourth propeller 304. Correspondingly, two propellers are provided on the third linear support 330, namely the fifth propeller 305 and the sixth propeller 306, and two propellers are also provided on the fourth linear support 340, namely the seventh propeller 307 and the eighth propeller 308.

[0053] In one embodiment, the first propeller 301 is arranged at the upper front end of the first linear support 310, and the second propeller 302 is arranged at the upper end of the first linear support 310, so that the two propellers are arranged separately at the front and rear ends of the linear support so that there is no interference when the two propellers are running. Similarly, the third propeller 303 is arranged at the upper front end of the second linear support 320, the fourth propeller 304 is arranged at the upper end of the second linear support 320, the fifth propeller 305 is arranged at the upper front end of the third linear support 330, the sixth propeller 306 is arranged at the upper end of the third linear support 330, the seventh propeller 307 is arranged at the upper front end of the fourth linear support 340, and the eighth propeller 308 is arranged at the upper end of the fourth linear support 340. The reasons for such a layout are as described above and will not be repeated here.

[0054] In another embodiment, the first propeller 301 and the second propeller 302 are arranged at opposite sides of the front end and the rear end of the first linear support 310, respectively. Such arrangement at opposite sides of the front and rear ends of the linear support can increase the blade size of the propeller as much as possible, and even if the rotating blade ranges of the two propellers intersect when viewed from a top view, there will be no physical interference between the two propellers during operation. Similarly, the third propeller 303 and the fourth propeller 304 are arranged at opposite sides of the front end and the rear end of the second linear support 320, the fifth propeller 305 and the sixth propeller 306 are arranged at opposite sides of the front end and the rear end of the third linear support 330, and the seventh propeller 307 and the eighth propeller 308 are arranged at opposite sides of the front end and the rear end of the fourth linear support 340. The reasons for such a layout are as described above and will not be repeated here.

[0055] In some other embodiments, the first propeller 301 is located below the first linear support 310, and the second propeller 302 is located above the first linear support 310; the third propeller 303 is located above the second linear support 320, and the fourth propeller 304 is located below the second linear support 320; the fifth propeller 305 is located below the third linear support 330, and the sixth propeller 306 is located above the third linear support 330; the seventh propeller 307 is located above the fourth linear support 340, and the eighth propeller 308 is located below the fourth linear support 340.

[0056] Furthermore, each propeller on each linear support of the drone provided in the present application can have two blades each. When the drone enters the fixed-wing flight mode, these propellers are no longer needed to work. At this time, the blades of each propeller can be locked in a position parallel to the longitudinal position of the drone body 100 during high-speed flight, thereby achieving improved aerodynamic performance.

[0057] In the drone provided by the present application, each linear support is parallel to the longitudinal axis of the fuselage 100, so that each propeller arranged on each linear support is arranged in parallel with each other, thereby providing optimal stability and redundancy. When a propeller on a linear support in the drone fails, it is only necessary to turn off the corresponding propeller on another linear support corresponding to the failed propeller, so that the remaining working propellers remain balanced and the drone stays in the air. For example, when the first propeller 301 fails, the eighth propeller 308 can be turned off accordingly, so that the remaining working propellers remain balanced and the drone stays in the air.

[0058] Preferably, the drone provided by the present application may also be equipped with other accessories, such as a camera (not shown in the figure), for aerial surveillance and other data collection. The camera may be arranged at any other position on the drone.

[0059] Furthermore, in the drone of the present application, the end of the left main wing 210 away from the drone body 100 extends out of the middle position of the first linear support member 310, and correspondingly, the end of the right main wing 220 away from the drone body 100 extends out of the middle position of the fourth linear support member 340. It is worth noting that in the drone provided by the present application, the left main wing 210 and the right main wing 220 of the drone form an anhedral structure between the second linear support member 320 and the third linear support member 330. Specifically, the left main wing 210 tilts or bends upward within the range between the connection with the second linear support 320, and correspondingly, the right main wing 220 tilts or bends upward within the range between the connection with the third linear support 330. Regardless of the upward tilt or bend of the left main wing 210 or the upward tilt or bend of the right main wing 220, their other ends extend out of the first linear support 310 or the fourth linear support 340, thereby enclosing an upward diagonal structure with each other, so that the position where they are connected to the first linear support 310 or the fourth linear support 340 is higher than the position where they are connected to the second linear support 320 or the third linear support 330, so that the UAV can resist stronger wind resistance during flight and improve its aerodynamic profile.

[0060] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all implementation methods here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A drone, characterized in that: include: body; at least two linear supports connected to the fuselage; A left main wing and a right main wing, wherein the left main wing and the right main wing are connected to the fuselage; Two propellers are arranged on each of the at least two linear supports; Wherein, the propellers are arranged linearly; Each of the at least two linear support members is spaced apart from each other and distributed on both sides of the fuselage; The drone includes a first linear support, a second linear support, a third linear support and a fourth linear support; The first linear support is provided with a first propeller and a second propeller, the second linear support is provided with a third propeller and a fourth propeller, the third linear support is provided with a fifth propeller and a sixth propeller, and the fourth linear support is provided with a seventh propeller and an eighth propeller; The first propeller is located below the first linear support, and the second propeller is located above the first linear support; the third propeller is located above the second linear support, and the fourth propeller is located below the second linear support; the fifth propeller is located below the third linear support, and the sixth propeller is located above the third linear support; the seventh propeller is located above the fourth linear support, and the eighth propeller is located below the fourth linear support; The drone also includes a tail wing connected to the rear of the fuselage, the tail wing includes a left tail wing piece abutting against the second linear support member and a right tail wing piece abutting against the third linear support member, and the left tail wing piece and the right tail wing piece together form an inverted V shape.

2. The drone according to claim 1, characterized in that: The left main wing and the right main wing form a dihedral structure.

3. The drone according to claim 2, characterized in that: Each of the linear supports is parallel to the axis of the fuselage.

4. The drone according to claim 3, characterized in that: The cross section of each linear support is a cylinder.

5. The drone according to claim 1, characterized in that: The left main wing is provided with a first folding portion that turns upwards at one end away from the UAV fuselage, and the right main wing is provided with a second folding portion that turns upwards at one end away from the UAV fuselage.

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