A wing structure for use in unmanned helicopters

Abstract

The invention relates to a wing (10) to be used in unmanned helicopters (50). The novelty of the invention lies in that the structure of the wing (10) comprises at least one mounting hole (13) to be connected to a drive element, at least one first module (11) and at least one second module (12) that are identical and symmetrical to each other being located on opposite sides of the said mounting hole (13), the side of the wing (10) that first contacts the air being a front portion (20), wherein this front portion (20) comprises a contact surface (21) that is slightly tapered and at least partially raised relative to the ground, a rear portion (30) located in the direction opposite to the front portion (20) comprising at least one serrated form (31), and a section of the said serrated form (31) comprising a protrusion region (32) extending at least partially outward.

Description

[0001] AWING STRUCTURE FOR USE IN UNMANNED HELICOPTERS

[0002] TECHNICAL FIELD

[0003] The invention relates to a wing to be used in unmanned helicopters.

[0004] PRIOR ART

[0005] An unmanned helicopter is an aircraft that operates via remote control or autonomously, does not carry humans, and is generally used for military, industrial, or research purposes. These helicopters operate based on the aerodynamic principles of conventional helicopters and are equipped with engine, rotor, and stability systems. However, they lack a pilot cabin and human-oriented control mechanisms. Unmanned helicopters provide high maneuverability and flexible usage advantages in missions such as reconnaissance, surveillance, cargo transport, emergency response, and mapping. Thanks to their autonomous systems, they are capable of following predetermined routes, analyzing environmental data, or being operated by remote operator commands.

[0006] One of the most significant issues encountered during the design of the wing structures of unmanned helicopters is the necessity of achieving a balance between aerodynamic efficiency and durability. The selection of materials used to ensure that the wings are lightweight yet sufficiently strong directly affects the design. Lightweight materials, particularly carbon fiber composites, may be sensitive to vibrations and excessive loads, which increases the risk of fatigue and deformation in the long term. In addition, optimizing the rotational speeds of the rotor blades, reducing vibrations, and precisely adjusting the control surfaces are of great importance for ensuring the stability and controllability of the helicopter. If the design is not properly executed, irregularities in the airflow may cause turbulence on the wing surfaces, thereby reducing energy efficiency.During use, rotor blades commonly encounter issues such as excessive vibration and wear due to weather conditions. Strong winds, high altitude, or sudden maneuvers increase the structural loads on the wings and shorten the material lifespan. In addition, the formation and gradual expansion of microscopic cracks on the continuously moving wing surfaces pose safety risks. Environmental factors such as sand, dust, or humidity may accumulate on the surfaces of the wings, reducing aerodynamic performance and leading to a loss of control. In order to manage all these problems effectively, methods such as regular maintenance, the use of advanced technologies in wing materials, and vibration analyses must be implemented.

[0007] As a result, all the problems mentioned above have made it necessary to introduce an innovation in the relevant technical field.

[0008] BRIEF DESCRIPTION OF THE INVENTION

[0009] The present invention relates to a wing structure intended to eliminate the above-mentioned disadvantages and to provide new advantages to the relevant technical field.

[0010] One objective of the invention is to provide a wing that is lightweight, durable, and has high aerodynamic efficiency.

[0011] Another objective of the invention is to provide a modular wing that enables silent flight and facilitates maintenance and repair processes.

[0012] In order to achieve all the objectives mentioned above and those that will emerge from the detailed description below, the present invention is a wing to be used in unmanned helicopters. Accordingly, its novelty lies in that the structure of the wing comprises at least one mounting hole to be connected to a wing drive element, at least one first module and at least one second module that are identical and symmetrical to each other being located on opposite sides of the mounting hole, the side of the wing that first contacts the air being a front portion, wherein this front portion comprises a contact surface that is slightly tapered and at least partiallyraised relative to the ground, a rear portion located in the direction opposite to the front portion comprising at least one serrated form, and a protrusion region extending at least partially outward in a section of the serrated form.

[0013] A feature of a possible embodiment of the invention is that the serrated form is in the shape of domes arranged side by side in a sequential manner. In this way, the airflow is smoothed, aerodynamic efficiency is increased, and silent flight is achieved.

[0014] A feature of another possible embodiment of the invention is that the serrated form continues within the protrusion region as well. In this way, the air circulating inside the wing is directed in a regular manner and is pressed downward, thereby increasing flight stability.

[0015] A feature of another possible embodiment of the invention is that it is manufactured from carbon fiber material. In this way, the wing provides a lightweight, durable, and long-lasting structure, thereby optimizing the performance of the unmanned aerial vehicle.

[0016] A feature of another possible embodiment of the invention is that the wing has a length of 200 mm, a width of 25 mm, and a thickness of 2.5 mm. In this way, the wing is enabled to generate optimum lift force by providing lightness and aerodynamic balance.

[0017] A feature of another possible embodiment of the invention is that it has a maximum weight of 8 grams. In this way, the energy consumption of the unmanned aerial vehicle is reduced, the payload capacity is increased, and overall flight efficiency is achieved.

[0018] A feature of another possible embodiment of the invention is that the wing comprises a tip portion that tapers on the environmentally outward-facing side. In this way, air resistance is minimized, the aerodynamic performance of the wing is increased, and flight maneuverability is supported.A feature of another possible embodiment of the invention is that the serrated form is positioned toward the tip portions of the modules in order to regulate airflow and reduce turbulence. In this way, the airflow is made more uniform, the effect of turbulence is minimized, and silent flight performance is enhanced.

[0019] BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 shows a representative perspective view of the wing subject to the invention.

[0021] Figure 2 shows a representative side view of the wing subject to the invention.

[0022] Figure 3 shows a representative top view of the wing subject to the invention.

[0023] Figure 4 shows a representative perspective view of the unmanned helicopter on which the wing subject to the invention is positioned.

[0024] DETAILED DESCRIPTION OF THE INVENTION

[0025] In this detailed description, the subject matter of the invention is explained through examples intended solely for a better understanding of the subject, without creating any limiting effect.

[0026] Figure 1 shows a representative perspective view of the wing (10) subject to the invention. Accordingly, the wing (10) subject to the invention is a structural element used in aircraft, particularly in unmanned helicopters (50), intended to direct airflow and generate lift force. The wing (10) possesses aerodynamic properties and contributes to the generation of lift power, balanced movement, and energy efficiency of the unmanned helicopter (50). In unmanned helicopters (50), the design of the wing (10) is specifically optimized in terms of both lightness and durability.

[0027] Figure 2 shows a representative side view of the wing (10) subject to the invention. Accordingly, the structure of the wing (10) comprises at least one mounting hole(13), and this mounting hole (13) is used to connect the wing (10) to a drive element. The mounting hole (13) is connected to at least one first module (11) and at least one second module (12) located on opposite sides of the wing (10). The mounting hole (13) ensures that the wing (10) is fixed in the correct position and securely during assembly. The first module (11) and the second module (12) are two identical and symmetrical parts. This modular structure offers significant convenience during maintenance and repair processes of the wing (10). In the event of a malfunction, it is sufficient to replace only the damaged module. This approach reduces costs and saves time. Additionally, the modular structure makes it possible to design custom configurations for different missions.

[0028] The wing (10) is configured with a length of 200 mm, a width of 25 mm, and a thickness of 2.5 mm in order to provide lightness and aerodynamic efficiency. These dimensions allow the wing (10) to generate optimum lift force while keeping the load on the unmanned helicopter (50) at a minimum. The wing (10) has a maximum weight of 8 grams and is manufactured from carbon fiber material. In addition to being lightweight, carbon fiber provides a long-lasting and durable structure due to its high strength and flexibility. The aerodynamic design of the wing (10) is inspired by the owl wing. The owl wing is a natural structure known for its silent flight capability, and this feature is of great importance in minimizing noise in the unmanned helicopter (50). The owl-inspired wing (10) design includes special forms that direct airflow in a smooth and orderly manner. Thanks to this wing (10) structure, turbulence and air friction that may occur during flight are minimized. The aerodynamically shaped wing (10), similar to the owl wing, provides high performance particularly in applications requiring silence, such as surveillance and reconnaissance missions.

[0029] Figure 3 shows a representative top view of the wing (10) subject to the invention. The region of the wing (10) that first comes into contact with the air is defined as the front portion (20), which is aerodynamically optimized. The front portion (20) comprises a contact surface (21) that extends along the wing (10) and is raised relative to the ground. This contact surface (21) facilitates the entry of air into the wing (10) and enables the wing (10) to control the airflow. The slightly tapered structure of the front portion (20) reduces air resistance and provides energysavings during flight. This contact surface (21) minimizes the adverse effects that may occur upon initial contact with air, thereby enhancing the stability of the wing (10) and supporting the balanced generation of lift force.

[0030] On the opposite side of the front portion (20) of the wing (10), there is a rear portion (30). The rear portion (30) is positioned closer to the ground compared to the front portion (20), thereby allowing the wing (10) to strike the air and lift the aircraft. At least one serrated form (31) is located on the rear portion (30) of the wing (10), which directs and optimizes the air outlet. The serrated form (31) is designed similarly to the domed, trapezoidal structure found in owl wings and has been developed to enhance aerodynamic efficiency and enable silent flight. This serrated form (31) consists of domes arranged in sequence and of trapezoidal geometry, allowing the air to be distributed in a regular manner. The serrated form (31) is specifically positioned toward the tip portions (40) facing outward in each module, thereby completing the overall aerodynamic structure of the wing (10). The serrated form (31) also reduces turbulence while enhancing the performance of the wing (10) and supporting energy efficiency.

[0031] The region of the wing (10) that faces outward environmentally is referred to as the tip portion (40). The tip portion (40) has a tapered shape. This tapered shape allows the air to disperse more smoothly and minimizes air resistance. The tip portion (40) completes the aerodynamic structure and enhances the performance of the wing (10). On the side of the serrated form (31) facing the tip portion (40), at least one protrusion region (32) is located. The said protrusion region (32) is the area where the front portion (20) and the rear portion (30) of the wing (10) diverge abruptly, resulting in a widening between them. The protrusion region (32) enables the air circulating inside the wing (10) to be pressed downward. This protrusion region (32) directs the air in a regular manner, allowing the wing (10) to perform a more stable flight. The serrated form (31) also continues within the protrusion region (32), and this continuity facilitates the balanced control of the airflow. The protrusion region (32) provides a complementary feature in the aerodynamic design of the wing (10) and has a direct impact on performance.The wing (10) structure subject to the invention provides numerous significant advantages with its design features and aerodynamic structure. Firstly, the silent flight design inspired by the owl wing offers a major advantage particularly in surveillance and reconnaissance missions by minimizing the likelihood of the aircraft being detected. Its modular structure facilitates maintenance and repair processes, reduces costs, and saves time. While the aerodynamically optimized front portion (20) increases energy efficiency by reducing air resistance, the serrated form (31) and the protrusion region (32) located in the rear portion (30) regulate airflow and provide the possibility of a silent and stable flight. The wing (10) being manufactured from lightweight and durable carbon fiber material both enhances performance and positively contributes to the overall payload capacity of the unmanned helicopter. With this design, the effect of turbulence is minimized, and flight stability and control capability are maximized.

[0032] The scope of protection of the invention is defined in the claims provided in the annex and shall by no means be limited to the examples described in this detailed description. It is evident that a person skilled in the art may develop similar embodiments in light of the above explanations without departing from the main concept of the invention.REFERENCE NUMBERS GIVEN IN THE DRAWINGS

[0033] 10 Wing

[0034] 11 First Module

[0035] 12 Second Module

[0036] 13 Mounting Hole

[0037] 20 Front Portion

[0038] 21 Contact Surface

[0039] 30 Rear Portion

[0040] 31 Serrated Form

[0041] 32 Protrusion Region

[0042] 40 Tip Portion

[0043] 50 Unmanned Helicopter

Claims

CLAIMS1. A wing (10) to be used in unmanned helicopters (50), characterized in that:the structure of the wing (10) comprises at least one mounting hole (13) to be connected to a drive element,at least one first module (11) and at least one second module (12) that are identical and symmetrical to each other are located on opposite sides of the mounting hole (13),the side of the wing (10) that first contacts the air is a front portion (20), and this front portion (20) comprises a contact surface (21) that is slightly tapered and at least partially raised relative to the ground,and on the rear portion (30) of the wing (10), located opposite the front portion (20), at least one serrated form (31) is included, wherein a section of said serrated form (31) comprises a protrusion region (32) extending at least partially outward.

2. The wing (10) according to claim 1, characterized in that the serrated form (31) is in the shape of domes arranged side by side in a sequential manner.

3. The wing (10) according to claim 1, characterized in that the serrated form (31) also continues within the protrusion region (32).

4. The wing (10) according to claim 1, characterized in that it is manufactured from carbon fiber material.

5. The wing (10) according to claim 1, characterized in that the wing (10) has a length of 200 mm, a width of 25 mm, and a thickness of 2.5 mm.

6. The wing (10) according to claim 1, characterized in that it has a maximum weight of 8 grams.

7. The wing (10) according to claim 1, characterized in that the wing (10) comprises a tip portion (40) that tapers on the environmentally outwardfacing side.

8. The wing (10) according to claim 7, characterized in that the serrated form (31) is positioned toward the tip portions (40) of the modules in order to regulate airflow and reduce turbulence.

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