Vertical take-off and landing (VTOL) unmanned aerial vehicle capable of flying at low and high cruising speeds

Abstract

The present invention relates to an unmanned aerial vehicle providing stable and vibration-free flight at low cruising speeds, capable of staying airborne for longer durations during extended flights, having an optimal aerodynamic balance with its wing structure, and comprising an advanced telemetry and data transmission system, and is characterized in that it comprises a wing (1) with a profile structure providing stable and vibration-free flight at aerodynamically low speed, a tiltrotor mechanism (2) symmetrically arranged on the wing (1) with respect to the x-axis, adjusting the direction of the propellers (4) to horizontal or vertical position by making a circular movement in its position by means of the engine (3) integrated in the U-plate (2.1), a connection shaft (5) linking the symmetrical tiltrotor mechanisms (2) on the wing (1) to each other, at least one folding foot (6) integrated in the lower part of the aircraft and equipped with a shock absorber (7) system, a telemetry system remotely monitoring the aircraft and providing real-time data to the aircraft control unit, a camera and sensor system for collecting environmental data and obtaining images, a central processor unit and image processor unit processing the obtained data, and a battery powering the electronic components of the system.

Description

[0001] VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE CAPABLE OF FLYING AT LOW AND HIGH CRUISING SPEEDS

[0002] Technical Field:

[0003] The present invention relates to an unmanned aerial vehicle providing stable and vibration-free flight at low cruising speeds, capable of staying airborne for longer durations during extended flights, having an optimal aerodynamic balance with its wing structure, and comprising an advanced telemetry and data transmission system.

[0004] State of the Art:

[0005] An unmanned aerial vehicle (UAV) is a device capable of flight, usually remotely controlled or autonomously operated. These can come in various shapes and sizes and are used for various purposes. UAVs can be used in many areas such as observation and reconnaissance, mapping and research, emergency and rescue, cargo and delivery, entertainment and sports, and agriculture. However, today's UAVs have many disadvantages.

[0006] Fixed-wing UAVs, despite having long flight times, lack operational flexibility due to the runway requirement. In other words, they require large runway areas for take-off and landing, which limits operational flexibility. Such UAVs cannot be used in confined spaces or in areas where there are no runways.

[0007] UAVs with moving wings (multicopters), on the other hand, suffer from vibration problems due to the continuous operation of each engine, resulting in poor quality results, especially in imaging and data collection operations. In addition, the use of separate systems for vertical take-off / landing and horizontal flight in conventional methods increases costs. Furthermore, the combined operation of two different systems creates operational complexity.

[0008] UAVs operating over long distances may face difficulties in data transmission and risk mission interruption in the event of a lost connection. These UAVs have either a fixed- wing design for long-range flights or a multicopter design for short-range and vertical take-off / landing. However, this may limit their scope of application.

[0009] The utility model application no. TR2021021 130 describes a “hybrid unmanned aerial vehicle”. Hybrid Unmanned Aerial Vehicle is a hybrid aerial vehicle hybridized with propulsion engines positioned on the outer lower part of the main wall designed in the form of a circular bagel, having flight dynamics supported by the buoyancy forces of lighter-than-air gases, operating wirelessly at low and medium altitudes, wherein the main fuselage pipes made of carbon fiber are fixed to each other and to the main wall with fiber ropes using fiber rope fixing apparatus and fiber rope tensioning apparatus in order to make the entire aircraft behave like a mono-block fuselage and to converge the fuselage flexibility to zero, performing suspension, route calculation, new route determination operations autonomously and manually wirelessly from the ground control station, measuring the suspension dynamics at the mission altitude with the sensors located thereon and transferring them to the ground control station via wireless data systems, wherein the main wall made of PVC and graphene-reinforced transparent mylar fabric, which provides lighter-than-air gas seal, has zero visibility and radar visibility at medium and high altitudes, capable of operating with different payloads, wherein the energy infrastructure is provided by a battery unit fixed on the main control unit and flexible solar energy panels mounted on the main perimeter.

[0010] The patent application no. TR2021013913 describes an unmanned aerial vehicle. The present invention relates to unmanned aerial vehicles that function more efficiently by connecting to a power plant on the ground or in a vehicle and supplying compressed air from the related power plants. During the energy transfer to unmanned aerial vehicles in flight, the use of compressed air transported through the lines, the efficiency gained due to the lightweight material carried in the system, the additional use of compressed air during the vehicles' flights, and the supply of the battery with compressed air contribute to fuel and energy savings.

[0011] The unmanned aerial vehicles described in the above-mentioned applications are equipment that have not been able to go beyond the existing configuration, have vertical take-off and landing capability, but incapable of creating thrust in the air and therefore cause an increase in flight time from one position to another, consume too much power, and cannot overcome the disadvantages created by the fixed wing formation. As a result, there is a need for a new technology which can overcome the disadvantages mentioned above.

[0012] Definition of the Invention:

[0013] The object of the present invention is to provide an unmanned aerial vehicle (UAV) capable of vertical take-off and landing (VTOL) and equipped with tiltrotor technology. The invention combines the long range and energy efficiency advantages of fixed-wing aircraft and the vertical take-off / landing capability of multicopters to provide an effective, flexible, and reliable solution for a wide range of applications. In particular, this addresses critical needs such as long flight times, stable flight, cost effectiveness, and the ability to operate in harsh conditions.

[0014] In the invention, thanks to the tiltrotor technology, the UAV can take-off and land vertically and then switch to horizontal flight mode, providing the energy efficiency of fixed-wing UAVs. Turning off the rear engines during glide in airplane mode increases energy savings and extends flight time.

[0015] The invention eliminates the need for a runway thanks to its vertical take-off and landing capability. Thus, it can easily operate in confined spaces, mountainous areas, urban areas, or emergency zones.

[0016] The invention provides stable and vibration-free flight with the wing structure and tilt-rotor technology of the UAV. This ensures high quality results, especially in sensitive imaging and data collection tasks.

[0017] The tiltrotor mechanism in the invention offers both vertical and horizontal flight capability in a single system, eliminating the need for additional horizontal engine and thus providing a cost-effective solution. This reduces both production and maintenance costs.

[0018] The advanced telemetry system in the invention ensures that data transmission can continue securely even over long distances. In the unlikely event of a loss of connectivity, the UAV can autonomously resume its mission or return to its take-off location, increasing operational reliability. The Tiltrotor VTOL UAV provides versatility and application flexibility, offering a suitable solution for both long-range flights and missions requiring vertical take-off / landing in confined spaces. Additionally, tiltrotors provide energy efficiency by shutting down the rear engines when switching to horizontal flight mode. This offers longer flight times compared to conventional multicopters and increases mission duration.

[0019] Thanks to the fuselage wing structure and aerodynamic design, the aircraft provides stable and vibration-free flight even at low speeds. This feature allows for high quality results in imaging and data collection.

[0020] Description of the Drawings:

[0021] The invention will be described with reference to the accompanying figures, so that the features of the invention will be more clearly understood and appreciated, however it is not intended to limit the invention to these particular embodiments. On the contrary, it is intended all alternatives, modifications, and equivalences that may be included in the field of the invention as defined by the accompanying claims are within the scope. It should be understood that the details shown are for the sole purpose of illustrating preferred embodiments of the present invention and are intended to provide the most useful and easily understandable description of both the forming of the methods and the rules and conceptual features of the invention. In the drawings;

[0022] Figure 1 The overall perspective view of the system of the invention.

[0023] Figure 2 The perspective view of the tiltrotor mechanism.

[0024] Figure 3 The perspective view of the aircraft foot section.

[0025] The figures which will help understand this invention are numbered as indicated in the accompanying drawing and are given below with their names.

[0026] Description of the References:

[0027] 1 . Wing

[0028] 2. Tiltrotor mechanism

[0029] 2.1. U-plate

[0030] 2.2. Bearing 2.3. Shaft

[0031] 3. Engine

[0032] 4. Propeller

[0033] 5. Connection shaft

[0034] 6. Folding foot

[0035] 7. Shock Absorber

[0036] 8. Wheel

[0037] Detailed Description of the Invention:

[0038] The constituent parts of the invention are essentially: wing (1), tiltrotor mechanism (2), engine (3), propeller (4), connection shaft (5), folding foot (6), shock absorber (7), and wheel (8). The tiltrotor mechanism (2) comprises a U-plate (2.1), bearing (2.2), and shaft (2.3).

[0039] The wings (1) on the aircraft fuselage are formed from profiles with suitable hump and angle of attack. The winglet section at the tip of the wing aims to reduce induced friction and increase flight efficiency. This part reduces the size and impact of the vortices produced at the tips of the wing, allowing the aircraft to consume less fuel.

[0040] The system of the invention is an unmanned aerial vehicle capable of vertical take-off and landing. The vertical take-off and landing feature is provided by the tiltrotor mechanism (2) and engine (3). There are four engines (3) in the system. These engines (3) are connected to the U-plates (2.1) of the tiltrotor mechanisms (2). When the shaft of the engine (3) moves clockwise or counterclockwise, the U-plates (2.1) and the propellers (4) connected to the U-plates (2.1) also move the same way. When the propellers (4) point perpendicular to the ground, the aircraft is ready for take-off and landing. In order to increase the take-off and landing efficiency of the system, the propellers (4) are arranged symmetrically with respect to the x-axis of the wing (1) (Figure 1). These propellers (4) are connected to each other by a connection shaft (5). Bearings (2.2) are used in order to prevent the forces falling on the shaft (2.3) during the rotational movement of the propellers (4) from damaging the parts. When the tiltrotor mechanism (2) moves to the horizontal position, the central processor unit commands the rear engines to shut these engines down. The folding feet (6) at the bottom of the body have a shock absorber (7) each. Shock absorber spring (6) were used to dampen the load on the fuselage in take-off and landing situations and to minimize fuselage damage. The autonomous control system of the invention enables the unmanned aerial vehicle to take-off or land automatically, and allows commands to be sent to the unmanned aerial vehicle via mobile application or server through remote communication protocols. The telemetry in the system ensures reliable data transmission even over long distances and provides autonomous operation capability in the event of a lost connection. The telemetry system supports data collection, transmission, and autonomous operation capability.

[0041] The sensors and camera enable to collecting environmental data and obtaining images and provide the necessary information for navigation. The central processor unit and image processor units process this information received and transmit it to the control unit and pilot command unit. There is also a rechargeable battery that feeds the electronic parts of the system.

Claims

CLAIMS1 - A vertical take-off and landing (VTOL) unmanned aerial vehicle capable of flying at low and high cruising speeds, characterized in that it comprises:- a wing (1) with a profile structure providing stable and vibration-free flight at aerodynamically low speed,- a tiltrotor mechanism (2) symmetrically arranged on the wing (1) with respect to the x-axis and adjusting the direction of the propellers (4) to horizontal or vertical position by making a circular movement in its position by means of the engine (3) integrated in the U-plate (2.1),- a connection shaft (5) linking the symmetrical tiltrotor mechanisms (2) on the wing (1) to each other,- at least one folding foot (6) integrated in the lower part of the aircraft and equipped with a shock absorber (7) system,- a telemetry system remotely monitoring the aircraft and providing realtime data to the aircraft control unit,- a camera and sensor system for collecting environmental data and obtaining images,- a central processor unit and image processor unit processing the obtained data, and- a battery powering the electronic components of the system.2 - The vertical take-off and landing (VTOL) unmanned aerial vehicle capable of flying at low and high cruising speeds according to claim 1 , characterized in that the tiltrotor mechanism (2) has at least one bearing (2.2) that provides load balance over the shaft (2.3).

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