Unmanned aerial vehicle capable of vertical take-off and landing (VIOL) with an electric fan engine (EDF)

Abstract

The present invention relates to an unmanned aerial vehicle capable of vertical take-off and landing (VTOL) with an electric fan engine (EDF), which can be used in the aviation sector in areas such as military, civil, agricultural, surveillance and reconnaissance, characterized in that it has a sharp-lined aircraft fuselage (1) forming the unmanned aerial vehicle, 2 aircraft wings (2) extending from the aircraft fuselage (1) to both sides, 2 tail wings (3) extending from the rear part of the aircraft fuselage (1) to both sides, a vertical wing (4) extending upwards from the rear part of the aircraft fuselage (1), at least 2 front electric fan engines (5) positioned under the aircraft wing (2) and capable of operating in 3 phases, i.e. horizontal-45°-vertical, a wing engine cover (6), which moves with the front electric fan engine (5) and acts as an air brake to maintain the stability of the aircraft fuselage (1) when the front electric fan engine (5) is in a vertical position during landing and take-off, at least 2 rear electric fan engines (7) positioned at the rear part of the aircraft fuselage (1) and capable of operating in 3 phases, i.e. horizontal-45°-vertical, a fuselage engine cover (8), which moves with the rear electric fan engine (7) and acts as an air brake to maintain the stability of the aircraft fuselage (1) when the rear electric fan engine (7) is in a vertical position during landing and take-off, a rotational clearance (9) on the aircraft fuselage (1) for rotation of the rear electric fan engine (7), an air inlet opening (10), which is positioned under the aircraft fuselage (1) and through which the air inlet takes place, an air inlet path (11) specially designed for the rear electric fan engine (7) located in the rear part and through which the air entering through the air inlet opening (10) advances and a landing gear (12) positioned on the lower part of the aircraft fuselage (1) and designed for both vertical and normal landing and take-off.

Description

[0001] SPECIFICATION

[0002] UNMANNED AERIAL VEHICLE CAPABLE OF VERTICAL TAKE-OFF AND LANDING (VTOL) WITH AN ELECTRIC FAN ENGINE (EDF)

[0003] Technical Field:

[0004] The present invention relates to an unmanned aerial vehicle capable of vertical take-off and landing (VTOL) with an electric fan engine (EDF), which can be used in the aviation sector in areas such as military, civil, agricultural, surveillance and reconnaissance.

[0005] State of the Art:

[0006] Today, unmanned aerial vehicles are widely used for a variety of purposes and there has been a very rapid development in unmanned aerial vehicle technologies in recent times. The areas of use can be diversified as military, civil, agricultural, surveillance, etc. The widespread use of unmanned aerial vehicles has created a number of problems. For example, fixed-wing unmanned aerial vehicles can remain airborne for extended periods and carry heavy loads, but the unmanned aerial vehicles require a lengthy airfield for landing and take-off. Rotary wing unmanned aerial vehicles, on the other hand, do not require any runway, but their useful load carrying capacity and endurance are low. Many models of unmanned aerial vehicles have fixed wings and require an airfield to take off. If a suitable airfield cannot be found, the mission cannot be carried out.

[0007] The patent application no. EP3643602A1 describes an “Unmanned Aerial Vehicle”. The invention relates to the field of aircraft technology and provides an unmanned aerial vehicle (UAV) comprising a vehicle fuselage and arms attached to the vehicle fuselage. The arm is hinged to the vehicle fuselage using a spherical hinge part and can be folded or unfolded relative to the vehicle fuselage. The arm is connected to the vehicle fuselage of the UAV using a spherical hinge, as described above. The arm can be folded and unfolded smoothly without intervention, in accordance with users’ known operating habits, making the structure more compact and easier to transport once the entire UAV is folded. In addition, damage to the UAV due to impact during the transportation process can be effectively prevented.

[0008] The patent application no. CN111186568A describes a “Multifunctional Unmanned Aerial Vehicle”. The invention relates to an unmanned aerial vehicle, in particular a multifunctional unmanned aerial vehicle. The device is equipped with illumination lamps and can provide lighting in poor light conditions. The device is equipped with a camera that can take and store pictures. The device is equipped with a horn, warning birds in the vicinity and preventing damage to the device by birds approaching. The signal transceivers are mounted on the device body and the rotor blades are mounted on the device body. The illumination lamps are located on the device body and at the lower end of the device body, and the speakers are located on the device body and at the lower end of the device body. A control box is located at the lower end of the device body and in the middle of the device body, a control chip and a storage battery are arranged both on the control box and in the control box, and a camera is located on the control chip and is placed at the lower end of the control chip. A support is connected to the device body and is located at the lower end of the device body and a fixing frame is placed on this support.

[0009] Unmanned aerial vehicles of various designs are described above. These vehicles are manufactured to be used for a variety of tasks. There are many small and large UAVs with various designs. Some of these UAVs are capable of vertical take-off and landing, while others are capable of normal take-off and landing. A runway is required for normal take-off and landing. Those capable of vertical take-off and landing cannot operate with sufficient efficiency.

[0010] As a result, there is a need for a new technology that can overcome the disadvantages mentioned above.

[0011] Disclosure of the Invention:

[0012] The present invention is an unmanned aerial vehicle capable of vertical take-off and landing (VTOL) with an electric fan engine (EDF), which overcomes the disadvantages mentioned above, characterized in that it is capable of both vertical take-off and landing and normal take-off and landing, it has an electric fan engine, it can be used in gas turbine engines, the engines can operate in horizontal, 45° and vertical positions, there are covers that can rotate the engines, the covers act as air brakes, there is provided a specially designed air inlet, the aircraft fuselage has sharp-lined aerodynamics, it operates more efficiently, and it has a compact structure.

[0013] The invention is capable of vertical landing and take-off by means of front and rear electric fan engines. The engines operate in 3 positions, i.e. horizontal, 45° and vertical. There are covers for the movement of the engines. The covers also increase the stability of the vehicle by acting as an air brake during vertical landing and take-off when they are in the vertical position. The engines can be either electric or gas turbine. There is provided a specially designed air inlet at the rear that feeds air to the engines. The aircraft fuselage has a specific sharp-lined aerodynamic design for vertical take-off and landing, normal take-off and landing and flight. It is capable of vertical landing and take-off in places where there is no runway. As the wings are fixed and only the engines are movable, energy is saved and high efficiency is achieved during flight.

[0014] The simple attachment of the components of the invention facilitates easy installation, leading to cost-effectiveness due to the short assembly time. The invention also has a robust structure.

[0015] Description of the Drawings:

[0016] The invention will be described with reference to the accompanying figures, so that the features of the invention can be more clearly understood and appreciated, without intending to limit the invention to these particular embodiments. Rather, it is intended to cover all alternatives, modifications and equivalents of the invention which may be included within the scope defined by the appended claims. It should be appreciated that the details shown are given for the sole purpose of describing the preferred embodiments of the present invention and are presented for the purpose of both illustrating the methods and providing the most useful and easily understood description of the rules and conceptual features of the invention. In these drawings:

[0017] Fig. 1 Front and rear views of the system.

[0018] Fig. 2 Top view of the system.

[0019] Fig. 3 Bottom view of the system.

[0020] Fig. 4 Perspective view of the system. Fig. 5 Left and right views of the system.

[0021] Fig. 6 Perspective view of the system.

[0022] Fig. 7 Perspective view of the system.

[0023] Fig. 8 Cross-sectional view of the system.

[0024] The figures useful for the understanding of the present invention are numbered as indicated in the accompanying drawing and given below together with their names.

[0025] Description of the Reference Numbers:

[0026] 1. Aircraft Fuselage

[0027] 2. Aircraft Wing

[0028] 3. Tail Wing

[0029] 4. Vertical Wing

[0030] 5. Front Electric Fan Engine

[0031] 6. Wing Engine Cover

[0032] 7. Rear Electric Fan Engine

[0033] 8. Fuselage Engine Cover

[0034] 9. Rotational Clearance

[0035] 10. Air Inlet Opening

[0036] 11. Air Inlet Path

[0037] 12. Landing Gear

[0038] Description of the Invention:

[0039] The invention has a sharp-lined aircraft fuselage (1) forming the unmanned aerial vehicle, 2 aircraft wings (2) extending from the aircraft fuselage (1) to both sides, 2 tail wings (3) extending from the rear part of the aircraft fuselage (1) to both sides, a vertical wing (4) extending upwards from the rear part of the aircraft fuselage (1), at least 2 front electric fan engines (5) positioned under the aircraft wing (2) and capable of operating in 3 phases, i.e. horizontal-45°-vertical, a wing engine cover (6), which moves with the front electric fan engine (5) and acts as an air brake to maintain the stability of the aircraft fuselage (1) when the front electric fan engine (5) is in a vertical position during landing and take-off, at least 2 rear electric fan engines (7) positioned at the rear part of the aircraft fuselage (1) and capable of operating in 3 phases, i.e. horizontal-45°-vertical, a fuselage engine cover (8), which moves with the rear electric fan engine (7) and acts as an air brake to maintain the stability of the aircraft fuselage (1) when the rear electric fan engine (7) is in a vertical position during landing and takeoff, a rotational clearance (9) on the aircraft fuselage (1) for rotation of the rear electric fan engine (7), an air inlet opening (10), which is positioned under the aircraft fuselage

[0040] (1) and through which the air inlet takes place, an air inlet path (11) specially designed for the rear electric fan engine (7) located in the rear part and through which the air entering through the air inlet opening (10) advances and a landing gear (12) positioned on the lower part of the aircraft fuselage (1) and designed for both vertical and normal landing and take-off.

[0041] Detailed Description of the Invention:

[0042] The constituent parts of the invention are mainly the aircraft fuselage (1), aircraft wing

[0043] (2), tail wing (3), vertical wing (4), front electric fan engine (5), wing engine cover (6), rear electric fan engine (7), fuselage engine cover (8), rotational clearance (9), air inlet opening (10), air inlet path (11) and landing gear (12).

[0044] The unmanned aerial vehicle has an aircraft fuselage (1) with sharp lines specifically designed for vertical and normal flight. There is provided an aircraft wing (2) extending from both sides of the aircraft fuselage (1). There is provided a tail wing (3) positioned at the rear part of the aircraft fuselage (1) and extending to both sides and a vertical wing (4) extending upwards. At least 2 front electric fan engines (5) are positioned under the aircraft wing (2). The front electric fan engine (5) can operate in 3 positions, i.e. vertical, 45° and horizontal, for vertical take-off and landing, horizontal take-off and landing and flight. The front electric fan engine (5) is connected to the wing engine cover (6) which is part of the aircraft wing (2). The wing engine cover (6) can move vertically, 45° and horizontally by means of a shaft. The front electric fan engine (5) moves together with the wing engine cover (6). Thus, when the aircraft takes off or lands vertically, the wing engine cover (6) neutralizes the horizontal movement. It also acts as a stabilizer for movement at 45 degrees. At least 2 rear electric fan engines (7) are positioned under the aircraft fuselage (1). The rear electric fan engine (7) can operate in 3 positions, i.e. vertical, 45° and horizontal, by means of a shaft for vertical take-off and landing, horizontal take-off and landing and flight. The rear electric fan engine (7) is connected to the fuselage engine cover (8) which is part of the aircraft fuselage (1). The fuselage engine cover (8) can move vertically, 45° and horizontally by means of a shaft. The rear electric fan engine (7) moves together with the fuselage engine cover (8). There is provided a rotational clearance (9) in the aircraft fuselage (1) for the rotation of the rear electric fan engine (7). Gas turbine engines can also be used instead of the front electric fan engine (5) and the rear electric fan engine (7). There is provided in the lower part of the aircraft fuselage (1) an air inlet opening (10) through which air enters. The air entering through the air inlet opening (10) can feed the rear electric fan engine (7) via the specially designed air inlet path (11). The landing gear (12), which is specially designed for vertical and horizontal landing and take-off of the unmanned aerial vehicle, is positioned under the aircraft fuselage (1).

Claims

CLAIMS1. An unmanned aerial vehicle capable of vertical take-off and landing (VTOL) with an electric fan engine (EDF), characterized in that it has:- a sharp-lined aircraft fuselage (1) forming the unmanned aerial vehicle,- 2 aircraft wings (2) extending from the aircraft fuselage (1) to both sides,- 2 tail wings (3) extending from the rear part of the aircraft fuselage (1) to both sides,- a vertical wing (4) extending upwards from the rear part of the aircraft fuselage (1),- at least 2 front electric fan engines (5) positioned under the aircraft wing (2) and capable of operating in 3 phases, i.e. horizontal, 45° and vertical,- a wing engine cover (6), which moves with the front electric fan engine (5) and acts as an air brake to maintain the stability of the aircraft fuselage (1) when the front electric fan engine (5) is in a vertical position during landing and take-off,- at least 2 rear electric fan engines (7) positioned at the rear part of the aircraft fuselage (1) and capable of operating in 3 phases, i.e. horizontal, 45° and vertical,- a fuselage engine cover (8), which moves with the rear electric fan engine (7) and acts as an air brake to maintain the stability of the aircraft fuselage (1) when the rear electric fan engine (7) is in a vertical position during landing and take-off,- a rotational clearance (9) on the aircraft fuselage (1) for rotation of the rear electric fan engine (7),- an air inlet opening (10), which is positioned under the aircraft fuselage (1) and through which the air inlet takes place,- an air inlet path (11) specially designed for the rear electric fan engine (7) located in the rear part and through which the air entering through the air inlet opening (10) advances and- a landing gear (12) positioned on the lower part of the aircraft fuselage (1) and designed for both vertical and normal landing and take-off.

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