RU208636U1 - UNMANNED ROTOR-WING AIRCRAFT (UAV) - Google Patents

Abstract

The utility model relates to the field of aircraft engineering, namely unmanned rotary-wing aircraft, and can be used in various industries, including for the transport of goods and/or passengers, for observation and/or surveying. The technical result, which the utility model is aimed at, is to provide the possibility of rapid transformation of the structure for the purposes of transportation. The technical result is achieved in a device containing a body connected to the tail beam, a coaxial carrier system, including the upper and lower rotors driven by a gearbox connected to the engine, an on-board electronic equipment unit, control system servo drives, a landing gear, a fuel tank , while the gearbox, engine, avionics unit, control system servos are located inside the body on a frame to which the fuel tank and the tail assembly are attached, made removable, as well as the landing gear, made folding, in addition, the blades of the carriers are also removable screws. 12 w.p. f-ly, 4 ill.

Description

The utility model relates to the field of aircraft engineering, namely unmanned rotary-wing aircraft, and can be used in various industries, including for the transport of goods and/or passengers, for observation and/or surveying.

An unmanned rotary-wing aircraft (UAV) is known according to a utility model patent No. 185205 (published on November 26, 2018), characterized in that it has a semi-monocoque fuselage type with one tail boom, a coaxial carrier system, including upper and lower rotors driven by means of a gearbox connected to the main engine, a flight and navigation complex, a fuel tank system, a landing gear and additionally contains a tail engine at the end of the tail boom.

The disadvantage of the utility model is the inability to quickly transform the device for the purpose of transportation due to the complexity of the design.

The technical result, which the utility model is aimed at, is to provide the possibility of rapid transformation of the structure for the purposes of transportation.

The technical result is achieved in a device containing a body connected to the tail beam, a coaxial carrier system, including upper and lower rotors driven by a gearbox connected to the engine, an avionics unit, control system servos, a landing gear, a fuel tank , while the gearbox, engine, avionics unit, control system servos are located inside the body on a frame to which the fuel tank and the tail assembly are attached, made removable, as well as the landing gear, made folding, in addition, the blades are made removable bearing screws.

The tail unit and blades are removable, and the landing gear is collapsible, which makes it possible to bring the UAV into a compact transport state, which allows transporting up to 6 UAVs in a standard twenty-foot container or easily placing the UAV on a light trailer or in a pickup truck.

Preferably, the carrier system is provided with swashplates.

It is preferable to attach the fuel tank and detachable tail fin, as well as the landing gear to the bottom of the hull frame.

In one of the UAV variants, the empennage beam is made protruding in front of the hull, and an optoelectronic unit for observation and/or shooting is installed at its front end.

In one of the versions of the BVLA, the optoelectronic unit for observation and/or shooting is made gyro-stabilized with view cameras.

In one of the versions of the UAV, the body is made with a hole in the front part, in which the engine radiator is fixed.

In one of the versions of the UAV, the fuel tank mount is made with the possibility of installing fuel tanks of various capacities without disturbing the alignment of the device.

In one of the versions of the UAV, the landing gear is made in the form of skid trapezoidal shock-absorbing tubular structures, between which a cargo platform is fixed to accommodate the target load.

In one of the variants of the BVLA, the loading platform is made with a container fixed on it, equipped with a sprayer for pollinating the fields and/or applying fertilizers.

In one of the variants of the BVLA, the cargo platform is made with the possibility of fixing various cargoes and/or mail containers on it.

In one of the versions of the UALA, the cargo platform is made with the possibility of attaching a medical stretcher with the victim on it.

In one of the embodiments, inside the cavity of the shaft of the main rotors, the UAV parachute rescue system, located above the main rotors, is fastened to the UAV frame.

In one of the UAV variants, the cargo platform is equipped with an additional fuel tank for monitoring remote, hard-to-reach objects.

The proposed technical solution is illustrated in the figures.

In Fig.1, shows a General view of the BVLA, where positions 1-13 designate the structural elements:

1 - upper rotor,

2 - lower main rotor,

3 - parachute rescue system,

4 - body,

5 - tail beam,

6 - horizontal tail,

7 - vertical plumage,

8 - fuel tank,

9 - landing gear,

10 - chassis skids,

11 - cargo platform,

12 - struts,

13 - optoelectronic unit for observation and / or shooting.

Figure 2 shows the internal contents of the hull UAV, where the positions 14-19 denote structural elements:

12 - struts,

14 - frame,

15 - gearbox,

16 - engine,

17 - block of on-board radio-electronic equipment,

18 - servo drives of the control system,

19 - radiator.

Figure 3 shows the placement of UAVs in a cargo container in a folded state for transportation.

Figure 4 shows BVLA with a cargo platform with a medical stretcher attached to it with the victim.

The utility model can be implemented in a device containing a body 4 connected to the tail beam 5, the rear part of which is made with horizontal 6 and vertical tail 7, and an optoelectronic unit for observation and/or shooting 13 is attached to the front part. also contains a coaxial carrier system, including the upper 1 and lower 2 rotors, driven by means of a gearbox 15 connected to the engine 16, an avionics unit 17, servos of the control system 18, a landing gear 9 connected by struts 12 to the tail beam 5 , made with skids 10 interconnected by a cargo platform 11, a fuel tank 8, while the gearbox 15, the engine 16, the avionics unit 17, the servo drives of the control system 18, are compactly located inside the body 4 on the frame 14, to which the fuel tank is attached from below tank 8 and tail beam 5, made removable, as well as landing e chassis 9, made folding, in addition, the blades of the rotors 1 and 2 are also removable. Through the internal cavity of the shaft of the rotors 1 and 2, the parachute rescue system 3, located above the rotors 1 and 2, is fastened to the frame 14. In the front part housing 4, a hole is made in which the radiator 19 of the engine 16 is fixed.

The utility model works as follows. The engine 16 creates on its own output shaft a torque input to the gearbox 15, which converts the high-speed rotation of the output shaft of the engine 16 into a counter-rotation of two rotors - the upper 1 and the lower 2. The rotors 1, 2 rotate at the same speed. With the help of the avionics unit 17, it controls the UAV flight, in particular, the operation of the engine 16, as well as the upper 1 and lower 2 main rotors. The engine 16 is powered by fuel from the fuel tank 8. Using the swashplates of the rotors 1 and 2, forces and moments are created that control the spatial position of the UAV.

In preparation for transportation from the BVLA, the blades are removed from the upper 1 and lower 2 rotors, the fuel tank 8 is disconnected from the frame 14 of the body 4, after which the tail beam 5 with plumage 6 and 7 is disconnected from the frame 14 of the body 4, as well as the struts 12 from landing gear 9, then the cargo platform 11 is disconnected from the skids of the landing gear 10. After that, the elements of the landing gear 9 are rotated around the longitudinal axis of their attachment to the frame 14 so that the body 4 is under the skids of the chassis 10. This ensures a compact form of the device, most adapted to transportation.

Preparation of the UAV after transportation for flight is carried out in the reverse order. The parts of the landing gear 9 are rotated around the longitudinal axis of their fastening to the frame 14 so that the skids of the landing gear 10 are under the body 4, the skids of the landing gear 10 are connected by attaching the loading platform 11 to them, then the tail beam 5 with plumage 6 and 7 is fixed to the lower part body 4, and the struts 12 to the landing gear 9. After that, the fuel tank 8 is attached to the frame 14 of the body 4, and the blades are installed in the upper 1 and lower 2 rotors.

Thus, the technical result, which the utility model is aimed at, is achieved in the form of enabling the rapid transformation of the structure for transportation purposes.

Claims (13)

1. An unmanned rotorcraft (UAVLA), containing a body connected to the tail beam, a coaxial carrier system, including the upper and lower rotors driven by a gearbox connected to the engine, an on-board electronic equipment unit, control system servo drives, a landing chassis, fuel tank, characterized in that the gearbox, engine, avionics unit and control system servo drives are located inside the body on a frame to which the removable fuel tank and tail beam are attached, as well as a folding landing gear, in addition , removable rotor blades are made. 2. UAV according to claim 1, characterized in that the carrier system is made with swashplates. 3. UAV according to claim 1, characterized in that the fuel tank and the removable tail beam, as well as the landing gear, are attached to the lower part of the hull frame. 4. UVLA according to claim 1, characterized in that the tail beam is made protruding in front of the body, and an optoelectronic unit for observation and / or shooting is installed at its front end. 5. UAV according to claim 1, characterized in that the optical-electronic unit for observation and / or shooting is made gyro-stabilized and with view cameras. 6. UAV according to claim 1, characterized in that the body is made with a hole in the front, in which the engine radiator is fixed. 7. UAV according to claim 1, characterized in that the fastening of the fuel tank is made with the possibility of installing fuel tanks of various capacities without disturbing the alignment of the device. 8. UAV according to claim 1, characterized in that the landing gear is made in the form of skid trapezoidal shock-absorbing tubular structures, between which a cargo platform is fixed to accommodate the target load. 9. UAV according to claim 8, characterized in that the loading platform is made with a container fixed on it, equipped with a sprayer for pollinating fields and / or fertilizing. 10. UAV according to claim 8, characterized in that the cargo platform is made with the possibility of fixing various cargoes and/or mail containers on it. 11. UVLA according to claim 8, characterized in that the cargo platform is made with the possibility of attaching a medical stretcher with the victim on it. 12. UAV according to claim 8, characterized in that the cargo platform is made with an additional fuel tank for monitoring remote, hard-to-reach objects. 13. UAV according to claim 1, characterized in that inside the cavity of the shaft of the main rotors, the parachute rescue system of the UAV, located above the main rotors, is attached to the frame of the UAV.

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