Drones and their multi-rotor flight platforms

Abstract

This application relates to the technology of drones and discloses a drone and its multi-rotor wing flight platform. The multi-rotor wing flight platform according to this application includes at least one pair of arms arranged symmetrically with respect to a central axis, each arm having a plurality of vertical takeoff and landing power units inside; main wings arranged symmetrically with respect to a central axis and connected to at least one pair of arms; and canard wings and a central power distribution room connected to a pair of arms near the central axis and forming a closed structure integrally molded with the pair of arms. In this application, by configuring the canard wings, arms and central power distribution room as a closed structure integrally molded, the rigidity of the motor mounting structure on the arms is significantly improved.

Description

Technical Field

[0005] ,

[0001] This application relates to the technical field of drones, particularly to drones and their multi-rotor flight platforms.

Background Art

[0002] Currently, the body structure of unmanned aerial vehicles is assembled from components such as a tail fin, arms, and a central power distribution chamber. For assembly, many fastening means need to be combined, which increases the weight of the drone. Also, it is necessary to perform regular maintenance to detect looseness. Otherwise, it may lead to safety accidents.

Summary of the Invention

Problems to be Solved by the Invention

[0003] An object of this application is to provide a drone and its multi-rotor flight platform. In the multi-rotor flight platform according to this application, by configuring it as a closed structure with integral molding of the tail fin, arms, and central power distribution chamber, the rigidity of the mounting structure of the motors on the inner arms is significantly improved.

Means for Solving the Problems

[0004] To solve the above technical problems, this application provides a multi-rotor flight platform including at least one pair of arms symmetrically arranged about a central axis, with a plurality of vertical takeoff and landing power devices provided inside each of the arms; a main wing symmetrically arranged about the central axis and connected to the at least one pair of arms; and a tail fin and a central power distribution chamber respectively connected to a pair of arms close to the central axis and forming a closed structure integrally molded with the pair of arms.

[0005] This application provides a drone including the above multi-rotor flight platform and a fuselage connected to the bottom of the multi-rotor flight platform.

[0006] Selectively, the cross-sectional shape of the arm is streamlined, and the thickness of the arm (1) is 1.5 times or more its width.

[0007] Selectively, a pair of arms near the central axis includes an inner left arm and an inner right arm, the inner left arm includes a first left arm portion and a second left arm portion, and the inner right arm includes a first right arm portion and a second right arm portion. The forewing and central power distribution chamber, together with the first left arm portion and the first right arm portion, constitute an integrally molded closed structure.

[0008] Selectively, the first left arm portion is provided with at least one pair of vertical takeoff and landing power units, and the first right arm portion is provided with at least one pair of vertical takeoff and landing power units.

[0009] Selectively, the at least pair of arms includes a pair of inner arms and a pair of outer arms, wherein the pair of inner arms are close to the central axis and the pair of outer arms are farther from the central axis.

[0010] Selectively, each of the arms is provided with a mounting notch, and the main wing is provided with a wing connection portion that is connected to the edge of each of the mounting notches.

[0011] Selectively, a horizontal flight power unit is installed on the tail section of a pair of arms located near the central axis.

[0012] Selectively, the canard further includes a pair of canard extensions, each of which protrudes from the pair of arms and exhibits a streamlined mechanism that gradually decreases in size away from the canard.

[0013] Selectively, the distance between the central power distribution room and the canard wing is half the length of the arm closest to the central axis.

[0014] In the multi-rotor wing flight platform according to this application, the canard, arms, and central power distribution room are configured as a closed-type structure in which they are integrally molded, thereby significantly improving the rigidity of the motor mounting structure on the closed-type structure. [Brief explanation of the drawing]

[0015] [Figure 1] A schematic diagram of the structure of a multi-rotor wing flight platform according to an embodiment of this application is shown. [Figure 2] A perspective view of the Type A structure of the multi-rotor wing flight platform according to an embodiment of this application is shown. [Figure 3] This shows a top view of the Type A structure of a multi-rotor wing flight platform according to an embodiment of this application. [Figure 4] This shows a cross-sectional view of the arm of a multi-rotor wing flight platform according to an embodiment of this application. [Modes for carrying out the invention]

[0016] The technical solutions of this application will be further described below by embodiments. It should be understood that the specific embodiments described herein are merely for the purpose of interpreting this application. Furthermore, for the sake of clarity, it should be noted that the drawings show only some of the structures relevant to this application, not all of them.

[0017] In the description of this application, unless otherwise explicitly defined or limited, the terms "attach," "connect," and "connect" should be understood in a broad sense. For example, a connection may be fixed, detachable, mechanical, electrical, direct, indirectly via an intermediate medium, or involve internal communication between two elements. A person skilled in the art will understand the specific meaning of these terms in this application depending on the specific situation.

[0018] In this application, unless otherwise explicitly defined or limited, the phrase "above" or "below" the second feature of the first feature may include cases where the first and second features are in direct contact, or cases where they are not in direct contact but are in contact through another feature between them. Furthermore, the phrase "above," "above," and "on the top surface" of the second feature may include cases where the first feature is directly above and diagonally above the second feature, or simply means that the horizontal height of the first feature is greater than that of the second feature. The phrase "below," "below," and "on the bottom surface" of the second feature may include cases where the first feature is directly below and diagonally below the second feature, or simply means that the horizontal height of the first feature is less than that of the second feature.

[0019] Embodiments of this application will be described below with reference to the drawings. As shown in Figures 1 to 3, the multi-rotor wing flight platform according to the embodiment of this application includes two pairs of arms 1, a main wing 2, a canard 3, and a central power distribution room 4. The two pairs of arms 1 are arranged symmetrically with respect to a central axis S, and multiple vertical takeoff and landing power units 5 are provided inside each of the arms 1. The main wing 2 is arranged symmetrically with respect to the central axis S and connected in series to the two pairs of arms 1. The canard 3 and the central power distribution room 4 are each connected to a pair of arms 1 that are close to the central axis S, and together with this pair of arms 1, they form a closed structure that is integrally molded.

[0020] Specifically, the two pairs of arms 1 include a pair of inner arms 11 and a pair of outer arms 12. The pair of inner arms 11 are close to the central axis S, while the pair of outer arms 12 are further away from the central axis S. As shown in Figure 1, the pair of outer arms 12 are provided separately on both sides of the pair of inner arms 11. The inner arms 11 include an inner left arm 11L and an inner right arm 11R, and the outer arms 12 include an outer left arm 12L and an outer right arm 12R. As shown in Figure 2, the inner left arm 11L includes a first left arm portion 111L and a second left arm portion 112L, and the inner right arm 11R includes a first right arm portion 111R and a second right arm portion 112R. Each of the arms 1 is provided with a mounting notch, and the main wing 2 is provided with wing connection portions that are connected to the edges of each mounting notch, thereby connecting the main wing 2 to the two pairs of arms 1. Consequently, the second left arm section 112L and the second right arm section 112R behind the main wing 2 are also shortened, resulting in a shorter moment arm of the motor's tail overhang, reducing the pitching moment and improving mounting rigidity. The canard wing 3 and the central power distribution room 4 form a closed structure integrally molded with the first left arm section 111L and the first right arm section 111R, significantly improving the strength of the main structure and clearly improving the rigidity of the motor mounting structure on the arms. Furthermore, the distance between the outer and inner arms is greater than the sum of the rotation radius of the lift propeller of the vertical takeoff and landing power unit mounted on the inner arm, the rotation radius of the lift propeller mounted on the outer arm, and the convection gap, and the convection gap is 8% to 15% of the maximum propeller diameter between the outer and inner arms, thereby balancing structural strength and pneumatic efficiency while meeting the requirements for structural strength and pneumatic efficiency.

[0021] As shown in Figure 3, the first left arm section 111L is equipped with a pair of vertical takeoff and landing power units 5, and the first right arm section 111R is equipped with a pair of vertical takeoff and landing power units 5. Specifically, the vertical takeoff and landing power units 5 are rotary-wing motors. In addition, a horizontal flight power unit 6 is installed in the tail section of the inner arm 11, and the horizontal flight power unit 6 is specifically a thrust motor.

[0022] As shown in FIG. 4, the vertical takeoff and landing power device 5 includes a propeller 50. The cross-sectional shape of the arm 1 facing the propeller 50 is streamlined, preferably presenting a water droplet-shaped structure that gradually decreases from top to bottom. Also, the thickness M of the arm 1 is 1.5 times or more of its width N. The water droplet-shaped streamlined structure can reduce the eddy flow formed by the downwash parling of the propeller being affected by the drone body, reduce the loss of the lift motor, and increase the efficiency of the lift motor.

[0023] Furthermore, by making the center of gravity of the central power distribution chamber 4 coincide with the center of gravity of the multi-rotor flight platform, the control calculation amount of the flight control system is reduced, which is helpful for the attitude control of the drone by the flight control system and reduces the calculation stress of the flight control system.

[0024] Furthermore, as shown in FIG. 1, the tail wing 3 further includes a pair of tail wing extension parts 30. The pair of tail wing extension parts 30 respectively project a pair of inner arms 11 and present a streamlined mechanism that gradually decreases in the direction away from the tail wing 3. Specifically, the tail wing extension parts 30 are provided on the other side facing the tail wing 3 of the inner left arm 11L and the other side facing the tail wing 3 of the inner right arm 11R. This pair of tail wing extension parts 30 presents a structure that gradually decreases in the direction away from the tail wing. The tail wing extension parts 30 can increase the lift of the drone in the fixed-wing state, which is helpful for leveling the drone. Leveling achieves the purpose of stabilizing the attitude and flight path of the drone by finely adjusting the operating surfaces (ailerons, elevators, rudders, etc.), avoids pitching moment, and further avoids affecting the flight efficiency by compensating for the pitching moment.

[0025] This application provides a drone including the above multi-rotor flight platform and a fuselage connected to the bottom of the multi-rotor flight platform. In the multi-rotor flight platform of the drone according to this application, by configuring the tail wing, arm, and central power distribution chamber as an integrally formed closed structure, the rigidity of the mounting structure of the motor on the arm is significantly improved.

[0026] The above embodiments are merely illustrative examples illustrating the principles and effects of the present application. A person skilled in the art can modify or alter the above embodiments without violating the purposes of this application. Accordingly, all equivalent modifications or alterations made by a person skilled in the art without departing from the purposes disclosed herein shall still be included in the claims of this application.

Claims

1. At least one pair of arms (1) are arranged symmetrically with respect to the central axis (S), A pair of arms (1) each having multiple vertical takeoff and landing power units (5) inside, The main wings (2) are arranged symmetrically with respect to the central axis (S) and connected to at least one pair of arms (1), A multi-rotor flight platform characterized by including a canard (3) and a central power distribution room (4) which are connected to a pair of arms (1) near the central axis (S) and form a closed structure integrally molded together with the pair of arms (1).

2. The multi-rotor wing flight platform according to claim 1, characterized in that the cross-sectional shape of the arm (1) is streamlined and the thickness of the arm (1) is 1.5 times or more its width.

3. The pair of arms (1) near the central axis (S) includes an inner left arm (11L) and an inner right arm (11R), and the inner left arm (11L) includes a first left arm portion (111L) and a second left arm portion (112L). The multi-rotor flight platform according to claim 1, characterized in that the inner right arm (11R) includes a first right arm portion (111R) and a second right arm portion (112R), and the canard (3) and central power distribution room (4) form a closed structure integrally molded together with the first left arm portion (111L) and the first right arm portion (111R).

4. The multi-rotor flight platform according to claim 3, characterized in that the first left arm portion (111L) is provided with at least one pair of vertical takeoff and landing power units (5), and the first right arm portion (111R) is provided with at least one pair of vertical takeoff and landing power units (5).

5. The multi-rotor flight platform according to claim 1, characterized in that the at least one pair of arms (1) includes a pair of inner arms (11) and a pair of outer arms (12), the pair of inner arms (11) being close to the central axis (S), the pair of outer arms (12) being far from the central axis (S), and the distance between the outer arms and the inner arms being greater than the sum of the rotation radius of the lift propellers of the vertical take-off and landing power unit attached to the inner arms, the rotation radius of the lift propellers attached to the outer arms, and the convection gap, the convection gap being 8% to 15% of the maximum propeller diameter between the outer arms and the inner arms.

6. The multi-rotor wing flight platform according to claim 1, characterized in that each of the arms (1) is provided with a mounting notch, and the main wing (2) is provided with a wing connection portion that is connected to the edge of each of the mounting notches.

7. The multi-rotor wing flight platform according to claim 1, characterized in that a horizontal flight power unit (6) is installed at the tail portion of a pair of arms (1) close to the central axis (S).

8. The multi-rotor wing flight platform according to claim 1, wherein the canard (3) further includes a pair of canard extensions (30), each of which protrudes from the pair of arms (1) and exhibits a streamlined mechanism that gradually decreases in size in the direction away from the canard (3).

9. The multi-rotor wing flight platform according to claim 5, characterized in that the distance between the central power distribution room (4) and the canard wing (3) is half the length of the arm (1) closest to the central axis (S).

10. A drone comprising a multi-rotor wing flight platform according to any one of claims 1 to 9, and a fuselage connected to the bottom of the multi-rotor wing flight platform.

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