A freight unmanned autogyro

Abstract

The present invention relates to a freight unmanned autogyro, which comprises a fuselage, a frame, a mast and a landing gear. The fuselage is sleeved on the frame. The cavity inside the fuselage is provided for avionics equipment. The rear part of the fuselage is an engine compartment for an engine. The mast is vertically arranged at the rear of the frame. The top of the mast is provided for a rotor. The landing gear is arranged at the bottom of the frame. The landing gear is connected with several wheels. The cavity inside the fuselage is divided into an upper cabin and a lower cabin by the frame. The upper cabin includes a front cabin, a cargo cabin and a rear cabin arranged in sequence from front to back. The lower cabin is provided for a battery compartment and a fuel tank. The avionics equipment includes an avionics box and an engine control box. The avionics box and the engine control box are respectively arranged in the front cabin and the rear cabin. The avionics box and the engine control box are respectively connected to the battery compartment. Sensors for collecting flight information are arranged inside the avionics box. The engine control box is connected to and controls the engine.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a cargo unmanned autogyro. Background Art

[0002] Among many aircraft, the autogyro is considered to be one of the safest. Due to its simple structure and convenient operation, it has received extensive attention. Different from a helicopter, the rotor of an autogyro is not driven by power, but rotates by itself by the oncoming flow when moving forward, thereby generating lift. Therefore, the autogyro does not require a tail rotor to balance the counter torque, but generally has a tail rudder to adjust the heading.

[0003] At first, autogyros were all manned aircraft. With the development of autogyros and the increasing demand for autogyros, unmanned autogyros for cargo transportation or harsh flight environments have emerged.

[0004] Chinese Patent No. CN201911109109.8 proposes an unmanned autogyro, which directly transforms a manned aircraft into an unmanned aircraft for use, and its airframe structure does not further prepare corresponding space for cargo transportation. Summary of the Invention

[0005] To solve the above problems, the purpose of the present invention is to provide a cargo unmanned autogyro to facilitate unmanned cargo transportation.

[0006] In an embodiment of the present invention, the following solution is adopted: A cargo unmanned autogyro includes a fuselage, a frame, a mast, and a landing gear. The fuselage is sleeved on the frame. The cavity inside the fuselage is for arranging avionics equipment. The rear part of the fuselage is an engine compartment for arranging an engine. The mast is vertically arranged at the rear of the frame. The top of the mast is for arranging a rotor. The landing gear is arranged at the bottom of the frame.

[0007] The cavity inside the fuselage is divided by the frame into an upper cabin and a lower cabin. The upper cabin includes a front cabin, a cargo cabin, and a rear cabin arranged in sequence from front to back. The lower cabin is for arranging a battery compartment and a fuel tank.

[0008] The avionics equipment includes an avionics box and an engine control box. The avionics box and the engine control box are respectively arranged in the front cabin and the rear cabin. The avionics box and the engine control box are respectively connected to the battery compartment. Sensors for collecting flight information are arranged inside the avionics box. The engine control box is connected to and controls the engine.

[0009] Preferably, it further includes a counterweight box.

[0010] The counterweight box is arranged in the front cabin. Several detachable weights are arranged inside the counterweight box. A front cabin cover for adjusting the number of weights in the counterweight box is opened on the front cabin.

[0011] Preferably, it further includes a control system disposed on the mast. The control system includes a rotary servo, a rotating rod, a connecting rod, and a rotor support.

[0012] One end of the rotor support is hinged to the top of the mast. The top of the rotor support is for the rotor to be installed. Two rotary servos are symmetrically arranged on both sides of the mast. Each rotary servo is connected to and drives a rotating rod. One end of each rotating rod is hinged to a connecting rod. The two connecting rods are respectively hinged to both sides of the rotor support.

[0013] Preferably, it further includes a braking system which is disposed in the lower cabin. The braking system includes a braking servo and a brake master cylinder arranged opposite to each other. The braking servo is connected to and drives a cam to rotate. The cam has a raised stop position. The brake master cylinder extends towards the braking servo and is provided with a push rod for starting / stopping the brake master cylinder. The push rod rolls against the cam.

[0014] Preferably, it further includes GPS antennas. Two groups of GPS antennas are respectively disposed on the tops of the front cabin and the rear cabin. The two groups of GPS antennas are respectively connected to the avionics box and the engine control box.

[0015] Preferably, it further includes an airspeed tube which is inserted into the front of the front cabin. The airspeed tube is connected to the avionics box.

[0016] The present invention provides a freight unmanned autogyro. Compared with the prior art, the present invention has at least the following technical effects:

[0017] In this case, the avionics equipment is separated into an avionics box and an engine control box, and the avionics box and the engine control box are respectively disposed in the front cabin and the rear cabin. The middle cavity of the fuselage is emptied for subsequent cargo use, and the cargo capacity is strong. And the avionics equipment is respectively arranged according to modules, with a high degree of modularization and strong control ability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is the three-dimensional view of the present invention Figure 1 ;

[0019] Figure 2 is the three-dimensional view of the present invention Figure 2 ;

[0020] Figure 3 is the sectional view of the present invention;

[0021] Figure 4 is the structural schematic diagram of the frame of the present invention;

[0022] Figure 5 is the structural schematic diagram of the control system of the present invention;

[0023] Figure 6 is the structural schematic diagram of the braking system of the present invention.

[0024] Description of reference numerals: fuselage - 1, frame - 2, mast - 3, landing gear - 4, rotor - 5, engine compartment - 11, front cabin - 12, cargo hold - 13, rear cabin - 14, battery compartment - 15, avionics box - 16, engine control box - 17, counterweight box - 6, front cabin cover - 120, control system - 30, swivel servo - 31, rotating rod - 32, connecting rod - 33, rotor support - 34, braking system - 7, GPS antenna - 8, airspeed tube - 9, braking servo - 71, braking master cylinder - 72, cam - 73, dead center position - 74, push rod - 75. Detailed implementation manners

[0025] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0026] Please refer to Figures 1 to 6 , a cargo unmanned autogyro, comprising a fuselage 1, a frame 2, a mast 3 and a landing gear 4. The fuselage 1 is sleeved on the frame 2. The cavity inside the fuselage 1 is for arranging avionics equipment. The rear part of the fuselage 1 is an engine compartment 11 for arranging an engine. The mast 3 is vertically arranged at the rear part of the frame 2. The top of the mast 3 is for arranging a rotor 5. The landing gear 4 is arranged at the bottom of the frame 2. The landing gear 4 is connected to several wheels.

[0027] The cavity inside the fuselage 1 is separated by the frame 2 into an upper cabin and a lower cabin. The upper cabin includes a front cabin 12, a cargo hold 13 and a rear cabin 14 which are arranged in sequence from front to back. The lower cabin is for arranging a battery compartment 15 and a fuel tank.

[0028] The avionics equipment includes an avionics box 16 and an engine control box 17. The avionics box 16 and the engine control box 17 are respectively arranged in the front cabin 12 and the rear cabin 14. The avionics box 16 and the engine control box 17 are respectively connected to the battery compartment 15. Sensors for collecting flight information are arranged inside the avionics box 16. The engine control box 17 is connected to and controls the engine.

[0029] For the fuselage 1 of the autogyro to adapt to flight, a streamlined outer shape is adopted. This means that the cavities at the front and rear ends of the fuselage 1 are small, and the cavity in the middle is large. In this case, the avionics equipment is separated into an avionics box 16 and an engine control box 17, and the avionics box 16 and the engine control box 17 are respectively arranged in the front cabin 12 and the rear cabin 14. The cavity in the middle of the fuselage 1 is left empty for subsequent cargo loading, and the cargo capacity is strong. And the avionics equipment is arranged separately by module, with a high degree of modularity and strong control ability.

[0030] Moreover, in order to further facilitate the center of gravity balance of the aircraft during cargo loading, a counterweight box 6 is also provided.

[0031] The counterweight box 6 is arranged in the front cabin 12. Several detachable heavy blocks are arranged in the counterweight box 6. A front cabin cover 120 for adjusting the number of heavy blocks in the counterweight box 6 is provided on the front cabin 12.

[0032] It further includes a control system 30 arranged on the mast 3. The control system 30 includes a rotary servo 31, a rotating rod 32, a connecting rod 33 and a rotor support 34.

[0033] One end of the rotor support 34 is hinged to the top of the mast 3. The top of the rotor support 34 is for the rotor 5 to be arranged. Two rotary servos 31 are symmetrically arranged on both sides of the mast 3. Each rotary servo 31 is connected to and drives a rotating rod 32. A connecting rod 33 is hinged to the end of each rotating rod 32. The two connecting rods 33 are respectively hinged to both sides of the rotor support 34.

[0034] When the rotary servos 31 on both sides rotate in the same direction, the two connecting rods 33 driven by the rotary servos 31 simultaneously pull the rotor support 34 to lift / pull down, realizing the pitching of the rotor support 34; when the rotary servos 31 on both sides are differentially driven, the two connecting rods 33 driven by the rotary servos 31 pull the rotor support 34 to tilt to one side, realizing the rolling motion of the rotor support 34. The control system 30 proposed by the present invention uses the symmetrically arranged rotary servos 31 and connecting rods 33 to control the steering and ascending / descending of the autogyro, with a fast control response speed and more sensitive control.

[0035] It further includes a braking system 7. The braking system 7 is arranged in the lower cabin. The braking system 7 includes a braking servo 71 and a brake master cylinder 72 arranged opposite to each other. The braking servo 71 is connected to and drives a cam 73 to rotate. The cam 73 is provided with a stop position 74 in a raised manner. The brake master cylinder 72 extends towards the braking servo 71 and is provided with a push rod 75 for starting / stopping the brake master cylinder 72. The push rod 75 rolls against the cam 73; when the braking servo 71 rotates the cam 73, the push rod 75 is lifted at the stop position 74, and the push rod 75 starts the brake master cylinder 72. The brake master cylinder 72 is connected to the wheels arranged under the landing gear 4.

[0036] It further includes GPS antennas 8. Two groups of GPS antennas 8 are respectively arranged on the tops of the front cabin 12 and the rear cabin 14. The two groups of GPS antennas 8 are respectively connected to the avionics box 16 and the engine control box 17.

[0037] It further includes an airspeed tube 9. The airspeed tube 9 is inserted into the front part of the front cabin 12. The airspeed tube 9 is connected to the avionics box 16.

[0038] The following points should be noted: First, in the description of this application, it should be noted that unless otherwise specified and defined, the terms "installed", "connected", and "linked" should be understood in a broad sense, which can be a mechanical connection or an electrical connection, or the communication inside two components, and can be directly connected. The terms "upper", "lower", "left", "right", etc. are only used to represent relative position relationships. When the absolute position of the object being described changes, the relative position relationship may change.

[0039] Second, in the drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are involved. For other structures, reference can be made to the general design. Without conflict, the same embodiment and different embodiments of the present invention can be combined with each other.

[0040] Finally, the above description is only the preferred embodiment of the present invention. The protection scope of the present invention is not limited to the above embodiments. All technical solutions within the idea of the present invention belong to the protection scope of the present invention.

Claims

1. A freight unmanned autogyro, comprising a fuselage (1), a frame (2), a mast (3) and landing gears (4). The fuselage (1) is sleeved on the frame (2). The cavity inside the fuselage (1) is for arranging avionics equipment. The rear part of the fuselage (1) is an engine compartment (11) for arranging an engine. The mast (3) is vertically arranged at the rear of the frame (2). The top of the mast (3) is for arranging a rotor (5). The landing gears (4) are arranged at the bottom of the frame (2). It is characterized in that: The cavity inside the fuselage (1) is separated by the frame (2) into an upper cabin and a lower cabin. The upper cabin includes a front cabin (12), a cargo hold (13) and a rear cabin (14) which are arranged in sequence from front to back. The lower cabin is for arranging a battery compartment (15) and a fuel tank. The avionics equipment includes an avionics box (16) and an engine control box (17). The avionics box (16) and the engine control box (17) are respectively arranged in the front cabin (12) and the rear cabin (14). The avionics box (16) and the engine control box (17) are respectively connected to the battery compartment (15). Sensors for collecting flight information are arranged inside the avionics box (16). The engine control box (17) is connected to and controls the engine. It further includes a counterweight box (6). The counterweight box (6) is arranged in the front cabin (12). Several detachable weights are arranged inside the counterweight box (6). A front hatch (120) for adjusting the number of weights in the counterweight box (6) is opened on the front cabin (12). It further includes a braking system (7). The braking system (7) is arranged in the lower cabin. The braking system (7) includes a braking servo (71) and a brake master cylinder (72) which are arranged oppositely. The braking servo (71) is connected to and drives a cam (73) to rotate. The cam (73) is provided with a stop position (74) in a raised manner. The brake master cylinder (72) extends towards the braking servo (71) and is provided with a push rod (75) for starting / stopping the brake master cylinder (72). The push rod (75) rolls against the cam (73).

2. The cargo unmanned autogyro according to claim 1, wherein: It further includes a control system (30) arranged on the mast (3). The control system (30) includes a rotary servo (31), a rotating rod (32), a connecting rod (33) and a rotor support (34). One end of the rotor support (34) is hinged to the top of the mast (3). The top of the rotor support (34) is for arranging the rotor (5). Two rotary servos (31) are symmetrically arranged on both sides of the mast (3). Each rotary servo (31) is connected to and drives a rotating rod (32). The end of each rotating rod (32) is hinged to a connecting rod (33). The two connecting rods (33) are respectively hinged to both sides of the rotor support (34).

3. The cargo unmanned autogyro according to claim 1, wherein: It further includes GPS antennas (8). Two groups of GPS antennas (8) are respectively arranged on the tops of the front cabin (12) and the rear cabin (14). The two groups of GPS antennas (8) are respectively connected to the avionics box (16) and the engine control box (17).

4. A freight unmanned autogyro according to claim 1, characterized in that: It further includes an airspeed tube (9). The airspeed tube (9) is inserted into the front part of the front cabin (12). The airspeed tube (9) is connected to the avionics box (16).

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