POD HOUSING CONCEPT WITH DIFFERENT GEOMETRIES FOR ROBOTS

Abstract

The invention is a concept for a detachable and geometrically changeable pod mount (10) for unmanned robots that is suitable for use in different tasks with the same or different task modules at the same and / or different time intervals.

Description

1 TARIFF POD HOUSING CONCEPT WITH DIFFERENT GEOMETRIES FOR ROBOTS TECHNICAL FIELD The invention is a multipurpose pod that can be integrated into different types of unmanned and unarmed manned vehicles. It is related to its nest. 5 STATE OF THE ART Today, unmanned aerial vehicles (UAVs) are used on land and sea platforms, both in the military and elsewhere. It is also used in an increasingly wider range of tasks in the civilian sector, especially reconnaissance. Surveillance, target identification, communication transmission, logistical support, agricultural monitoring, disaster monitoring, Unmanned systems in various classes for many tasks such as border security and search and rescue 10 They have been developed. However, most of the current systems are designed to serve a specific type of task. They have customized fixed hardware. This increases the mission flexibility of the platforms. This limits and necessitates multi-system investments to meet different mission needs. It brings. Most unmanned aerial vehicle systems used in current technology carry 15 largely customized design in terms of workload type, capacity and connection interfaces It includes elements such as a micro-class UAV used for reconnaissance and surveillance purposes. They were generally equipped with electro-optical cameras and simple data transmission systems; for military purposes The larger class of UAVs (Armed Unmanned Aerial Vehicles) used can simultaneously deploy numerous useful weapons. 20 more capable of carrying payload (ammunition, electro-optical systems, SAR radar, communication relays, etc.) They have complex integrated structures. However, these structures are mostly integrated systems. Since it was developed, the payload modification involves platform-level engineering changes. It requires. In this context, rapid switching of workloads or transferring them from platform to platform The need for transportation arises. However, in existing systems, the workload is generally transported by air. 25 It is positioned fixed to the vehicle's body and configured specifically for the vehicle. This is why a UAV or other unmanned vehicle (land or sea-based) Changing the type of task quickly in the field is either not possible or is complex and time-consuming. and requires costly procedures. These hardware fixations are both operational and costly. It increases the preparation time and reduces the variety of tasks. 30 2 On the other hand, the modular system concept has begun to be used in some advanced systems. However, these systems are generally limited to only a specific family of aircraft, Cross-platform task module compatibility cannot be ensured. This means that a task module... use in different UAV classes or on land-sea platforms This prevents. Such platform-specific solutions provide diversity in the supply chain and maintenance and repair 5 This leads to complexity in the processes. Electronic warfare, signal intelligence (SIGINT), laser targeting, electro-optical reconnaissance, SAR. Diverse tasks such as monitoring, load handling, and fire detection can be performed on the same platform. The need for execution via interoperability and standardization of task modules This highlights the fact that most of the payload pods currently under development are either 10 designed to be integrated into the platform, or for specialist personnel and task changes. It has complex interfaces that require specialized equipment. Therefore, users should consider the task type. They may have to acquire multiple systems depending on the situation, which increases costs. It also increases the transportation and deployment burden in the operational field. Furthermore, most current mission pods are only available in 15-inch sizes that meet specific size and connectivity requirements. Therefore, it can be used cross-functionally in unmanned systems developed by different manufacturers. This is not possible. Therefore, when pod hardware is supplied, that pod is only compatible with that platform. This remains limited, which reduces the flexibility of integration and the long-term sustainability of the system. This has a negative impact. However, the agility and task-oriented nature required for today's operations. its diversity, platform-specific, universal mounting and interface features, plug-and-play 20 This feature necessitates the development of task modules. Research conducted using the known technology has revealed a number of drawbacks. It has been determined that this is the case.  One of the biggest drawbacks encountered is that pod systems are limited to a single task. It is achieved in a focused manner. Today, many UAVs or UCAVs are only available for a specific 25 It is manufactured in a way that is customized for the task. However, a different type of aircraft Because different tasks are not suitable for use at different times, the same thing is not always used. The need arises to produce products for different tasks, thus technology... The opportunities for development and the achievement of different production methods are decreasing.  Lack of a Pod Standard: There is no standardized connection for attachable pod systems. 30 There is no infrastructure for this. Pods are generally manufactured specifically for aircraft. and they cannot be used on multiple platforms. This situation affects the manufacturer. It increases dependency and limits task diversity. 3  Limited Mission Variety: Many commercial aircraft are only suitable for one or two mission scenarios. It provides a service. When users want to change tasks, they can do so completely from the new system. They are forced to acquire additional hardware. This increases user costs. In conclusion, the current technology allows for easy integration into various types of unmanned systems, resulting in a highly versatile system. modular 5 that supports purpose-built tasks and can be quickly assembled and disassembled in the field. in a structure with high interoperability and functionally diversifiable tasks. The need for a modular infrastructure continues. Such a solution would be beneficial for both operational and other needs. in terms of both reducing costs and increasing system flexibility for the user. This provides a significant advantage. As a result of the aforementioned drawbacks, the technical structure... As a result of the research, applications that were put forward in order to provide a solution were identified. 10 The general interface in the Chinese document with application number CN112537449B is on the same UAV platform. because it is used to perform the switching of different overhead loads and the overhead antenna is the same Sharing antennas for different overheads on the UAV platform and the same on different UAV platforms. It is mentioned that the overall payload is used for antenna compatibility. Here, the interface is used... The section mentioned is the software used in UAVs. General antenna sharing is obtained from the software. The collected data is used to control automation systems. As can be understood from the relevant document, the resulting... Even though it was stated that the installed software would be compatible with different aircraft, This situation does not offer a direct solution to the aforementioned problems. The known technique mentioned... The disadvantage is that it prevents the use of an aircraft in different, independent missions. While the goal is to recognize; the solution obtained with the relevant document is the software operation across different devices 20 It allows for use. According to the UK document with application number GB202410431D0, the connector module... When the controller receives an integration instruction, it transmits it via the rotor assembly connectors. because it is configured to control the rotor assemblies attached to it and the connector It was mentioned that the module could be integrated with the connector module of another UAV. 25 Connector modules enable compatibility between electronic or hardware systems. It provides this. Again, as in the Chinese document, the British document also mentions software and... Although it has been mentioned electronically that the system is suitable for use with different aircraft. Furthermore, there is no indication of its suitability for different aircraft in terms of its mission structure. It does not take. 30 THE PURPOSE OF THE INVENTION The main purpose of the invention is to provide unmanned land, air and sea vehicles with different classes and mission types. an integrated, modular, plug-and-play, and multi-purpose system that increases task flexibility. The goal is to develop a mission module (pod dock). 4 The aim of the invention is to enable different types of missions (e.g., reconnaissance) to be performed on the same unmanned platform. (surveillance, communications relay, electronic warfare, logistics transport, laser targeting, etc.) to enable its implementation. Another objective of the invention is to enable the developed mission module to be used on fixed-wing or rotary-wing UAVs, 5 common features in different types of platforms such as land robots and unmanned marine vehicles The goal is to ensure its use. Another aim of the invention is to allow the same task module to be used repeatedly on different vehicles. Thanks to its usability, the task load investment per unit is reduced, thus lowering the total system cost. and reducing the need for spare parts. Another objective of the invention is to enable pre- and post-mission configuration changes to be made in a short time (10). The goal is to minimize task preparation times by ensuring completion. Another objective of the invention is to allow the module structure to accommodate new sensors, payloads, or electronics when needed. It has a scalable and open architecture that allows for the addition of new hardware. Another purpose of the invention is to enable the task module to function during maintenance, calibration, or malfunction situations. It can be easily removed from the vehicle and serviced as modular components. 15 It is in the structure. Another aim of the invention is to accommodate different types of payloads (camera, radar, etc.) within the same module housing. (allows for the placement of ammunition, sensors, communication units, transport cases, etc.) The goal is to provide the ability to configure tasks according to their type by recognizing them. BRIEF DESCRIPTION OF THE INVENTION 20 The invention allows for the simultaneous and / or differential operation of the same or different task modules with different functions at different time intervals. It is an unmanned or unarmed aerial vehicle developed for use in various missions. An alternative configuration of the invention would allow for the use of different types of aircraft. the use of vehicles in multiple missions simultaneously or of an aircraft in different 25 different types of task modules are placed on it to enable its use in tasks. It has at least one pod slot that allows for connection. In another alternative configuration of the invention, different geometries and lengths are obtained, thus The pod body allows the pod mount to be integrated into different aircraft. It is located. Another alternative configuration of the invention would allow for the creation of an additional section on the pod body. There is a connection area for this purpose. In another alternative configuration of the invention, the connection area and through the connection area the created additional section moves on the pod body to a desired location There is a sliding system to ensure this. 5 In another alternative configuration of the invention, it is desired that the aircraft accomplish different things. mission area to enable the attachment of mission modules onto the pod body. It is located. In another alternative configuration of the invention, the additional section is connected to the chassis, forming a pod. by preventing the fuselage from shaking during the aircraft's takeoff and / or landing, task 10 There are mounting holes to prevent the modules from falling out. In another alternative configuration of the invention, the pod body could be used on specific aircraft. Transformation angle to enable its conversion into different geometries for use It is located. In another alternative configuration of the invention, the sufficiency of the power provided by the motors is such that the motors are 15 Their simultaneous operation ensures that power is transferred to the propellers at the same time and at the same rate. ESC to check whether it is provided and the adequacy of the motor lifespan. It is located. Another alternative configuration of the invention involves determining the aircraft's position, targeting... It includes a GPS antenna to enable location changes and real-time tracking. 20 Another alternative configuration of the invention involves users recalling the aircraft, in a different way. to move to a location, to speed up, to slow down, to drop down, or to perform the tasks it has Telemetry is used to enable the issuance of commands for all operations, such as fetching the item. It includes the antenna. Another alternative configuration of the invention would be 25 years after the aircraft begins operating. It provides the power necessary for the propeller to rotate and requires at least one to turn the propeller. It includes several motors. Another alternative configuration of the invention rotates in the air, powered by the motor. to create the necessary air space for the aircraft to take off and to give the aircraft altitude It contains at least one propeller to generate power. 30 6 In another alternative configuration of the invention, a motor would be placed under each propeller. It is located. In another alternative configuration of the invention, a single motor could provide the necessary power to all the propellers. The transfer is ensured. Another alternative design of the invention is to give the aircraft an aesthetic appearance and air 5 Hood star to ensure that relevant text, images, etc. are displayed on the vehicle. It includes. In another alternative configuration of the invention, various videos are shown along with the operation of the aircraft. the records or images are to be displayed in a pre-arranged order. The hood star is the screen. 10 In another alternative configuration of the invention, ESCs could provide users with audio and / or visual feedback. It is to make a notification. Another alternative configuration of the invention involves symmetrical ESCs located on either side of the ESCs. and the belt (not referenced in the figures) running in the same direction to the chassis It includes a chassis mounting bracket to enable connection. 15 Another alternative configuration of the invention places the battery (not referenced in the figures) to the right, to restrict its movement to the left, forward, and backward, and to prevent it from leaving its current position. It includes a battery holder. In another alternative configuration of the invention, the pod mounts are located on the underside of the chassis, connected to each other. They are positioned symmetrically. 20 In another alternative configuration of the invention, the connection area is placed on top of the sliding system. It is located. In another alternative configuration of the invention, the sliding system is located at the edge of the pod body. It is receiving. In another alternative configuration of the invention, the task modules are 25 according to their geometric characteristics. By growing and shrinking, lengthening and shortening, and expanding and contracting, any aircraft can move in the same way. It can perform multiple tasks simultaneously by integrating with multiple task modules at the same time. It is bringing. 7 BRIEF DESCRIPTION OF THE FIGURES Figure 1 shows the front view of the aircraft. Figure 2 shows the view of the wing-engine connection of the aircraft. Figure 3 shows the underside of the chassis. Figure 4 shows the underside view of the chassis. 5 Figure 5 shows the front view of the chassis. Figure 6 shows a detailed view of the pod housing. EXPLANATION OF REFERENCES IN THE FIGURES H. Aircraft 1. GPS Antenna 10 2. Telemetry Antenna 3. Engine 4. Propeller 5. ESC 6. Chassis hanger mount 15 7. Hood star 9. Battery holder 10. Pod slot 101. Pod body 102. Connection area 20 103rd Annex 104. Area of ​​responsibility 105. Sliding system 8 106. Transformation angle 107. Connection hole DETAILED DESCRIPTION OF THE INVENTION This section is intended solely to help to make the subject more understandable. Explanations are being provided. 5 The invention, described in detail below, is designed for various types of unmanned and unarmed aerial vehicles. pods that are integrated into the vehicles (H) and enable the use of an aircraft (H) in different missions It is related to its nest (10). Figure 1 shows the front view of the aircraft (H). The aircraft (H) in question can be seen from Figure 1. As can be understood, it contains at least one GPS antenna (1) in its upper section; the aforementioned 10 The GPS antenna (1) can be placed in any area of ​​the aircraft (H) in question. It can be positioned in line with the GPS antenna (1) but below the aircraft (H). On the side, there is a telemetry antenna (2). Together with the aforementioned GPS antenna (1), the air Determining the position of the vehicle (H), changing the target position and real-time tracking While this is ensured, the telemetry antenna (2) is used to power the aircraft (H) 15 Communication between users / operators is enabled. Users can return the aircraft (H). calling, moving to a different location, speeding up, slowing down, dropping, or possessing Commands related to all operations such as performing the tasks are transmitted via the telemetry antenna (2). It is transferred to the aircraft (H). Figure 2 shows the propeller (3) and engine (3) system of the aircraft (H). From Figure 2 20 As can be understood, the aircraft (H) has at least one propeller (4) connected to each propeller (4). In this case, engine (3) is located. The mentioned engines (3) enable the aircraft (H) to operate. after it starts, it provides the necessary power for the propeller (4) to turn and the propeller (4) rotates. The propellers (3) rotate in line with the power they receive from the motor (4). With the start of the flight, the necessary air space is created for the aircraft (H) to take off. 25 and the aircraft (H) begins to gain altitude. Figure 3 shows the underside of the chassis forming the fuselage of the aircraft (H); Figure 5 shows the aforementioned chassis. The front view of the chassis is given. When Figure 3 and Figure 5 are examined simultaneously, the air The propellers (4) and the hood star (7) are located on the underside of the vehicle (H) in the same direction. The aforementioned bonnet star (7) is there to give the aircraft (H) an aesthetic appearance. 30 and information about the aircraft (H) such as text, images etc. are located on the bonnet star (7) It is accessible to users. The hood star mentioned in an alternative configuration of the invention. 9 (7) includes a screen and various video recordings along with the operation of the aircraft (H). or the images are displayed in a pre-set order. Firstly, when examining Figure 3, the lower and upper chassis of the aircraft (H) are shown in Figure 3. It appears to have a symmetrical structure. Figure 3 shows the upper part of the lower side of the chassis. Considering their appearance, they are aligned with each other and are equal to each other. 5 ESCs (5) are located at these distances. The mentioned ESCs (5) are electronic components, It enables the control of the motors (3) through the ESCs (5). the sufficiency of the power supplied by the motors (3), the motors (3) starting and stopping simultaneously, whether power transfer to the propellers (4) is provided at the same time and in the same proportion and the motor (3) the adequacy of their lifespan is checked. Thus, the 10 foreseen in any engine (3) is checked. Users can intervene in the aircraft (H) when and / or an unforeseen error occurs. Time is being gained in order to make it happen. There is no alternative structure to the invention. If any fault occurs in the motor (3), warning signals are given in the ESCs (5). These signals are generated and transmitted to the user as audio and / or visual signals. As shown in Figure 3, the pod holder (10) is located between the ESCs (5); Figure 15 The pod mount (10) is explained in detail in Figure 6. Finally, in Figure 3, both ESCs (5) are shown. Next to it are chassis hanger mounts (6) which are symmetrical and on the same line. It includes the aforementioned chassis hanger housing (58) and the belt (as shown in the figures). (not referenced) connection to the chassis is ensured. As shown in Figure 5, the upper section of the chassis has battery holders positioned symmetrically to each other. (9) is located. Through the aforementioned battery holders (9), the battery (as shown in the figures) (not referenced) movement to the right, left, front and back is restricted and its location He was prevented from leaving the location. Finally, as can be seen from Figure 5, the aircraft (H) has multiple pod mounts. (10) are located; the aforementioned pod mounts (10) are symmetrically positioned on the underside of the chassis 25 This allows an aircraft (H) to perform multiple missions simultaneously. Its use is permitted. Figure 4 shows the underside of the chassis. As can be seen from Figure 4, the pod mounts (10) are for air The aircraft (H) is integrated into the lower section of the chassis. In this way, any part of the aircraft (H) During a mission, the products located in the pod mount (10) can be transported to the aircraft (H) without damaging it for 30 days. will be provided for use. Finally, in Figure 6, a detailed view of the pod mount (10) located on the aircraft (H). The aforementioned pod mount (10); pod body (101), connection area (102), and task area are given. (104) consists of sliding system (105), transformation angle (106) and connection hole (107). The aforementioned pod body (101) was obtained in different geometries and lengths as shown in figure 6. It is being made available for use on different aircraft (H) by the pod mount (10). It allows integration. The sliding system (105) is located on the edge of the pod body (101). It is located on the sliding system (105) and the connection area (102) is positioned; connection An addition is made to the pod body (101) via the area (102). Primarily mentioned Attaching and removing the additional section formed on the pod body (101) via the connection area (102) Thus, the pod mount (10) is integrated onto the chassis. Subsequently, the sliding system 10 (105) together with the connection area (102) created via the connection area (102). the additional region (103) can be moved to another desired area on the pod body (101) It is ensured that it is brought. As shown in Figure 6, the mission area (104) is located on the pod body (101). It includes. The mentioned mission areas are 15 different tasks that the aircraft (H) are required to perform. It enables the linking of task modules onto each task module. are integrated. The mentioned task areas (104) are geometric task modules. It can grow and shrink to allow for attachment to it according to its characteristics. It has the properties of lengthening and shortening, expanding and contracting. Thus, any air The vehicle (H) can also integrate with more than one task module at a time, up to 20 It is made possible to perform more tasks. Again, the aforementioned additional regions (103) Connection holes (107) have been made on it. Through the aforementioned connection holes (107) The additional area (103) is connected to the chassis and the aircraft (H) takes off or lands by preventing the pod housing (10) from shaking and the mission pods from falling during the process It prevents. 25 Finally, as shown in the bottom right of figure 6, the transformation on the pod body (101) The angle (106) is located. By using the transformation angle (106), the pod body (101) Conversion to different geometries for use in specific aircraft (H) is provided.

Claims

11 REQUESTS 1. The invention relates to the simultaneous and / or differential operation of the same or different task modules. unmanned or unarmed aerial vehicles developed for use in various missions (H) and its characteristic is; Suitable for use with different aircraft (H), the same 5 aircraft (H) being used in more than one mission at the same time or in different aircraft (H) different types of tasks to enable its use in tasks at least one pod that allows the modules to be attached to it nest (10) Obtained in different geometries and lengths, thus the pod housing (10) 10 pod body that allows integration into different aircraft (H) (101); To enable the creation of an additional region (103) on the Pod body (101) connection area (102); the connection area (102) and the additional 15 created through the connection area (102) by moving on the pod body (101) of the region (103) desired sliding system to enable it to be brought to an area (105); different mission modules that the aircraft (H) wants to perform The task is to ensure that the pod body (101) is attached to it. area (104); 20 By connecting the aforementioned additional region (103) to the chassis, the pod body (101) shaking of the aircraft (H) during takeoff and / or landing by preventing the task modules from dropping, the connection hole; 25 for the use of the Pod body (101) on specific aircraft (H) Transformation angle (106) to enable it to transform into different geometries;  The sufficiency of the power supplied by the motors (3), the motors (3) can operate simultaneously with each other working continuously, power transfer to the propellers (4) at the same time and in the same proportion to check whether it is provided and the adequacy of the motor (3) lifespans ESC (5) 30 It is characterized by its inclusion.

2. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, characterized by its ability to operate in conjunction with other aircraft. Determining the position of the vehicle (H), changing the target position and real-time tracking It includes a GPS antenna (1) to enable it to be made. 12 3. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, whose characteristic is that it allows users to air recalling the vehicle (H), moving it to a different location, speeding it up, slowing it down, all its processes, such as dropping it or performing the tasks it has telemetry antenna (2) to enable it to give commands for execution It includes. 5 4. The unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and its characteristic is that the aircraft (H) after it starts working, the necessary power to make the propeller (4) turn It is to provide and to include at least one motor (3) to rotate the propeller (4).

5. It is an unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and its characteristic is that it receives power from the engine (4). The necessary air gap for the aircraft (H) to take off by rotating in the direction of the power is 10 to generate and give altitude (H) to the aircraft at least one propeller (4) It includes.

6. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, 4 or 5, and characterized by: each The motor (3) is positioned under the propeller (4).

7. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, 4 or 5, characterized by being a single 15 The goal is to ensure the necessary power transfer to all propellers (4) by the motor (3).

8. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and its characteristic is that the aircraft (H) to give an aesthetic appearance and to add relevant text, images etc. on the aircraft (H). It includes a hood star (7) to make the information visible.

9. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1 or 8, with the characteristic of being: air 20 Various video recordings or pictures are taken in advance along with the operation of the vehicle (H). The display of the hood star (7) is to take place within the set order. It is the fact that.

10. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and having the following characteristics: ESCs provide users with audible and / or visual notifications. 25 11. It is an unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and its characteristic is that both ESCs (5) the belt located next to it, symmetrical and aligned with each other (in the figures) (not referenced) chassis hanger mount (6) to ensure connection to the chassis It includes.

12. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, characterized by having a battery of 30 (not referenced in figures) to restrict its movement to the right, left, front, and back, and It includes a battery holder (9) to prevent it from moving away from its position.

13. It is an unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and its characteristic is the aforementioned pod. The housings (10) are positioned symmetrically to each other on the underside of the chassis.

14. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and its characteristic is; link 35 mentioned above. The area (102) is positioned on the sliding system (105). 13 15. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, and characterized by the aforementioned sliding The system (105) is located on the edge of the pod body (101).

16. An unmanned or unarmed aerial vehicle (H) conforming to Claim 1, characterized by its mission modules. By growing and shrinking, lengthening and shortening, and expanding according to their geometric properties. by narrowing down, any aircraft (H) can also have multiple mission modules 5 It is about being integrated, performing multiple tasks at once.