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11	Effects Of Flight Factors On Pilot Performance, Workload, And Stress At Final Approach To Landing Phase Of Flight Lee, Kyongsun 01 January 2010 (has links) Since human errors are one of the major causes of flight accidents, the design and operation of the modern aircraft system deals with them seriously. Particularly, the pilot workload on aviation causes human errors. Whenever new procedures are introduced and operated, the aircraft capabilities have been checked in every aspect. However, there has been little study on the impact of the new procedures such as LDLP, SCDA, SATS, and Steep Angle approach on the pilot performance, workload, and stress. In this study, different methods have been tried to understand the relationship between new procedures and the pilots in terms of performance, workload, and stress. The flight factors (e.g. flight experience, gliding angle, and approach area) were examined by the pilot performance, workload, and stress at the "Final Approach to L/D" phase using the single engine Cessna 172R type flight simulator. Five students and five instructor pilots from Embry-Riddle Aeronautical University in Dayton Beach, Florida, participated and they flew under four different simulation tasks of gliding angle and approach area. Their Heart Rate Variability (HRV) and NASA-Task Load Index (TLX) were measured to determine their stress level and subjective workload, respectively. In addition, Landing Performance (LP) data (e.g. landing distance, landing speed) and Above Glide Path Tracking Performance (AGPTP) data were also collected to evaluate pilot performance. As a result, the type of approach area showed a significant effect on pilot performance, workload, and stress determined by ANOVA (HRV, TLX, LP, AGPTP: all are p < .05). Flying over "Populated" area (e.g. a large city) resulted in lower pilot performance and higher pilot workload and stress than that over "Non-Populated" area (e.g. a grass field). Similarly, the levels of a gliding angle showed the statistical difference on the performance, workload, and stress (HRV, TLX, and LP: all are p < .05). During the flight with 4.5 degree, the pilots showed lower performance with higher workload and stress. However, the levels of the flight experience did not have any influence on the performance, workload, and stress levels (AGPTP, LP, TLX, HRV: all are p > .05). In conclusion, flying in Populated area and flying with a 4.5 degree gliding angle increases the workload and stress level of the pilots. In addition, when the pilots were flying over Populated area at Final Approach to L/D phase, they showed lower performance on tracking the glide path. Based on the results, stresses and workload can have a significant impact on flight performance. Therefore, in order to reduce the workload and stress that can cause human errors, it is highly recommended to carefully examine the impact of new flight procedures on pilot workload and stress before they are implemented. Aeronautics -- Human factors Air pilots -- Job stress Air pilots -- Workload Airplanes -- Piloting Engineering
12	Lateral control system design for VTOL landing on a DD963 in high sea states Bodson, Marc January 1982 (has links) Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science; and, (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1982. / MICROFICHE COPY AVAILABLE IN ARCHIVES AND ENGINEERING / Includes bibliographical references. / by Marc Bodson. / M.S. Aeronautics and Astronautics. Vertically rising aircraft Airplanes Control systems Airplanes Landing Destroyers (Warships) Ships Hydrodynamics Automatic pilot (Airplanes)
13	Efficient and robust aircraft landing trajectory optimization Zhao, Yiming 18 January 2012 (has links) This thesis addresses the challenges in the efficient and robust generation and optimization of three-dimensional landing trajectories for fixed-wing aircraft subject to prescribed boundary conditions and constraints on maneuverability and collision avoidance. In particular, this thesis focuses on the airliner emergency landing scenario and the minimization of landing time. The main contribution of the thesis is two-fold. First, it provides a hierarchical scheme for integrating the complementary strength of a variety of methods in path planning and trajectory optimization for the improvement in efficiency and robustness of the overall landing trajectory optimization algorithm. The second contribution is the development of new techniques and results in mesh refinement for numerical optimal control, optimal path tracking, and smooth path generation, which are all integrated in a hierarchical scheme and applied to the landing trajectory optimization problem. A density function based grid generation method is developed for the mesh refinement process during numerical optimal control. A numerical algorithm is developed based on this technique for solving general optimal control problems, and is used for optimizing aircraft landing trajectories. A path smoothing technique is proposed for recovering feasibility of the path and improving the tracking performance by modifying the path geometry. The optimal aircraft path tracking problem is studied and analytical results are presented for both the minimum-time, and minimum-energy tracking with fixed time of arrival. The path smoothing and optimal path tracking methods work together with the geometric path planner to provide a set of feasible initial guess to the numerical optimal control algorithm. The trajectory optimization algorithm in this thesis was tested by simulation experiments using flight data from two previous airliner accidents under emergency landing scenarios.The real-time application of the landing trajectory optimization algorithm as part of the aircraft on-board automation avionics system has the potential to provide effective guidelines to the pilots for improving the fuel consumption during normal landing process, and help enhancing flight safety under emergency landing scenarios. The proposed algorithms can also help design optimal take-off and landing trajectories and procedures for airports. Quadratic programming Optimal control Trajectory optimization Aircraft landing Minimum time Minimum fuel Nonlinear programming Landing aids (Aeronautics) Airplanes Landing
14	Ausgewählte statistische Betrachtungen im Flugzeugentwurf: Superkritische Profile und Fahrwerk Gulla, Duncan January 2019 (has links) (PDF) Kenntnisse über Parametereigenschaften und Charakteristiken von Flugzeugkomponenten sind eine wesentliche Grundlage für Methoden des Flugzeugentwurfs. Daher ist Ziel dieser Arbeit, statistische Merkmale und Kenngrößen einer für den Flugzeugbau und Entwurf relevanten Auswahl an Komponenten zu erschließen. Dabei wurden zunächst superkritische Tragflügelprofile hinsichtlich ihrer geometrischen Eigenschaften (relative Profildicke, Wölbung, Dickenrücklage, Wölbungsrücklage und der sogenannte "Leading Edge Sharpness Parameter") untersucht. Diese Eigenschaften wurden mit der Software XFLR5 aus einer Auswahl an superkritischen Profilgeometrien erhoben und mit grafischen und beschreibenden Statistikmethoden ausgewertet. Die Profile wiesen relative Wölbungen von 0 % bis 3,4 % auf, die Mehrzahl entfiel auf Wölbungen von 1 % bis 2 %. Die Wölbungsrücklagen zeigten die für superkritische Profile typische Lage im hinteren Profilbereich zwischen 70 % und 90 % der Profiltiefe. Die Dickenrücklagen verteilten sich um einen Mittelwert von 37 % der Profiltiefe. Eine Betrachtung von Flugzeugreifendimensionen sollte das Verhältnis von Reifenbreite zum Durchmesser w/d charakterisieren. Es wurde ein annähernd lineares Verhalten festgestellt. Die Werte des Parameters w/d umfassten einen Bereich von 0,3 bis 0,4. Durch Regressionsanalysen konnten auch die Abhängigkeiten des Parameters w/d von nur einer bekannten Reifendimension (Breite oder Durchmesser) aufgezeigt werden. Die im Rahmen dieser Arbeit dargestellten Erkenntnisse können als Grundlage weiterführender Untersuchungen genutzt werden. ddc:620 info:eu-repo/classification/ddc/629.13 Luftfahrt Luftfahrzeug Flugzeugaerodynamik Fahrwerk Aeronautics Airplanes Aerodynamics Airplanes--Landing gear Tragflügelprofil Superkritischer Flügel Flugzeugentwurf Profildicke Wölbung Dickenrücklage Wölbungsrücklage XFLR5 Flugzeugreifen Reifenbreite Reifendurchmesser airfoil supercritical wing aircraft thickness camber tire regression
15	Reverse Engineering of Passenger Jets - Classified Design Parameters De Grave, Emiel January 2017 (has links) (PDF) This thesis explains how the classified design parameters of existing passenger jets can be determined. The classified design parameters are; the maximum lift coefficient for landing and take-off, the maximum aerodynamic efficiency and the specific fuel consumption. The entire concept is based on the preliminary sizing of jet powered civil aeroplanes. This preliminary sizing is explained in detail because it is the foundation of the final result. The preliminary sizing is combined using reverse engineering which is not a strict method. Therefore, only the basics are explained. By applying reverse engineering on the preliminary sizing and aiming for the classified design parameters as output, formulas are derived to calculate the maximum lift coefficients, the maximum aerodynamic efficiency and the specific fuel consumption. The goal is to calculate these parameters, using only aircraft specifications that are made public by the manufacturer. The calculations are complex with mutual relations, iterative processes and optimizations. Therefore, it is interesting to integrate everything in a tool. The tool is built in Microsoft Excel and explained in detail adding operating instructions. The program is executed for miscellaneous aeroplanes, supported with the necessary comments. Investigated aeroplanes are: Caravelle 10B (Sud-Aviation), Boeing 707-320C, BAe 146-200 (British Aerospance), A320-200 (Airbus), "The Rebel" (based on A320), Boeing SUGAR High, Boeing 747-400, Blended Wing Body VELA 2 (VELA) and Dassault Falcon 8X. ddc:620 info:eu-repo/classification/ddc/629.13 Luftfahrt Luftfahrzeug Passagierflugzeug Reverse Engineering Aeronautics Airplanes Design Reverse engineering Luftfahrttechnik Luftfahrzeug Passagierflugzeug Reverse Engineering Luftfahrttechnik Aerodynamik Passagier Flugzeug Entwurf Dimensionierung Verifikation Kraftstoffverbrauch Start Landung Reiseflug Gleitzahl Auftriebsbeiwert Aeronautics Airplanes Design Reverse engineering Aerodynamics Aeroplanes Computer software Electronic Spreadsheets Verification (Logic) Airplanes--Fuel Consumption Lift (Aerodynamics) Airplanes-Takeoff Airplanes-Landing Preliminary sizing Glide ratio L/D Cruise

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