Unmanned aerial vehicle

Abstract

An unmanned aerial vehicle, comprising: a body (100); at least two linear support members (310, 320, 330, 340), which are connected to the body (100); and a left main wing (210) and a right main wing (220), which are connected to the body (100), wherein two propellers (301, 302, 303, 304, 305, 306, 307, 308) are provided on each linear support member (310, 320, 330, 340). In this way, during a takeoff process of the unmanned aerial vehicle, a better lift force can be provided; moreover, when any one of one or a plurality of propellers (301, 302, 303, 304, 305, 306, 307, 308) fails, only the faulty propeller is required to be shut down, and the unmanned aerial vehicle can continue to operate, such that built-in configuration redundancy is realized, and thus the flight distance of the unmanned aerial vehicle is greatly extended and the endurance capability thereof is significantly improved.

Description

A drone Technical Field

[0001] The present application relates to the technical field of drones, and in particular to a drone. Background Art

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control and self-contained programmable control devices. UAVs in existing technology are primarily categorized as fixed-wing, multi-rotor, and compound-wing. In practical applications, fixed-wing and multi-rotor drones each have their own advantages. Fixed-wing UAVs, characterized by long flight time and high altitude flight, are widely used in surveying and mapping, geology, petroleum, agriculture, and forestry. Multi-rotor UAVs, on the other hand, are capable of vertical takeoff and landing, as well as hovering, and are primarily suitable for low-altitude, low-speed operations requiring vertical takeoff and landing, as well as hovering.

[0003] With the rapid development of drone technology, drones are becoming increasingly versatile and integrated into practical operations across various industries. However, the increasing complexity of drone applications is also posing greater challenges to drone performance. Currently, composite-wing drones are becoming a hot topic in the drone industry, as they offer both vertical takeoff and landing capabilities and long flight times.

[0004] Although existing drones 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, existing drones are limited by the number of linear supports and propellers, and during 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 existing drones.

[0005] Application Contents

[0006] One purpose of this application is to provide a drone with improved flight performance.

[0007] To achieve this goal, this application adopts the following technical solutions:

[0008] A drone, comprising:

[0009] body;

[0010] at least two linear supports connected to the fuselage;

[0011] A left main wing and a right main wing, wherein the left main wing and the right main wing are connected to the fuselage;

[0012] Two propellers are arranged on each of the at least two linear supports;

[0013] Wherein, the propellers are arranged linearly;

[0014] The at least two linear support members are distributed on both sides of the fuselage.

[0015] Preferably, the left main wing and the right main wing form a dihedral structure.

[0016] Preferably, the at least two linear supports include a first linear support, a second linear support, a third linear support and a fourth linear support.

[0017] Preferably, each of the linear supports is parallel to the axis of the fuselage.

[0018] Preferably, the cross section of each linear support member is cylindrical.

[0019] Preferably, the UAV also includes a tail wing connected to the rear of the fuselage, and 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-shaped tail wing.

[0020] Preferably, 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.

[0021] Preferably, the propellers are arranged at the same side of both ends of the linear supports.

[0022] Preferably, the propellers are arranged at opposite sides of both ends of the linear supports.

[0023] Preferably, the left main wing is provided with a first folding portion that turns upward at the end away from the drone fuselage, and the right main wing is provided with a second folding portion that turns upward at the end away from the drone fuselage.

[0024] Beneficial effects of this application:

[0025] This application configures a total of four linear supports and eight lift propellers on both sides of the fuselage, which can provide better lift during the take-off of the drone. At the same time, a total of eight propellers are configured on the linear supports, with four propellers on the left and four propellers on the right arranged linearly to form four parallel arrays. In this way, when any one or more propellers fails, the drone only needs to shut down the corresponding faulty propeller and continue to work, thereby achieving built-in configuration redundancy, thereby significantly improving the flight distance and endurance of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] FIG1 is a schematic diagram of the UAV provided in this application;

[0027] FIG2 is a top view of the UAV provided in this application;

[0028] FIG3 is a schematic diagram of the UAV provided in this application;

[0029] FIG4 is a side view of the drone provided by the present application;

[0030] FIG5 is a front view of the drone provided in this application. DETAILED DESCRIPTION

[0031] The technical solution of the present application is further described below in conjunction with the accompanying drawings and implementation methods. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application and are not intended to limit the present application. It should also be noted that, for ease of description, the accompanying drawings only show portions relevant to the present application, not all of them.

[0032] In the description of this application, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed or detachable connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application in specific contexts.

[0033] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0034] In the description of this embodiment, the terms "upper," "lower," "right," and other orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely for ease of description and simplified operation. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first" and "second" are used solely for descriptive purposes and have no special meanings.

[0035] As shown in Figure 1, the present application generally depicts the overall structure of a drone. Overall, the drone comprises a fuselage 100, which features an aerodynamic design that utilizes its contours to minimize air resistance during flight. A left main wing 210 is attached to the left side of fuselage 100, and a corresponding right main wing 220 is attached to the right side of fuselage 100. The left and right main wings 210 and 220 are each attached to the sides of fuselage 100.

[0036] In one embodiment, the left main wing 210 and the right main wing 220 are each 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.

[0037] In another embodiment, the left main wing 210 and the right main wing 220 are each attached to the front end portion of each side of the fuselage 100, approximately located at a position approximately one-third of the length of the entire fuselage 100 from the front end of the fuselage 100, and are detachably connected to the fuselage 100, allowing the wings to be directly and quickly disassembled and assembled from the fuselage 100.

[0038] In one embodiment, the left main wing 210 and the right main wing 220 are respectively attached to the middle portion of both sides of the fuselage 100 , approximately midway between the front and rear ends of the fuselage 100 , and are integrally formed with the fuselage 100 .

[0039] In another embodiment, the left main wing 210 and the right main wing 220 are each attached to the middle portion of both sides of the fuselage 100, approximately halfway between the front and rear ends of the fuselage 100, and are detachably connected to the fuselage 100, allowing the wings to be directly and quickly disassembled and assembled from the fuselage 100.

[0040] In the drone provided in this application, the left main wing 210 and the right main wing 220 are used to provide lift for the drone during level flight. In this application, the two main wings are fixed, meaning they cannot rotate relative to the fuselage 100 and are symmetrically arranged on either side of the fuselage 100 along the longitudinal axis of the fuselage 100. Regarding the shape of the main wings, in this embodiment, the two main wings have a straight wing structure. In other embodiments, the two main wings have a delta wing structure, etc. The drone provided in this application does not further limit the structure of the two main wings.

[0041] Continuing with FIG. 1 , it can be seen that in the drone provided herein, the left main wing 210 is provided with an upwardly tilted first folding portion 201 at the end away from the drone body 100. The first folding portion 201 is integrally formed with the left main wing 210. Correspondingly, the right main wing 220 is provided with an upwardly tilted second folding portion 202 at the end away from the drone body 100. The second folding portion 202 is integrally formed with the left main wing 210.

[0042] 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.

[0043] Furthermore, the drone provided in the present application also includes two left linear supports, namely a first linear support 310 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 away from the fuselage 100, each located at the right end of the drone fuselage 100.

[0044] 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.

[0045] Preferably, each linear support member is made of a suitable material to withstand the physical demands of flight and 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. Specifically, during flight, air passing through the left and right main wings 210, 220, and the up and down motion of the left and right main wings 210, 220, exerts a twisting force on the drone fuselage 100. Each linear support member minimizes this twisting force, thereby providing a more complete structural support for the drone.

[0046] It is understood that the main body of each linear support member can be a straight body parallel to the longitudinal axis of the fuselage 100. The straight body structure 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 present application does not impose any further limitations on this.

[0047] In one embodiment, the linear support members are arranged parallel to each other, and each linear support member is parallel to the longitudinal axis of the drone body 100 provided in the present application.

[0048] 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, and the third linear support member 330 is parallel to the fourth linear support member 340. The center lines of each linear support member intersect with the front end of the longitudinal axis of the drone fuselage 100 provided in this application and are arranged at a certain angle.

[0049] 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, and the third linear support member 330 is parallel to the fourth linear support member 340. The center lines of each linear support member intersect with the tail end of the longitudinal axis of the drone fuselage 100 provided in this application and are arranged at a certain angle.

[0050] Referring now to Figures 2-5 , it can be seen that in the drone provided herein, a thrust propeller is disposed at the tail end of the drone fuselage 100. This thrust propeller has a rotation axis perpendicular to the rotation axes of the propellers on the linear supports. During high-speed flight, the thrust propeller is used to propel the drone, while the propellers on the linear supports are locked and do not rotate.

[0051] Furthermore, in the drone provided in this application, a tail wing 400 is disposed at the rear of the drone body 100. Specifically, the tail wing 400 includes a left tail wing piece 410 abutting against the second linear support member 320 and a right tail wing piece 420 abutting against the third linear support member 330. Together, these tail wing pieces 410 and 420 form an inverted V-shaped tail wing 400 of the drone provided in this application. In this embodiment, the left tail wing piece 410 and the right tail wing piece 420 are designed in an inverted V-shape and form an angle with each other, and the angle formed between the left tail wing piece 410 and the right tail wing 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 provide longitudinal stability in vertical takeoff and lateral stability in 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 to enable 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 320 and the third linear support 330.

[0052] It is noteworthy that in this embodiment, the connection between the left and right tail fins 410 and 420 forms an arc-shaped transition. The cross-sectional thickness of the arc-shaped transition can be slightly thicker than the average cross-sectional thickness of the left and right tail fins 410 and 420, thereby increasing the structural strength of the transition. The left tail fin 410 is attached to the left side of the drone fuselage 100 via the second linear support 320. Correspondingly, the right tail fin 420 is attached to the right side of the drone fuselage 100 via the third linear support 330. The connection between the left and right tail fins 410 and 420 is higher than the tail end of the fuselage 100, so that the angled area enclosed by the left and right tail fins 410 and 420 is located above the thrust propeller at the tail end of the fuselage 100.

[0053] Continuing with reference to FIG1-FIG5, a left rudder is provided on the left tail fin 410 for controlling the pitch and turn of the aircraft. Similarly, a right rudder is provided on the right tail fin 420 for controlling the pitch and turn of the aircraft. The left and right rudders simultaneously have the functions of the rudder and elevator surfaces provided on ordinary drones. Therefore, in the drone provided by this embodiment, the rudder and elevator surfaces provided on 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 and right rudders can simultaneously control the pitch and turn of the aircraft in the same direction, or they can control the pitch and turn of the aircraft in different directions, i.e., in opposite directions.

[0054] Furthermore, in this application, each linear support is equipped with a propeller to enable vertical takeoff and landing of the drone. In the embodiment shown in the figure, the first linear support 310 is equipped with two propellers, namely the first propeller 301 and the second propeller 302. Meanwhile, the second linear support 320 is equipped with two propellers, namely the third propeller 303 and the fourth propeller 304. Correspondingly, the third linear support 330 is equipped with two propellers, namely the fifth propeller 305 and the sixth propeller 306. Furthermore, the fourth linear support 340 is also equipped with two propellers, namely the seventh propeller 307 and the eighth propeller 308.

[0055] 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 rear end of the first linear support 310. This separate arrangement at the front and rear ends of the linear support prevents interference between the two propellers during operation. 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 rear 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 rear 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 rear end of the fourth linear support 340. The reasons for this arrangement are as described above and will not be repeated here.

[0056] In another embodiment, the first propeller 301 and the second propeller 302 are arranged on opposite sides of the front and rear ends of the first linear support 310, respectively. This arrangement on opposite sides of the front and rear ends of the linear support maximizes the propeller blade size. Even if the rotating blade ranges of the two propellers intersect when viewed from a top view, the two propellers will not physically interfere with each other during operation. Similarly, the third propeller 303 and the fourth propeller 304 are arranged on opposite sides of the front and rear ends of the second linear support 320, the fifth propeller 305 and the sixth propeller 306 are arranged on opposite sides of the front and rear ends of the third linear support 330, and the seventh propeller 307 and the eighth propeller 308 are arranged on opposite sides of the front and rear ends of the fourth linear support 340. The reasons for this arrangement are as described above and will not be repeated here.

[0057] Furthermore, each propeller on each linear support of the drone provided in the present application can have two blades. 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.

[0058] In the drone provided herein, each linear support member is parallel to the longitudinal axis of the fuselage 100, allowing the propellers arranged on each linear support member to be arranged parallel to each other, thereby providing optimal stability and redundancy. If a propeller on a linear support member in the drone fails, only the corresponding propeller on the corresponding linear support member needs to be shut down to maintain balance with the remaining functioning propellers, allowing the drone to remain airborne. For example, if the first propeller 301 fails, the eighth propeller 308 can be shut down to maintain balance with the remaining functioning propellers, allowing the drone to remain airborne.

[0059] 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 location on the drone.

[0060] Furthermore, in the drone of the present application, the end of the left main wing 210 that is away from the drone body 100 extends out from the middle of the first linear support 310. Correspondingly, the end of the right main wing 220 that is away from the drone body 100 extends out from the middle of the fourth linear support 340. It is worth noting that in the drone provided by the present application, the left and right main wings 210, 220 of the drone form a dihedral structure between the second linear support 320 and the third linear support 330. Specifically, the left main wing 210 tilts or bends upward within the range between the connection with the second linear support 320. Correspondingly, the right main wing 220 tilts or bends upward within the range between the connection with the third linear support 330. Regardless of whether the left main wing 210 tilts or bends upward or the right main wing 220 tilts or bends upward, their other ends extend out of the first linear support 310 or the fourth linear support 340, thereby forming an upward dihedral 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. This enables the UAV to resist stronger wind resistance during flight and improve its aerodynamic profile.

[0061] Obviously, the above embodiments of the present application are merely examples for the purpose of clearly illustrating the present application, and are not intended to limit the embodiments of the present application. For those skilled in the art, other variations or modifications can be made based on the above description. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present application shall be included within the scope of protection of the claims of the present application.

Claims

1. A drone, characterized in that: include: Body (100); at least two linear supports, the at least two linear supports being connected to the fuselage (100); A left main wing (210) and a right main wing (220), wherein the left main wing (210) and the right main wing (220) are connected to the fuselage (100); Two propellers are arranged on each of the at least two linear supports; Wherein, the propellers are arranged linearly; The at least two linear support members are distributed on both sides of the fuselage (100).

2. The drone according to claim 1, characterized in that: The left main wing (210) and the right main wing (220) form a dihedral structure.

3. The drone according to claim 2, characterized in that: The drone comprises a first linear support (310), a second linear support (320), a third linear support (330) and a fourth linear support (340).

4. The drone according to claim 3, characterized in that: Each of the linear supports is parallel to the axis of the fuselage (100).

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

6. The drone according to claim 1, characterized in that: The drone also includes a tail wing (400) connected to the rear of the fuselage (100), the tail wing (400) including a left tail wing piece (410) abutting against the second linear support member (320) and a right tail wing piece (420) abutting against the third linear support member (330), the left tail wing piece (410) and the right tail wing piece (420) together forming an inverted V shape.

7. The drone according to claim 6, characterized in that: The first linear support (310) is provided with a first propeller (301) and a second propeller (302), the second linear support (320) is provided with a third propeller (303) and a fourth propeller (304), the third linear support (330) is provided with a fifth propeller (305) and a sixth propeller (306), and the fourth linear support (340) is provided with a seventh propeller (307) and an eighth propeller (308).

8. The drone according to claim 7, characterized in that: The propellers are arranged at the same sides of both ends of the linear supports.

9. The drone according to claim 7, characterized in that: The propellers are arranged at opposite sides of both ends of the linear supports.

10. The drone according to claim 1, characterized in that: The left main wing (210) is provided with a first folding portion (201) that turns upward at an end away from the drone fuselage (100), and the right main wing (220) is provided with a second folding portion (202) that turns upward at an end away from the drone fuselage (100).

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