Relevant bibliographies by topics / Flying and Handing Qualities

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Flying and Handing Qualities'

Author: Grafiati
Published: 4 June 2021
Last updated: 13 February 2022

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Journal articles on the topic "Flying and Handing Qualities"

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Rogalski, Tomasz, and Boguslaw Dołęga. "ALGORITHMS IMPROVING FLYING QUALITIES OF GENERAL AVIATION AIRCRAFT." Aviation 10, no. 2 (June 30, 2006): 17–21. http://dx.doi.org/10.3846/16487788.2006.9635930.

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The dynamic growth of general aviation as a mean of transport over medium distances means that people having no extraordinary qualifications or extraordinary physical or mental abilities more often pilot such types of airplanes. This phenomenon creates the necessity of giving planes flying qualities that allow them to be safely piloted by ordinary people. One way of solving this problem is equipping airplanes with fly‐by‐wire control systems that modify their handling qualities. Then the computer included into such control systems modifies the actions taken by the pilot, making the airplane both easier and more comfortable to control. This paper presents sample software tools – control algorithms that allowing an airplane's handling qualities to be improved. They are prepared by the authors and tested on board an experimental plane. That plane was equipped with a prototypical fly‐by‐wire control system, which can modify a plane's responses to a pilot's actions.
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Capello, Elisa, Giorgio Guglieri, Paolo Marguerettaz, and Fulvia Quagliotti. "Preliminary assessment of flying and handling qualities for mini-UAVs." Journal of Intelligent & Robotic Systems 65, no. 1-4 (August 16, 2011): 43–61. http://dx.doi.org/10.1007/s10846-011-9565-5.

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Campos, Luís M. B. C., and Joaquim M. G. Marques. "On the Handling Qualities of Two Flying Wing Aircraft Configurations." Aerospace 8, no. 3 (March 16, 2021): 77. http://dx.doi.org/10.3390/aerospace8030077.

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The coupling of the longitudinal and lateral stability modes of an aeroplane is considered in two cases: (i) weak coupling, when the changes in the frequency and damping of the phugoid, short period, dutch roll, and helical modes are small, i.e., the square of the deviation is negligible compared to the square of the uncoupled value; (ii) strong coupling, when the coupled values may differ significantly from the uncoupled values. This allows a comparison of three values for the frequency and damping of each mode: (i) exact, i.e., fully coupled; (ii) with the approximation of weak coupling; (iii) with the assumption of decoupling. The comparison of these three values allows an assessment of the importance of coupling effects. The method is applied to two flying wing designs, concerning all modes in a total of eighteen flight conditions. It turns out that lateral-longitudinal coupling is small in all cases, and thus classical handling qualities criteria can be applied. The handling qualities are considered for all modes, namely the phugoid, short period, dutch roll, spiral, and roll modes. Additional focus is given to the pitch axis, considering the control anticipation parameter (CAP). The latter relates to the two kinds of manouever points, where damping vanishes, that are calculated for minimum speed, take-off, and initial and final cruise conditions. The conclusion compares two flying wings designs (the “long narrow” and “short wide” fuselage concepts) not only from the point of view of flight stability, but also from other viewpoints.
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Nasir, Rizal E. M., and Wahyu Kuntjoro. "Longitudinal Flight Stability Augmentation of a Small Blended Wing-Body Aircraft with Canard as Control Surface." Applied Mechanics and Materials 393 (September 2013): 329–37. http://dx.doi.org/10.4028/www.scientific.net/amm.393.329.

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Transient response of an aircraft in longitudinal motion has two modes of oscillatory motion short period mode and phugoid modes and failure to achieve satisfactory level would mean poor flying and handling qualities leading to unnecessary pilot workload. This study proposes a stability augmentation system (SAS) in longitudinal flying modes for steady and level flight at all airspeeds and altitudes within Baseline-II E-2 BWBs operational flight envelope (OFE). The main controlling component of this stability augmentation system is a set of canard, a control surface located in front of the wing. It must be able to compensate Baseline-II E-2 BWB poor transient responses damping ratios so that good flying quality can be achieved. Observation from the transient responses of the unaugmented system signify high-frequency short-period oscillations with almost constant low damping ratio at an altitude, and low-frequency phugoid oscillation with varying damping ratio depending on airspeed. A conclusive behaviour of natural frequencies and damping ratios against dynamic pressure leads to the understanding on how dynamic pressure influences the flying qualities. Derivation of dynamic equations in terms of dynamic pressures enables one to design and device a feedback system to compensate poor flying qualities of the original unaugmented aircraft with conclusive relationship between important parameters and dynamic pressure are put in the overall dynamic equation. Two feedback gain systems, pitch attitude and pitch rate gains are scheduled based on dynamic pressure values and are combined into the aircraft longitudinal SAS. The proposed SAS has proven to be the suitable candidate for Baseline-II E-2 BWB as it is able to ensure Level 1 flying qualities, longitudinally.
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Callaghan, Patrick M., and Donald L. Kunz. "Evaluation of Unmanned Aircraft Flying/Handling Qualities Using a Stitched Learjet Model." Journal of Guidance, Control, and Dynamics 44, no. 4 (April 2021): 842–53. http://dx.doi.org/10.2514/1.g004748.

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Cook, M. V., and H. V. de Castro. "The longitudinal flying qualities of a blended-wing-body civil transport aircraft." Aeronautical Journal 108, no. 1080 (February 2004): 75–84. http://dx.doi.org/10.1017/s0001924000005029.

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Abstract This paper describes an evaluation of the longitudinal flying qualities of a generic blended-wing-body (BWB) transport aircraft at low speed flight conditions. Aerodynamic data was obtained from several sources and integrated into the equations of motion of a typical BWB configuration in order to provide a reasonable basis for flying qualities assessment. The control requirements to trim are enumerated for a representative range of cg position and static margin over the typical range of approach speeds for both stable and unstable configurations. The linear dynamic characteristics of the unaugmented airframe are also described for the same range of stability margin. Subsequent work describes the development of a rate command-attitude hold command and stability augmentation system configured to comply with representative modern handling criteria. Finally, the flight dynamics of the augmented aircraft are described after refinement of the control law by means of piloted simulation in a fixed base flight simulator.
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Rogalski, Tomasz, and Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM." Aviation 9, no. 2 (June 30, 2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.

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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft should be equipped with fly‐by‐wire control systems, and there are no clear, straight, rules rate and describe the handling qualities of small airplanes with fly‐by‐wire control systems. This paper presents a methodology created by the authors that classifies and compares the handling qualities of general aviation aircraft equipped with fly‐by‐wire control systems. It takes into consideration two parameters: pilot's effort during realization of ordered tasks and precision of his control.
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Humphreys-Jennings, Clayton, Ilias Lappas, and Dragos Mihai Sovar. "Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator." Aerospace 7, no. 5 (April 28, 2020): 51. http://dx.doi.org/10.3390/aerospace7050051.

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The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3000 nautical miles, carrying 200 passengers. The BWB design was flight tested at an engineering flight simulator to first determine its static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the mean aerodynamic chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; while meeting all the requirements of the dynamic modes.
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Evangelou, L. D., A. W. Self, J. E. Allen, and S. Lo. "Trimmed deep stall on the F-16 Fighting Falcon." Aeronautical Journal 105, no. 1054 (December 2001): 679–83. http://dx.doi.org/10.1017/s0001924000012720.

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Abstract High performance fighter aircraft have problems with handling qualities, at high angles of incidence. Pilots are limiting combat effectiveness by cautiously avoiding hazardous regions of the flight envelope. This paper presents and extends existing work on the F-16 aircraft's handling characteristics during the deep stall condition. Inflight experience shows that there are two types of control problems when flying at high angles-of-attack, the ‘pitch departures’ and the ‘deep stall trim’. This paper investigates the critical deep stall condition, assesses the effectiveness of the proposed method of recovery and suggests an augmented and reliable method of returning to normal flight.
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Portapas, Vilius, and Alastair Cooke. "SIMULATED PILOT-IN-THE-LOOP TESTING OF HANDLING QUALITIES OF THE FLEXIBLE WING AIRCRAFT." Aviation 24, no. 1 (March 19, 2020): 1–9. http://dx.doi.org/10.3846/aviation.2020.12175.

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This article aims to indicate the differences between rigid and flexible wing aircraft flying (FQ) and handling (HQ) qualities. The Simulation Framework for Flexible Aircraft was used to provide a generic cockpit environment and a piloted mathematical model of a bare airframe generic high aspect ratio wing aircraft (GA) model. Three highly qualified test pilots participated in the piloted simulation trials campaign and flew the GA model with both rigid and flexible wing configurations. The results showed a negligible difference for the longitudinal HQs between rigid and flexible wing aircraft. However, significant changes were indicated for the lateral/directional HQs of the flexible wing aircraft. A wing ratcheting phenomenon manifested itself during the roll mode tests, the spiral mode exhibited neutral stability and the Dutch roll mode shape changed from a horizontal to a vertical ellipse. The slalom task flight tests, performed to assess the FQs of the aircraft, revealed the degradation of both the longitudinal and lateral/directional FQs.
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Dissertations / Theses on the topic "Flying and Handing Qualities"

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Zhu, Yan. "Longitudinal control laws design for a flying wing aircraft." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7423.

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This research is concerned with the flight dynamic, pitch flight control and flying qualities assessment for the reference BWB aircraft. It aims to develop the longitudinal control laws which could satisfy the flying and handing qualities over the whole flight envelope with added consideration of centre of gravity (CG) variation. In order to achieve this goal, both the longitudinal stability augmentation system (SAS) and autopilot control laws are studied in this thesis. Using the pole placement method, two sets of local Linear-Time-Invariant (LTI) SAS controllers are designed from the viewpoints of flying and handing qualities assessment and wind disturbance checking. The global gain schedule is developed with the scheduling variable of dynamic pressure to transfer gains smoothly between these two trim points. In addition, the poles movement of short period mode with the varying CG position are analysed, and some approaches of control system design to address the problem of reduced stability induced by CG variation are discussed as well. To achieve the command control for the aircraft, outer loop autopilot both pitch attitude hold and altitude hold are implemented by using the root locus method. By the existing criteria in MIL-F-8785C specifications being employed to assess the augmented aircraft response, the SAS linear controller with automatic changing gains effectively improve the stability characteristic for the reference BWB aircraft over the whole envelope. Hence, the augmented aircraft equals to a good characteristic controlled object for the outer loop or command path design, which guarantee the satisfactory performance of command control for the BWB aircraft. The flight control law for the longitudinal was completed with the SAS controller and autopilot design. In particular, the SAS was achieved with Level 1 flying and handing qualities, meanwhile the autopilot system was applied to obtain a satisfactory pitch attitude and altitude tracking performance.
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Pergamalis, Nikolaos. "Conceptual design, flying and handling qualities of a supersonic transport aircraft." Thesis, KTH, Flygdynamik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-211167.

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The purpose of this project is the design of a supersonic aircraft that is able to meet the market’s requirements, be economically viable and mitigate the current barriers. The initial requirements of the design have been set according to the understanding obtained from a brief market research, taking into account the market needs, in addition to the economical and environmental restrictions. The conceptual design proposed is a supersonic transport able to execute transatlantic flights carrying 15 passengers. The aerodynamics, propulsion data and weight of the design have been estimated using empirical relations and experimental data found in references. The design has been evaluated regarding its performance, stability, flying and handling qualities. The relevant models have been created using the software Matlab, while the flight testing has been executed at the Merlin MP521 engineering flight simulator. Finally, a discussion is made about the environmental impact of the supersonic transport, focusing on the aerodynamic noise, generated by the sonic boom, and the air pollutants emissions.
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Lee, Brian P. "Pilot and control system modelling for handling qualities analysis of large transport aircraft." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/10203.

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The notion of airplane stability and control being a balancing act between stability and control has been around as long as aeronautics. The Wright brothers’ first successful flights were born of the debate, and were successful at least in part because they spent considerable time teaching themselves how to control their otherwise unstable airplane. This thesis covers four aspects of handling for large transport aircraft: large size and the accompanying low frequency dynamics, the way in which lifting surfaces and control system elements are modelled in flight dynamics analyses, the cockpit feel characteristics and details of how pilots interact with them, and the dynamic instability associated with Pilot Induced Oscillations. The dynamics associated with large transport aircraft are reviewed from the perspective of pilot-in-the-loop handling qualities, including the effects of relaxing static stability in pursuit of performance. Areas in which current design requirements are incomplete are highlighted. Issues with modelling of dynamic elements which are between the pilot’s fingers and the airplane response are illuminated and recommendations are made. Cockpit feel characteristics are examined in detail, in particular, the nonlinear elements of friction and breakout forces. Three piloted simulation experiments are described and the results reviewed. Each was very different in nature, and all were designed to evaluate linear and nonlinear elements of the cockpit feel characteristics from the pilot’s point of view. These included understanding the pilot’s ability to precisely control the manipulator itself, the pilot’s ability to command the flight path, and neuro-muscular modelling to gain a deeper understanding of the range of characteristics pilots can adapt to and why. Based on the data collected and analyzed, conclusions are drawn and recommendations are made. Finally, a novel and unique PIO prediction criterion is developed, which is based on control-theoretic constructs. This criterion identifies unique signatures in the dynamic response of the airplane to predict the onset of instability.
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de, Castro Helena V. "Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft." Thesis, Cranfield University, 2003. http://hdl.handle.net/1826/119.

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The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept. Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs. The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power. The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.
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Foster, Tyler Michael. "Dynamic Stability and Handling Qualities of Small Unmanned-Aerial-Vehicles UNMANNED-AERIAL-VEHICLES." BYU ScholarsArchive, 2004. https://scholarsarchive.byu.edu/etd/219.

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General aircraft dynamic stability theory was used to predict the natural frequencies, damping ratios and time constants of the dynamic modes for three specific small UAVs with wingspans on the scale from 0.6 meters to 1.2 meters. Using USAF DatCom methods, a spreadsheet program for predicting the dynamic stability and handling qualities of small UAVs was created for use in the design stage of new small UAV concept development. This program was verified by inputting data for a Cessna-182, and by then comparing the program output with that of a similar program developed by DAR Corporation. Predictions with acceptable errors were made for all of the dynamic modes except for the spiral mode. The design tool was also used to verify and develop dynamic stability and handling qualities design guidelines for small UAV designers. Using this design tool, it was observed that small UAVs tend to exhibit higher natural frequencies of oscillation for all of the dynamic modes. Comparing the program outputs with military handling qualities specifications, the small UAVs at standard configurations fell outside the range of acceptable handling qualities for short-period mode natural frequency, even though multiple test pilots rated the flying qualities as acceptable. Using dynamic scaling methods to adjust the current military standards for the short period mode, a new scale was proposed specifically for small UAVs. This scale was verified by conducting flight tests of three small UAVs at various configurations until poor handling qualities were observed. These transitions were observed to occur at approximately the boundary predicted by the new, adjusted scale.
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Lesiário, Ana. "Parametric Studies on UAV Flying Qualities." Thesis, KTH, Reglerteknik, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-105898.

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When developing an aircraft, one of several important aspects is to predict and properly design the dynamic behaviour of the aircraft. This holds for manned aircraft as well as for UAVs. The optimal dynamic behaviour for an aircraft depends on the mission or purpose: for a certain use an aircraft should be agile, other may require a more stable one. In aeronautics, the properties that describe the aircraft ecacy with respect to some task are known as ying qualities, and our goal is to study their dependence on some design parameters. As a test model we use an existing UAV. After deriving its 6-DOF dynamic model and assessing its baseline characteristics, we perform parametric studies. The strategy followed is divided in two steps: the rst consists on analyzing ying qualities sensitivity to changes in model parameters. The second step studies how specific design changes affect model parameters. Because the rst step only depends on the dynamic model form, we verify, by testing two other dierent aircrafts, that conclusions drawn from this step are valid to other congurations. Finally we show how results from parametric studies can be used to improve the UAV ying qualities regarding a certain mission, through the introduction of slight modications on baseline design.
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Lawrence, Ben. "The flying qualities of the Wright flyers." Thesis, University of Liverpool, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.408567.

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Ahmad, Shah Shahrul. "Improved autogyro flying qualities using automatic control methods." Thesis, University of Glasgow, 2018. http://theses.gla.ac.uk/39052/.

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An autogyro or Autogiro is a unique type of rotary-wing aircraft that was successfully flown in the 1920s, many years before the first helicopter came to service. As far as the rotorcraft technology is concerned, the technical issues addressed by autogyros were eventually rectified and paved the way for the success of helicopter development. When helicopter became more popular and accepted in the civil aviation industry in the 1940s, autogyros were nearly forgotten and the popularity slowly diminished. The re-emergence of autogyros in the last two decades in hobby and sports flight activities, however, coincides with bad safety records due to stability issues. At the time of this writing, there are no specific flying qualities standards to be em- ployed as guidelines to design a light autogyro with good stability attributes. The only requirements available are addressed in the BCAR Section T airworthiness standard for light autogyros which only prescribes some basic dynamic stability requirements for the vehicle. For existing conventional light autogyros which mostly of 'home-built' type, complying with the airworthiness standards would be an issue as most of them were built beforehand. From these concerns, this Thesis aims to improve the flying qualities performance of existing light autogyros through automatic flight control methods, as one of the ways to practically achieve the required performance. Consequently, specific flying qualities requirements for light autogyros must first be proposed as preliminary guidelines for design and flying qualities improvement. A generic mathematical model of light autogyros named ARDiS is developed based on the 'multiblade' simulation ap- proach which is computationally cost-effective. This model was successfully validated against real autogyro flight data and later implemented in the control enhancement of the vehicle. The control enhancement was developed using classical approaches with limitation in size and simplicity of the vehicle as a light aircraft. Proper actuation control hard- ware was separately modelled and deployed into the autogyro to demonstrate a higher dynamics in the control mechanism so that a more realistic attitude behaviour of the vehicle is presented. This control enhancement was successfully evaluated with both, linear and nonlinear simulations according to the proposed autogyro flying qualities attributes. All presented results signify a higher possibility of improving the flying qualities of currently used and future built light autogyros through control enhance- ment.
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Field, Edmund. "Flying qualities of transport aircraft : precognitive or compensatory?" Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10636.

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The introduction of fly-by-wire electronic flight control systems into transport aircraft has given the flying qualities engineer the opportunity to optimise the flying qualities of these aircraft for their specific tasks. With this technology has come the opportunity to introduce new technologies into the cockpit, such as non-linked or backfed sidesticks and non-backfed throttle levers. A comparative survey of airline pilots flying such a very high technology unconventional aircraft and a high technology but conventional aircraft suggests that these technologies may reduce the available channels of communication to the pilot in the very high technology aircraft, resulting in the possibility of reduced situational awareness. A closed loop piloted simulation survey of ten transport aircraft in current operation was undertaken which demonstrated that they all suffered from flying qualities deficiencies, limiting the performance that the pilot could achieve. In particular poor dynamics precluded the pilot adopting tight closed loop, or compensatory, control. Instead it was necessary to adopt a more open loop, precognitive, technique with medium frequency modulation, resulting in a degradation in landing performance. Through appropriate flight control system design it should be possible to produce aircraft that can be flown using the full range of control inputs from open to closed loop. The major study of this thesis assessed, through piloted simulation evaluations, the suitability of a wide range of longitudinal commanded response types for the approach and landing tasks. It was concluded that a response type that closely resembles that of angle of attack is optimum for these tasks due to its conventional characteristics of speed stability on the approach and monotonic stick forces in the flare. Such a system, appropriately implemented, should allow the transport aircraft pilot the full range of piloted control inputs, from open loop, precognitive, to closed loop, compensatory, resulting in improved landing performance.
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Field, Edmund J. "Flying qualities of transport aircraft : precognitive or compensatory?" Thesis, Cranfield University, 1995. http://dspace.lib.cranfield.ac.uk/handle/1826/10636.

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The introduction of fly-by-wire electronic flight control systems into transport aircraft has given the flying qualities engineer the opportunity to optimise the flying qualities of these aircraft for their specific tasks. With this technology has come the opportunity to introduce new technologies into the cockpit, such as non-linked or backfed sidesticks and non-backfed throttle levers. A comparative survey of airline pilots flying such a very high technology unconventional aircraft and a high technology but conventional aircraft suggests that these technologies may reduce the available channels of communication to the pilot in the very high technology aircraft, resulting in the possibility of reduced situational awareness. A closed loop piloted simulation survey of ten transport aircraft in current operation was undertaken which demonstrated that they all suffered from flying qualities deficiencies, limiting the performance that the pilot could achieve. In particular poor dynamics precluded the pilot adopting tight closed loop, or compensatory, control. Instead it was necessary to adopt a more open loop, precognitive, technique with medium frequency modulation, resulting in a degradation in landing performance. Through appropriate flight control system design it should be possible to produce aircraft that can be flown using the full range of control inputs from open to closed loop. The major study of this thesis assessed, through piloted simulation evaluations, the suitability of a wide range of longitudinal commanded response types for the approach and landing tasks. It was concluded that a response type that closely resembles that of angle of attack is optimum for these tasks due to its conventional characteristics of speed stability on the approach and monotonic stick forces in the flare. Such a system, appropriately implemented, should allow the transport aircraft pilot the full range of piloted control inputs, from open loop, precognitive, to closed loop, compensatory, resulting in improved landing performance.
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Books on the topic "Flying and Handing Qualities"

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Stinton, Darrol. Flying qualities and flight testing of the airplane. Oxford: Blackwell Science, 1998.

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Stinton, Darrol. Flying qualities and flight testing of the aeroplane. Oxford, OX: Blackwell Science, 1996.

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Stinton, Darrol. Flying qualities and flight testing of the airplane. Reston, VA: American Institute of Aeronautics and Astronautics, 1998.

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Stinton, Darrol. Flying qualities and flight testing of the aeroplane. Oxford, OX: Blakwell Science, 1996.

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Soparkar, Sherard. The effects of simulator motion on handling qualities. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2002.

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Soparkar, Sherard. The effects of simulator motion on handling qualities. Ottawa: National Library of Canada, 2002.

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Padfield, G. D. Helicopter flight dynamics: The theory and applicationof flying qualities and simulation modelling. Oxford: Blackwell Science, 1996.

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Padfield, G. D. Helicopter flight dynamics: The theory and application of flying qualities and simulation modelling. 2nd ed. Oxford: Blackwell, 2007.

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Padfield, G. D. Helicopter flight dynamics: The theory and application of flying qualities and simulation modelling. 2nd ed. Washington, DC: American Institute of Aeronautics and Astronautics, 2007.

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Helicopter flight dynamics: The theory and application of flying qualities and simulation modeling. Washington , DC: AIAA, 1995.

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Book chapters on the topic "Flying and Handing Qualities"

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Capello, Elisa, Giorgio Guglieri, Paolo Marguerettaz, and Fulvia Quagliotti. "Preliminary assessment of flying and handling qualities for mini-UAVs." In Recent Developments in Unmanned Aircraft Systems, 43–61. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-3033-5_4.

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Sissingh, G. "Flying Qualities." In Göttinger Monograph N: German Research and Development on Rotary-Wing Aircraft (1939–1945), 135–73. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2015. http://dx.doi.org/10.2514/5.9781624102738.0135.0174.

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Krag, Bernd, and Bernd Gmelin. "Flying Qualities—Some History." In In-Flight Simulators and Fly-by-Wire/Light Demonstrators, 5–17. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-53997-3_2.

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Gratton, Guy. "An Introduction to Flying Qualities Evaluation." In Initial Airworthiness, 193–99. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-11409-5_11.

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Gratton, Guy. "An Introduction to Flying Qualities Evaluation." In Initial Airworthiness, 233–40. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-75617-2_11.

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Hafer, Andreas, Gottfried Sachs, Holger Friehmelt, Heinz-Jürgen Pausder, Carl Ockier, Helmut John, Ulrich Butter, and Günter Braun. "Flying Qualities, Unstable Flight, Avionics, Cockpit, Sensors." In Aeronautical Research in Germany, 475–539. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-642-18484-0_18.

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Cook, M. V. "Flying and Handling Qualities." In Flight Dynamic Principles, 240–73. Elsevier, 2007. http://dx.doi.org/10.1016/b978-075066927-6/50013-1.

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Cook, Michael V. "Flying and Handling Qualities." In Flight Dynamics Principles, 259–91. Elsevier, 2013. http://dx.doi.org/10.1016/b978-0-08-098242-7.00010-9.

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Cook, M. V. "Flying and Handling Qualities." In Flight Dynamics Principles, 203–33. Elsevier, 1997. http://dx.doi.org/10.1016/b978-0-340-63200-0.50015-0.

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"Flying Qualities." In Flight Testing Of Fixed-Wing Aircraft, 359–63. Reston ,VA: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/5.9781600861840.0359.0363.

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Conference papers on the topic "Flying and Handing Qualities"

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Tomczyk, Andrzej. "Flying Laboratory for Aircraft Handling Qualities Evaluation." In AIAA Modeling and Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-6352.

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Kemper, Jay, and M. Christopher Cotting. "Simulator Design for Flying and Handling Qualities Instruction." In AIAA Modeling and Simulation Technologies Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1664.

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Clark, Curtis. "Current Flying and Handling Qualities Simulations in AFRL/VA." In AIAA Modeling and Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-5760.

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Lemaignan, Benoit. "Flying with no Flight Controls: Handling Qualities Analyses of the Baghdad Event." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-5907.

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Elwahab, Safa Abd, Safa Najm Elden, Osman M. Imam, and Raheeg AL Amin. "Evaluation of Boeing 747-E lateral autopilot using flying and handling qualities specifications." In 2017 International Conference on Communication, Control, Computing and Electronics Engineering (ICCCCEE). IEEE, 2017. http://dx.doi.org/10.1109/iccccee.2017.7867653.

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Ehlers, Jana, Dominik Niedermeier, and Dirk Leissling. "Verification of a Flying Wing Handling Qualities Analysis by means of In-Flight Simulation." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6540.

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Mansor, S., Yasser A. M. Nogoud, and Raheeg Alamin. "Longitudinal command stability augmentation system design for unstable aircraft using flying and handling qualities specifications." In 2015 International Conference on Computing, Control, Networking, Electronics and Embedded Systems Engineering (ICCNEEE). IEEE, 2015. http://dx.doi.org/10.1109/iccneee.2015.7381444.

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Leggett, David, and Thomas Cord. "Flying qualities demonstration maneuvers." In Biennial Flight Test Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2113.

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MOENNICH, WULF, and LOTHAR DALLDORFF. "A new flying qualities criterion for flying wings." In Flight Simulation and Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3668.

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McFarlane, Cormac, Thomas Richardson, and Chris Jones. "Unmanned Aerial Vehicle Flying Qualities." In AIAA Guidance, Navigation and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-7156.

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Reports on the topic "Flying and Handing Qualities"

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities, Chapter 1: Introduction to Flying Qualities. Fort Belvoir, VA: Defense Technical Information Center, March 1991. http://dx.doi.org/10.21236/ada319972.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 8: Dynamics. Fort Belvoir, VA: Defense Technical Information Center, September 1988. http://dx.doi.org/10.21236/ada319979.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 9: Roll Coupling. Fort Belvoir, VA: Defense Technical Information Center, April 1989. http://dx.doi.org/10.21236/ada319980.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 3: Differential Equations. Fort Belvoir, VA: Defense Technical Information Center, February 1988. http://dx.doi.org/10.21236/ada319974.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 6: Maneuvering Flight. Fort Belvoir, VA: Defense Technical Information Center, October 1990. http://dx.doi.org/10.21236/ada319977.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 14: Flight Control Systems. Fort Belvoir, VA: Defense Technical Information Center, December 1988. http://dx.doi.org/10.21236/ada319984.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 2: Vectors and Matrices. Fort Belvoir, VA: Defense Technical Information Center, January 1988. http://dx.doi.org/10.21236/ada319973.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 4: Equations of Motion. Fort Belvoir, VA: Defense Technical Information Center, October 1988. http://dx.doi.org/10.21236/ada319975.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Phase. Chapter 5: Longitudinal Static Stability. Fort Belvoir, VA: Defense Technical Information Center, October 1990. http://dx.doi.org/10.21236/ada319976.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Flight Test. Chapter 11: Engine-Out Theory. Fort Belvoir, VA: Defense Technical Information Center, August 1992. http://dx.doi.org/10.21236/ada319982.

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