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U ovom diplomskom radu proveden je eksperiment za analizu opterećenja pilota na simulatoru leta. Za simulaciju u stvarnom vremenu s pilotom u petlji korišten je model leta borbenog zrakoplova, nalik na Dassault Rafale. Postojeća simulacijska platforma nadograđena je novim programskim paketima za vizualizaciju i prikaz instrumenata. Za provedbu eksperimenta osmišljena su tri zadatka praćenja prisilnog signala kuta propinjanja. U prvom i trećem zadatku zadaća kandidata bila je praćenje kuta propinjanja bez poremećaja, dok su u drugom zadatku uvedeni poremećaju u obliku leđnog i čeonog vjetra. Nakon zadataka na simulatoru proveden je generički n-back zadatak za procjenu radne memorije kandidata. Tijekom eksperimenta snimani su fiziološki parametri kandidata koji uključuju brzinu otkucaja srca, vodljivost kože i intenzitet disanja. Praćena je i usmjerenost pogleda svakog kandidata. Prikupljeni su podaci o letovima svih kandidata i njihovi odgovori na NASA-TLX upitnik i Cooper-Harper ljestvicu za ocjenu upravljivosti. Na temelju tih podataka provedena je objektivna i subjektivna procjena opterećenja i učinka pilota. Na kraju je prikazan dio prikupljenih fizioloških podataka. In this master's thesis an experiment was conducted to analyze the pilot's workload in a flight simulator environment. A model of a fighter aircraft, similar to the Dassault Rafale, was used for real-time simulation with the pilot in the loop. The existing simulation platform was upgraded with new software packages for visualization and instrument display. Three tasks were designed to track the imposed pitch angle signal during the experiment. In the first and third task, the candidates were required to track the pitch angle without disturbances, while the second task introduced disturbances in the form of tail and headwinds. After the simulator tasks, a generic n-back task was performed to assess the candidates' working memory. Physiological parameters, including heart rate, skin conductance and respiration rate were recorded during the experiment. Gaze direction of each participant was also tracked. Flight data of all participants, along with their responses to the NASA-TLX questionnaire and the Cooper-Harper rating scale for maneuverability assessment, were collected. Based on these data, an objective and subjective evaluation of pilot workload and performance was conducted. Finally, part of the collected physiological data is shown.

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.

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.

Glavni cilj ovoga rada je modeliranje i implementacija modela atmosfere u simulator leta koji simulira let trenažnog propelerskog zrakoplova generalne avijacije. U fokusu rada je analiza i primjena različitih vrijednosti parametara vezanih za model atmosfere na značajke performansi, kao i na simulacije u realnom vremenu s pilotom u petlji. Model atmosfere ugrađen je kao podređeni sustav u postojeći simulacijski model leta u MATLAB-u i SIMULINK-u. Ovaj model nam omogućuje određivanje nekih važnih i korisnih veličina vezanih za atmosferu oko zrakoplova. Ugrađeni model atmosfere sastoji se od: modela standardne atmosfere prema ISO standardu, modela nestandardne atmosfere, modela vjetra i odabranog modela turbulentnog vjetra. Model nestandardne atmosfere podijeljen je na četiri tipa atmosfere koji su izrađeni preko podataka iz vojnih standarda. Vjetar je podijeljen na konstantan vjetar i vjetar u graničnom sloju, dok je za modeliranje turbulentnog vjetra za potrebe simulacije odabran Dryden-ov model. Razmatrani zrakoplov ovog rada je Cessna 172 za kojeg su prikazane i pojedine performanse u različitim tipovima atmosfere. Isto tako unaprijeđeni su pojedini postojeći sustavi upravljanja zrakoplovom i instrumenti potrebni za vizualizaciju podataka tokom simulacije leta. U svrhu evaluacije ugrađenog modela napravljeni su zadaci i provedeni ispitni letovi sa pilotima na simulatoru prilikom kojih su prikupljene subjektivne ocjene i podaci o letu. Na kraju rada napravljena je analiza prikupljenih podataka i provedena ocjena razine kvalitete upravljanja te opterećenja pilota. Za obradu podataka i programiranje korišten je programski jezik MATLAB te SIMULINK, a za potrebe vizualizacije korištena je platforma FlightGear. The main goal of this paper is to model and implement an atmospher model in a flight simulator that simulates the flight of a general aviation training propeller aircraft. This paper also focuses on the analysis and application of various parameter values related to the atmosphere model on performance features as well as to real-time simulations with a pilot in the loop. The atmosphere model was built as a subordinate system into the existing flight simulation model in MATLAB and SIMULINK. This model allows us to determine some important and useful quantities related to the atmosphere around the aircraft. The built-in atmosphere model consists of: the standard atmosphere model according to the ISO standard, a non-standard atmosphere model, a wind model and a selected turbulent wind model. The non-standard atmosphere model is divided into four types of atmospheres that are created through data from military standards. The wind was divided into constant wind and wind in the boundary layer, while the Dryden model was chosen to model the turbulent wind for simulation purposes. The considered aircraft of this paper is a Cessna 172 for which individual performances in different types of atmosphere are shown. Some existing aircraft control systems and instruments required for data visualization during flight simulation have also been improved. For the purpose of evaluating the embedded model, tasks were performed and test flights were conducted with pilots on a simulator, during which subjective assessments and flight data were collected. At the end of the work, an analysis of the collected data was made and an assessment of the level of handling quality and pilot workload was performed. MATLAB and SIMULINK were used for data processing and programming, while FlightGear platform was used for visualization purposes.