RING-MOUNTED CHASSIS DESIGN WITH HIGH COMPATIBILITY AND INTEGRATION CAPABILITIES.

Abstract

The invention is an improved chassis (Ş) onto which components of unmanned and / or unarmed aerial vehicles are integrated, and the chassis (Ş) is obtained by including a bottom and top layer (1,2), a ring (5) to wrap the motor arms to be positioned on the chassis (Ş) and to ensure their centering on the chassis (Ş), and a ring housing (6) to hold the ring (5), to place the ring (5) on the chassis (Ş) and to adjust the direction of its position.

Description

1 TARIFF RING-MOUNTED CHASSIS WITH HIGH COMPATIBILITY AND INTEGRATION CAPABILITIES. DESIGN TECHNICAL FIELD The invention relates to the development of chassis integration in unmanned or unarmed aerial vehicles. 5 STATE OF THE ART Unmanned aerial vehicles (UAVs) and armed unmanned aerial vehicles (AUAVs) are used today for both military purposes. It also has a wide range of applications in civilian settings. Reconnaissance, surveillance, targeting. used in numerous tasks such as reconnaissance, logistical support, agricultural analysis, and even disaster management. The success of these platforms depends largely on the robustness of their load-bearing structural systems (chassis), 10 It depends on integration capability and intra-system compatibility. Traditional aircraft chassis structures are typically monocoque or derived from aircraft engineering. It is designed according to semi-monocoque structural principles, and the body itself is load-bearing. These are systems in which it operates. These structures generally require low weight, high rigidity, and impact resistance. To ensure strength, aluminum alloys, carbon fiber composites, or other advanced 15 It is manufactured using engineering materials. In modern UAV / UAS systems, the chassis and engine... aircraft components, electronic control systems (avionics), landing gear, payloads (cameras, weapons) systems etc.) and components such as power supplies are directly mounted or integrated It serves as the main load-bearing structure. However, chassis integration systems used in current technologies are technically flawed in many ways. It includes limitations. In particular, the reconfiguration of tools for different mission profiles. When needed, the non-modular chassis designs make task changes difficult, and This restricts operational flexibility. On some platforms, payloads or equipment... Replacing the vehicle requires extended maintenance, which wastes both time and resources. This creates inefficiencies in terms of equipment. Furthermore, many existing platforms use 25 different pieces of equipment. Non-standard mounting systems are used in chassis integration, which affects the components. This leads to mechanical, electrical, or communication incompatibilities between them. On the other hand, electromagnetic compatibility (EMC), heat transfer, and vibration are important considerations in chassis integrations. Important engineering requirements such as insulation are often addressed through a holistic approach. This is not taken into consideration, and this situation affects system stability and component lifespan over long service periods. 30 This poses a risk, especially with high-powered actuators, radar systems, or weapons. 2 In UAV platforms where these integrations are present, these problems become more pronounced. These include vibration-induced loosening of connections, deformations due to overheating, and Malfunctions occur due to electromagnetic interference. In addition, during maintenance and servicing processes on most existing UAV / UAS platforms 5 challenges include difficulty accessing the chassis, complex placement of connection points, and the need for specialized tools. For these reasons, it is possible to quickly repair or restructure the system in the field. This is not possible. Especially in war or disaster conditions, rapid maintenance is of great importance. In this process, these shortcomings negatively affect operational capacity. In addition, most connection interfaces in existing systems have a custom design and are modular. Integration and compatibility with different manufacturer systems are weak. This situation reduces interoperability to 10. This restricts, complicates the supply chain, and increases costs. For these reasons, in the UAV and UCAV chassis integration systems used today;  High modularity,  Adaptability to the task profile,  Standardization, 15  Easy maintenance and repair,  Thermal and vibration insulation,  EMC compliance,  Technological advancements and innovations in areas such as flexibility in compact design Solutions are needed. 20 In this context, it both increases structural resilience and improves operational and maintenance processes. Next-generation chassis integration solutions that simplify things and address existing technological shortcomings. It stands out as a critical area of ​​research and development. In research conducted on the state of the art, chassis integration has been shown to be effective. Various documents have been identified to ensure this. 25  Primarily, in the EPO document with application number EP3814222B1, it states "At least one a transmission housing that secures the transmission to the chassis and at least one motor housing that secures the engine to the chassis an engine housing; where the transmission housing and engine housing are separated by the load support area. 3 "It is fixed to the chassis outside of a defined area." More than chassis integration. The focus has been largely on the integration of aircraft components into the chassis.  In the French document with application number FR3145744A1, it is stated that "during the transportation of the drone To limit its bulk, the arms and chassis can be easily and quickly separated and assembled. "It can be done." The arms and chassis can be separated to limit the aircraft's volume. 5 It was also mentioned that it can be used in a disassembled state.  FR3112328B1, another French document, states that "each inflatable arm must be attached to the support chassis It includes at least one connecting piece, which allows for quick connection between the support chassis and the inflatable arms. and allows for easy connection. A connecting piece between the arms and the chassis. because it contains and the chassis can be separated by removing the connecting piece from the arms 10 It has been mentioned.  In WIPO document number WO2015109700A1, it is stated that "The chassis is generally the front It involves a phase separation of the outer and back shell, with numerous front and back shells. They need to be locked together with screws, which greatly reduces the weight of the drone. will increase, seriously affect the flight performance of the unmanned aerial vehicle and 15 Assembly and disassembly are convenient, allowing for easy maintenance and replacement of the part. Its enclosure is relatively robust; signal shielding between each module in the housing is good. They are not, they are easy to interfere with each other, thus affecting the signal transmission quality of each module. and even seriously affects the flight safety of the unmanned aerial vehicle. The chassis the excess of connecting parts on it causes unnecessary increase in load and 20 It was mentioned that flight time was affected. Also, assembly and disassembly... the nonconformities affect the maintenance and repair costs of the aircraft It has been given. As can be understood from the documents mentioned, the current documentation describes an improved chassis. 25 Why chassis integration, rather than just integration, needs to be improved It is aimed at addressing existing problems rather than finding a direct solution. It stands out as such. THE PURPOSE OF THE INVENTION The main purpose of the invention is to create chassis used in unmanned and / or unarmed aerial vehicles (UAVs / UASs). By improving the integration features of its structure, it becomes a modular, highly task-compatible, maintenance-efficient 30 The aim is to provide a load-bearing system that facilitates ease of use and enhances structural integrity. The purpose of the invention is to adapt the use of different payloads (camera, radar, weapon) to suit mission changes. structural design that allows modules, etc., to be integrated into the chassis quickly, safely, and without tools. It is about improving regulations. 4 Another aim of the invention is to make current, repair and parts replacement processes fast and user-friendly. To achieve this, the connection interfaces located on the chassis have been simplified. and increasing its accessibility. Another aim of the invention is to analyze the aerodynamic forces, vibrations, and New geometry, materials and 5 that increase the rigidity and strength of the chassis against impact effects. It is about providing connectivity solutions. Another aim of the invention is to allow electrical systems passing through the chassis to interact with each other without interference. to ensure it can function properly and at the same time to control the heat emitted by electronic components. is the distribution in this way. Another aim of the invention is to improve the performance of optical or avionics systems requiring high precision. The goal is to reduce vibrations that impair performance. A BRIEF DESCRIPTION OF THE INVENTION The invention is integrated onto components of unmanned and / or unarmed aerial vehicles. It is an improved chassis. In another alternative configuration of the invention, the lower and upper 15s are used to obtain the chassis. There are layers. In another alternative configuration of the invention, the engine would be positioned on the chassis. There are rings to wrap around the arms and ensure they are centered on the chassis. In another alternative configuration of the invention, the ring is to be housed on a chassis. ring 20 to ensure its placement and adjustment of its orientation. It has a nest. In another alternative configuration of the invention, the rigidity of the top and bottom plates can be ensured and a sandwich structure can be created. By obtaining this structure, the aircraft generates energy dissipation against impacts / contacts during landing. This will ensure the aircraft's safety in the event of a possible crash and / or altitude-related impact. It has a pressure element to reduce the damage it will suffer. 25 In another alternative configuration of the invention, the strength of the top plate and the load-bearing capacity of the chassis are increased. It features curves to increase its capacity and air resistance. In another alternative configuration of the invention, the upper and lower layers are connected to each other, forming the aforementioned ring. to prevent the housing from separating from the chassis, the bottom and top layers and the aforementioned printing Connector 30 to ensure the element is connected to the upper and lower layers. It is located. In another alternative configuration of the invention, the chassis is centered as the load-bearing structure. The core is there to provide that. In another alternative design of the invention, the upper layer is placed on top of the lower layer. They are linked. In another alternative configuration of the invention, the fastening element consists of a bolt, nut, washer, screw, 5 rivet, stud, clamp, pin, circlip, wedge, clip, connecting wire, welding piece, nipple, nail It is any product to be selected from the group containing. Again, the mentioned top and bottom plate (2,1) carbon fiber, kevlar, titanium alloy, aluminum alloy, magnesium alloy, high strength plastics, graphene, glass fiber reinforced plastics, aramid fiber, boron fiber, thermoplastic composites, PET sheet, PP sheet, PC sheet, ABS sheet, honeycomb panel, foam core sandwich structure, 10 It is any product selected from the group containing carbon nanotube-reinforced polymers. In another alternative configuration of the invention, the ring is placed inside the ring housing. It is located. In another alternative design of the invention, the ring housing is located inside the upper layer. It is located. 15 In another alternative construction of the invention, the coils are made of carbon fiber, Kevlar, titanium alloy, aluminum alloy, magnesium alloy, high-strength plastic, graphene, glass fiber reinforced plastics, aramid fiber, boron fiber, thermoplastic composites, PET sheet, PP sheet, PC sheet, ABS sheet, honeycomb panel, foam core sandwich structure, carbon nanotube reinforced It is any product selected from the polymer-containing group. 20 Another alternative design of the invention involves increasing the spatial strength of the chassis through the use of curves. It includes surface 1, surface 2 and surface 3 to enhance. In another alternative configuration of the invention, the core structure consists of one ring and two rings. It is obtained by assembling its parts together. Another alternative configuration of the invention is to ensure the centrality of the core configuration and 25 To increase its strength, it includes at least one external clamp and at least one internal clamp. Another alternative configuration of the invention is a core structure where the motor is connected to the chassis. It includes a core ring to ensure a secure fit around your arms. BRIEF DESCRIPTION OF THE FIGURES Figure 1 shows the top view of the chassis with the arranged design. 30 6 Figure 2 shows the disassembled version of the design shown in Figure 1. Figure 3 shows the appearance of the folds. Figure 4 shows the view of the ring and ring housing connection. Figure 5 shows the assembly view of the core structure. Figure 6 shows a detailed view of the core structure. 5 Figure 7 shows a topographic view of the core structure. EXPLANATION OF REFERENCES IN THE FIGURES S. Chassis 1. Substrate 2. Top layer 10 A. Surface 1 C. Surface 2 F. Surface 3 3. Printing element 4. Connector 15 5. Ring 6. Ring slot 7. Fold 8. Core 81. Core ring 20 82. External clamp 83. Internal clamp DETAILED DESCRIPTION OF THE INVENTION This section is intended solely to help to better understand the subject. Explanations are being given. 25 7 The invention, described in detail below, is designed for use in unmanned and / or unarmed aerial vehicles. It relates to the improved chassis (S) on which the components are integrated. Figure 1 shows the general view of the chassis (Ş) structure that is the subject of the invention; Figure 2 shows the chassis structure that is the subject of the invention. The disassembled appearance of the chassis (S) structure in question is given in Figures 1 and 2. When viewed simultaneously, the chassis (Ş) structure of the invention consists of a substrate (1) and a sub-layer 5 It contains a top layer (2) connected to the bottom layer (1). The aforementioned bottom and top The layers (1,2) are connected to each other by means of a connecting element (4). In an alternative design of the invention, the fastener mentioned (4) is a bolt, nut, washer, washer, screw, rivet, stud, clamp, pin, circlip, wedge, clip, connecting wire, welding The part is any product to be selected from the group containing nipples and nails. Again, the aforementioned upper and lower 10 plate (2,1) carbon fiber, kevlar, titanium alloy, aluminum alloy, magnesium alloy, high high-strength plastic, graphene, glass fiber reinforced plastic, aramid fiber, boron fiber, thermoplastic composites, PET sheet, PP sheet, PC sheet, ABS sheet, honeycomb panel, foam core A sandwich structure is any product selected from the group containing carbon nanotube-reinforced polymers. As shown in Figure 1, a ring slot (6) was opened on the underside (inside) of the top layer (2). and a ring is placed inside the ring slot (6). The ring slot (6) is located on the aforementioned ring slot. The area is connected to the bottom and top layers (1,2) via the connecting element (4) passing through the holes. They are connected. This prevents the ring housing (6) from separating from the chassis (Ş). The aforementioned ring housing (6) ensures the retention of the ring (5), the ring (5) on the chassis (Ş). It enables placement and adjustment of the orientation of its position. 20 The mentioned ring (5) is used to wrap the motor arms that will be positioned on the chassis (Ş) and It ensures centering on the chassis (S). As shown in more detail in Figure 2, both the top plate (2) is connected to the top plate. There are curves (7) on the bottom side of the plate (2) and on the top side. It is taking. Increasing the strength of the top plate (2) through the mentioned bends (7) 25 In addition, the load-carrying capacity of the chassis (S) is provided by means of the curves (7). Air resistance has been increased. The aforementioned curves are carbon in an alternative construction of the invention. fiber, kevlar, titanium alloy, aluminum alloy, magnesium alloy, high strength plastics, graphene, glass fiber reinforced plastics, aramid fiber, boron fiber, thermoplastic composites, PET sheet, PP sheet, PC sheet, ABS sheet, honeycomb panel, foam core sandwich structure, 30 It is any product selected from the group containing carbon nanotube-reinforced polymers. As shown in Figure 1, the top plate and the bottom plate (2,1) must come into contact with each other. There is a printing element (3) that provides and is positioned between them. The mentioned printing element (3) is connected to the bottom and top plates (1,2) via connecting element (4). Printing 8 element (3) through the rigidity of the top and bottom plates (1,2) and having a sandwich structure This is ensured. By obtaining the aforementioned sandwich structure, the aircraft can land safely. It is designed to generate energy release in response to impacts / contacts. Thus, the air... Minimizing the damage your vehicle might sustain in the event of a fall and / or impact due to altitude. is being reduced. At the same time, with the achievement of the sandwich structure, the rigidity of the aircraft and 5 Its balance is maintained during flight. Figure 3 shows a detailed view of the folds mentioned (7). As can be seen from Figure 3 There are surfaces (1,2,3) (A,C,F) on the curves (7) located on the top plate (2). The mentioned surfaces 1, 2 and 3 (A,C,F) form each curve on the top plate (2) (7) are located in different areas and are used to increase the spatial strength of the chassis. is being created. Figure 4 shows the view of the connection of the ring (5) and the ring housing (6). From Figure 4 As can be understood, two ring slots (6) are connected to the ring (4) from the bottom and top. The structure obtained as a result of the aforementioned connection is the core (8) structure. Again, in Figure 5, the core (8) The positioned structure of the structures on top of each other is given. The core (8) structure created is the chassis 15 (S) is the carrier structure and also the center. It is used for the operation of the aircraft. The area where all the arms of the motor are gathered and connected is the core (8) structure. Core (8) structures The centering of the chassis (S) is being performed. Detailed views of the core (8) structure mentioned in Figures 6 and 7 are given. An outer clamp (82) is attached to the outer surface of the mentioned core (8) structure, and 20 to its middle surface (center). The inner clamp (83) and core ring (81) are positioned on its side surfaces. The mentioned outer clamp and the centrality of the core (8) structure of the inner clamp (82,83) is ensured and its strength It is increased. The part of the core (8) structure that connects to the motor arms is the core ring (81).

Claims

9 REQUESTS 1. The invention relates to components incorporated into unmanned and / or unarmed aerial vehicles. It is an improved chassis (Ş) into which it is integrated, and its feature is;  In order to obtain the aforementioned chassis (Ş), the bottom and top layers (1,2);  Wrapping the motor arms that will be positioned on the chassis (S) and chassis (S) 5 ring (5) to ensure centering on it;  Keeping the aforementioned ring (5) on the chassis (Ş) placement and adjustment of the orientation of its position ring slot (6) to provide;  To ensure the rigidity of the bottom and top plates (1,2) and to obtain a sandwich structure by air 10 Energy is released in response to impacts / contacts during the vehicle's landing. This will allow the aircraft to recover from a possible fall and / or altitude-related impact. In order to reduce the damage it will suffer in this situation, the printing element (3);  Strength of the top plate (2) and load-carrying capacity of the chassis (Ş) and air to increase its resistance (7); 15  The aforementioned lower and upper layers (1,2) are connected to each other, and the aforementioned ring slot (6) to prevent separation from the chassis (Ş) the bottom and top layers (1,2) and the connection of the mentioned printing element (3) to the bottom and top layers (1,2) fastening element to provide (4);  By assembling one ring (5) and two ring housings (6) together, 20 and to ensure that the chassis (Ş) is centered as the load-bearing structure. core (8) It is characterized by its inclusion.

2. Improved chassis (Ş) in accordance with Claim 1, its feature being; the upper layer (2) the lower layer (1) It is linked to it. 25 3. The chassis (Ş) is an improved chassis in accordance with Claim 1, and its feature is the aforementioned connecting element (4) bolt, nut, washer, washer, screw, rivet, stud, clamp, pin, circlip, wedge, clip, This is any product to be selected from the group containing connecting wire, welding piece, nipple, and nail. The aforementioned top and bottom plates (2,1) are carbon fiber, kevlar, titanium alloy, aluminum. alloy, magnesium alloy, high-strength plastic, graphene, glass fiber reinforced 30 plastics, aramid fiber, boron fiber, thermoplastic composites, PET sheet, PP sheet, PC sheet, ABS sheet, honeycomb panel, foam core sandwich structure, carbon nanotube reinforced. It is any product selected from a group containing polymers.

4. Improved chassis (Ş) in accordance with Claim 1, its feature is that the ring (5) fits inside the ring housing (6). It is positioning. 5 5. Improved chassis (Ş) in accordance with Claim 1, its feature is that the ring housing (6) top layer (2) It is positioned inside.

6. The chassis (Ş) is improved in accordance with Claim 1, and its feature is that the mentioned curves (7) are carbon fiber, Kevlar, titanium alloy, aluminum alloy, magnesium alloy, high strength. plastic, graphene, glass fiber reinforced plastic, aramid fiber, boron fiber, thermoplastic 10 composites, PET sheet, PP sheet, PC sheet, ABS sheet, honeycomb panel, foam core sandwich structure, selected from the group containing carbon nanotube reinforced polymer. It is any product.

7. The chassis developed in accordance with Claim 1 (Ş) is characterized by the passage of the aforementioned curves (7). to increase the spatial strength of the chassis (S) on surfaces 1, 2 and 3 15 It contains (A, C, F).

8. The chassis (Ş) is an improved chassis in accordance with Claim 1, and its feature is that it is the core (8) structure mentioned. It is obtained by assembling one ring and two ring housings together.

9. The chassis (Ş) is an improved chassis in accordance with Claim 1, and its feature is that it is the core (8) structure mentioned. To ensure its centrality and increase its strength, at least one external clamp (82) 20 and includes at least one internal clamp (83).

10. The chassis (Ş) is an improved chassis in accordance with Claim 1, and its feature is that it is the core (8) structure mentioned. core ring (81) to ensure the winding of the motor arms connected to the chassis (Ş) It includes.

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