Wing structure with dual opposing distributed thrust system for unmanned aerial vehicles.

Abstract

The invention relates to a wing structure with a dual counter-distributed thrust system developed for unmanned aerial vehicles. The system includes a primary and secondary engine positioned in opposing mechanical orientations on the wing structure, and associated propellers operating in a counter-rotating configuration. The propellers are configured to generate the same overall thrust direction. The invention also includes engine carrier structures, an internal cable routing channel, an internal support structure, and a flaperon control surface. This structure contributes to balancing the load distribution on the wing, regulating airflow interactions, and supporting aerodynamic stability.

Description

1 DEFINITION Wing with Dual Opposing Distributed Thrust System for Unmanned Aerial Vehicles Its structure TECHNICAL AREA 5 The invention relates to wing structures and distributed propulsion systems used in unmanned aerial vehicles (UAVs). More specifically, the invention is intended for use in fixed-wing unmanned aerial vehicles. an improved wing with a bidirectional and distributed thrust system that works integrated with the wing structure It relates to the system. Although the invention was primarily developed for use in fixed-wing unmanned aerial vehicles, 10 Together, this can also be applied to different unmanned aerial platforms with similar structural characteristics. It is of a certain quality. STATE OF THE ART In traditional fixed-wing unmanned aerial vehicles, propulsion systems are usually mounted on the fuselage or They are positioned on the wings in the same orientation pattern. In these designs, the engines are mostly 15 They are positioned in similar directions and standard propeller layouts are used. In current systems, the positions of the engines on the wing and the direction of thrust are similar in character. Due to this, some technical limitations may arise. Especially during flight. rotational moments, uneven load distributions, aerodynamic effects on the wing, and airflow These interactions can negatively impact system performance. 20 In addition, airflow interactions between engines in systems using multiple engines are considered. This can cause undesirable turbulence effects, which negatively impact flight stability. This can lead to consequences. Furthermore, in current solutions, the wing structure and the propulsion system are not optimized together. Some disadvantages arise in terms of weight distribution, structural efficiency and flight stability. 25 It is possible to get out. Therefore, a more balanced thrust distribution, increased aerodynamic stability, and wing structure are important. A new structure is needed that integrates and regulates the propulsion system. THE PURPOSE OF THE INVENTION The thrust distribution, aerodynamic stability, and 30 seen in current fixed-wing unmanned aerial vehicles. This invention was developed to reduce the technical limitations related to load balancing. The aim of the invention is to integrate the wing structure with the distributed propulsion system in a more efficient manner. The goal is to provide a balanced thrust distribution. Other purposes of the invention include:  Reducing rotational moments that may occur during flight, 35  Increased aerodynamic stability,  Optimizing airflow interactions between motors,  Making the load distribution on the wing more balanced, 2  Contributing to the improvement of flight performance and structural efficiency It is located there. Furthermore, the invention creates an integrated structure in which the wing structure and propulsion system work together, thus surpassing existing ones. It aims to reduce some of the technical disadvantages that can be seen in the systems. DESCRIPTION OF THE FIGURES 5 Figure 1: Perspective view of a twin opposing thrust wing structure. Figure 2: Top view of the wing structure. Figure 3: Top view of the engine layout on the wing. Figure 4: View of the opposite arrangement of the first and second engines. Figure 5: Schematic view of the propellers operating in the opposite direction. 10 Figure 6: Cross-sectional view of the wing's internal structure. Figure 7: View of the motor carrier structural elements. Figure 8: Schematic view of load distribution and thrust directions on the wing. Reference Marks 15 Reference No. Component 1. Main body structure 2 Wing structure 3 First engine 4 Second engine First propeller 6 Second propeller 7 First engine carrier arm 8 Second engine carrier arm 9. Flaperon structure First thrust direction 11 Second thrust direction 12 Wing assembly areas 13 Internal cable routing channels 14 Internal support structure Motor housing area 16 Airflow direction 3 Detailed Description of the Invention 1. General Wing Structure The invention's dual opposing thrust wing structure is attached to the main body (1) and forms the basis of the unmanned aerial vehicle. It includes a wing structure (2) which forms one of its supporting structures. The wing structure in question is 5 (2) is shown in Figure 1 and Figure 2 in terms of general appearance. The wing structure (2) is arranged to form a carrier aerodynamic surface, and flight It has an internal support structure (14) that ensures the loads generated during the process are distributed evenly. The mentioned internal support structure (14) provides structural strength along the wing and load distribution. It is positioned with the aim of improving. 10 The wing structure (2) is connected to the main body (1) via a wing mounting area (12). The aforementioned assembly area (12) will provide the mechanical connection between the wing and the fuselage. It has been arranged. The wing structure (2) also contains an internal cable passage channel (13). The mentioned internal cable The transition channel (13) is the channel for electrical connections and data transmission lines that can be used within the system. or is designed to accommodate the transport of other internal connecting elements. As shown in Figure 6, the internal support structure (14) and internal cable passage channel (13), wing structure (2) They are positioned together inside, maintaining structural integrity while preserving the aerodynamic exterior surface. It ensures its continuation. 2. Engine Placement System 20 On the wing structure (2), the first engine (3) and the second engine are shown in Figure 3 and Figure 4. There is an engine placement system that includes (4). The first engine mentioned (3) is approximately the length of the wing from the wing mounting area (12). It is located in the 1–5% section. The second engine (4) is located in the wing mounting area (12) It is positioned at approximately 40–50% of the wing length. 25 The first engine (3) and the second engine (4) are attached to the wing structure (2) via the engine carrier arms (7,8). They are connected. The mentioned motor carrier arms (7,8) provide structural support for the motors. and also to facilitate the movement of connecting elements within the system It has been arranged. The engine support arms (7,8) extend between the wing structure (2) and the engine mounting area (15) 30 It is arranged to be connected with the internal cable passage channel (13). As shown in Figure 3, the airflow interaction between the first engine (3) and the second engine (4) for the purpose of regulation, a portion corresponding to approximately 1–5% of the wing length A separation zone has been left. The mentioned engine placement system affects the load distribution on the wing structure (2) and the mechanical 35 It is structured to support balance. 3. Dual Counter-Push Structure As shown in Figure 4 and Figure 5, the system of the invention consists of the first motor (3) and the second motor (4), They are positioned in mechanically opposing directions relative to each other. 4 The first engine (3) and the second engine (4) mentioned are the first propeller (5) and the second propeller (6) respectively. It works together with the mentioned propellers (5,6), the mechanical orientation difference of the motors. However, it is configured in a reverse rotation pattern to create the same general thrust direction. Within the structure in question, the first thrust direction (10) and the second thrust direction (11) are generally the same. It is created in this direction, and despite the opposing mechanical arrangement in the system, a common thrust effect is achieved. 5 is being created. The first engine (3) and the second engine (4) are arranged to operate simultaneously during flight. and the aforementioned dual opposing thrust structure makes the air flow direction (16) more balanced in particular. introduction, increased aerodynamic stability, reduced torque and engines It is designed to reduce airflow interactions between the surfaces. 10 As shown in Figure 5, the arrangement between the airflow direction (16) and the thrust directions (10,11), The wing structure (2) is designed to support the load distribution on it. 4. Control Surface Structure As shown in Figure 2, the flaperon structure (9) is used as a control surface on the wing structure (2). It is located. 15 The mentioned flaperon structure (9) is located on a part of the trailing edge of the wing structure (2). positioned starting from approximately 88–90% of the wing length. It is arranged in this way. The aforementioned flaperon structure (9) will cover approximately 9–11% of the wing length. It is structured in this way. In addition, the width of the flaperon structure (9) is approximately 24–20% of the wing width. It has been adjusted to correspond to 26%. As shown in Figure 2, after the flaperon structure (9), at the tip of the wing structure (2) A fixed tip area of ​​approximately 1–2% is left. The mentioned flaperon structure (9) is arranged in an integrated manner with the wing structure (2), and flight It is structured in such a way as to enable the necessary control actions to be performed during the process. 25 5. Internal Load-Bearing and Transition Structure As shown in Figure 6 and Figure 7, various internal connecting elements are present within the wing structure (2). It has an internal passage structure that facilitates its transportation. The mentioned internal passage structure is designed to work together with the internal cable passage channel (13). and the wing structure of electrical connections, data transmission lines and other system elements (2) 30 It ensures that it is transported in an orderly manner. The first engine support arm (7) and the second engine support arm (8) are only structurally suitable for the engines. elements that provide support, as well as the transportation of internal transition elements. It is designed as a hollow structure that will provide this opportunity. The aforementioned motor carrier arms (7,8) have 35 connecting elements along a portion of their internal volume. It is structured in a way that allows it to pass through. As shown in Figure 6, the internal cable passage channel (13) is the support within the wing structure (2). It is arranged together with the structures (14) and the structural integrity is preserved and the internal elements are arranged regularly. It ensures that transportation is carried out in this manner. Thanks to this structure, the external surface aerodynamics of the elements located within the wing structure (2) It is possible to arrange it in a way that will not damage it. 5 6. Aerodynamic Interaction Structure As shown in Figure 5, the system of the invention is powered by the first engine (3) and the second engine (4). The first thrust direction (10) and the second thrust direction (11) created, together with the air flow direction (16). It is designed to create aerodynamic interaction. 10 Within the aforementioned dual opposing mechanical layout, the first engine (3) and the second engine (4), Although mechanically positioned in opposite directions, the first propeller (5) and the second The thrust flows generated by the propeller (6) are generally arranged in the same direction. Thanks to this structure, unbalanced flow regions that may occur along the air flow direction (16) can be avoided. It is possible to contribute to its reduction. 15 From an aerodynamic point of view, a conventional engine positioned in the same direction. The rotational airflow components that can occur in their structures create local turbulence on the wing surface. It can create regions. In the invention mentioned, however, rotation is achieved due to the counter-rotating propeller arrangement. It can help reduce the effects of airflow. This situation makes the airflow direction (16) more regular, and the wing structure (2) 20 more balanced distribution of aerodynamic loads and imbalances that may occur during flight It can contribute to reducing [the impact of the virus]. In addition, the structure in question makes the load distribution along the wing structure (2) more balanced. This can contribute to its arrival and this situation by reducing rotational moments. It is possible to provide support for improving aerodynamic stability. 25 As shown in Figure 5, the interaction between thrust directions (10,11) and airflow direction (16) This design helps to reduce unwanted airflow interactions that may occur between the engines. It is structured in a way that will provide this. How the invention can be applied to industry. The invention describes a wing and distributed propulsion system that can be used in fixed-wing unmanned aerial vehicles. 30 It relates to its structure. The structure in question can be applied to unmanned aerial vehicles of varying sizes and capacities. It is capable of being produced in this way. The wing structure (2), engine placement system, dual opposing thrust structure, and control described within the scope of the invention. Surface structure and internal load-bearing systems, together or in separate structural arrangements. 35 It can be produced. The structure in question can be produced using different manufacturing methods and different types of materials. It is capable of being integrated into existing unmanned aerial vehicle systems. The invention is suitable for 40 different structurally diverse applications, primarily fixed-wing unmanned aerial vehicles. It is suitable for use in unmanned aerial vehicles.

Claims

6 REQUESTS 1. The invention is a wing and distributed propulsion system structure for unmanned aerial vehicles, characterized by: a wing structure attached to the main body, The first and second engines are positioned in opposite mechanical orientations on the wing structure, first propeller associated with first engine, 5 second propeller associated with the second engine and It includes motor support structures.

2. According to Claim 1, the wing and distributed propulsion system structure is characterized by; the first propeller and the second The propeller is configured in a counter-rotating pattern to generate the same overall thrust direction. that is. 10 3. According to Claim 1, the wing and distributed propulsion system structure is characterized by; the first engine and the second engine It is structured to work together.

4. According to Claim 1, the wing and distributed propulsion system structure has the following characteristics: the first engine is mounted on the wing. It is positioned approximately 1–5% of the wing length, starting from the region.

5. Wing and distributed propulsion system structure according to Claim 1; its characteristic is that the second engine is mounted on the wing. 15 It is positioned approximately 40–50% of the wing length, starting from the region.

6. According to Claim 1, the wing and distributed propulsion system structure is characterized by; the first engine and the second engine. among them, to reduce airflow interaction, approximately 1–3% of the wing length. The problem is that there is a separating region corresponding to the section.

7. According to Claim 1, it has a wing and distributed propulsion system structure, characterized by having a 20 on the wing structure. It has a flaperon structure.

8. According to claim 7, the wing and distributed propulsion system structure is characterized by its flaperon structure on the wing. arrangement starting from approximately 85–90% of its length and wing It comprises approximately 9–11% of its length.

9. According to Claim 1, the wing and distributed propulsion system structure has the following characteristics: engine carrier structures, 25 while providing structural support for the motors, it also provides internal connecting elements. It contains a hollow structure suitable for passage.

10. According to Claim 1, it is a wing and distributed propulsion system structure, characterized by its internal structure within the wing. It is the arrangement of the transition channel and the internal support structure together.

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