Cargo autorotary rotorcraft

Abstract

The present application relates to a kind of freight autorotating rotorcraft, including frame and body, body is set outside frame, body includes engine cabin and fuselage cabin, engine cabin is the cabin body of rear part of body, engine is arranged in engine cabin, fuselage cabin is the cabin body of lower part of body, the body further includes main cargo hold and lower cargo hold, the main cargo hold is the cabin body of front and middle part of body, main cargo hold is located above frame, the lower cargo hold is the cabin body of embedding in the middle part of fuselage cabin, the lower cargo hold is located below frame;The engine cabin, fuselage cabin, main cargo hold and lower cargo hold jointly constitute body.The main cargo hold and lower cargo hold for carrying are arranged in upper and lower part of body respectively in the present application, lower cargo hold is set in the middle of lower part of body, two cargo holds can promote rotorcraft load weight.And lower cargo hold controls the center of gravity of rotorcraft below the middle of body, and the center of gravity of body is more stable when rotorcraft carries load.

Description

Technical Field

[0001] This invention relates to the field of autogyro aircraft technology, and in particular to a cargo autogyro. Background Technology

[0002] An autogyro is a rotorcraft that uses its own rotor as the lifting surface and a propeller for forward propulsion. The rotor provides lift and attitude control torques such as pitch and roll. Therefore, unlike helicopters which rely on engine power to drive their rotors, if the engine fails in flight, the autogyro's rotor continues to rotate due to the airflow in front, allowing it to land safely by relying on its rotor's rotation.

[0003] Typical autogyros are designed for manned use, with the frame positioned high in the middle and low at the front and rear to facilitate the installation of components such as seats.

[0004] With the development of drone technology, autogyros have emerged for various purposes. As autogyros are used in agriculture, logistics, and other fields, the original autogyro structure is gradually becoming unsuitable for these applications.

[0005] For example, autogyros required in the logistics sector need to be designed to facilitate loading and unloading of goods. Existing autogyros are mainly designed for carrying people and are not convenient for loading and unloading goods.

[0006] Chinese patent application number CN202020207621.8 proposes a landing gear for an autogyro, which uses a tilted nose landing gear. However, in actual use, this structure results in a high center of gravity, making it inconvenient for cargo transport. Summary of the Invention

[0007] To address the aforementioned problems, the purpose of this invention is to provide a cargo autogyro with a stable center of gravity when carrying cargo.

[0008] The present invention is implemented using the following scheme in this embodiment: a cargo autogyro, comprising a frame and a fuselage, the fuselage being fitted outside the frame, the fuselage including an engine nacelle and a fuselage compartment, the engine nacelle being the compartment at the rear of the fuselage and housing the engine, and the fuselage compartment being the compartment at the lower part of the fuselage.

[0009] The fuselage also includes a main cargo hold and a lower cargo hold. The main cargo hold is the front and middle section of the fuselage and is located above the frame. The lower cargo hold is a section embedded in the middle of the fuselage and is located below the frame.

[0010] The engine compartment, fuselage compartment, main cargo compartment, and lower cargo compartment together constitute the fuselage.

[0011] Preferably, the frame includes a main beam and a fuselage rod; the main beam is horizontally arranged, and the rear of the main beam is connected to the vertically arranged fuselage rod, the main beam and the fuselage rod are connected to the fuselage body, the engine compartment is located on the rear side of the fuselage rod, and the fuselage compartment is located at the lower part of the main beam;

[0012] Several load-bearing rods are horizontally installed on the main beam, and a load-bearing plate is horizontally laid on the load-bearing rods. The edge of the load-bearing plate is connected to the machine body.

[0013] A vertically downward cabin bulkhead is provided on the front side of the fuselage mast, and the edge of the cabin bulkhead is connected to the inner wall of the fuselage.

[0014] Preferably, a cargo hold cover is fastened to the load-bearing plate, and the cargo hold cover is fastened to the body along the edge of the load-bearing plate. The inner cavity between the cargo hold cover, the cabin bulkhead and the load-bearing plate forms the main cargo hold at the bottom of the cabin.

[0015] Preferably, the lower part of the load-bearing plate has a lower cargo compartment that runs through both sides of the body, and a cargo compartment flap is provided at the junction of the lower cargo compartment and the body.

[0016] Preferably, the bottom of the lower cargo hold is horizontal.

[0017] Preferably, an extension flap is also provided parallel to the front side of the cabin bulkhead. The upper part of the extension flap is rotatably connected to the inner wall of the engine room, and the lower part of the extension flap is fixedly connected to the inner wall of the engine room. The upper part and the lower part of the extension flap are directly hinged together by a hinge. The cavity between the cabin bulkhead and the extension flap constitutes an extension compartment, which is located between the engine room and the main cargo compartment.

[0018] Preferably, a front landing wheel is provided below the front part of the main beam; an arc-shaped rod is provided at the lower part of the fuselage rod, which is a rod that bends downward at both ends and extends to both sides of the main beam, and a landing wheel is connected to each end of the arc-shaped rod.

[0019] Preferably, a tail fin is provided at the rear of the main beam along the rear direction of the engine compartment.

[0020] Preferably, the cabin bulkhead has multiple expansion mounting holes for installing avionics equipment.

[0021] This invention provides a cargo autogyro, which, compared to existing autogyro technology, has at least the following technical advantages:

[0022] 1. This invention places the main cargo hold and the lower cargo hold, used for carrying cargo, on the upper and lower parts of the fuselage respectively, with the lower cargo hold located in the middle of the lower part of the fuselage. The two cargo holds can increase the load capacity of the rotorcraft. Furthermore, the lower cargo hold controls the rotorcraft's center of gravity to be below the middle of the fuselage, making the rotorcraft's center of gravity more stable when carrying cargo.

[0023] 2. The horizontal main beam and horizontal load-bearing plate in this case are designed to make the bottom of the main cargo hold horizontal, which facilitates the loading and unloading of goods. Attached Figure Description

[0024] Figure 1 This is a perspective view of the present invention;

[0025] Figure 2 This is a schematic diagram of the structure of the present invention. Figure 1 ;

[0026] Figure 3 This is a schematic diagram of the structure of the present invention. Figure 2 ;

[0027] Figure 4 This is a schematic diagram of the structure of the present invention. Figure 3 ;

[0028] Figure 5 This is a perspective view of the frame of the present invention;

[0029] Figure 6 This is a side view of the frame of the present invention;

[0030] Figure 7 This is a cross-sectional view of the present invention.

[0031] Labeling Explanation: Frame-1, Fuselage-2, Engine Nacelle-3, Fuselage Nacelle-4, Main Cargo Hold-5, Lower Cargo Hold-6, Main Beam-7, Fuselage Hook-8, Extension Cabin-9, Cargo Hold Cover-51, Cargo Hold Flip-Top-61, Load-Bearing Boom-71, Load-Bearing Plate-72, Nose Wheel for Landing-73, Tail Wing-74, Cabin Bulkhead-81, Extension Flip-Top-82, Curved Boom-83, Rear Wheel for Landing-84, Extension Mounting Hole-80. Detailed Implementation

[0032] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0033] Existing autogyros are designed for passenger transport and performances, and are not suitable for cargo transport. Autogyros used for cargo transport require greater load-bearing capacity and a more stable center of gravity. Therefore, this invention designs a novel autogyro structure with a stable center of gravity, facilitating cargo transport.

[0034] Please see Figures 1 to 7 A cargo autogyro includes a frame 1 and a fuselage 2. The fuselage 2 is mounted on the outside of the frame 1. The fuselage 2 includes an engine nacelle 3 and a fuselage compartment 4. The engine nacelle 3 is located at the rear of the fuselage 2 and houses the engine. The fuselage compartment 4 is located at the lower part of the fuselage 2.

[0035] The fuselage 2 also includes a main cargo hold 5 and a lower cargo hold 6. The main cargo hold 5 is the front and middle section of the fuselage 2 and is located above the frame 1. The lower cargo hold 6 is a section embedded in the middle of the fuselage compartment 4 and is located below the frame 1.

[0036] The engine compartment 3, fuselage compartment 4, main cargo compartment 5, and lower cargo compartment 6 together constitute the fuselage 2. In this invention, the main cargo compartment 5 and the lower cargo compartment 6, used for cargo carrying, are respectively located at the upper and lower parts of the fuselage 2, with the lower cargo compartment 6 positioned in the middle of the lower part of the fuselage 2. The two cargo compartments can increase the load capacity of the rotorcraft. Furthermore, the lower cargo compartment 6 controls the rotorcraft's center of gravity to be below the middle of the fuselage 2, making the rotorcraft's center of gravity more stable when carrying cargo.

[0037] To further optimize the cargo-carrying capacity of the rotorcraft and specify the structural details of each cabin, the frame 1 of this invention includes a main beam 7 and a fuselage strut 8; the main beam 7 is horizontally arranged, and the rear of the main beam 7 is connected to the vertically arranged fuselage strut 8. The main beam 7 and the fuselage strut 8 are connected to the fuselage 2. The engine nacelle 3 is located behind the fuselage strut 8, and the fuselage nacelle 4 is located below the main beam 7; the upper part of the fuselage strut 8 is used to mount the rotor, and the rotor generates lift through engine transmission within the engine nacelle 3.

[0038] Several load-bearing rods 71 ​​are horizontally arranged on the main beam 7, and a load-bearing plate 72 is horizontally laid on the load-bearing rods 71. The edge of the load-bearing plate 72 is connected to the body 2.

[0039] A vertically downward-pointing cabin bulkhead 81 is provided on the front side of the fuselage mast 8, and the edge of the cabin bulkhead 81 is connected to the inner wall of the fuselage 2. The horizontal main beam 7 and horizontal load-bearing plate 72 are provided in this design to further level the bottom of the main cargo hold 5, facilitating cargo loading and unloading. Furthermore, the horizontal main beam 7 also facilitates the installation of the lower cargo hold 6.

[0040] A cargo hatch cover 51 is fastened to the load-bearing plate 72. The cargo hatch cover 51 is fastened to the body 2 along the edge of the load-bearing plate 72. The cavity between the cargo hatch cover 51, the cabin bulkhead 81, and the load-bearing plate 72 forms the main cargo compartment 5 at the bottom of the cabin. In this case, the cargo hatch cover 51 and the load-bearing plate 72 are connected by interlocking edges. In addition, various other connection methods such as slide rails and hinges can also be used.

[0041] The lower part of the fuselage 2 under the load-bearing plate 72 has a lower cargo compartment 6 that runs through both sides of the fuselage 2. A cargo compartment flap 61 is also provided at the junction of the lower cargo compartment 6 and the fuselage 2. The bottom of the lower cargo compartment 6 is horizontal. Furthermore, the lower cargo compartment 6 can also be embedded in the middle of the fuselage 4 from the bottom of the fuselage compartment 4. This design is to increase the volume of the lower cargo compartment 6. The lower cargo compartment 6 is formed by the outer shell of the fuselage 2.

[0042] An extension flap 82 is also parallel to the front side of the cabin bulkhead 81. The upper part of the extension flap 82 is rotatably connected to the inner wall of the fuselage 2, and the lower part of the extension flap 82 is fixedly connected to the inner wall of the fuselage 2. The upper and lower parts of the extension flap 82 are directly hinged together by a hinge. The cavity between the cabin bulkhead 81 and the extension flap 82 constitutes an extension compartment 9, which is located between the engine compartment 3 and the main cargo compartment 5. The reason for setting up the cabin bulkhead 81 in the rotorcraft is that the engine compartment 3 needs to be separated from the main cargo compartment 5. Also, since the rotor of the rotorcraft needs to be connected to the fuselage rod 8, in addition to the fuselage rod 8, there are also structures such as a drive shaft. Therefore, the structure of the cabin bulkhead 81 is not regular. In order to optimize the structure of the main cargo compartment 5, the extension flap 82 is set in front of the cabin bulkhead 81. The cabin bulkhead 81 and the extension flap 82 constitute an independent extension compartment 9, which further isolates the main cargo compartment 5 and the engine compartment 3, ensuring that cargo transportation is not affected. Furthermore, the cabin bulkhead 81 has multiple expansion mounting holes 80 for installing avionics equipment. The expansion compartment 9 houses avionics equipment for selective installation, increasing the rotorcraft's expandability.

[0043] A front landing gear 73 is installed below the front of the main beam 7; an arc-shaped rod 83 is installed at the lower part of the fuselage rod 8. The arc-shaped rod 83 is a rod that bends downward at both ends and extends to both sides of the main beam 7. Each end of the arc-shaped rod 83 is connected to a rear landing gear 84. The front landing gear 73, the two rear landing gears 84, and the arc-shaped rod 83 constitute a three-point landing gear.

[0044] A tail fin 74 is provided at the rear of the main beam 7 along the rear direction of the engine compartment 3.

[0045] Several points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection" and "linkage" should be interpreted broadly, and can be mechanical or electrical connection, or internal connection between two components, or direct connection. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationship. When the absolute position of the described object changes, the relative positional relationship may change.

[0046] Secondly: The accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0047] Finally, the above description is only a preferred embodiment of the present invention, and the scope of protection of the present invention is not limited to the above embodiments. All technical solutions that fall within the scope of the present invention are within the scope of protection of the present invention.

Claims

1. A cargo autogyro, comprising a frame (1) and a fuselage (2), the fuselage (2) being fitted over the frame (1), the fuselage (2) comprising an engine nacelle (3) and a fuselage compartment (4), the engine nacelle (3) being the rear compartment of the fuselage (2) and housing an engine, the fuselage compartment (4) being the lower compartment of the fuselage (2), characterized in that: The fuselage (2) also includes a main cargo compartment (5) and a lower cargo compartment (6). The main cargo compartment (5) is the front and middle compartment of the fuselage (2) and is located above the frame (1). The lower cargo compartment (6) is a compartment embedded in the middle of the fuselage compartment (4) and is located below the frame (1). The engine compartment (3), fuselage compartment (4), main cargo compartment (5) and lower cargo compartment (6) together constitute the fuselage (2); The frame (1) includes a main beam (7) and a fuselage rod (8); the main beam (7) is horizontally arranged, and the rear of the main beam (7) is connected to the vertically arranged fuselage rod (8). The main beam (7) and the fuselage rod (8) are connected to the body (2). The engine compartment (3) is located behind the fuselage rod (8), and the fuselage compartment (4) is located below the main beam (7). Several load-bearing rods (71) are horizontally arranged on the main beam (7), and a load-bearing plate (72) is horizontally laid on the load-bearing rods (71). The edge of the load-bearing plate (72) is connected to the machine body (2). A vertically downward cabin bulkhead (81) is provided on the front side of the fuselage rod (8), and the edge of the cabin bulkhead (81) is connected to the inner wall of the fuselage (2); A cargo hatch cover (51) is fastened on the load-bearing plate (72). The cargo hatch cover (51) is fastened to the body (2) along the edge of the load-bearing plate (72). The inner cavity between the cargo hatch cover (51), the cabin bulkhead (81) and the load-bearing plate (72) constitutes the main cargo compartment (5) at the bottom of the cabin. An extension flap (82) is also provided parallel to the front side of the cabin bulkhead (81). The upper part of the extension flap (82) is rotatably connected to the inner wall of the fuselage (2), and the lower part of the extension flap (82) is fixedly connected to the inner wall of the fuselage (2). The upper part of the extension flap (82) and the lower part of the extension flap (82) are directly hinged by a hinge. The cavity between the cabin bulkhead (81) and the extension flap (82) constitutes the extension compartment (9), which is located between the engine compartment (3) and the main cargo compartment (5).

2. The cargo autogyro as described in claim 1, characterized in that: The lower part of the body (2) of the load-bearing plate (72) has a lower cargo compartment (6) that runs through both sides of the body (2), and a cargo compartment flap (61) is also provided at the junction of the lower cargo compartment (6) and the body (2).

3. A cargo autogyro according to claim 2, characterized in that: The bottom of the lower cargo hold (6) is horizontal.

4. A cargo autogyro according to claim 1, characterized in that: A front landing wheel (73) is provided at the lower front of the main beam (7); an arc-shaped rod (83) is provided at the lower part of the fuselage rod (8). The arc-shaped rod (83) is a rod that bends downward at both ends and extends to both sides of the main beam (7). A landing wheel (84) is connected to both ends of the arc-shaped rod (83).

5. A cargo autogyro according to claim 1, characterized in that: A tail fin (74) is provided at the rear of the main beam (7) along the rear direction of the engine compartment (3).

6. A cargo autogyro according to claim 1, characterized in that: The cabin bulkhead (81) has multiple expansion mounting holes (80) for the installation of aviation electrical equipment.

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