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During the last decade, the world faced the mass insertion of small satellites in the space technology scenario. Every year, the number of micro and nanosatellites launched increases and gets more attention from players in the space market. Despite the lack of a national launcher, the Brazilian Space Program is known for some successful development in the last century, including its space assets, such as a privileged launch site near the equator, a family of flight proven and reliable sounding rockets for suborbital flights and microgravity experiments and universities with established small satellites programs. Thereby, the present work proposes a modification of the Brazilian VSB-30 sounding rocket in order to allow the launch and insertion in low Earth orbit (LEO) of small satellites fulfilling the gap of a national launcher. It also presents a CubeSat orbital decay simulation and orbital insertion simulation with the modified rocket launched from the Alcântara Launch Center as a matter of verifying the potential of national missions using this modified launcher.

The use of unmanned aircraft vehicles (UAVs) for the most diverse aeronautic missions is a reality. Then, with the rise of precision agriculture (PA), the viability of the incorporation of this technology in the countryside on both big and small proprieties is under study. This work aims to analyze the handling qualities of an UAV with a mission of pest control chemical spraying. With this objective, aircraft data was used to analyze the eigenvalues of the aircraft modes. Then, the impact of mass and inertia variation during its mission was studied. Also, the longitudinal and latero-directional dynamics were evaluated based on the Cooper–Harper scale. The results found indicate that all aircraft modes are stable for both full hopper and empty hopper conditions. Moreover, the determined handling quality grades of the UAV in the Cooper–Harper scale indicate the need for some correction applied by the pilot during flight.

Calculating hinge moments during the morphing process is a critical aspect in the folding wing design. The deficiencies of the traditional flat-plate aerodynamic model in the calculation are expounded in this work, and a flight simulation platform based on a high-order panel method is established. On the basis of the platform, a typical flight-folding process of the aircraft is simulated, and the results of different aerodynamic models are compared. Results show that airfoil thickness has a great influence on the aerodynamic loading distribution of wing surfaces and thus affects the hinge moments during the folding process. The flat-plate method, which ignores the influence of the airfoil thickness, shows a great simulation error in hinge moment, whereas the high-order panel method can effectively describe the thickness effect and obtain reliable simulation results.

In the article, based on the research, the Tiredness Indicator was proposed. The research concerned the pilot's concentration and reaction time to individual stimuli. They were carried out using a flight simulator - CKAS MotionSim 5, located at the Poznan University of Technology. Measurements were made before and during the flight Analysis of the results showed a periodic course of tiredness characteristics, a marked increase in tiredness in the middle of tests and tiredness of only one sense organ confirmed by the results of reaction time and subjective assessment. Based on the conducted research, it can be stated that tiredness reduces the cognitive abilities of the human brain and extends the reaction time to stimuli.

In this paper, a deep reinforcement learning-based robust control strategy for quadrotor helicopters is proposed. The quadrotor is controlled by a learned neural network which directly maps the system states to control commands in an end-to-end style. The learning algorithm is developed based on the deterministic policy gradient algorithm. By introducing an integral compensator to the actor-critic structure, the tracking accuracy and robustness have been greatly enhanced. Moreover, a two-phase learning protocol which includes both offline and online learning phase is proposed for practical implementation. An offline policy is first learned based on a simplified quadrotor model. Then, the policy is online optimized in actual flight. The proposed approach is evaluated in the flight simulator. The results demonstrate that the offline learned policy is highly robust to model errors and external disturbances. It also shows that the online learning could significantly improve the control performance.

The loads acting on rapid maneuver aircrafts are characterized by high accelerations, high jerks and multiple directions in the space. The flight simulation tests for aircraft loads are usually carried out on a three-axis centrifuge. Due to the difference between flight and centrifugal environments, the loads in the simulation tests are not completely consistent with those in the actual flight environment. To verify that the dynamic responses of aircrafts in the three-axis centrifuge can be used to predict the responses in the flight environment, a beam installed in the three-axis centrifuge is considered. The velocity and acceleration models of the beam are established by the motion synthesis method. The rigid-flexible coupling dynamic equations of the beam are derived using the Kane’s method. Under different flight accelerations, the dynamic responses of beam in the three-axis centrifugal environment are simulated, which agree well with the responses in the flight environment. Besides, the influence of accelerations and jerks on the responses is analyzed. The results of this paper demonstrate that the present dynamic model can be used effectively to predict the experimental results in flight environments.

The paper is devoted to the non-coplanar interplanetary Earth–Venus flight of a spacecraft equipped with a non-perfectly reflecting solar sail, the magnitude and direction of acceleration from which is calculated taking into account specular and diffuse reflections, absorption and transmission of photons by the surface of the solar sail. The goal of the heliocentric motion is to transfer the solar sail spacecraft into the Hill sphere of Venus with zero hyperbolic excess of speed. A feature of the paper is the study of the motion of a non-perfectly reflecting solar sail spacecraft taking into account the motion relative to the center of mass. The problem is divided into three stages. At the first stage, a nominal program for controlling the motion of the spacecraft center of mass is formed. At the second stage, sufficient angular velocities are determined to ensure the obtained nominal control program and the parameters of the spacecraft controls – thin-film controls located along the perimeter of the solar sail – are calculated. The operating principle of the thin-film controls is quite simple. When the voltage applied to the thin-film controls changes, they become transparent or opaque, there is a difference in the normal components of the light pressure forces, which provides a control torque for changing the orientation of the spacecraft in space. At the third stage, the joint motion of the center of mass and relative to the center of mass of the spacecraft is simulated to demonstrate the feasibility of the obtained control program. As a result, a comparison is made of non-coplanar interplanetary Earth–Venus flights with and without thin-film control elements.

This article looks at the role of flight training devices in the process of instruction and training pilots. It also examines the impact of pilot training using flight simulators on reducing the human factor in accidents.

Objective This study evaluated the usefulness of a medical transport simulation to increase residents’ understanding of medical transport. Methods Twenty-four medical residents participated in an intensive half-day medical transport simulation experience. Two questionnaires were administered, a pre/postsimulation questionnaire containing 11 questions that assessed the impact of the simulation training and a questionnaire that assessed realism of the flight simulator. Results There were statistically significant differences between the pre/postsimulation questions assessing perceived level of knowledge, experience, and training of transferring a patient in a helicopter with a mean change of 25 points on a 0 to 100 scale (P ≤ .001) and awareness of obstacles to treating patients during air transport exhibiting a mean change of 28 (P ≤ .001). The mean stress level for all participants increased from 32 (0-100 scale) before the start of the simulation to 47 during the simulation and decreased to 31 after the simulation (F2,46 = 20.67, P ≤ .001). Conclusion The findings from this study provide evidence that the air medical simulation experience increases residents’ perceived awareness of the context and difficulties of transferring a patient by helicopter and that the experience would influence their medical decision making in their future practice related to patient transfers.

The paper aims to create a mathematical model of a wake vortex behind a civil aircraft and to determine the parameters of a flight zone that would be dangerous for the following aircraft in terms of a possible encounter. The model employs half-empirical and analytic approaches. The model obtained is suitable for using in various flight simulators.

The article proposes a hardware-software complex for flight simulation of a multirotor unmanned aerial vehicle, which allows near real-time operation in the MatLab / Simulink software package. To obtain adequate control characteristics and estimate flight time, simulation models of propellers and brushless motors have been developed and verified. The unmanned aerial vehicle system model allows to combine various propellers, brushless electric motors, batteries; to test control system software in automatic, semi-automatic, manual control modes, with various combinations of external factors, such as flight altitude relative to sea level, wind direction and force; as well as to simulate errors in determining coordinates and altitude. The results of the work were used for the flight modes test of a real multirotor unmanned aerial vehicle.

The haptic interface force feedback is one of the key factors for a reliable flight simulation. This paper addresses the design and control implementation of a simple joystick-like haptic interface to be used for a helicopter flight simulator. The expression of the haptic interface force is obtained by dynamic analysis of the haptic interface operation. This paper proposes a new strategy aiming at avoiding the use of an expansive and complex force/torque sensor. Accordingly, specific dynamic model is implemented by including Stribeck friction to describe the friction moment. Experimental data are processed as based on a genetic algorithm for identifying the dynamic parameters in the Stribeck friction model. This allows to obtain the friction moment parameters of the haptic interface, as well as the torque distribution due to gravity and the rotational inertia parameters of the haptic interface for the calculation of the haptic interface force. Experimental tests are carried out and results are used to validate the proposed dynamic model and dynamic parameter identification method and demonstrate the effectiveness of the proposed force feedback while using a cheap photoelectric sensor instead of an expansive force/torque sensor.

Modern techniques to estimate wind from a flight vehicle often combine onboard sensor measurements with mathematical models of the aircraft’s dynamics. Whereas prior studies have investigated the i...

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: PA2020019000

Past studies have found poorer performance on vertical heading judgement accuracy compared to horizontal heading judgement accuracy. In everyday life, precise vertical heading judgements are used less often than horizontal heading judgements as we cannot usually control our vertical direction. However, pilots judging a landing approach need to consistently discriminate vertical heading angles to land safely. This study addresses the impact of training on participants’ ability to judge their touchdown point relative to a target in a virtual environment with a clearly defined ground plane and horizon. Thirty-one participants completed a touchdown point estimation task twice, using three angles of descent (3°, 6° and 9°). In between the two testing tasks, half of the participants completed a flight simulator landing training task which provided feedback on their vertical heading performance; while, the other half completed a two-dimensional puzzle game as a control. Overall, participants were more precise in their responses in the second testing compared to the first (from a SD of ± 0.91° to ± 0.67°), but only the experimental group showed improvement in accuracy (from a mean error of − 2.1° to − 0.6°). Our results suggest that with training, vertical heading judgments can be as accurate as horizontal heading judgments. This study is the first to show the effectiveness of training in vertical heading judgement in naïve individuals. The results are applicable in the field of aviation, informing possible strategies for pilot training.

This paper presents the validation results of a study conducted at the Laboratory of Applied Research in Actives Controls, Avionics, and Aeroservoelasticity to develop a modeling technique for dete...

Compared with land-based helicopters, ship-based helicopters are required to land in a more challenging working environment as the airwakes generated by the wind field flowing through the superstructure of the ship changes the wind field structure. This complicates the wind field structure and affects the safety of flight control. The flight safety of the helicopter pilot can be significantly improved with prior understanding of the relevant information in the ship-based helicopter operating limits (SHOL) diagram. In previous studies, the SHOL diagram of ship-based helicopters has been obtained using numerical simulations in conjunction with a flight simulator. However, the flight simulator equipment is expensive and difficult to maintain. This study references the aforementioned studies by initially employing a numerical simulation method to obtain the flow field information of the interaction between the airwakes of the ship’s superstructure and the downwash flow of the helicopter. Then, the flight simulator is replaced by computational intelligence methods involving artificial intelligence. This significantly reduces the research cost for envelope construction. This study integrates design of experiments (DOE) and computational intelligence techniques (soft computing) to establish a recommended range for the SHOL diagram of ship-based helicopters. This study utilizes the DOE and computational intelligence techniques to construct the SHOL diagram of ship-based helicopters, provide suggestions, and serve as a reference for helicopter pilots and engineering designers to improve the safety during flight.

This paper presents the optimization of multi-element aerofoil for the LAR-3 Puffin -- STOL light transport aircraft concept proposal. Based on the geometry and aerodynamic characteristics of the well-known and proven in flight three-segment NACA 63A416 aerofoil, the authors explore the possibility of enhancing its high-lift performance by the movement of slot and flap position in extended (deployed) aerodynamic configuration. In order to determine the optimum positions of aerofoil segments (elements), a multi-step optimization approach was developed. It combines computational fluid dynamics simulations that were used for design space screening and preliminary optimization together with low-turbulence wind tunnel tests which yielded certain results. To decrease the numerical cost of the computer simulation campaign, Design of experiment methods (optimal space-filling design among others) were employed instead of exhausting full factorial (parametric) design. Response surface models of major aerodynamic coefficients (lift, drag, pitching moment) at predicted maximum lift coefficient ( C L max) point allowed to narrow down search space and identify several candidates for optimal configuration to be checked experimentally. Wind tunnel tests campaign confirmed the major trends observed in computational fluid dynamics derived response surface contour plots. For the optimum aerodynamic configuration, chosen experimental C L max is over 3.9, which is a 10% increase over the baseline (initial slat and flap positions) case. In parallel, the maximum lift-to-drag ratio gain at that point was almost 19%. The research outlined in this paper was conducted on behalf of the aircraft production company and its results will be applied in a newly designed transport aircraft.

Purpose The purpose of this paper is to investigate the estimation methodology with a highly generalized cost-effective single hidden layer neural network. Design/methodology/approach The aerodynamic parameter estimation is a challenging research area of aircraft system identification, which finds various applications such as flight control law design and flight simulators. With the availability of the large database, the data-driven methods have gained attention, which is primarily based on the nonlinear function approximation using artificial neural networks. A novel single hidden layer feed-forward neural network (FFNN) known as extreme learning machine (ELM), which overcomes the issues such as learning rate, number of epochs, local minima, generalization performance and computational cost, as encountered in the conventional gradient learning-based FFNN has been used for the nonlinear modeling of the aerodynamic forces and moments. A mathematical formulation based on the partial differentiation is proposed to estimate the aerodynamic parameters. Findings The real flight data of longitudinal and lateral-directional motion have been considered to estimate their respective aerodynamic parameters using the proposed methodology. The efficacy of the estimates is verified with the results obtained through the conventional parameter estimation methods such as the equation-error method and filter-error method. Originality/value The present study is an outcome of the research conducted on ELM for the estimation of aerodynamic parameters from the real flight data. The proposed method is capable to estimate the parameters in the presence of noise.

Purpose The purpose of this paper is to describe simulation research carried out for the needs of multi-sensor anti-collision system for light aircraft and unmanned aerial vehicles. Design/methodology/approach This paper presents an analysis related to the practical possibilities of detecting intruders in the air space with the use of optoelectronic sensors. The theoretical part determines the influence of the angle of view, distance from the intruder and the resolution of the camera on the ability to detect objects with different linear dimensions. It has been assumed that the detection will be effective for objects represented by at least four pixels (arranged in a line) on the sensor matrix. In the main part devoted to simulation studies, the theoretical data was compared to the obtained intruders’ images. The verified simulation environment was then applied to the image processing algorithms developed for the anti-collision system. Findings A simulation environment was obtained enabling reliable tests of the anti-collision system using optoelectronic sensors. Practical implications The integration of unmanned aircraft operations in civil airspace is a serious problem on a global scale. Equipping aircraft with autonomous anti-collision systems can help solve key problems. The use of simulation techniques in the process of testing anti-collision systems allows the implementation of test scenarios that may be burdened with too much risk in real flights. Social implications This paper aims for possible improvement of safety in light-sport aviation. Originality/value This paper conducts verification of classic flight simulator software suitability for carrying out anti-collision systems tests and development of a flight simulator platform dedicated to such tests.

To adapt the autonomous level of agents in current, and to perform the advantages of multi-agent in air combat, the form of manned/unmanned aircraft cooperative system has gradually become a hot topic. To solve the issue of three-dimensional (3D) real-time obstacle avoidance, the 3D maneuvering obstacle model is established firstly based on the traditional velocity obstacle method. Then the flight mode is selected and the optimal obstacle avoidance plane is determined by setting the Right-of-way rules when the system encountering obstacles. Finally, the difference of obstacle avoidance plane, the feasibility of avoiding maneuvering obstacle and the effectiveness of obstacle avoidance of cooperative system are verified by several flight simulations. The results show that the proposed method can realize the avoidance of 3D maneuvering obstacle for manned/unmanned aircraft cooperative system safely and efficiently.

Coaxial rotor configurations are common in multirotor unmanned aircraft systems (UAV) and are used in some manned helicopters. In the case of small-to-medium-sized unmanned rotorcraft, there is a lack of experimental data on icing and a lack of analysis of vehicle performance and flight characteristics in icing conditions. This paper (a) describes experimental methodology and results of a coaxial rotor system with 0.46-m-diameter rotors operating in hover in an icing cloud, (b) develops an empirical model relating the change in torque and thrust as a function of rotor speed and ice accretion rate based on experimental data, and (c) applies this model to a simulation of UAV in icing conditions. Experimental results showed linear growth in required torque and linear reduction in thrust at a given rotor speed as ice accretes, with the rate of change of torque and thrust dependent on shaft speed and temperature. A significant difference in ice accretion rate was observed between the upper and lower rotors, with the lower rotor showing a lower rate of ice accretion. Simulation of UAV flight in icing conditions showed rapid loss of control and a loss of ability to maintain hover, with loss of sustained flight occurring within 40 s of the onset of icing. Simulation of flight with an ice-shedding event (which results in a step change in thrust and torque) results in a perturbation in pitch and roll, leading to significant lateral acceleration in addition to loss of altitude.

The fast maneuver of aerovehicles is one of the typical multiphysics coupled problems. The numerical virtual flight (NVF) simulation is a very useful and effective tool to analyze this kind of mult...

It has been reported that the decrease in performance of airplane pilots, due to extreme work conditions, could potentially lead to an accident. Additionally, exposure to heat conditions has been linked to increased accident rates. The objective of this experimental study was to examine the influence of temperature (21°C and 35°C) and the maneuver complexity, in the pilots’ performance, measured by the time spent to complete a maneuver, using a Static Flight Driving Device simulator. We used an experimental design with ten () professional pilots who had an average flight experience of 420 hours. The results obtained show that there is an effect of both, temperature and the maneuver difficulty, in the time needed to complete a flight maneuver. Maneuvers that are more complex or expose pilots to heat , increase the time to complete a maneuver. Even though the interaction term had a p-value of 0.103, what was seen in the experiment suggest that the temperature has a bigger effect when the maneuver is considered difficult.

The influence of acoustic characteristics of in-flight noise on airplane operations and sound impression has been investigated through objective and subjective measure including the flight simulation. The authors verified the influence of the noise conditions including seven conditions, in which the sound pressure levels and frequency characteristics of them were parametrically changed, on the airplane operations using shortterm flight simulation. Resultantly, the change of the sound pressure levels of the in-flight noise did not greatly affect the operation accuracy although clearly affected the subjective impressions. On the other hand, it has been suggested that the change of the frequency characteristics of in-flight noise affected not only the subjective impressions but also the operation accuracy.

Maintaining and balancing an optimal level of workload is essential for completing the task productively. Fighter aircraft is one such example, where the pilot is loaded heavily both physically (due to G manoeuvering) and cognitively (handling multiple sensors, perceiving, processing and multi-tasking including communications and handling weapons) to fulfill the combat mission requirements. This cognitive demand needs to be analysed to understand the workload of fighter pilot. Objective of this study is to analyse dynamic workload of fighter pilots in a realistic high-fidelity flight simulator environment during different flying workload conditions. The various workload conditions are (a) normal visibility, (b) low visibility, (c) normal visibility with secondary task, and (d) low visibility with secondary task. Though, pilot’s flying performance score was good, the physiological measure like heart rate variability (HRV) features and subjective assessment (NASA-TLX) components are found to be statistically significant (p

In this article, a novel flight simulator manipulator with four degrees of freedom (DOFs) is introduced. The manipulator is called 4RPSP + PS parallel manipulator (PM) having a fixed platform, a pl...

To compute the most efficient route that the aircraft has to fly, the flight management system (FMS) needs a mathematical representation of the aircraft performance. However, after several years of...

Previous studies show that pilots sometimes make roll reversal errors (RREs) when responding to the aircraft bank angle shown on the attitude indicator (AI). This is suggestive of a perceptual ambiguity in the AI. In the current study, we investigated whether expectation contributes to such misperception. Twenty nonpilots performed tasks in a fixed-base flight simulator. Their expectation about the bank angle was manipulated with a flying task using outside view only. When flying at a bank angle, the outside view disappeared, a moving-horizon type AI was shown, and participants had to roll the wings level, trusting the AI. The AI often matched the previously flown turn. However, in some runs, it showed an opposite bank direction (Opposite condition), which was hypothesized to facilitate a misperception. In some other runs, it showed level flight (Level condition), which should not facilitate this. In a second session, participants rolled wings level without preceding flying task (Baseline condition). Participants made 11.2 times more RREs in the Opposite condition (75% error rate) compared to Baseline condition (6.7%), and 2.5 times more compared to the Level condition (30%). This indicates that RREs were in many cases caused by expectation-induced misperception of the AI bank angle.

Objective: This study aimed to investigate whether pilots and non-pilots differ in their susceptibility to spatial disorientation (SD) during a flight in various disorienting scenarios, and in copi...

An automation system for detecting the pilot's diversified mental states is an extremely important and essential technology, as it could prevent catastrophic accidents caused by the deteriorated cognitive state of pilots. Various types of biosignals have been employed to develop the system, since they accompany neurophysiological changes corresponding to the mental state transitions. In this study, we aimed to investigate the feasibility of a robust detection system of the pilot's mental states (i.e., distraction, workload, fatigue, and normal) based on multimodal biosignals (i.e., electroencephalogram, electrocardiogram, respiration, and electrodermal activity) and a multimodal deep learning (MDL) network. To do this, first, we constructed an experimental environment using a flight simulator in order to induce the different mental states and to collect the biosignals. Second, we designed the MDL architecture – which consists of a convolutional neural network and long short-term memory models – to efficiently combine the information of the different biosignals. Our experimental results successfully show that utilizing multimodal biosignals with the proposed MDL could significantly enhance the detection accuracy of the pilot's mental states.

This paper deals with the Unmanned Aircraft Vehicle (UAV) flight phases dynamics simulation. It predicts the accuracy of the UAV flight using the output graphs. The monitoring of the main flight phases (take-off, en-route, landing) is carried out using instruments, UAV standard procedures and rules established by the applicable aviation standards for the method of Unmanned Aircraft Vehicle operation. The fundamental peculiarity of flight and technical analysis is based on a gradual qualitative change in the movement of a known flying vehicle, where its operating systems and its management and control rules are gradually changed and transformed in accordance with technical, operational and legislative conditions which means the transfer of flight and technical analysis from the area of mathematical-mechanical precise flight tracking and the sophistication of its operation in a mountainous environment.

The article is focused on the objective measurement of pilot workload during IFR flight. Reducing pilot’s mental load is a major aspect in the design modern aviation systems, and it’s operation. However, as technology has been improving, the aircraft became increasingly complex. As the amount of information needed to be increased, the cockpit layout became the limiting factor. We have decided to focus our measurements on the effects of mental stress caused by a lack of training and flight experience during IFR flight. For our research, we decided to use eye monitoring technology to record eye movements to determine the pilot’s performance. Eye monitoring provides data on the number of eye movements, number of visual intakes, number of saccades, number of blinks, fixations, and the duration of these. The research involved overall six pilots divided into two groups: the experienced and inexperienced. The measurements were performed on the ELITE S923 flight simulator located at Zilina airport, Dolny Hricov. The conclusion of our article summarizes the measurement results and the use of eye track technology in the future.

To ensure safety in aviation, it is important that the flight crew, and especially pilots, function properly. One way to check the functioning of the pilot is to assess his psychophysical state and the ability to control it. One way of influencing to psychophysical state may be physical activity. The article presents the impact of physical activity to pilot’s psychophysical state during flight. The research was carried out using a flight simulator - CKAS MotionSim 5, located in the Simulator Research Laboratory of the Poznan University of Technology. To assess the psychophysical state, an EEG device and a pulse oximeter were used. The research group consisted of 5 pilots holding a PPL license. Each pilot made two flights: the first before stimulating the pilot’s physicality through physical activity and the second after stimulation. Measurements were made during flights. The research of the psychophysical state was carried out using an EEG device - Mindwave and a pulse oximeter. The results of the research are presented in the form of a table and distributions for individual variables: concentration level (CL), relaxation (RL) and pulse. The results were analyzed using basic statistical functions. The collected data allowed the assessment and comparison of the psychophysical state of pilots before and after physical exercises. Based on the results of the study, it can be concluded that physical activity affects the psychophysical state of the pilot during the flight.

This work presents the implementation of system identification and model predictive control for a tail-sitter unmanned aerial vehicle (UAV) in cruise flight. The mathematical model of longitudinal and lateral directions of the UAV has been derived in the state-space form for grey-box modeling. The least-square regression method is augmented with regulation and solved by applying the trust-region algorithm. Outdoor flight tests were conducted to acquire the data for system identification assisted by a signal generator module. The UAV dynamic was sufficiently excited in both longitudinal and lateral directions during the flight test. The flight data were applied to the grey box system identification, and the parameters were validated by fitting the reconstructed model to a set of flight data with a different excitation waveform. The flight controller with model predictive control was formed using the identified models for flight simulation. The results demonstrate that the system identification results are able to provide reference models for the model-based controller development of the novel-design tail-sitter UAV.

In order to meet the needs of the Armed Forces of Ukraine (AFU) for specialists in the operation of unmanned aerial systems, the Zhitomir Military Institute named by S. P. Korolev deployed training for operators - military pilots. While creating the material and technical base, the issue of developing and introducing into the training process of simulators that would meet the requirements of higher military education training. Development of the scientific training system was carried out on the basis of the list of basic training issues, profound mastery of which is mandatory for the UAV operator’s. The training system was developed, manufactured and implemented in the training process, which is built as a schematic-abstracted one to ensure the conditions of effective learning material assimilation. The content basis of the scientific training system is a flat schematic outline of the aircraft, which contains typical onboard equipment of unmanned aerial vehicles and a reconstructed connection scheme of the elements. The power of the onboard equipment is provided from the classroom power supply via a stabilized power supply unit. Operation of the onboard equipment can be controlled from the manual control panel and from the ground control station via the Mission Planner program. The Mission Planner can also be controlled from the X - Plane flight simulator. In flight simulation mode, the Mission Planner screen displays a map of the flight route, the X-Plane screen displays the view and spatial orientation as well as the corresponding servo drives of the aircraft's steering surfaces and the main engine operation modes. The software of the scientific training system allows planning and adjusting the route and flight program, practicing UAV piloting skills in the flight simulator mode, simulating flight in different weather conditions. The scientific training system includes a two-channel hardware-software oscilloscope which allows to research electric processes in different electric lines of airborne equipment of the aircraft and pair interconnections between them. Functional properties of scientific training system allow to study theoretically and practice practically a wide range of training issues required in training of UAV operators. Up to this circle includes both the issues necessary for mastering drone piloting and the issues necessary for mastering the maintenance and repairs of UAV., Для задоволення потреби Збройних Сил України у фахівцях з експлуатації безпілотних авіаційних комплексів у Житомирському військовому інституті імені С.П.Корольова розгорнуто підготовку операторів - зовнішніх пілотів. У ході створення матеріально-технічної бази було порушено питання розробки та впровадження в навчальний процес тренажерних засобів, які б відповідали вимогам підготовки фахівців із вищою військовою освітою. Тому було створено навчально-тренувальну систему на основі переліку базових навчальних питань, глибоке оволодіння якими є обов’язковим для оператора безпілотних авіаційних комплексів. Розроблено, виготовлено та впроваджено в навчальний процес навчально-тренувальну систему, яка для забезпечення умов ефективного засвоєння навчального матеріалу побудована як схематично-абстрагована. Її змістовну основу становить плоский схематичний контур літака, на якому розміщене типове бортове обладнання безпілотних літальних апараті та відтворена схема сполучень елементів. Живлення бортового обладнання забезпечується від аудиторної електромережі через стабілізований блок живлення. Керування роботою бортового обладнання можливе з ручного пульта управління та з наземної станції через програму Mission Planner. Також реалізовано управління роботою Mission Planner від програмного симулятора польотів X-Plane. У режимі симуляції польоту на екрані Mission Planner відображається карта маршруту польоту, на екрані X-Plane відтворюється вигляд та просторова орієнтація літака. На схематичному контурі літака відпрацьовують відповідні сервоприводи рульових поверхонь літального апарата та змінюються режими роботи головного двигуна. Програмне забезпечення навчально-тренувальної системи дозволяє проводити планування та коригування маршруту і програми польоту, відпрацьовувати навички пілотування безпілотного літального апарата в режимі симулятора польоту, симулювати політ за різних погодних умов. До складу навчально-тренувальної системи включено двоканальний програмно-апаратний осцилограф, який дозволяє досліджувати електричні процеси в різних електричних лініях бортового обладнання літального апарата та попарні взаємозв’язки між ними. Функціональні властивості навчально-тренувальної системи надають можливості вивчати теоретично та відпрацьовувати практично широке коло навчальних питань, зокрема тих, що стосуються освоєння не лише пілотування безпілотних літальних апаратів, а й технічного обслуговування та ремонтів безпілотних авіаційних комплексів.

U ovom diplomskom radu u Simulink je implementiran model borbenog zrakoplova L-21, nalik na MiG-21. Za izradu modela leta je korišten 6DOF model krute letjelice konstantne mase, a zanemaren je utjecaj vjetra i zakrivljenosti Zemlje. Osim modela letjelice modelirani su i instrumenti u programskom paketu MATLAB. Prikazan je poseban osvrt jednog od ispitnih pilota, iskusnog pilota mlaznog zrakoplova, koji je prvi isprobao model. Osmišljene su dvije zadaće za provedbu ispitivanja. Jedna zadaća je praćenje putanje prilaza za slijetanje, a druga zadaća je praćenje signala kuta valjanja. Odabrani su ispitni piloti koji moraju izvršiti prethodno osmišljene zadatke. Prikupljeni su podaci o letovima ispitnih pilota i njihove subjektivne ocjene kvalitete upravljanja. Analiza subjektivne kvalitete upravljanja je provedena uz pomoć Cooper - Harper skale. Na kraju rada je napravljena objektivna analiza letova kao i usporedba objektivne i subjektivne analize. In this master thesis model of a fighter aircraft L-21, similar to MiG-21 was implemented in Simulink. The 6DOF model of a rigid constant-mass aircraft was used to create a flight model, with the neglected influences of the wind and curvature of the Earth. Instruments were modeled using MATLAB software package in addition to the aircraft model. A special review of one of the test pilots, an experienced jet pilot, who first tested the model is presented. Two mission task elements have been designed for the test. One task is to monitor the landing approach path and the other task is to monitor the rolling angle signal. Test pilots have been selected to perform pre-designed tasks. Data of the test pilot flights and their subjective assessments of management quality were collected. The analysis of subjective quality of management was conducted using Cooper - Harper scale. At the end of the paper, an objective analysis of flights was made, as well as a comparison of objective and subjective analysis.

Purpose This paper aims to offer a simultaneous design approach for helicopter having swept anhedral blade tip shape and helicopter flight control system (HFCS) to minimize controller cost. Design/methodology/approach By considering previously stated offer, control-oriented models and a stochastic optimization method are applied to minimize controller cost of the HFCS. Findings Using simultaneous design approach for helicopters having blade tip swept and blade tip anhedral causes considerably less control effort than the helicopters not benefiting this related design approach. Practical implications Simultaneous design approach for helicopters having blade tip swept and blade tip anhedral is applicable to consider fuel economy. Originality/value One important novelty of this paper is using simultaneous approach for determining optimum shape of blade tip swept and anhedral. Another considerable novelty of this paper is also using a stochastic optimization method called simultaneous perturbation stochastic approximation for previously mentioned purpose. In this paper, it is also reached that using simultaneous design approach for swept anhedral helicopter blade tip shape and HFCS causes less control effort than the helicopters not using this approach. This leads to less fuel consumption and green environment.

Тема выпускной квалификационной работы: «Разработка системы клиент/сервер отображения тактической обстановки для авиасимулятора DCS World». Данная работа посвящена разработке программы для передачи и вывода тактической информации на языке программирования C++ с применением фреймворка Qt. Задачи, которые решались в Ñ Ð¾Ð´Ðµ разработки: 1. Изучение рынка ÑÐ¾Ð²Ñ€ÐµÐ¼ÐµÐ½Ð½Ñ‹Ñ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¼ÑƒÐ»ÑÑ‚Ð¾Ñ€Ð¾Ð²; 2. Анализ ÑÑƒÑ‰ÐµÑÑ‚Ð²ÑƒÑŽÑ‰Ð¸Ñ Ð¿Ñ€Ð¾Ð³Ñ€Ð°Ð¼Ð¼Ð½Ñ‹Ñ Ð¿Ñ€Ð¾Ð´ÑƒÐºÑ‚Ð¾Ð², Ñ€ÐµÑˆÐ°ÑŽÑ‰Ð¸Ñ ÑÑ Ð¾Ð¶Ð¸Ðµ задачи 3. Анализ и выбор Ð¿Ñ€Ð¾Ð³Ñ€Ð°Ð¼Ð¼Ð½Ñ‹Ñ ÑÑ€ÐµÐ´ÑÑ‚Ð² для разработки программы; 4. Построение Ð°Ñ€Ñ Ð¸Ñ‚ÐµÐºÑ‚ÑƒÑ€Ñ‹ приложения; 5. Разработка клиентской части приложения; 6. Разработка серверной части приложения. Работа проведена на базе среды разработки Qt Creator на C++ с применением фреймворка Qt, QML и языка программирования Lua для написания скрипта импорта Ð´Ð°Ð½Ð½Ñ‹Ñ Ð² DCS World. В результате была разработана программа для передачи и вывода тактической информации для авиасимулятора DCS World., The theme of the final qualifying work: “Development of client/server application of tactical display in flight simulator DCS World”. This work is devoted to the development of a application for transfer and output of tactical information on C++ programming language with Qt Framework. Tasks that were solved during a development: 1. Studying modern flight simulators market 2. Analysis of existing software, solving similar tasks; 3. Building the architecture of the program; 4. Development of a client application; 5. Development of a server application. The work was done based on the Qt Creator development environment using the Qt Framework, QML and Lua programming language for scripting DCS data export. As a result, tactical display program was developed for DCS World flight simulator.

Protection of the natural environment is a key activity driving development in the transport discipline today. The use of simulators to train civil aviation pilots provides an excellent opportunity to maintain the balance between efficiency and limit the negative impact of transport on the environment. Therefore, we decided to determine the impact of selected simulations of air operations on energy consumption. The aim of the research was to determine the energy consumption of the flight simulator depending on the type of flight operation and configuration used. We also decided to compare the obtained result with the energy consumption of an aircraft of a similar class, performing a similar aviation operation and other means of transport. In order to obtain the results, a research plan was proposed consisting of 12 scenarios differing in the simulated aircraft model, weather conditions and the use of the simulator motion platform. In each of the scenarios, energy consumption was measured, taking into account the individual components of the simulator. The research showed that the use of a flight simulator has a much smaller negative impact on the natural environment than flying in a traditional plane. Use of a motion platform indicated a change in energy consumption of approximately 40% (in general, flight simulator configuration can change energy consumption by up to 50%). The deterioration of weather conditions during the simulation caused an increase in energy consumption of 14% when motion was disabled and 18% when motion was enabled. Energy consumption in the initial stages of pilot training can be reduced by 97% by using flight simulators compared to aircraft training.

U ovom završnom radu provedena je analiza ravnotežnog leta zrakoplova sličnog nadzvučnom borbenom zrakoplovu MiG-21, za različite uvjete leta. Analiza ravnotežnog leta izvršena je analitičkim postupkom i eksperimentom na simulatoru leta. U prvom dijelu rada definiran je pojam ravnotežnog leta i opisan analitički postupak izračuna vrijednosti napadnog kuta i kuta otklona kormila visine, te su dobiveni rezultati grafički prikazani dijagramima. U drugom dijelu opisan je simulator leta, kao i postav za provođenje eksperimenta s više pilota te su prikazani dobiveni rezultati. Na kraju je provedena usporedba analitičkih rezultata i rezultata eksperimenta, analitički rezultati uspoređeni su s podacima iz dokumentacije zrakoplova te je napravljena statistička analiza eksperimentalnih rezultata. In this Bachelor's thesis, trimmed flight analysis of an aircraft similar to the MiG-21 supersonic fighter jet aircraft was performed for different flight conditions. Trimmed flight analysis was performed by analytical procedure and experiment on a flight simulator. In the first part of the paper, the concept of trimmed flight is defined and the analytical procedure for calculating the values of the angle of attack and the elevator angle, and the obtained results are graphically represented by diagrams. The second part describes the flight simulator, as well as the setup for conducting a multi-pilot experiment and presents the obtained results. Finally, a comparison of analytical and experimental results was performed, analytical results were compared with data from aircraft documentation, and a statistical analysis of experimental results was performed.

Transfer from experiments in the laboratory to real-life tasks is challenging due notably to the inability to reproduce the complexity of multitasking dynamic everyday life situations in a standardized lab condition and to the bulkiness and invasiveness of recording systems preventing participants from moving freely and disturbing the environment. In this study, we used a motion flight simulator to induce inattentional deafness to auditory alarms, a cognitive difficulty arising in complex environments. In addition, we assessed the possibility of two low-density EEG systems a solid gel-based electrode Enobio (Neuroelectrics, Barcelona, Spain) and a gel-based cEEGrid (TMSi, Oldenzaal, Netherlands) to record and classify brain activity associated with inattentional deafness (misses vs. hits to odd sounds) with a small pool of expert participants. In addition to inducing inattentional deafness (missing auditory alarms) at much higher rates than with usual lab tasks (34.7% compared to the usual 5%), we observed typical inattentional deafness-related activity in the time domain but also in the frequency and time-frequency domains with both systems. Finally, a classifier based on Riemannian Geometry principles allowed us to obtain more than 70% of single-trial classification accuracy for both mobile EEG, and up to 71.5% for the cEEGrid (TMSi, Oldenzaal, Netherlands). These results open promising avenues toward detecting cognitive failures in real-life situations, such as real flight.

The objective of this chapter is to focus on the use of unobtrusive easy-to-use electrophysiological systems for neuroergonomic research. In a first section, we describe the challenges and limits related to the use of such systems. Electrode localization and signal processing solutions are then proposed to overcome some of the raised issues. In a second section, we explore the feasibility to measure pilots’ auditory attention in a flight simulator using an unobtrusive EEG system [1] on a small number of participants. This study aims at measuring the cerebral activity associated with inattentional deafness in an ecological context with varying degrees of workload. The end goal was to assess the possibilities of such a system to be transferred to real-flight conditions. Our results illustrate this paradox: we were able to reproduce some of the results observed in the literature, but we also faced difficulties in terms of signal processing and measure identifications. We show that despite the lower signal-to-noise ratio observed with this kind of devices, we are able to detect event-related potentials (ERPs) and frequency features. In a last part we discuss our results with regards to Neuroadaptive Systems challenges, and how we were able to overcome some of the current limits in neuroergonomics.