A composite wing vertical take-off and landing aircraft

Abstract

The present invention relates to the field of aircraft technology, and in particular to a composite-wing vertical take-off and landing aircraft, comprising a fuselage, a front wing and a tail wing; propeller mounting frames are provided on the front wings on both sides of the fuselage, and the propeller mounting frames include a middle rod, an inner rod and an outer rod; lift propeller mechanisms are installed on the middle rod, inner rod and outer rod; the present invention adopts the method of arranging propeller mounting frames on the front wings on both sides of the fuselage, which is convenient for installing multiple lift propeller mechanisms, so that the aircraft can be transported with a large load; the propeller mounting frames are provided with a middle rod connected to the front wing and the rear tail wing respectively, and inner rods and outer rods are distributed on both sides of the middle rod, so that the aircraft has good stability during flight, while reducing the force on the front wing and making the force more balanced, thereby improving the service life.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, in particular to a composite-wing vertical take-off and landing aircraft. Background Art

[0002] Chinese invention patent publication number CN115723948A discloses a V-tail single-thrust electric vertical take-off and landing composite wing aircraft, which includes a fuselage, wings installed on both sides of the fuselage, motor arms installed on the wings, winglets installed at the ends of the wings, lift propellers installed on the motor arms, a single V-tail and thrust propellers installed at the tail of the fuselage, the thrust propellers are located at the rear end of the single V-tail, and a tail thrust fairing is installed at the rear end of the thrust propellers. The aircraft combines the advantages of helicopters and fixed-wing aircraft, and has good terrain adaptability and cruising performance. The aircraft can perform vertical take-off and landing without a runway, can adapt to complex urban traffic environments, and has strong safety and adaptability.

[0003] The aforementioned aircraft utilizes two motor arms mounted on the wings, with propellers and motors installed on them, to achieve vertical takeoff and landing (VTOL) capabilities and, to a certain extent, improve the aircraft's load-bearing capacity. However, the use of two motor arms arranged side by side on a single wing results in poor stability when loaded with heavy loads. Furthermore, the two motor arms, along with the propellers and motors mounted on each wing, exert uneven forces on the wing, resulting in poor balance. Long-term use can also damage the wing, making it unsuitable for use. An improved technical solution is needed. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the present invention provides a composite wing vertical take-off and landing aircraft with balanced force, stable flight, and the ability to achieve heavy-load flight.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0006] The present invention provides a composite wing vertical take-off and landing aircraft, comprising a fuselage, a front wing connected to the fuselage, and a tail wing;

[0007] A propeller mounting frame is provided on the front wings on both sides of the fuselage, and the propeller mounting frame includes a middle pole, an inner pole and an outer pole respectively provided on both sides of the middle pole, the inner pole and the outer pole are both connected to the front wings, and the tail end of the middle pole is connected to the tail wing;

[0008] The middle rod, the inner rod and the outer rod are all equipped with lift propeller mechanisms; the fuselage is equipped with the first thrust propeller mechanism.

[0009] Wherein, the propeller mounting frame is further provided with a connecting rod, both ends of the inner rod are connected to the middle rod by the connecting rod; both ends of the outer rod are connected to the middle rod by the connecting rod.

[0010] Wherein, both ends of the inner rod and both ends of the outer rod are provided with the lift propeller mechanism; and both ends of the middle rod and the connection points of the connecting rod are provided with the lift propeller mechanism.

[0011] The inner rod, outer rod and four connecting rods in the propeller mounting frame form a parallelepiped frame, the middle rod is located at the center line position of the length direction of the parallelepiped frame, and the front wing is connected to the middle position of the parallelepiped frame.

[0012] Wherein, a second thrust propeller mechanism is provided at the tail of the center rod.

[0013] Preferably, the two second thrust propeller mechanisms and the first thrust propeller mechanism on the center poles on both sides of the fuselage are distributed in a triangle.

[0014] Wherein, the lift propeller mechanism includes a propeller and a motor for driving the propeller to rotate.

[0015] Wherein, a cabin is arranged inside, and a wheel assembly is arranged at the bottom of the fuselage.

[0016] Beneficial effects of the present invention:

[0017] The present invention provides a composite wing vertical take-off and landing aircraft, in which a propeller mounting frame is provided on the front wing, and a plurality of lift propeller mechanisms are provided on the propeller mounting frame, thereby achieving vertical take-off and landing with a high load; during cruising, the first thrust propeller mechanism provides flight thrust. The present invention adopts the method of providing propeller mounting frames on the front wings on both sides of the fuselage, facilitating the installation of multiple lift propeller mechanisms, so that the aircraft can be transported with a high load; the propeller mounting frame is provided with a center rod connected to the front wing and the rear tail respectively, and inner rods and outer rods are distributed on both sides of the center rod, so that the aircraft has good stability during flight, while reducing the force on the front wing and making the force more balanced, thereby improving the service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention.

[0019] Figure 2 It is a schematic diagram of the three-dimensional structure from another perspective of the present invention.

[0020] Figure 3 It is a schematic diagram of the three-dimensional structure from another perspective of the present invention.

[0021] Figure 4 It is a schematic diagram of the three-dimensional structure from another perspective of the present invention.

[0022] Figure 5 It is a top view of the present invention.

[0023] Figure 6 It is a bottom view of the present invention. DETAILED DESCRIPTION

[0024] In order to facilitate understanding by those skilled in the art, the present invention will be further described below with reference to the embodiments and the accompanying drawings. The contents mentioned in the embodiments are not intended to limit the present invention. The present invention will be described in detail below with reference to the accompanying drawings.

[0025] refer to Figures 1 to 6 As shown, the present invention provides a composite wing vertical take-off and landing aircraft, including a fuselage 1, a front wing 2 and a tail 3 connected to the fuselage 1; propeller mounting frames 4 are provided on the front wings 2 on both sides of the fuselage 1, and the propeller mounting frames 4 include a center rod 41, an inner rod 42 and an outer rod 43 respectively provided on both sides of the center rod 41, the inner rod 42 and the outer rod 43 are both connected to the front wing 2, and the tail end of the center rod 41 is connected to the tail 3; a lift propeller mechanism 5 is installed on the center rod 41, the inner rod 42 and the outer rod 43; the fuselage 1 is installed on a first thrust propeller mechanism 6.

[0026] The present invention provides a propeller mounting frame 4 on the front wing 2, and a plurality of lift propeller mechanisms 5 are provided on the propeller mounting frame 4, thereby achieving vertical take-off and landing with a high load; during cruising, the first thrust propeller mechanism 6 provides flight thrust. The present invention adopts the arrangement of propeller mounting frames 4 on the front wings 2 on both sides of the fuselage 1, facilitating the installation of multiple lift propeller mechanisms 5, enabling the aircraft to be transported with a high load; the propeller mounting frames 4 are provided with a center rod 41 connected to the front wing 2 and the rear tail 3, respectively, and inner rods 42 and outer rods 43 are distributed on both sides of the center rod 41, thereby improving the stability of the aircraft during flight, while reducing the stress on the front wing 2 and ensuring a more balanced stress, thereby improving the service life.

[0027] In this embodiment, the propeller mounting frame 4 is further provided with connecting rods 44. Both ends of the inner rod 42 are connected to the center rod 41 via connecting rods 44; and both ends of the outer rod 43 are connected to the center rod 41 via connecting rods 44. Specifically, the inner rod 42 and outer rod 43 are rods of equal length, and the connecting rods 44 at both ends connect to the center rod 41 at the same cross-section. In this embodiment, the use of connecting rods 44 to connect the inner rod 42, outer rod 43, and center rod 41 into an integrated structure makes the propeller mounting frame 4 more stable, further improves the stability of the aircraft during flight, and ensures more balanced force on the front wing 2.

[0028] In this embodiment, the lift propeller mechanisms 5 are provided at both ends of the inner rod 42 and the outer rod 43. Lift propeller mechanisms 5 are also provided at the junctions between both ends of the center rod 41 and the connecting rod 44. Specifically, ten lift propeller mechanisms 5 are designed, with three located forward and backward of the front wing 2 on one side of the fuselage 1. These three lift propeller mechanisms 5 are arranged in a triangular pattern, ensuring that the composite wing vertical takeoff and landing aircraft exhibits powerful power and excellent stability during vertical takeoff and landing.

[0029] In this embodiment, the inner rods 42, outer rods 43, and four connecting rods 44 of the propeller mounting frame 4 form a parallelepiped frame. The center rod 41 is located at the centerline of the parallelepiped frame along its length, and the front wing 2 is connected to the center of the parallelepiped frame. The parallelepiped frame is symmetrically designed on the front wing 2 relative to the center rod 41. The load of the center rod 41 is shared by both the front wing 2 and the tail wing 3, resulting in a balanced layout of the lift propeller mechanism 5 and excellent flight stability.

[0030] In this embodiment, the tail of the center rod 41 is provided with a second thrust propeller mechanism 7 to increase the power of cruising. Furthermore, the two second thrust propeller mechanisms 7 and the first thrust propeller mechanism 6 on the center rod 41 on both sides of the fuselage 1 are distributed in a triangular shape to provide a stable thrust.

[0031] In this embodiment, the lift propeller mechanism 5 includes a propeller and a motor for driving the propeller. The structures and principles of the second thrust propeller mechanism 7 and the first thrust propeller mechanism 6 are similar to those of the lift propeller mechanism 5 and are not described in detail. The interior includes an engine cabin, and the bottom of the fuselage 1 is provided with an engine wheel assembly 8.

[0032] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Although the present invention is disclosed as a preferred embodiment as above, it is not used to limit the present invention. Any technician familiar with this profession can make some changes or modifications to equivalent embodiments of equivalent changes by using the technical content disclosed above without departing from the scope of the technical solution of the present invention. However, any simple modifications, equivalent changes and modifications made to the above embodiments according to the technology of the present invention are all within the scope of the technical solution of the present invention without departing from the content of the technical solution of the present invention.

Claims

1. A composite wing vertical take-off and landing aircraft, comprising a fuselage (1), a front wing (2) connected to the fuselage (1), and a tail wing (3); characterized in that: A propeller mounting frame (4) is provided on each of the front wings (2) on both sides of the fuselage (1), and the propeller mounting frame (4) comprises a center rod (41), an inner rod (42) and an outer rod (43) respectively provided on both sides of the center rod (41), the inner rod (42) and the outer rod (43) being connected to the front wing (2), and the tail end of the center rod (41) being connected to the tail wing (3); The middle rod (41), the inner rod (42) and the outer rod (43) are all equipped with a lift propeller mechanism (5); The fuselage (1) is mounted on a first thrust propeller mechanism (6); A second thrust propeller mechanism (7) is provided at the tail of the middle rod (41); The two second thrust propeller mechanisms (7) and the first thrust propeller mechanism (6) on the center rods (41) on both sides of the fuselage (1) are distributed in a triangular shape; The propeller mounting frame (4) is further provided with a connecting rod (44), and both ends of the inner rod (42) are connected to the middle rod (41) by the connecting rod (44); and both ends of the outer rod (43) are connected to the middle rod (41) by the connecting rod (44); The inner rod (42), the outer rod (43) and the four connecting rods (44) in the propeller mounting frame (4) form a parallelepiped frame, the middle rod (41) is located at the center line position of the length direction of the parallelepiped frame, and the front wing (2) is connected to the middle position of the parallelepiped frame; The lift propeller mechanisms (5) are provided at both ends of the inner rod (42) and both ends of the outer rod (43); the lift propeller mechanisms (5) are provided at the connection points between both ends of the middle rod (41) and the connecting rod (44); three lift propeller mechanisms (5) are distributed front and rear of the front wing (2) on one side of the fuselage (1), and the lift propeller mechanisms (5) are distributed in a triangular pattern.

2. The composite wing vertical take-off and landing aircraft according to claim 1, characterized in that: The lift propeller mechanism (5) comprises a propeller and a motor for driving the propeller to rotate.

3. The composite wing vertical take-off and landing aircraft according to claim 1, characterized in that: A cabin is provided inside the fuselage (1), and a wheel assembly (8) is provided at the bottom of the fuselage (1).

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