Skip to main content

2023 | Buch

New Achievements in Unmanned Systems

International Symposium on Unmanned Systems and the Defense Industry 2021

herausgegeben von: T. Hikmet Karakoc, Nadir Yilmaz, Alper Dalkiran, Ali Haydar Ercan

Verlag: Springer International Publishing

Buchreihe : Sustainable Aviation

insite
SUCHEN

Über dieses Buch

Unmanned systems are one of the fastest-growing and widely developing technologies in the world, offering many possibilities for a variety of research fields. This book comprises the proceedings of the 2021 International Symposium on Unmanned Systems and the Defense Industry (ISUDEF), a multi-disciplinary conference on a broad range of current research and issues in areas such as autonomous technology, unmanned aircraft technologies, avionics, radar systems, air defense, aerospace robotics and mechatronics, and aircraft technology design. ISUDEF allows researchers, scientists, engineers, practitioners, policymakers, and students to exchange information, present new technologies and developments, and discuss future direction, strategies, and priorities in the field of autonomous vehicles and unmanned aircraft technologies.Covers a range of emerging topics;Addresses current issues on autonomous vehicles and unmanned aircraft;Full proceedings of ISUDEF 2021 held at Howard University.

Inhaltsverzeichnis

Frontmatter
A Short Review on New Development Achievements and Market Opportunities in Unmanned Systems

Unmanned systems are fundamental robotics technologies that, in the widest sense, do not require human components unless they have missions, may be operated remotely or autonomously, and perform specific responsibilities. Since they are not swayed by fear, tiredness, fury, frustration, or revenge, autonomous robots would behave more ethically than humans in warfare. Developers are simplifying control algorithms to let autonomous ground vehicles choose a job, operating condition, and route. Accurate slippage predictions and correcting mechanisms will help create a safer and more effective navigation system, along with other improvements. Software systems such as artificial intelligence and image processing should be researched for unmanned aerial vehicle systems development. In this chapter, the market opportunities have been assessed for UAV systems.

Selcuk Ekici, Alper Dalkiran, T. Hikmet Karakoc
Inference of Civil Infrastructure Vibrations Using Unmanned Aerial Vehicles

Extracting vibration features of civil infrastructure enables authorities to identify structural safety and integrity, as well as preparedness for hazardous events such as earthquakes. Unmanned aerial vehicle (UAV) systems are used as mobile sensors to measure vibrations and deformations of civil infrastructure. Compared with the conventional structural health monitoring systems, UAVs provide essential advantages such as remoteness, mobility, automation, and scalability in contrast with stationary and permanent vibration sensing systems. In this study, the possible use of sensor technology to detect civil infrastructure vibration with the help of UAV sensors, particularly bridge infrastructure was evaluated. The method is an invasive sensing technology that makes use of embedded accelerometer data from smartphones and UAVs which is used for bridge acceleration response measurement. This method relies on high landing accuracy and coupling with the structural surface under extreme conditions.

Abeer Jazzar, Utku Kale
Electrical System Design for Very Light Aircraft

In this study, electrical system designs of the first very light aircraft being built in Turkey are presented. An electrical system was designed for a very light aircraft (VLA) with a single motor. In any action to be taken on the subject such as system architectures to be created, selection of electrical equipment and layout of these equipment, selection of suitable cable, connectors and lights, etc., the EASA CS-VLA Standard was applied. The design process includes the selection of electrical systems and equipment according to the selected motor, the construction of the system architecture, the electrical load analysis, the selection of the battery as a result of load analysis, the examination of cable standards and the determination of the necessary cables and connectors, and the transfer of the system to the drawing programs. At the end of the design process, the determined electrical equipment will be placed in the aircraft.

Merve Aluc, Guven Komurgoz
A Test-Bed for Attitude Determination and Control System of Nanosatellite

In order to ensure a reliable verification of attitude and control systems for nanosatellites, a test platform is developed. It is used to improve and implement the test scenarios of the sensors, actuators, and algorithms. Magnetometer, accelerometer, and gyroscope are used as attitude sensors to estimate the state of the satellite. As the primary attitude control actuator, three reaction wheels are used in each axis. The test setup is composed of the main octagonal table, balancing blocks, adapters for installation of equipment, adapters including anodized coating for corrosion protection. In order to manage balancing, the coarse balance blocks are placed in four corners and the precise balancing blocks are placed on each axis. The platform has a wireless monitoring system for online analysis and a power distribution unit. A computer is used to determine attitude determination and control tasks in a distributed control mechanism. Several scenarios are tested and analyzed in the traditional and nontraditional Kalman-type filters for attitude estimation of the satellite and magnetometer calibration purposes.

Aykut Kutlu, Demet Cilden-Guler, Chingiz Hajiyev
Satellite Formation Flight via Thrusters and Proportional-Integral-Derivative Control Approaches

This chapter is focused to control of relative satellite vector estimations with various Kalman filter (KF) and Proportional-Integral-Derivative (PID) approaches. The identical 3U target and follower satellites orbits and initial conditions are simulated according with desired formation geometry limitations. In this study, target and follower satellites states are determined as derived simulation data. The various satellites thruster’s scenario is analyzed with various relative state estimation which use Kalman filters. The novel methods, which satellites and relative orbit estimation are determined via two stages, are inputted to the control section of follower satellites within formation flight of satellites architecture.

Tuncay Yunus Erkec, Chingiz Hajiyev
Adaptive Kalman Filter-Based Sensor Fault Detection, Isolation, and Accommodation for B-747 Aircraft

Sensor fault detection, isolation, and accommodation via Adaptive Kalman Filter (AKF) algorithm are applied to the lateral dynamics of Boeing-747 aircraft in this study. The flight dynamic model of Boeing-747 aircraft in steady state flight condition is presented and investigated. In nominal case, the Optimal Linear Kalman Filter (OLKF) gives fine estimation values. However, when there is a malfunction on the measurement channels, the accuracy of the filter estimations become poor and the filter becomes unreliable. Two faulty scenarios are investigated. The first scenario comprises the single sensor fault and the second is a simultaneous double sensor fault. The fault detection algorithm detects the fault and isolation process performs via calculating and comparing the statistics of sample and theoretical error variances to distinguish the faulty sensor. Lastly, fault accommodation process is presented in the study as implemented by Adaptive Kalman filter algorithm and demonstrates very efficient, firm, and reliable performance on behalf of enhancing the estimation values of the filter.

Akan Guven, Chingiz Hajiyev
STEM Opportunities in Flight Testing Sunlight Reflector Ultralights

The Glitter Belt architecture uses swarms of autonomous, ultralight, high altitude reflector vehicles to measure atmospheric and surface properties and any effects of solar reflection and then to scale up and reduce global warming. This chapter deals with the Western Hemisphere part of the architecture. The flight test process invites global participation, particularly from STEM students interested in autonomous aerial vehicles. Conceptual design, scale model construction and testing, and issues in autonomous rendezvous, maneuvers to reflect sunlight, and positional accuracy needs for use in detecting objects in Low Earth orbit are summarized.

Narayanan Komerath, Ravi Deepak, Adarsh Deepak
Modelling and Simulation of Vertical Landing Dynamics of an Aircraft Based on a Model System

In this study, to develop a mathematical model for a short take-off and vertical landing (STOVL) aircraft dynamics a model system which resembles such aircraft dynamics was studied. The proposed model system uses the thrust of axial fans to hover the whole system in the air. The dynamic equations of the model system are derived and a lift force model is also proposed for a stable landing condition. A simulation model is built and tested for some initial values of the variables and results were evaluated.

Selim Sivrioglu
Examination of Supercapacitors in Terms of Sustainability in Aviation

The development in the aviation industry progresses depending on the development in propulsion systems. Propulsion systems have changed and developed over the years according to needs. In recent years, efforts have been made to replace traditional propulsion systems with more environmental- friendly alternatives. For this reason, electric propulsion systems have gained popularity in recent years. Although batteries and fuel cells already exist amongst devices that store electrical energy, these devices have some limitations. Supercapacitor technology is a new and promising energy storage technology. In this chapter, supercapacitors with their aerospace-friendly and environmental-friendly properties are discussed.

S. Cansu Gorgulu, Isil Yazar, T. Hikmet Karakoc
Improving the Risk Matrix

A risk matrix is a widely used tool to assess risk during project development by combining severity and likelihood of undesired events. Unfortunately, risk matrices have some major limitations, particularly with likelihood assessment. This chapter describes a new method for creating a risk matrix to assess safety that uses a hazard analysis technique called System-Theoretic Process Analysis (STPA) in the assessment of hazard likelihood. The approach uses the causal scenarios derived from STPA to identify potential risks, along with a measure of mitigation effectiveness as a proxy for likelihood. By combining the strengths of STPA and traditional risk assessment methods, decision-makers will be better equipped to determine the risk level associated with their projects. The new risk assessment method is demonstrated on the development concept of a complex Future Rotary Wing Aircraft (FRWA) system and can be applied in any industry that uses a risk matrix to assess risk.

Sam Yoo, Dro Gregorian, Andrew Kopeikin, Nancy Leveson
The Artificial Immune System Paradigm for Generalized Unmanned Aerial System Monitoring and Control

Monitoring and control of dynamic systems must address their operation for maximum safety and performance. This means that the dynamic system is expected to maintain a desirable or acceptable level of performance in completing a mission under both normal and abnormal operational conditions. These abnormal conditions include off-design situations, excessive and unpredictable environmental conditions, adverse interaction with external agents, and subsystem faults and failures. This chapter presents the envisioned general development process of an integrated and comprehensive methodology for monitoring and control of an autonomous unmanned aerial system inspired by the beneficial properties of the biological immune system. This includes outlining for each phase of the abnormal condition monitoring and control process of the biological sources of inspiration and the implementation methods with their potential benefits and drawbacks.

Ryan McLaughlin, Mario Perhinschi
Nonlinear Six-Degree-of-Freedom Flight Modelling and Trimming of a Single-Propeller Airplane

A mathematical model based on the solution of nonlinear aircraft equation of motion for six-degree-of-freedom flight was developed by using MATLAB programming. This mathematical model was adopted for evaluating the flight motion of single-propeller airplane. The aerodynamic data for the flight model was obtained from wind tunnel tests of power-off and stick-fixed 1/12 scale model of the airplane. The propulsion data, on the other hand, was obtained from two engines used within a flight envelope defined by altitude and airspeed. Linear interpolations were performed to evaluate the input data available in look-up tables. The damping derivatives needed for the flight model were obtained from empirical USAF DATCOM methods. Airplane equation of motion was solved numerically at equilibrium condition for cruising velocity and altitude. Time history variations of all 12 state variables for trimmed flight show instantaneous motion of airplane. The procedure described in this chapter should be useful for the mission evaluation of such a propeller airplane during its preliminary design.

Kasim Biber
Transonic Airfoil Development for an Unmanned Air System

The process of developing a new energy efficient 16% thick airfoil for an unmanned air system operating at transonic speeds is presented. The airfoil specifications included a range of Reynolds number per foot from 1.7 million to 2.5 million and Mach number from 0.4 to 0.8. Shape optimization in geometry and inverse design modules of the MSES program were initially used for a preliminary design of the 16% thick airfoil. The MSES/LINDOP program was then used to obtain the final airfoil shape, optimizing the performance of the initial airfoil with an objective of minimizing drag coefficient for seven design points with conflicting requirements in Reynolds and Mach number. The optimization produces an upward shift of drag bucket in the direction of higher lift coefficient. This shift is also seen on the location of transition producing an increase in the extent of laminar flow.

Kasim Biber
Optimization of Energy Efficiency According to Freud’s Disk Theory Depending on Propel Pitch Angles

Propeller systems are used extensively in many areas, especially in ships, airplanes, air conditioning and wind turbines. Unmanned aerial vehicles (UAVs), which are produced and used intensively nowadays, are also one of the most important areas where propeller systems are used. Thanks to the propeller system, UAVs can hover in the air and move. It is of great importance that the propellers are designed in a stable, efficient and reliable manner. In this study, drone propellers are optimized in terms of energy efficiency by considering Freud’s Disc Theory. For the optimization process, a new mathematical model, which is used for the first time in the literature, is proposed, and the efficiency of the proposed model is analysed by comparing it with the simulation algorithm and real propeller values. As a result of the analysis study, it has been determined that an improvement of 11.84% compared to the real propeller data and 11.39% compared to the simulation results has been achieved in terms of energy efficiency. It is estimated that high efficiency can be achieved by applying the proposed solution approach to other propeller systems.

Ukbe Ucar, Zehra Ural Bayrak, Burak Tanyeri
Concept Design and Analysis for a Fixed-Wing Unmanned Aerial Vehicle to Perform Surveillance and Mapping Missions

Unmanned aerial vehicles have important position for both civil and military applications today. Fixed-wing unmanned aerial vehicles have an important place in the literature. In this study, the design stages of military and high-altitude unmanned aerial vehicles were examined, and a scaled model was produced to perform ground tests and flight tests. For airfoil selection, 2D analyzes were made using the XFLR5 program. Speed and aerodynamic analysis of unmanned aerial vehicle were performed by modeling a CFD code. As a result, the parameters required for observation, locating, and mapping have been determined. A successful model has been developed in terms of stable and aerodynamic flight.

Osman Kumuk, Mustafa Ilbas
Flow Patterns in Double Planar Synthetic Jets

Synthetic jets are devices with high relevance due to their several industrial applications. For instance, their application as an actuator for active flow control of the boundary layer is very useful for improving the efficiency in aircrafts. This work studies the main flow physics in several types of synthetic jets, at different Reynolds number, using a data-driven method, higher order dynamic mode decomposition (HODMD). The cases studied are a single active jet, two jets moving synchronously and asynchronously with phase shift between them of π and π/2 radians. The flow structures reveal the interaction between the two jets. The flow is found symmetric at low Reynolds number and asymmetric at high Reynolds number. HODMD extracts the main flow patterns with two aims: finding the mechanism triggering the symmetry breaking and to generate a reduced order model, which is interesting for the temporal prediction of the flow, reducing the computational time in the numerical simulations.

Eva Muñoz, Soledad Le Clainche
Coordinated Path-Following for Multi-Agent Fixed-Wing Aircraft

This chapter addresses the problem of coordinated path-following for fixed-wing unmanned aerial vehicles (UAVs) for a fixed altitude set-point. This problem is decomposed into two components: path following by commanding the attitude of the UAV and synchronization of their respective along-path parameters. In relation to the path following problem, two different algorithms are considered. In the first, the path is decomposed into a concatenation of straight-lines where the controller is linearization based. In the second, a non-linear curved path-following controller is considered. For the synchronization, a proportional-integral coordination control law is considered for a communication topology with integral connectivity.

Hugo S. Costa, Stephen Warwick, Paulo Oliveira, Afzal Suleman
Onboard Trajectory Coordination of Multiple Unmanned Air Vehicles

The increasing proliferation of autonomous air vehicles (AAV) and their applications has created an increased need for effective aircraft trajectory coordination within airspaces. Here, a method to coordinate a flight formation of multiple AAVs using onboard command and control is introduced. The proposed system has been verified in simulation and validated in flight. The results show that it is possible to control a fleet of multi-rotor aircraft using equipment present onboard the aircraft. Areas of improvement to increase accuracy and reliability of the system have also been proposed.

James Sease, Stephen Warwick, Afzal Suleman
In-Flight Nonlinear System Identification for UAS Adaptive Control

Fast aircraft prototyping, fault detection, morphing surfaces, and real-time generation of dynamic models are just some of the advantages of a model identification adaptive controller. The research presented in this chapter investigates a proposed control architecture and validates the novel data-driven algorithm SINDy to be used for online system identification of a UAS. The reported simulation results explore the effects and the limits of short training time and sensor noise on the identified model fitness.

Sean Bazzocchi, Afzal Suleman
Drone Simulation, Mapping and Navigation via ROS

In recent years, simulation environments with robust physics engines, high-quality graphics and user-friendly interfaces allow researchers to validate their work in simulation environments before real-test environments. In this study, a ROS-based mapping and navigation of a real drone model in three-dimensional simulation environment Gazebo is described. The mapping process is carried out using the Gmapping algorithm. The purpose of this study is to evaluate the drone’s mapping, location and navigation in an unknown environment.

Demet Canpolat Tosun
Hierarchical Adaptive Fault-Tolerant Model Predictive Control of a Quadrotor

This chapter proposes a hierarchical control design for trajectory tracking of a quadrotor subject to unexpected actuator faults, where a lower level attitude control and a higher level position controller are developed successively based on the time-scale decomposition between the two control loops. For the higher level position control, an adaptive fault-tolerant model predictive controller is developed by introducing an adaptive parameter estimator to the Lyapunov-based model predictive control framework. The attitude controller is designed using feedback linearization to regulate the quadrotor’s rotation rapidly. Closed-loop stability is proven according to the Lyapunov stability theorem. The tracking performance and fault-tolerant capability of the proposed design are substantiated with simulation results.

Binyan Xu, Yang Shi, Afzal Suleman
Higher Order Dynamic Mode Decomposition to Model Reacting Flows

In this work, we analyse an axisymmetric, time varying, non-premixed laminar co-flow flame. To this aim, a data-driven algorithm (higher order dynamic mode decomposition) has been used to identify the main patterns leading the flow dynamics and modelling the turbulent combustion. The results show that this complex turbulent flow can be modelled using a reduced number of modes identified by the method, which represent the flow physics. These modes can be used to reconstruct the original solution. This flow reconstruction represents a reduced order model that can be used to model the main flow dynamics at a reduced computational time. Modelling turbulent combustion using methods based on physical principles, such as the one presented in this work, could be used to generate several databases in a fast and efficient manner, bringing new possibilities to improve the efficiency in combustion systems in aircrafts.

Adrián Corrochano, Giuseppe D’Alessio, Alessandro Parente, Soledad Le Clainche
Fault-Tolerant Estimation of Relative Motion of Satellites in Cluster

This chapter is devoted to the relative satellite state estimations that are detected and estimated by fault-tolerant Kalman filters via measurement of actual distance between 4 GPS satellites and target satellite. The novel approach is fault-tolerant relative satellite state estimations, which were designed according to two version. One of them is reconfiguration fault-tolerant cluster satellite localization and the other one is adaptively fault-tolerant cluster satellite localization. The Extended Kalman Filter (EKF) is used for target and follower satellites orbital state vector estimations and detection of GPS measurement errors. The reconfigurable version and the adaptive version of fault-tolerant localization architecture eliminate the GPS measurement errors while estimating relative satellites position and velocity vectors.

Tuncay Yunus Erkec, Chingiz Hajiyev
Trajectory Tracking Control of an Unmanned Ground Vehicle Based on Fractional Order Terminal Sliding Mode Controller

In this chapter, fractional order terminal sliding mode control (FOTSMC) method, which is a hybrid control approach, is used to improve the trajectory tracking control performance of an unmanned ground vehicle (UGV). First, a kinematic controller design has been carried out to estimate the linear and angular velocities that will stabilize the vehicle asymptotically. Then, FOTSMC, which is a hybrid control method that combines the advantages of fractional control and terminal sliding mode control methods, is proposed to perform vehicle reference velocities tracking. In addition, terminal sliding mode control (TSMC) and sliding mode control (SMC) methods are used for trajectory tracking control of the same vehicle to demonstrate the performance of the proposed controller. Simulation results show that the proposed controller performs trajectory tracking with smaller error and lower amplitude chattering compared to TSMC and SMC.

Hayriye Tuğba Sekban, Abdullah Başçi
Nonlinear Control of Multi-quadrotor Flight Formations

The design of a controller based on classical methods to control flight formation of multi-UAV quadrotors is presented. A leader-follower methodology is implemented where the leader has some predefined trajectory and a follower is controlled in order to track the leader keeping a constant displacement in its reference frame. The formation control solution is done in two steps: first, by considering only the motion at constant height, and second, a three-dimensional motion was considered. In both cases, the nonlinear control laws are derived based on Lyapunov stability and the backstepping method.

Diogo Santos Ferreira, Afzal Suleman, Paulo Oliveira
Dynamic Modeling of Main Landing Gear of a High-Altitude Long Endurance UAV

Main landing gear of a high-altitude long endurance UAV was modeled as a mass-spring-damper system in this study. Landing gear components including the oleo-pneumatic shock strut, tire, and wheel were included in the constructed model in the study. An oleo-pneumatic shock absorber with fixed orifice area was used in the model and dynamic behavior of the system was investigated. A representative input dataset for UAV specifications and oleo-pneumatic shock absorber characteristics were collected from literature to form the input dataset, and dynamic model was solved with using computer software. Three main cases were run in accordance with the CS-25 certification requirements which are at 1.83, 3.05, 3.7 m/s (6,10,12 fps) descent velocities and lift equals to weight condition. Within the constraints, the results are satisfactory and can be used as a baseline configuration to be optimized in future research.

Ali Dinc, Yousef Gharbia
GNSS-Aided Satellite Localization by Using Various Kalman Filters

This chapter is devoted comparison of the satellite position and velocity states estimation with the use of traditional extended, extended with linear measurements, and Newton Raphson aided extended Kalman Filters. In this study, a low-earth orbiting satellite position and velocity states are estimated by using the above filters. A global navigation satellite system (GNSS) receiver is modeled using a pseudo-range approach. Obtained results were compared and discussed. An attempt was made to determine the best method for estimating the satellite’s position. The accuracy of the estimates was shown for each estimation approach.

Mert Sever, Chingiz Hajiyev
Thermal Study of Cylindrical Lithium-Ion Battery at Different Discharge Rates

This study aims to simulate a commercially available 26,650 lithium-ion battery temperature. The multi-scale, multi-dimensional NTGK model was used to simulate battery temperature. The highest maximum battery temperature was 346.110 K obtained at 3.0C rate, while the lowest maximum battery temperature of 311.934 K was exhibited at 1.0C rate. The highest average battery temperature of 345.164 K and the lowest average battery temperature of 311.627 K were obtained at 3C rate and 1C rate, respectively. However, the results demonstrated that the temperature rise was more pronounced for the maximum battery temperature for all implemented C rates. The results also showed that the C rate should be carefully changed by monitoring the maximum battery temperature. The implemented battery thermal model can be used to improve battery thermal management systems in real-life applications.

Uğur Morali
The Effect of Control Cylinder Placed at Different Angles in Front of a Heated Cylinder on Heat Transfer

Controlling the flow structure on objects using different control techniques has been a vast field of study for researchers for many years. In this study, the temperature distribution around the heated cylinder was investigated in two different Reynolds numbers (Re = 1400 and Re = 2700) when a 25 mm diameter flow control cylinder is placed in the upstream region of a heated cylinder in a water channel at L/D = 2 position and at an angle of 21°. As a result, it was determined that the 21° angled positioning worsened the heat transfer compared to the fixed (0°) positioning of the control cylinder in the upstream region of the heated cylinder for each Re number examined within the scope of the study. The straight control cylinder in the L/D = 2 position produced better results than the cylinder in the 21° angled position.

Dogan Burak Saydam, Coskun Ozalp, Ertaç Hürdoğan
Aerodynamic Shape Optimization of the Morphing Leading Edge for the UAS-S45 Winglet

This chapter presents an aerodynamic optimization for a Morphing Leading Edge (MLE) winglet of a well-known UAV, the UAS-S45. The optimization algorithm is integrated with the modified Class Shape Transformation (CST) parameterization method and had the aim to enhance aerodynamic performance by minimizing drag and maximizing aerodynamic endurance at the cruise flight condition. The optimization scheme was carried out with in-house MATLAB code and by employing the Vortex Lattice Method (VLM) to calculate the aerodynamic properties of the morphing leading-edge winglet. This study presents the optimization technique and compares winglet geometries results by demonstrating that changing the winglet geometry in flight can enhance aircraft performance while lowering drag, therefore the fuel consumption. The optimized airfoils have shown a significant improvement in the overall aerodynamic performance by up to 8.55% drag reduction and 10.20% increase in aerodynamic endurance, as compared to the reference airfoil. Therefore, the results indicate the importance of leading-edge morphing in enhancing the aerodynamic efficiency of the UAS-S45 airfoil.

Ruxandra Mihaela Botez, Musavir Bashir, Simon Longtin-Martel, Tony Wong
Applications of Drones in the Field of Health and Future Perspectives

Drones can gather real-time data cost-effectively to deliver payloads and have initiated the rapid evolution of many industrial, commercial, and recreational applications. The advancement of unmanned aerial vehicle (UAV) technology in industrial processes and communication and networking technologies has increased their use in civil, business, and social applications. Drones offer various exciting opportunities: delivery of medical and laboratory supplies, blood products, including biopsy for emergency surgeries, is just a starting point. Drones can evolve medical care as well as propel advancement in the health industry. The use of an automated external defibrillator (AED) before emergency medical services (EMS) arrival can increase 30-day survival in out-of-hospital cardiac arrest (OHCA) significantly. Drones or UAVs can fly with high velocity and potentially transport devices such as AEDs to the site of OHCAs. This chapter provides a comprehensive review of current and future drone applications in health to empower and inspire more aggressive investigation.

Kursat Alp Yigit, Alper Dalkiran, T. Hikmet Karakoc
Comparison of 5th-Generation Fighters: Evaluation of Trends in Military Aviation

Nations attach great importance to their defense in order to ensure their survival against internal and external threats. The only defense force that can respond in the fastest and most effective way against possible threats is the air force. The power of the air force, which has such an important place in the country’s defense, is based mainly on fighters. For these reasons, the vision of purchasing or manufacturing fighter jets in line with the strategic plans and future goals of the countries in defense is of great importance. In this study, a detailed comparison of the 5th-generation fighters that have already been produced has been made. The comparison is made into a decision problem structure and solved with AHP, one of the multi-criteria decision-making methods. The result was the Sukhoi SU-57 as the optimum fighter aircraft. In addition, new trends and aims in fighters were examined. Trends and aims will guide countries and cooperations to be included in the new era of fighters.

Murat Ayar, T. Hikmet Karakoc
Backmatter
Metadaten
Titel
New Achievements in Unmanned Systems
herausgegeben von
T. Hikmet Karakoc
Nadir Yilmaz
Alper Dalkiran
Ali Haydar Ercan
Copyright-Jahr
2023
Electronic ISBN
978-3-031-29933-9
Print ISBN
978-3-031-29932-2
DOI
https://doi.org/10.1007/978-3-031-29933-9