Aircraft and multi-rotor flight platform therefor

Abstract

An aircraft and a multi-rotor flight platform therefor. The multi-rotor flight platform comprises at least one pair of aircraft arms (1), wherein the at least one pair of aircraft arms (1) are symmetrically arranged around a central axis (S), and the inside of each aircraft arm (1) is provided with a plurality of vertical takeoff and landing power devices (5); main aircraft wings (2), wherein the main aircraft wings (2) are symmetrically arranged around the central axis (S) and connect the at least one pair of aircraft arms (1); a canard (3) and a central avionics compartment (4), wherein both the canard (3) and the central avionics compartment (4) connect one pair of aircraft arms (1) close to the central axis (S) and, together with said one pair of aircraft arms (1), form an integral closed structure. By integrating the canard (3), the aircraft arms (1), and the central avionics compartment (4) into an integral closed structure, the present application enables the stiffness of a mounting structure for electric motors on the aircraft arms (1) to be significantly enhanced.

Description

Aircraft and multi-rotor flight platform Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft and a multi-rotor flight platform thereof. Background Art

[0002] Currently, the main structure of the UAV is assembled by assembling parts such as canards, arms, and central avionics compartments. The assembly process requires a large number of fastening devices, which not only increases the weight of the aircraft, but also requires regular maintenance to check for looseness, otherwise it is easy to cause safety accidents.

[0003] Summary of the Invention

[0004] The purpose of the present application is to provide an aircraft and a multi-rotor flight platform thereof. The multi-rotor flight platform of the present application significantly improves the rigidity of the installation structure of the motor on the inner arm by forming the canard, arm and central avionics cabin into an integrated closed structure.

[0005] In order to solve the above technical problems, the present application provides a multi-rotor flight platform, including: at least one pair of arms, which are symmetrically arranged around a central axis and each of the arms is equipped with multiple vertical lift power devices; main wings, which are symmetrically arranged around the central axis and connected to the at least one pair of arms; canards and a central avionics compartment, which are respectively connected to a pair of arms close to the central axis and form an integrally formed closed structure with the pair of arms.

[0006] The present application provides an aircraft, comprising the above-mentioned multi-rotor flight platform and a fuselage, wherein the fuselage is connected to the bottom of the multi-rotor flight platform.

[0007] Optionally, the cross-sectional shape of the arm is streamlined, and the thickness of the arm is more than 1.5 times its width.

[0008] Optionally, a pair of arms close to the central axis include 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, the inner right arm includes a first right arm portion and a second right arm portion, and the canard and central wing box form an integrally molded closed structure with the first left arm portion and the first right arm portion.

[0009] Optionally, the first left arm portion is provided with at least a pair of vertical lifting power devices, and the first right arm portion is provided with at least a pair of vertical lifting power devices.

[0010] Optionally, the at least one pair of arms includes a pair of inner arms and a pair of outer arms, the pair of inner arms are close to the central axis, and the pair of outer arms are far away from the central axis.

[0011] Optionally, each of the arms is provided with a mounting notch, and the main wing is provided with a wing connecting portion corresponding to the edge portion of each of the mounting notches.

[0012] Optionally, a level flight power device is provided at the tail of a pair of arms close to the central axis.

[0013] Optionally, the canard further includes a pair of canard extensions, and the pair of canard extensions respectively pass through the pair of aircraft arms and present a streamlined structure that gradually decreases in a direction away from the canard.

[0014] Optionally, the distance between the central avionics compartment and the canard is half of the length of the aircraft arm close to the central axis.

[0015] The multi-rotor flight platform of the present application forms an integrated closed structure by forming the canard, the arm and the central avionics compartment. The closed structure significantly improves the installation structural rigidity of the motor on the closed structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG1 is a schematic structural diagram of a multi-rotor flight platform according to an embodiment of the present application;

[0017] FIG2 is a perspective view of an A-type structure of a multi-rotor flight platform according to an embodiment of the present application;

[0018] FIG3 is a top view of the A-type structure of the multi-rotor flight platform according to an embodiment of the present application;

[0019] FIG4 is a cross-sectional view of the arm of the multi-rotor flight platform according to an embodiment of the present application. DETAILED DESCRIPTION

[0020] The following embodiments further illustrate the technical solutions of the present application. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application. It should also be noted that, for ease of description, only the parts relevant to the present application are shown in the accompanying drawings, not all of them.

[0021] 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.

[0022] 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.

[0023] The following describes an embodiment of the present application with reference to the accompanying drawings. As shown in Figures 1 to 3, the multi-rotor flight platform of the present embodiment includes: two pairs of arms 1, main wings 2, canards 3, and a central avionics compartment 4. The two pairs of arms 1 are symmetrically arranged around a central axis S, and each arm 1 is equipped with multiple vertical lift power units 5. The main wings 2 are symmetrically arranged about the central axis S and are connected in series with the two pairs of arms 1. The canards 3 and the central avionics compartment 4 are respectively connected to the pair of arms 1 near the central axis S, forming an integral, closed structure with the pair of arms 1.

[0024] Specifically, the two pairs of arms 1 include a pair of inner arms 11 and a pair of outer arms 12. The inner arms 11 are located closer to the central axis S, while the outer arms 12 are located further away from the central axis S. As shown in FIG1 , the outer arms 12 are positioned on either side of the inner arms 11. The inner arms 11 include an inner left arm 11L and an inner right arm 11R, while the outer arms 12 include an outer left arm 12L and an outer right arm 12R. As shown in FIG2 , the inner left arm 11L includes a first left arm portion 111L and a second left arm portion 112L, while the inner right arm 11R includes a first right arm portion 111R and a second right arm portion 112R. Each arm 1 is provided with a mounting notch, and the main wing 2 is provided with a wing connection portion that connects to the edge of each mounting notch, thereby connecting the main wing 2 to the two pairs of arms 1. The second left arm section 112L and second right arm section 112R behind the main wing 2 are also shortened, thereby shortening the moment arm of the motor tail boom, reducing pitching moment while improving installation rigidity. The canard 3 and central avionics compartment 4, together with the first left arm section 111L and the first right arm section 111R, form a one-piece, closed structure, significantly enhancing the strength of the main structure and significantly increasing the rigidity of the motor mounting structure on the arm. Furthermore, the distance between the outer and inner arms is at least greater than the sum of the rotation radius of the lift propeller of the vertical propulsion unit mounted on the inner arm, the rotation radius of the lift propeller mounted on the outer arm, and the convection clearance. The convection clearance is 8% to 15% of the maximum propeller diameter of the outer and inner arms. This achieves a balance between structural strength and aerodynamic efficiency, meeting both structural strength and aerodynamic efficiency requirements.

[0025] As shown in Figure 3, the first left arm portion 111L is equipped with a pair of vertical lift propulsion units 5, and the first right arm portion 111R is equipped with a pair of vertical lift propulsion units 5. The vertical lift propulsion units 5 are specifically rotor motors. Furthermore, the tail portion of the inner arm 11 is equipped with a horizontal flight propulsion unit 6, specifically a thrust motor.

[0026] As shown in Figure 4, the vertical take-off propulsion system 5 includes a propeller 50. The cross-section of the arm 1, which faces the propeller 50, is streamlined, preferably exhibiting a teardrop-shaped structure that tapers from top to bottom. The thickness M of the arm 1 is at least 1.5 times its width N. This streamlined teardrop-shaped structure reduces vortices formed by the propeller downwash being disturbed by the aircraft fuselage, thereby reducing losses in the lift motor and increasing its efficiency.

[0027] Furthermore, the center of gravity of the central avionics cabin 4 is consistent with the center of gravity of the multi-rotor flight platform, thereby reducing the amount of flight control calculations, facilitating the flight control to control the aircraft attitude, reducing the calculation pressure of the flight control, and thus reducing the calculation pressure of the flight control.

[0028] Furthermore, as shown in Figure 1, the canard 3 also includes a pair of canard extensions 30. The pair of canard extensions 3 extend through the pair of inner arms 11 and present a streamlined structure that gradually decreases in size as they move away from the canard 3. Specifically, the canard extensions 30 are located on the other side of the inner left arm 11L opposite the canard 3, and on the other side of the inner right arm 11R opposite the canard 3. The pair of canard extensions 30 present a structure that gradually decreases in size as they move away from the canard. The canard extensions 3 can enhance the lift of the aircraft in the fixed-wing configuration, facilitating aircraft trim. Trimming involves fine-tuning the control surfaces (ailerons, elevators, rudder, etc.) to stabilize the aircraft's attitude and heading, avoiding pitching moments and, consequently, the need to compensate for such pitching moments, which can affect flight efficiency.

[0029] The present application provides an aircraft comprising the aforementioned multi-rotor flight platform and a fuselage connected to the bottom of the multi-rotor flight platform. The multi-rotor flight platform of the present application significantly improves the rigidity of the motor mounting structure on the arm by integrating the canards, arms, and central avionics compartment into an integrated closed structure.

[0030] The above embodiments are merely illustrative of the principles and effects of this application. Anyone skilled in the art may modify or alter the above embodiments without departing from the objectives of this application. Therefore, all equivalent modifications or alterations made by persons skilled in the art without departing from the objectives disclosed herein are intended to be covered by the claims of this application.

Claims

1. A multi-rotor flying platform, characterized in that: include: At least one pair of machine arms (1), the at least one pair of machine arms (1) being symmetrically arranged around a central axis (S) and each of the machine arms (1) being provided with a plurality of vertical lifting power devices (5); A main wing (2), the main wing (2) being symmetrically arranged around the central axis (S) and connected to the at least one pair of arms (1); The canard (3) and the central avionics compartment (4) are respectively connected to a pair of machine arms (1) close to the central axis (S) and form an integrally formed closed structure with the pair of machine arms (1).

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

3. The multi-rotor flying platform according to claim 1, characterized in that: A pair of arms (1) close to the central axis (S) comprises an inner left arm (11L) and an inner right arm (11R), the inner left arm (11L) comprises a first left arm portion (111L) and a second left arm portion (112L), the inner right arm (11R) comprises a first right arm portion (111R) and a second right arm portion (112R), and the canard (3) and the central avionics compartment (4) form an integrally formed closed structure with the first left arm portion (111L) and the first right arm portion (111R).

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

5. The multi-rotor flying platform according to claim 1, characterized in that: The at least one pair of arms (1) comprises a pair of inner arms (11) and a pair of outer arms (12), wherein the pair of inner arms (11) are close to the central axis (S), and the pair of outer arms (12) are far away from the central axis (S), and the distance between the outer arms and the inner arms is at least greater than the sum of the rotation radius of the lift propeller of the vertical lift power device installed on the inner arms, the rotation radius of the lift propeller installed on the outer arms, and the convection gap, and the convection gap is 8% to 15% of the maximum propeller diameter of the outer arms and the inner arms.

6. The multi-rotor flying 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 connecting portion corresponding to the edge of each of the mounting notches.

7. The multi-rotor flying platform according to claim 1, characterized in that: A level flight power device (6) is arranged at the tail of a pair of machine arms (1) close to the central axis (S).

8. The multi-rotor flying platform according to claim 1, characterized in that: The canard (3) further comprises a pair of canard extensions (30), wherein the pair of canard extensions (3) respectively pass through the pair of machine arms (1) and present a streamlined structure that gradually decreases in a direction away from the canard (3).

9. The multi-rotor flying platform according to claim 5, characterized in that: The distance between the central avionics compartment (4) and the canard (3) is half of the length of the arm (1) close to the central axis (S).

10. An aircraft, comprising the multi-rotor flying platform according to any one of claims 1 to 9, and a fuselage, wherein the fuselage is connected to the bottom of the multi-rotor flying platform.

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