CN218949472U

CN218949472U - Freight autorotation gyroplane

Info

Publication number: CN218949472U
Application number: CN202222678569.6U
Authority: CN
Inventors: 许兴; 赖志伟; 江楚
Original assignee: Xiamen Tengxi Aviation Technology Co ltd
Current assignee: Xiamen Tengxi Aviation Technology Co ltd
Priority date: 2022-09-28
Filing date: 2022-09-28
Publication date: 2023-05-02
Anticipated expiration: 2032-09-28

Abstract

The utility model relates to a freight autorotation gyroplane, which comprises a frame and a machine body, wherein the machine body is sleeved outside the frame, the machine body comprises an engine cabin and a machine body cabin, the engine cabin is a cabin body at the rear part of the machine body, the engine cabin is provided with an engine, the machine body cabin is a cabin body at the lower part of the machine body, the machine body further comprises a main cargo cabin and a lower cargo cabin, the main cargo cabin is a cabin body at the front part and the middle part of the machine body, the main cargo cabin is positioned above the frame, the lower cargo cabin is a cabin body embedded in the middle part of the machine body cabin, and the lower cargo cabin is positioned below the frame; the engine compartment, the fuselage cell, the main cargo compartment and the lower cargo compartment together form a machine body. The utility model sets the main cargo hold and the lower cargo hold for carrying cargo on the upper and lower parts of the machine body respectively, the lower cargo hold is set in the middle of the lower part of the machine body, and the two cargo holds can lift the loading weight of the rotorcraft. And the lower cargo hold controls the gravity center of the rotorcraft below the middle part of the rotorcraft, so that the gravity center of the rotorcraft is more stable during cargo loading.

Description

Freight autorotation gyroplane

Technical Field

The utility model relates to the technical field of autorotation rotorcraft, in particular to a freight autorotation rotorcraft.

Background

Autogyro is a rotor type of aircraft that uses an autogyro as a lifting surface and propulsive thrust as forward power. Unlike a helicopter that drives a rotor by engine power, the rotor of a rotorcraft provides lift and attitude steering moments such as pitch, roll, etc., and once the engine is parked in the air, the rotor of the rotorcraft is always in a spinning state by virtue of forward flow, so that the rotor can still safely land by virtue of rotor spinning.

The general autorotation rotorcraft is used for carrying people, the middle position of a frame is high, and the front and back positions of the frame are low, so that the seat and other components can be conveniently arranged.

With the development of unmanned aerial vehicle technology, autorotors for multiple purposes have emerged. Along with the autogyro being used in fields such as agriculture, commodity circulation, original autogyro structure is not applicable to relevant field gradually.

For example, the autorotation gyroplane required in the logistics field needs to be designed with functions of being convenient for loading and unloading cargoes and the like, and the existing autorotation gyroplane mainly takes people as a carrier, so that the cargo is not convenient to load and unload.

Chinese patent application number CN202020207621.8 proposes an autogyro landing gear that employs a nose landing gear that is disposed obliquely. However, in practical use, the center of gravity of the fuselage of the structure is too high to facilitate cargo.

Disclosure of Invention

In order to solve the problems, the utility model aims to provide a freight autorotor, and the gravity center position is stable during freight loading.

The embodiment of the utility model is realized by adopting the following scheme: a freight autorotation rotorcraft comprises a frame and a body, wherein the body is sleeved outside the frame, the body comprises an engine cabin and a body cabin, the engine cabin is a cabin body at the rear part of the body, the engine cabin is provided with an engine, the body cabin is a cabin body at the lower part of the body,

the machine body further comprises a main cargo hold and a lower cargo hold, wherein the main cargo hold is a cabin body at the front part and the middle part of the machine body, the main cargo hold is positioned above the machine frame, the lower cargo hold is a cabin body embedded in the middle part of the machine body, and the lower cargo hold is positioned below the machine frame;

the engine compartment, the fuselage cell, the main cargo compartment and the lower cargo compartment together form a machine body.

Preferably, the frame comprises a main beam and a frame bar; the main beam is horizontally arranged, the rear part of the main beam is connected with a vertically arranged body rod, the main beam and the body rod are connected with the machine body, the engine cabin is positioned at the rear side of the body rod, and the body cabin is positioned at the lower part of the main beam;

a plurality of bearing rods are horizontally arranged on the main beam, a bearing plate is horizontally paved on the bearing rods, and the edge of the bearing plate is connected with the machine body;

the front side of the fuselage pole is provided with a vertical downward cabin partition board, and the edge of the cabin partition board is connected with the inner wall of the fuselage.

Preferably, a cargo hold cover is fastened on the bearing plate, the cargo hold cover is fastened with the machine body along the edge of the bearing plate, and an inner cavity among the cargo hold cover, the cabin partition plate and the bearing plate forms a main cargo hold at the bottom of the cabin body.

Preferably, the machine body at the lower part of the bearing plate is provided with a lower cargo hold which is communicated with two sides of the machine body, and a cargo hold flip is arranged at the position where the lower cargo hold is communicated with the machine body.

Preferably, the bottom of the lower cargo compartment body is horizontal.

Preferably, the front side of the cabin partition board is also provided with an expansion turning board in parallel, the upper part of the expansion turning board is connected with the inner wall of the engine body in a reversible manner, the lower part of the expansion turning board is fixedly connected with the inner wall of the engine body, the upper part of the expansion turning board is directly hinged with the lower part of the expansion turning board through a hinge, a cavity between the cabin partition board and the expansion turning board forms an expansion cabin, and the expansion cabin is positioned between the engine cabin and the main cargo hold.

Preferably, a landing front wheel is arranged below the front part of the main beam; the lower part of the machine body rod is provided with an arc-shaped rod, the arc-shaped rod is a rod piece, two ends of the rod piece are bent downwards and extend towards two sides of the main beam, and two ends of the arc-shaped rod are connected with a landing rear wheel.

Preferably, the rear part of the main beam is provided with a tail wing along the rear direction of the engine compartment.

Preferably, a plurality of expansion mounting holes for installing the avionics are formed in the cabin partition board.

Compared with the existing technology of the autorotation gyroplane, the utility model has at least the following technical effects:

1. the utility model sets the main cargo hold and the lower cargo hold for carrying cargo on the upper and lower parts of the machine body respectively, the lower cargo hold is set in the middle of the lower part of the machine body, and the two cargo holds can lift the loading weight of the rotorcraft. And the lower cargo hold controls the gravity center of the rotorcraft below the middle part of the rotorcraft, so that the gravity center of the rotorcraft is more stable during cargo loading.

2. The scheme is provided with a horizontal main beam and a horizontal bearing plate, so that the bottom of the main cargo hold is further arranged to be horizontal, and cargo loading and unloading are facilitated.

Drawings

FIG. 1 is a perspective view of the present utility model;

FIG. 2 is a schematic diagram of the structure of the present utility model;

FIG. 3 is a second schematic diagram of the structure of the present utility model;

FIG. 4 is a schematic diagram III of the structure of the present utility model;

FIG. 5 is a perspective view of the frame of the present utility model;

FIG. 6 is a side view of the frame of the present utility model;

fig. 7 is a cross-sectional view of the present utility model.

Description of the reference numerals: the engine comprises a frame-1, a frame-2, an engine compartment-3, a fuselage compartment-4, a main cargo compartment-5, a lower cargo compartment-6, a main girder-7, a fuselage pole-8, an extended cabin-9, a cargo compartment cover-51, a cargo compartment flip-61, a bearing pole-71, a bearing plate-72, a landing front wheel-73, a tail wing-74, a cabin partition plate-81, an extended turning plate-82, an arc-shaped pole-83, a landing rear wheel-84 and an extended mounting hole-80.

Detailed Description

The utility model will be further described with reference to the drawings and specific examples.

Existing autogyros are designed for manned, performance, etc., and are not suitable for shipping. Autorotation gyroplanes for cargo use require a stronger load-bearing capacity and a more stable center of gravity position. Therefore, the utility model designs the autorotation gyroplane with a brand new structure, and the barycenter is stable in position and convenient for freight transportation.

Referring to fig. 1 to 7, a freight autorotation rotorcraft comprises a frame 1 and a body 2, wherein the body 2 is sleeved outside the frame 1, the body 2 comprises an engine compartment 3 and a body compartment 4, the engine compartment 3 is a compartment body at the rear part of the body 2, the engine compartment 3 is provided with an engine, the body compartment 4 is a compartment body at the lower part of the body 2,

the machine body 2 further comprises a main cargo hold 5 and a lower cargo hold 6, the main cargo hold 5 is a body at the front part and the middle part of the machine body 2, the main cargo hold 5 is positioned above the machine frame 1, the lower cargo hold 6 is a body embedded in the middle part of the machine body cabin 4, and the lower cargo hold 6 is positioned below the machine frame 1;

the engine compartment 3, the fuselage cell 4, the main cargo compartment 5 and the lower cargo compartment 6 together form the machine body 2. The present utility model provides a main cargo hold 5 and a lower cargo hold 6 for cargo to be respectively provided at upper and lower portions of the body 2, and provides the lower cargo hold 6 to be provided at the middle of the lower portion of the body 2, both cargo holds being capable of elevating the loading weight of the rotorcraft. And the lower cargo hold 6 controls the center of gravity of the rotorcraft below the middle part of the machine body 2, so that the center of gravity of the machine body is more stable when the rotorcraft carries cargo.

To further optimize the cargo carrying of the rotorcraft, and in particular the structural details of the various cabins, the frame 1 of the present utility model comprises a main girder 7 and a fuselage mast 8; the main beam 7 is horizontally arranged, the rear part of the main beam 7 is connected with a vertically arranged body rod 8, the main beam 7 and the body rod 8 are connected with the machine body 2, the engine compartment 3 is positioned at the rear side of the body rod 8, and the body compartment 4 is positioned at the lower part of the main beam 7; the upper part of the fuselage pole 8 is used for erecting a rotor, which is driven by the engine in the nacelle 3 to generate lift.

A plurality of bearing rods 71 are horizontally arranged on the main beam 7, a bearing plate 72 is horizontally paved on the bearing rods 71, and the edge of the bearing plate 72 is connected with the machine body 2;

the front side of the fuselage pole 8 is provided with a vertical downward cabin partition 81, and the edges of the cabin partition 81 are connected to the inner wall of the machine body 2. The horizontal main beams 7 and the horizontal bearing plates 72 are arranged in order to further set the bottom of the main cargo hold 5 to be horizontal, so that cargo loading and unloading are facilitated. And the horizontal main beams 7 also facilitate the installation of the lower cargo compartment 6.

The bearing plate 72 is buckled with a cargo hold cover 51, the cargo hold cover 51 is buckled with the machine body 2 along the edge of the bearing plate 72, and the inner cavity among the cargo hold cover 51, the cabin partition 81 and the bearing plate 72 forms a main cargo hold 5 with the bottom of the cabin being horizontal. In this case, the cargo hold cover 51 and the bearing plate 72 are connected by fastening edges, and various connection modes such as a slide rail and a hinge may be adopted.

The machine body 2 at the lower part of the bearing plate 72 is provided with a lower cargo hold 6 penetrating through two sides of the machine body 2, and a cargo hold flip 61 is arranged at the penetrating position of the lower cargo hold 6 and the machine body 2. The bottom of the lower cargo hold 6 is horizontal. Further, the lower cargo compartment 6 may also be embedded in the middle of the fuselage cell 4 from the bottom of the protruding fuselage cell 4, which is designed to enlarge the volume of the lower cargo compartment 6. The lower cargo compartment 6 constitutes a compartment body by the outer shell of the machine body 2.

The front side of the cabin partition board 81 is also provided with an expansion turning board 82 in parallel, the upper part of the expansion turning board 82 is connected with the inner wall of the engine body 2 in a reversible manner, the lower part of the expansion turning board 82 is fixedly connected with the inner wall of the engine body 2, the upper part of the expansion turning board 82 is directly hinged with the lower part of the expansion turning board 82 through a hinge, a cavity between the cabin partition board 81 and the expansion turning board 82 forms an expansion cabin 9, and the expansion cabin 9 is positioned between the engine cabin 3 and the main cargo hold 5. The reason for providing the nacelle bulkhead 81 in the rotorcraft is that the nacelle 3 needs to be spaced apart from the main cargo compartment 5, and that the nacelle bulkhead 81 is not structured in part because the rotor of the rotorcraft needs to be connected to the fuselage mast 8 and a propeller shaft or the like is required in addition to the fuselage mast 8. In order to optimize the structure of the main cargo compartment 5, the expansion turning plate 82 is arranged on the front side of the cabin partition plate 81, and the cabin partition plate 81 and the expansion turning plate 82 form an independent expansion cabin 9, so that the main cargo compartment 5 and the engine cabin 3 are further isolated, and the cargo transportation is not influenced. And, a plurality of expansion mounting holes 80 for installing avionics are formed on the cabin partition board 81. Avionics equipment for selective installation is installed in the expansion cabin 9, and the expansion capacity of the gyroplane is improved.

A landing front wheel 73 is arranged below the front part of the main beam 7; the lower part of the body rod 8 is provided with an arc-shaped rod 83, the arc-shaped rod 83 is a rod piece with two ends bent downwards and extending towards two sides of the main beam 7, and two ends of the arc-shaped rod 83 are connected with a lifting rear wheel 84. The front landing wheel 73, the two rear landing wheels 84, and the curved lever 83 constitute a three-point landing gear.

The rear part of the main beam 7 is provided with a tail wing 74 along the rear direction of the engine compartment 3.

The points to be described are: first, in the description of the present application, it should be noted that, unless otherwise specified and defined, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be mechanical or electrical, or may be a direct connection between two elements, and "upper," "lower," "left," "right," etc. are merely used to indicate relative positional relationships, which may be changed when the absolute position of the object being described is changed.

Secondly: in the drawings of the disclosed embodiments, only the structures related to the embodiments of the present disclosure are referred to, and other structures may refer to the general design, so that the same embodiment and different embodiments of the present disclosure may be combined with each other without conflict.

Finally, the above description is only a preferred embodiment of the present utility model, and the scope of the present utility model is not limited to the above examples, but all technical solutions belonging to the concept of the present utility model are within the scope of the present utility model.

Claims

1. The utility model provides a freight transportation autogyro, includes frame (1) and organism (2), and organism (2) cover is established in frame (1) outside, and organism (2) are including engine compartment (3) and fuselage cabin (4), and engine compartment (3) are the cabin body at organism (2) rear portion, supply the engine setting in engine compartment (3), and fuselage cabin (4) are the cabin body of organism (2) lower part, its characterized in that:

the machine body (2) further comprises a main cargo hold (5) and a lower cargo hold (6), the main cargo hold (5) is a front and middle part of the machine body (2), the main cargo hold (5) is positioned above the machine frame (1), the lower cargo hold (6) is a middle part of the machine body (4) in an embedded manner, and the lower cargo hold (6) is positioned below the machine frame (1);

the engine compartment (3), the fuselage compartment (4), the main cargo compartment (5) and the lower cargo compartment (6) together form the machine body (2).

2. The freight autogyro of claim 1, wherein: the frame (1) comprises a main beam (7) and a frame rod (8); the main beam (7) is horizontally arranged, the rear part of the main beam (7) is connected with a vertically arranged main body rod (8), the main beam (7) and the main body rod (8) are connected with the main body (2), the engine compartment (3) is positioned at the rear side of the main body rod (8), and the main body compartment (4) is positioned at the lower part of the main beam (7);

a plurality of bearing rods (71) are horizontally arranged on the main beam (7), a bearing plate (72) is horizontally paved on the bearing rods (71), and the edge of the bearing plate (72) is connected with the machine body (2);

the front side of the machine body rod (8) is provided with a vertical downward cabin partition board (81), and the edge of the cabin partition board (81) is connected with the inner wall of the machine body (2).

3. The freight autogyro of claim 2, wherein: the cargo hold cover (51) is buckled on the bearing plate (72), the cargo hold cover (51) is buckled with the machine body (2) along the edge of the bearing plate (72), and an inner cavity among the cargo hold cover (51), the cabin partition plate (81) and the bearing plate (72) forms a main cargo hold (5) with the bottom of the cabin body being horizontal.

4. The freight autogyro of claim 2, wherein: the machine body (2) at the lower part of the bearing plate (72) is provided with a lower cargo hold (6) which penetrates through two sides of the machine body (2), and a cargo hold flip (61) is arranged at the penetration position of the lower cargo hold (6) and the machine body (2).

5. The freight autogyro of claim 4, wherein: the bottom of the lower cargo hold (6) is horizontal.

6. The freight autogyro of claim 2, wherein: the front side of the cabin partition board (81) is further provided with an expansion turning plate (82) in parallel, the upper part of the expansion turning plate (82) is connected with the inner wall of the engine body (2) in a turnover manner, the lower part of the expansion turning plate (82) is fixedly connected with the inner wall of the engine body (2), the upper part of the expansion turning plate (82) is directly hinged with the lower part of the expansion turning plate (82) through a hinge, a cavity between the cabin partition board (81) and the expansion turning plate (82) forms an expansion cabin (9), and the expansion cabin (9) is located between the engine cabin (3) and the main cargo hold (5).

7. The freight autogyro of claim 2, wherein: a landing front wheel (73) is arranged below the front part of the main beam (7); the lower part of the machine body rod (8) is provided with an arc-shaped rod (83), the arc-shaped rod (83) is a rod piece with two ends bent downwards and extending towards two sides of the main beam (7), and two ends of the arc-shaped rod (83) are connected with a lifting rear wheel (84).

8. The freight autogyro of claim 2, wherein: the rear part of the main beam (7) is provided with a tail wing (74) along the rear direction of the engine compartment (3).

9. The freight autogyro of claim 2, wherein: and a plurality of expansion mounting holes (80) for mounting avionics are formed in the cabin partition plate (81).