ACHIEVING MAXIMUM DATA FLOW IN AIRCRAFT

Abstract

The invention is an aircraft (H) developed to enhance data communication with unmanned or unarmed aircraft (H) and / or prevent interruptions, and it includes at least one GPS module (1) to determine and instantly track the location of the aircraft (H) in the area where it is located, a telemetry antenna (2) to enable users to communicate with the aircraft (H) and telemetry (4) to enable telecommunication between the central unit / operator and the aircraft (H).

Description

1 TARIFF ACHIEVING MAXIMUM DATA FLOW IN AIRCRAFT TECHNICAL FIELD The invention enhances data communication provided by unmanned or unarmed aerial vehicles. and / or preventing interruptions. 5 STATE OF THE ART Unmanned aerial vehicles (UAVs) and unarmed unmanned aerial vehicles (AUAVs) have become increasingly common in recent years. With the influence of technological advancements, it is effectively used in both civilian and military operations. It has come into use for observation, exploration, mapping, firefighting, border control, and disaster relief. UAVs offer 10 advantages in many areas such as management, agricultural analysis and military surveillance. Operational capabilities have become key elements that enhance the mission effectiveness of these systems. All these tasks can only be accomplished through communication between the aircraft and the ground control station (GCS). It directly depends on the reliability, continuity, and speed of data communication. In the current state of the art, data communication established between UAVs and ground stations is generally It is provided via radio frequency (RF). RF-based systems are particularly useful in the short and medium term. It is preferred in long-range missions and its operations are based on the principle of direct line of sight. due to terrain obstacles, construction or meteorological conditions directly It is affected. Therefore, signal attenuation in RF systems is due to multipath propagation. Effects such as shadowing and interference can cause interruptions, delays, and even disruptions to data transmission and communication. This causes it to completely detach. 20 On the other hand, satellite-linked communication systems used in long-range missions are, compared to RF. Even though it offers wider coverage, it suffers from high cost, signal delay, and limited bandwidth. And due to limitations such as high energy consumption, it is not suitable for every job profile. Especially In situations requiring real-time video streaming, target tracking, or instant decision-making, such as these... Delays significantly reduce system performance. 25 In addition, electromagnetic interference, signal jamming applied by hostile elements, can occur. (Jammer) technologies and naturally occurring electromagnetic effects (e.g., solar flares, Lightning strikes, etc., cause instabilities in data communication. This is especially true in critical situations. In operations, this jeopardizes the system's operational capability and the operator's control. The existence of these types of threats is important not only in terms of communication security, but also in terms of the platform's air 30 It is also important in terms of maintaining its presence in the field. 2 In the current state of technology, there are different technological approaches to solving these communication problems. Some systems have been improved with directional antennas, automatic frequency switching, and encrypted data. They offer solutions such as transmission. However, most of these systems are only suitable for certain purposes. They work in scenarios, are unable to adapt to environmental conditions in real time, and mostly Because they are hardware-based, they increase the overall weight and energy requirements of the system. 5 Furthermore, detecting communication disruptions in current systems is often delayed. This is happening and the reconnection process is taking a long time. This situation, especially This poses a significant risk for autonomous UAVs, affecting the success of the operation and... This jeopardizes their safety. In conclusion, the existing data communication infrastructures used in UAV and UCAV systems have certain 10 While offering advantages such as high reliability, uninterrupted operation, low latency, and adaptive control, in terms of offering features such as advanced signal processing and multi-channel management together. It is insufficient. These shortcomings are particularly noticeable in complex and variable task scenarios. (for example, in urban areas, environments with high magnetic interference, or hostile threats) (in the tasks below) this becomes even more pronounced. 15 Therefore, ensuring the continuity of data communication, anticipating and preventing interruptions, and different to enable intelligent transitions between communication channels and improve overall system performance The need for new methods and systems is increasing every day. Some findings have been identified as a result of research conducted on the known state of the art. The documents and explanations are given below. 20 Primarily, the fuel cell is mentioned in the Korean document with application number KR1020240152652A. a fuel cell network management unit mounted at a specific location in the system with a GPS It is mentioned that there is an antenna assembly. Also, in the relevant document, it is stated that the PCB board is mounted upwards. and downwards, there is a pair of antenna holders that will be attached at intervals along the first axis. It has been mentioned that a GPS antenna module is attached to the fuselage. 25 The Chinese document with application number CN218917666U states that there is an antenna assembly and It was mentioned that the antenna assembly includes an antenna holder and a foldable structure. The documents obtained as a result of research conducted using known techniques. It has been understood that it does not provide a complete solution to the aforementioned shortcomings, and a new invention... It has been determined that it needs to be presented. 30 3 THE PURPOSE OF THE INVENTION The main purpose of the invention is to create a connection between unmanned or unarmed aerial vehicles and ground control systems. to increase the continuity of the provided data communication, and to prevent connection problems that may occur during the mission. The goal is to prevent them from breaking. The purpose of the invention is to eliminate interruptions, delays, or attenuations that may occur during data transmission. identifying problems in advance and implementing preventive measures against these situations The goal is to ensure it is received. Another purpose of the invention is to protect against environmental conditions, electromagnetic interference, or hostile sources. To provide a communication infrastructure resilient against jamming attempts, thus enabling the system to perform its tasks. to increase its security and operational stability. 10 Another purpose of the invention is to facilitate mission integration between different communication technologies (e.g., RF, LTE, satellite). to enable dynamic and seamless transitions depending on the conditions, so that at any moment The goal is to ensure the maintenance of an optimal connection. Another aim of the invention is to provide a lower energy alternative to hardware-based solutions. Developing software or hybrid solutions that consume less energy and do not increase system weight, thus 15 The goal is to increase the aircraft's flight time and mission efficiency. Another aim of the invention is to integrate AI-powered decision-making algorithms into communication infrastructure. by integrating it, it can analyze potential communication threats in advance and provide adaptive responses. It is about providing a structure. Another purpose of the invention is to provide 20 solutions in emergency scenarios (e.g., sudden disconnection, disorientation). without losing control of the aircraft, he / she completed his / her mission through alternative communication channels. The goal is to ensure its sustainability. A BRIEF DESCRIPTION OF THE INVENTION The invention enhances data communication provided by unmanned or unarmed aerial vehicles. It is an aircraft developed to prevent and / or mitigate disruptions that may occur. 25 In an alternative configuration of the invention, the position of the aircraft in the area where it is located at least one GPS device to enable identification and real-time tracking. It has a module. Another alternative configuration of the invention would allow users to communicate with the aircraft. It has a telemetry antenna to provide this. 30 4 In another alternative configuration of the invention, the central unit / operator and the aircraft... Telemetry is used to provide telecommunications. Another alternative configuration of the invention involves fixing the telemetry antennas at the desired angle. and to ensure the best signal transmission over the aircraft's location It has a stabilizer. 5 Another alternative configuration of the invention involves determining the target route of the aircraft. flight duration calculation, changing the flight route in any situation, location flight computer for monitoring and ensuring communication It is located. In another alternative configuration of the invention, any vibrations that may occur on the chassis would be absorbed by 10 and / or sudden slope differences that may occur during hard landings and takeoffs There are upper and lower stabilizers to prevent it from being affected. In another alternative configuration of the invention, it is positioned between the lower and upper fasteners. and the magnitude of the current created by the shock, collision, or air resistance When it becomes too large for the upper and lower stabilizers to absorb, it automatically switches to 15. by absorbing all the energy accumulation that is activated and transferred to the upper and lower stabilizers The system includes isolators to absorb even the slightest possible vibration effects. In another alternative configuration of the invention, the stabilizer is controlled remotely. In another alternative design of the invention, the angle of the fastener can be changed. By increasing and / or decreasing the angular distance of the telemetry antennas, the aircraft's data 20 Transmission power is being increased. Another alternative configuration of the invention involves attaching the GPS module and telemetry antenna to the chassis. It includes a holder to ensure secure attachment. Another alternative configuration of the invention involves attaching the flight computer to the upper stabilizer; upper and lower 25 to ensure the connection of the stabilizer to the insulator and the lower stabilizer to the chassis. Includes a connecting element. In another alternative configuration of the invention, the fastener could be a bolt, nut, washer, or gasket. Any item selected from the group including rivets, screws, studs, pins, circlips, clamps, dowels and clips is an individual. BRIEF DESCRIPTION OF THE FIGURES Figure 1 shows the front view of the aircraft. Figure 2 shows a front view of the GPS antenna module. Figure 3 shows an internal view of the GPS antenna module. Figure 4 shows a side view of the GPS antenna module. 5 Figure 5 shows the view of the communication module. Figure 6 shows the communication module in its disassembled state. EXPLANATION OF REFERENCES IN THE FIGURES H. Aircraft 1. GPS Module 10 2. Telemetry Antenna 3. Stabilizer 4. Telemetry 5. Conservative 6. Flight computer 15 61. Bottom stabilizer 62. Upper stabilizer 63. Insulator 64. Fastener DETAILED DESCRIPTION OF THE INVENTION 20 This section is intended solely to help to better understand the subject. Explanations are being provided. 6 The invention described in detail below enables the use of unmanned or unarmed aerial vehicles. to strengthen data communication and / or prevent interruptions It relates to the improved aircraft (H). Figure 1 shows a general view of the aircraft (H). As can be seen from Figure 1... The aircraft in question (H) has a GPS module (1) and a telemetry antenna (2). 5 The position of the aircraft (H) in the area is determined via the aforementioned GPS module (1). This ensures the identification of the aircraft (H) and its real-time tracking. The telemetry antenna (2) mentioned allows users to communicate with the aircraft (H). This is ensured. Along with the aforementioned communication link, the aircraft's route can be changed. power status monitoring, appearance of any warnings and monitoring of real-time image transmission 10 is provided. Figures 2 and 3 show a detailed view of the GPS module (1). As can be seen from Figure 2 Telemetry (3) is located on the underside of the GPS module (1). Telemetry (4) is available on both sides. Telemetry antennas (2) are located on the side, and the aforementioned The stabilizer (3) is located on top of the telemetry antennas (2). 15 Through the aforementioned telemetry (4), communication can be established between the central unit / user / operator and the aircraft (H). Telecommunications are provided. Through the aforementioned telecommunications connection, air The vehicle's (H) RF link, data transmission, satellite link, steering, frequency hopping, The frequency network is encrypted. The mentioned stabilizer (3) fixes the telemetry antennas (2) at the desired angle and the air 20 It ensures that the vehicle (H) receives the best signal transmission at its location. In an alternative configuration of the invention, the mentioned stabilizer (3) is controlled remotely, by changing the angle it has, increasing the angular distance of the telemetry antennas (2) and / or Data transmission power is increased according to the distance covered by the aircraft (H) by reducing the range. Figure 4 shows the side view of the aforementioned GPS module (1). As can be seen from Figure 4, 25 There is a holder (5) located just below the GPS module (1). The aforementioned holder (5) together with the GPS module (1) and telemetry antenna (2) to the fuselage / chassis The connection is ensured. Figure 5 shows the general structure of the communication module, and Figure 6 shows the aforementioned communication module. The disassembled structure of the module is given. If Figure 6 is examined, the aforementioned communication 30 The flight computer (6) is located at the top of the module, and the mentioned flight The upper stabilizer (62) is located under the computer (6). The subject is a lower stabilizer (61) in the part of the flight computer (6) that contacts the chassis. It is located and the insulator (63) is positioned between the upper and lower stabilizers (62,61). Figure 7 As shown in 6, the aforementioned connections are made via the connecting element (64). It has been realized. The connecting element mentioned in an alternative configuration of the invention (64) including bolts, nuts, washers, washers, rivets, screws, studs, pins, circlips, clamps, dowels and clips It is any individual selected from the group. With the help of the aforementioned flight computer (6), the route to which the aircraft (H) will be targeted is determined. determining the flight duration, calculating the flight route, and changing the flight route in any situation, Tracking the position of aircraft (H) and ensuring communication with aircraft (H). This is carried out by detecting and analyzing the commands given by the operator to the aircraft (H). The control and guidance of the aircraft are carried out via the flight computer (6). The flight computer (6) is one of the most critical components of the aircraft (H) in terms of the task it performs. It is one of them. For the reason mentioned, any kind of vibration that may occur on the chassis and / or sudden slope differences that may occur during hard landings and takeoffs It is fixed with lower and upper stabilizers (61,62) so as not to be affected. The aforementioned lower stabilizer (61) is the first connection of the flight computer to the chassis, which absorbs any vibrations. It is the first area. The upper stabilizer, on the other hand, is especially important in situations such as sudden landing or altitude loss, and monitors the flight computer's 15 (6) is the first area to absorb any shock that may occur. The lower and upper stabilizers The isolator (63) located between them absorbs the shock, collision or air resistance experienced. The magnitude of the current it generates is too great for the lower and upper stabilizers (61,62) to absorb. When it is large, it comes into play and all the energy is transferred to the lower and upper stabilizers (61,62). By absorbing the accumulation, it eliminates even the slightest vibration effect that may occur. 20

Claims

8 REQUESTS 1. The invention relates to data communication provided by unmanned or unarmed aerial vehicles (H). to ensure that it is strengthened and / or that interruptions are prevented It is an improved aircraft (H), and its feature is;  Determining the location of the mentioned aircraft (H) in the area and 5 at least one GPS device to enable real-time tracking module (1);  Telemetry to enable users to communicate with the aircraft (H). antenna (2);  To provide telecommunications between the central unit / operator and the aircraft (H) 10 telemetry (4);  Fixing the telemetry antennas (2) at the desired angle and the aircraft (H) to ensure the best signal transmission at its location stabilizer (3);  Determining the route to be targeted by the aircraft (H), flight duration 15 calculation, changing the flight route in any situation, location flight to carry out tracking and ensure communication computer (6);  Any kind of vibration that may occur on the chassis and / or hard landings and To avoid being affected by sudden changes in slope that may occur during takeoff. 20 lower and upper stabilizers (61,62);  Positioned between the aforementioned lower and upper stabilizers (61,62) and the current created by the shaking, collision or air resistance its size is too large for the lower and upper stabilizers (61,62) to absorb When it gets too big, it automatically activates and has 25 lower and upper stabilizers. (61,62) absorbing all transferred energy accumulation and preventing even the slightest possible occurrence isolator (63) to eliminate even the effect of vibration It is characterized by its inclusion.

2. The aircraft (H) conforming to Claim 1 is characterized by the remote control of the aforementioned stabilizer (3). It is to be checked. 30 3. The aircraft (H) conforming to claim 1 or 2, and having the following characteristics: the stabilizer (3) Increasing the angular distance of the telemetry antennas (2) by changing the angle and / or The goal is to increase the data transmission power of the aircraft (H) by reducing the number of aircraft.

4. The aircraft (H) conforming to Claim 1 is characterized by having a GPS module (1) and a telemetry antenna. (2) It includes a holder (5) to ensure connection to the chassis. 35 9 5. The aircraft (H) conforming to Claim 1 is characterized by having the aforementioned flight computer on top. to the stabilizer (62); to the upper and lower stabilizers (62,61) to the insulator (63) and to the lower stabilizer (61) It includes a connecting element (64) to enable it to be connected to the chassis.

6. The aircraft (H) conforming to claim 1 or 5, and its characteristic is the aforementioned connecting element (64) bolt, nut, washer, washer, rivet, screw, stud, pin, circlip, clamp, dowel and 5 It is any individual selected from the group containing the clip.