Relevant bibliographies by topics / Aircraft controls

Contents

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

Academic literature on the topic 'Aircraft controls'

Author: Grafiati
Published: 4 June 2021
Last updated: 2 February 2022

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Journal articles on the topic "Aircraft controls"

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Zhang, X., B. Xiong, and G. Kuang. "AIRCRAFT SEGMENTATION IN SAR IMAGES BASED ON IMPROVED ACTIVE SHAPE MODEL." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-3 (April 30, 2018): 2331–35. http://dx.doi.org/10.5194/isprs-archives-xlii-3-2331-2018.

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In SAR image interpretation, aircrafts are the important targets arousing much attention. However, it is far from easy to segment an aircraft from the background completely and precisely in SAR images. Because of the complex structure, different kinds of electromagnetic scattering take place on the aircraft surfaces. As a result, aircraft targets usually appear to be inhomogeneous and disconnected. It is a good idea to extract an aircraft target by the active shape model (ASM), since combination of the geometric information controls variations of the shape during the contour evolution. However, linear dimensionality reduction, used in classic ACM, makes the model rigid. It brings much trouble to segment different types of aircrafts. Aiming at this problem, an improved ACM based on ISOMAP is proposed in this paper. ISOMAP algorithm is used to extract the shape information of the training set and make the model flexible enough to deal with different aircrafts. The experiments based on real SAR data shows that the proposed method achieves obvious improvement in accuracy.
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Robinson, K. "Engine Controls for Integrated Aircraft Systems." Aircraft Engineering and Aerospace Technology 58, no. 4 (April 1986): 8–15. http://dx.doi.org/10.1108/eb036267.

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Wright, W. E., and J. C. Hall. "Advanced Aircraft Gas Turbine Engine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 4 (October 1, 1990): 561–64. http://dx.doi.org/10.1115/1.2906205.

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With the advent of vectored thrust, vertical lift, and fly-by-wire aircraft, the complexity of aircraft gas turbine control systems has evolved to the point wherein they must approach or equal the reliability of current quad redundant flight control systems. To advance the technology of high-reliability engine controls, one solution to the Byzantine General’s problem (Lamport et al., 1982) is presented as the foundation for fault tolerant engine control architecture. In addition to creating a control architecture, an approach to managing the architecture’s redundancy is addressed.
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Zikmund, Pavel, Lukáš Dubnický, Michaela Horpatzká, Miroslav Macík, and Ivo Jebáček. "Flight Test of Pilot-Aircraft Haptic Feedback System." MATEC Web of Conferences 304 (2019): 06005. http://dx.doi.org/10.1051/matecconf/201930406005.

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This research is focused on an innovative improvement of pilot-aircraft interaction and is targeted on small aircraft. Haptic feedback is performed by actuators mounted on an aircraft's controls. The purpose of the actuators on a control stick and pedals is stall warning and a pilot guiding to safe and economical flight regimes. The feedback system mediates airflow data as angles of attack and sideslip. The paper brings results of a flight test of the proposed system. Qualitative evaluation of the haptic feedback inflight is presented. Benefits of the system are presented on a sideslip during turning. Some recommendations for the haptic pilot-aircraft interaction are stated within the discussion of the flight test results.
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Zajdel, Albert, Cezary Szczepański, Mariusz Krawczyk, Jerzy Graffstein, and Piotr Masłowski. "Selected Aspects of the Low Level Automatic Taxi Control System Concept." Transactions on Aerospace Research 2017, no. 2 (June 1, 2017): 69–79. http://dx.doi.org/10.2478/tar-2017-0016.

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Abstract Taxiing of manned and remotely piloted aircraft is still performed by pilots without using a system of automatic control of direction and speed. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge. The reasons are: decreased airport capacity due to the growing number of aircraft, poor ground operation conditions during poor visibility conditions, an increase in workload of pilots and air traffic controllers and the integration of simultaneous ground operations of manned and remotely piloted air vehicles. This paper presents selected aspects of the concept of a Low Level Automatic Taxi Control System. In particular, it emphasizes the means of controlling an aircraft during taxiing, accuracy requirements of the system and proposes control techniques. The resulting controller of the system is adaptable for different aircrafts. The actuators and their mechanical connections to available controls are the aircraft specific part and are designed for the particular type – in this case – a general aviation light airplane.
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Dos Santos, Guilherme P., Adriano Kossoski, Jose M. Balthazar, and Angelo Marcelo Tusset. "SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight." International Journal of Robotics and Control Systems 1, no. 2 (May 26, 2021): 131–44. http://dx.doi.org/10.31763/ijrcs.v1i2.329.

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This paper presents the design of the LQR (Linear Quadratic Regulator) and SDRE (State-Dependent Riccati Equation) controllers for the flight control of the F-8 Crusader aircraft considering the nonlinear model of longitudinal movement of the aircraft. Numerical results and analysis demonstrate that the designed controllers can lead to significant improvements in the aircraft's performance, ensuring stability in a large range of attack angle situations. When applied in flight conditions with an angle of attack above the stall situation and influenced by the gust model, it was demonstrated that the LQR and SDRE controllers were able to smooth the flight response maintaining conditions in balance for an angle of attack up to 56% above stall angle. However, for even more difficult situations, with angles of attack up to 76% above the stall angle, only the SDRE controller proved to be efficient and reliable in recovering the aircraft to its stable flight configuration.
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Bhardwaj, P., H. J. Kelley, and E. M. Cliff. "Aircraft Cruise Performance Optimization using Chattering Controls." IFAC Proceedings Volumes 20, no. 5 (July 1987): 175–80. http://dx.doi.org/10.1016/s1474-6670(17)55082-x.

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Stevens, B. L., F. L. Lewis, and F. Al-Sunni. "Aircraft flight controls design using output feedback." Journal of Guidance, Control, and Dynamics 15, no. 1 (January 1992): 238–46. http://dx.doi.org/10.2514/3.20824.

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Greshnikov, I. I. "Gaze Control Function Implementation in the Aircraft Cockpit Displays and Controls." INFORMACIONNYE TEHNOLOGII 27, no. 8 (August 11, 2021): 445–48. http://dx.doi.org/10.17587/it.27.445-448.

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The paper analyzes modern solutions applicable to advanced cockpit development using the gaze control function. Based on the analysis, the conclusion is made about the practicability of using the gaze control function and the intelligent information system is being developed for testing this function on the basis of universal cockpit prototyping bench.
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Ochi, Y. "Flight Control System Design for Propulsion-Controlled Aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 4 (April 1, 2005): 329–40. http://dx.doi.org/10.1243/095441005x30289.

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The loss of an aircraft's primary flight controls can lead to a fatal accident. However, if the engine thrust is available, controllability and safety can be retained. This article describes flight control using engine thrust only when an aircraft has lost all primary flight controls. This is a kind of flight control reconfiguration. For safe return, the aircraft must first descend to a landing area, decelerate to a landing speed, and then be capable of precise flight control for approach and landing. For these purposes, two kinds of controllers are required: a controller for descent and deceleration and a controller for approach and landing. The former controller is designed for longitudinal motion using a model-following control method, based on a linear quadratic regulator. The latter is designed by an H∞ state-feedback control method for both longitudinal and lateral-directional motions. Computer simulation is conducted using linear models of the Boeing 747. The results indicate that flight path control, including approach and landing, is possible using thrust only; however, speed control proves more difficult. However, if the horizontal stabilizer is available, the airspeed can be reduced to a safe landing speed.
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Dissertations / Theses on the topic "Aircraft controls"

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Montalvo, Carlos. "Meta aircraft flight dynamics and controls." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/51854.

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The field of mobile robotic systems has become a rich area of research and design. These systems can navigate difficult terrain using multiple actuators with conventional ambulation, by hopping, jumping, or for aerial vehicles, using flapping wings, propellers, or engines to maintain aerial flight. Unmanned Aerial Systems(UAS) have been used extensively in both military and civilian applications such as reconnaissance or search and rescue missions. For air vehicles, range and endurance is a crucial design parameter as it governs which missions can be performed by a particular vehicle. In addition, when considering the presence of external disturbances such as atmospheric winds, these missions can be even more challenging. Meta aircraft technologies is one area of research that can increase range and endurance by taking advantage of an increase in L/D. A meta aircraft is an aircraft composed of smaller individual aircraft connected together through a similar connection mechanism that can potentially transfer power, loads, or information. This dissertation examines meta aircraft flight dynamics and controls for a variety of different configurations. First, the dynamics of meta aircraft systems are explored with a focus on the changes in fundamental aircraft modes and flexible modes of the system. Specifically, when aircraft are connected, the fundamental modes change, can become overdamped or even unstable. In addition, connected aircraft exhibit complex flexible modes and mode shapes that change based on the parameters of the connection joint and the number of connected aircraft. Second, the connection dynamics are explored for meta aircraft where the vehicles are connected wing tip to wing tip using passive magnets with a particular focus on modeling the connection event between aircraft in a practical environment. It is found that a multi-stage connection control law with position and velocity feedback from GPS and connection point image feedback from a camera yields adequate connection performance in the presence of realistic sensor errors and atmospheric winds. Furthermore, atmosphericwinds with low frequency gusts at the intensity normally found in a realistic environment pose the most significant threat to the success of connection. The frequency content of the atmospheric disturbance is an important variable to determine success of connection. Finally, the geometry of magnets that create the connection force field can alter connection rates. Finally, the performance of a generic meta aircraft system are explored. Using a simplified rigid body model to approximate any meta aircraft configuration, adequate connection is achieved in the presence of realistic winds. Using this controller overall performance is studied. In winds, there is an overall decrease in outer loop performance for meta aircraft. However, inner loop performance increases for meta aircraft. In addition, the aerodynamic benefit of different configurations are investigated. Wing to wing tip connected flight provides the most benefit in terms of average increased Lift to Drag ratio while tip to tail configurations drop the Lift to Drag ratio as trailing aircraft fly in the downwash of the leading aircraft.
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Bhardwaj, Pradeep. "Aircraft cruise performance optimization using chattering controls." Thesis, Virginia Tech, 1986. http://hdl.handle.net/10919/45750.

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Aircraft Cruise Performance is examined by using energy-state modelling to investigate fuel-range optimal trajectories. Chattering controls are considered appropriate when the hodograph is non-convex. Classical steady-state cruise, simple chattering-cruise and the extended chattering-cruise models are studied as constrained parameter-optimization problems. The term "extended chattering" refers to vehicle system modelling extended to maintain vertical equilibrium only on the average. Numerical solution is obtained using a variable-metric gradient-protection algorithm and computational results are presented for three different aircraft. This study shows that simple chattering cruise for certain specific energies can result in substantial fuel savings over classical steady-state cruise. However extended chattering cruise results in only marginal fuel savings when compared to simple chattering cruise.
Master of Science
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Cadwell, John Andres Jr. "Control of Longitudinal Pitch Rate as Aircraft Center of Gravity Changes." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/426.

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In order for an aircraft to remain in stable flight, the center of gravity (CG) of an aircraft must be located in front of the center of lift (CL). As the center of gravity moves rearward, pitch stability decreases and the sensitivity to control input increases. This increase in sensitivity is known as pitch gain variance. Minimizing the pitch gain variance results in an aircraft with consistent handling characteristics across a broad range of center of gravity locations. This thesis focuses on the development and testing of an open loop computer simulation model and a closed loop control system to minimize pitch axis gain variation as center of gravity changes. DATCOM and MatLab are used to generate the open loop aircraft flight model; then a closed loop PD (proportional-derivate) controller is designed based on Ziegler-Nichols closed loop tuning methods. Computer simulation results show that the open loop control system exhibited unacceptable pitch gain variance, and that the closed loop control system not only minimizes gain variance, but also stabilizes the aircraft in all test cases. The controller is also implemented in a Scorpio Miss 2 radio controlled aircraft using an onboard microprocessor. Flight testing shows that performance is satisfactory.
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Ur, Rahman Naveed. "Propulsion and flight controls integration for the blended wing body aircraft." Thesis, Cranfield University, 2009. http://hdl.handle.net/1826/4095.

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The Blended Wing Body (BWB) aircraft offers a number of aerodynamic perfor- mance advantages when compared with conventional configurations. However, while operating at low airspeeds with nominal static margins, the controls on the BWB aircraft begin to saturate and the dynamic performance gets sluggish. Augmenta- tion of aerodynamic controls with the propulsion system is therefore considered in this research. Two aspects were of interest, namely thrust vectoring (TVC) and flap blowing. An aerodynamic model for the BWB aircraft with blown flap effects was formulated using empirical and vortex lattice methods and then integrated with a three spool Trent 500 turbofan engine model. The objectives were to estimate the effect of vectored thrust and engine bleed on its performance and to ascertain the corresponding gains in aerodynamic control effectiveness. To enhance control effectiveness, both internally and external blown flaps were sim- ulated. For a full span internally blown flap (IBF) arrangement using IPC flow, the amount of bleed mass flow and consequently the achievable blowing coefficients are limited. For IBF, the pitch control effectiveness was shown to increase by 18% at low airspeeds. The associated detoriation in engine performance due to compressor bleed could be avoided either by bleeding the compressor at an earlier station along its ax- ial length or matching the engine for permanent bleed extraction. For an externally blown flap (EBF) arrangement using bypass air, high blowing coefficients are shown to be achieved at 100% Fan RPM. This results in a 44% increase in pitch control authority at landing and take-off speeds. The main benefit occurs at take-off, where both TVC and flap blowing help in achieving early pitch rotation, reducing take-off field lengths and lift-off speeds considerably. With central flap blowing and a lim- ited TVC of 10◦, the lift-off range reduces by 48% and lift-off velocity by almost 26%. For the lateral-directional axis it was shown that both aileron and rudder control powers can be almost doubled at a blowing coefficient of Cu = 0.2. Increased roll authority greatly helps in achieving better roll response at low speeds, whereas the increased rudder power helps in maintaining flight path in presence of asymmetric thrust or engine failure, otherwise not possible using the conventional winglet rudder.
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Nelson, Mark David. "A Comparison of Two Methods Used to Deal with Saturation of Multiple, Redundant Aircraft Control Effectors." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/34673.

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A comparison of two methods to deal with allocating controls for unattainable moments in an aircraft was performed using a testbed airframe that resembled an F/A-18 with a large control effector suite. The method of preserving the desired moment direction to deal with unattainable moments is currently used in a specific control allocator. A new method of prioritizing the pitch axis is compared to the moment-direction preservation. Realtime piloted simulations are completed to evaluate the characteristics and performance of these methods. A direct comparison between the method of preserving the moment direction by scaling the control solution vector and prioritizing the pitching moment axis is performed for a specific case. Representative maneuvers are flown with a highly unstable airframe to evaluate the ability to achieve the specific task. Flight performance and pilot interpretation are used to evaluate the two methods. Pilot comments and performance results favored the method of pitch-axis prioritization. This method provided favorable flight characteristics compared to the alternative method of preserving the moment direction for the specific tasks detailed in this paper. NOTE: An updated copy of this ETD was added on 09/28/2010.
Master of Science
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Johnson, Bruce, and John Smith. "CAN BUS USED FOR DATA ACQUISITION SYSTEM CONTROLS (AUTOMOTIVE SOLUTION FOR AIRCRAFT PROBLEM)." International Foundation for Telemetering, 2005. http://hdl.handle.net/10150/604882.

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ITC/USA 2005 Conference Proceedings / The Forty-First Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2005 / Riviera Hotel & Convention Center, Las Vegas, Nevada
This paper discusses using the CAN (Control Area Network) Bus protocol for control and status of flight test data acquisition systems. The application of the CAN (Control Area Network) on an F/A-18 aircraft will be discussed in detail.
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ALONSO, ELENA. "CONTROL DESIGN AND IMPLEMENTATION FOR THE SELF-SEPARATION OF IN-TRAIL AIRCRAFT." University of Cincinnati / OhioLINK, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1116261083.

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Schmollgruber, Peter. "Enhancement of the conceptual aircraft design process through certification constraints management and full mission simulations." Thesis, Toulouse, ISAE, 2018. http://www.theses.fr/2018ESAE0036.

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La conception d'un nouvel avion est initiée durant la phase avant-projet. Dans un premier temps, lesconcepteurs d’aéronefs identifient un ensemble de concepts potentiels pouvant répondre aux exigencesdu client en s’appuyant sur des informations fournies par les spécialistes disciplinaires et expertssystème. Ensuite, les solutions sont évaluées via un processus de dimensionnement basé sur uneanalyse multidisciplinaire. Dans le domaine des avions de transport civil, les objectifs ambitieux entermes de consommation de carburant amènent à étudier des configurations innovantes incluant denouvelles technologies. Cependant, peu de données sur de telles architectures sont disponibles dans lesphases amont de la conception. Ainsi, afin d'éviter une sélection ou élimination erronée d'unesolution, un objectif clé de la recherche en conception d'aéronefs est l’ajout de connaissances dansl'analyse multidisciplinaire.Aujourd’hui, cet objectif est atteint avec différentes approches: application d’optimisationsmultidisciplinaires, ajout de précision grâce aux analyses haute fidélité, introduction de nouvellesdisciplines ou systèmes et enfin, gestion de l'incertitude. Le rôle du concepteur est alors de combinerces options dans un processus de conception multidisciplinaire afin de converger vers le concept leplus performant tout en répondant aux contraintes de certification. Afin d’illustrer ce processus,l’optimisation d'un avion de transport avec assistance au sol pour le décollage qui a mis en évidencel'impact des contraintes de certification sur la conception du véhicule a été effectuée. La revuesuccessive des textes réglementaires et de recherches associées de la gestion du trafic aérien ont concluà la nécessité d’inclure des simulations au sein de l’analyse multidisciplinaire. Tenant compte de cesconclusions, la recherche effectuée dans le cadre de cette thèse propose alors d’ajouter desconnaissances en développant l’analyse et l’optimisation de la conception multidisciplinaire avec unnouveau module de contrainte de certification et des fonctionnalités de simulation complètes.Développé dans le cadre de la thèse, le module de contraintes de certification (CCM) a été utilisé pourrésoudre quatre problèmes d’optimisation associés à un avion de transport civil classique basé surl’outil de dimensionnement ONERA / ISAE-SUPAERO appelé FAST. Grâce à l'interface utilisateurdu CCM, un gain de temps au niveau de la mise en place de ces optimisations a constaté. De plus, lesrésultats ont confirmé la nécessité de définir au mieux et dès que possible les contraintes decertification.Pour atteindre des capacités de simulation complètes, l'analyse multidisciplinaire au sein de FAST aété améliorée. Premièrement, l'outil d'analyse aérodynamique a été modifié afin de générer la base dedonnées complète pour alimenter un modèle à 6 degrés de liberté. Ensuite, un nouveau module decalcul des propriétés d'inertie a été ajouté. Enfin, le simulateur open source JSBSim a été utilisé avecdifférentes lois de contrôle pour augmenter la stabilité et permettre la navigation automatisée. Lacomparaison entre les trajectoires de vol obtenues avec FAST et les données réelles sur les avionsenregistrées avec une antenne ADS-B a confirmé la validité de l'approche
The design of a new aircraft is initiated at the conceptual design phase. In an initial step, aircraftdesigners, disciplinary and subsystems experts identify a set of potential concepts that could fulfill thecustomer requirements. To select the most promising candidates, aircraft designers carry out the sizingprocess through a Multidisciplinary Design Analysis. Nowadays, in the field of civil transport aircraft,environmental constraints set challenging goals in terms of fuel consumption for the next generationsof airplanes. With the “tube and wing” configuration offering low expectations on furtherimprovements, disruptive vehicle concepts including new technologies are investigated. However,little information on such architectures is available in the early phases of the design process. Thus, inorder to avoid mistakenly selecting or eliminating a wrong concept, a key objective in Aircraft Designresearch is to add knowledge in the Multidisciplinary Design Analysis.Nowadays, this objective is achieved with different approaches: implementation of MultidisciplinaryDesign Optimization, addition of accuracy through high fidelity analyses, introduction of newdisciplines or systems and uncertainty management. The role of the aircraft designer is then tocombine these options in a multidisciplinary design process to converge to the most promising conceptmeeting certification constraints. To illustrate this process, the optimization of a transport aircraftfeaturing ground based assistance has been performed. Using monolithic optimization architecture andadvanced structural models for the wing and fuselage, this study emphasized the impact ofcertification constraints on final results. Further review of the regulatory texts concluded that aircraftsimulation capabilities are needed to assess some requirements. The same need has been identified inthe field of Air Traffic Management that provides constraints for aircraft operations. This researchproposes then to add knowledge through an expansion of the Multidisciplinary Design Analysis andOptimization with a new Certification Constraint Module and full simulation capabilities.Following the development of the Certification Constraint Module (CCM), its capabilities have beenused to perform four optimization problems associated to a conventional civil transport aircraft basedon the ONERA / ISAE-SUPAERO sizing tool called FAST. Facilitated by the Graphical UserInterface of the CCM, the setup time of these optimizations has been reduced and the results clearlyconfirmed the necessity to consider certification constraints very early in the design process in order toselect the most promising concepts.To achieve full simulation capabilities, the multidisciplinary analysis within FAST had to beenhanced. First, the aerodynamics analysis tool has been modified so that necessary coefficients for a6 Degrees-of-Freedom model could be generated. Second, a new module computing inertia propertieshas been added. Last, the open source simulator JSBSim has been used including different controllaws for stability augmentation and automated navigation. The comparison between flight trajectoriesobtained with FAST and real aircraft data recorded with ADS-B antenna confirmed the validity of theapproach
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Ledet, Jeffrey H. "Simulation and Performance Evaluation of Algorithms for Unmanned Aircraft Conflict Detection and Resolution." ScholarWorks@UNO, 2016. http://scholarworks.uno.edu/td/2168.

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The problem of aircraft conflict detection and resolution (CDR) in uncertainty is addressed in this thesis. The main goal in CDR is to provide safety for the aircraft while minimizing their fuel consumption and flight delays. In reality, a high degree of uncertainty can exist in certain aircraft-aircraft encounters especially in cases where aircraft do not have the capabilities to communicate with each other. Through the use of a probabilistic approach and a multiple model (MM) trajectory information processing framework, this uncertainty can be effectively handled. For conflict detection, a randomized Monte Carlo (MC) algorithm is used to accurately detect conflicts, and, if a conflict is detected, a conflict resolution algorithm is run that utilizes a sequential list Viterbi algorithm. This thesis presents the MM CDR method and a comprehensive MC simulation and performance evaluation study that demonstrates its capabilities and efficiency.
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Hejkalová, Anna. "Návrh UL letounu pro piloty s pohybovým omezením." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417581.

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The diploma thesis deals with the issue of operating aircrafts by people with physical disabi-lities. Firstly, it formulates medical eligibility requirements for pilots with mobility restricti-ons. Because there is a large number of movement restrictions and each of them is very indi-vidual, an adaptation for only one of these categories was chosen for the conceptual design of the aircraft in this diploma thesis: limitation of the lower half of the body. The aircraft is designed to best meet the needs of pilots with this limitation of movement, with emphasis on ergonomics, the possibility of independent use without any help of other people and espe-cially on the safety of the user. Furthermore, the work examines possibilities of adjusting the control of aircraft for the disabled, tries to choose the most suitable one which is then desci-bed. In the end, an examination of the UL2 regulation requirements for the designed aircraft is done.
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Books on the topic "Aircraft controls"

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Delp, Frank. Aircraft propellers and controls. Casper, WY: IAP, Inc., 1992.

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Stevens, Brian L., Frank L. Lewis, and Eric N. Johnson. Aircraft Control and Simulation: Dynamics, Controls Design, and Autonomous Systems. Hoboken, NJ, USA: John Wiley & Sons, Inc, 2015. http://dx.doi.org/10.1002/9781119174882.

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Jaw, Link C. Aircraft engine controls: Design, system analysis, and health monitoring. Reston, VA: American Institute of Aeronautics and Astronautics, 2009.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Aerodynamics of combat aircraft controls and of ground effects. Neuilly sur Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Aerodynamics of combat aircraft controls and of ground effects. Neuilly-sur-Seine: AGARD, 1990.

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FEDERAL AVIATION ADMINISTRATION. Quality assurance controls for product acceptance software. [Washington, D.C.] (800 Independence Ave., S.W., Washington 20591): U.S. Dept. of Transportation, Federal Aviation Administration, 1993.

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Biezad, Daniel J. Controls design with crossfeeds for hovering rotcract using quantitative feedback theory. [Washington, DC: National Aeronautics and Space Administration, 1994.

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Biezad, Daniel J. Controls design with crossfeeds for hovering rotorcraft using quantitative feedback theory. [Washington, DC: National Aeronautics and Space Administration, 1994.

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United States. President (1989-1993 : Bush). Veto--Senate Joint Resolution 113: Message from the President of the United States returning without my approval Senate Joint Resolution 113, a joint resolution that would prohibit the export of certain technology, defense articles, and defense services in connection with the codevelopment and coproduction of the FS-X aircraft with Japan. Washington: U.S. G.P.O., 1989.

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United States. President (1989-1993 : Bush). Veto--Senate Joint Resolution 113: Message from the President of the United States returning without my approval Senate Joint Resolution 113, a joint resolution that would prohibit the export of certain technology, defense articles, and defense services in connection with the codevelopment and coproduction of the FS-X aircraft with Japan. Washington: U.S. G.P.O., 1989.

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Book chapters on the topic "Aircraft controls"

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Bailey, P. G., and J. M. Whalen. "Shot Peen Controls and Aircraft Engine Requirements." In Surface Engineering, 379–85. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0773-7_39.

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Li, Fei, Kaiwen Chen, Yuan Wang, and Pu Hong. "Human Factors Evaluation Principals for Civil Aircraft Flight Deck Controls Design and Integration." In Lecture Notes in Computer Science, 156–65. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-60114-0_11.

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Kaufman, Louis G., and Charles B. Johnson. "An Overview of some Investigations of Pressure and Thermal Distributions Induced by Trailing Edge Controls on Hypersonic Aircraft." In Turbulent Shear-Layer/Shock-Wave Interactions, 407–18. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-642-82770-9_32.

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Enns, Dale. "Aircraft Flight Control." In Encyclopedia of Systems and Control, 33–39. London: Springer London, 2015. http://dx.doi.org/10.1007/978-1-4471-5058-9_20.

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Enns, Dale. "Aircraft Flight Control." In Encyclopedia of Systems and Control, 1–8. London: Springer London, 2014. http://dx.doi.org/10.1007/978-1-4471-5102-9_20-1.

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L’Afflitto, Andrea. "Aircraft Automatic Control." In A Mathematical Perspective on Flight Dynamics and Control, 65–87. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-47467-0_3.

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Paluszek, Michael, and Stephanie Thomas. "Neural Aircraft Control." In MATLAB Machine Learning Recipes, 231–64. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-3916-2_11.

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Enns, Dale. "Aircraft Flight Control." In Encyclopedia of Systems and Control, 59–64. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-44184-5_20.

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Girgis, Sabry F. "Structural Control of Aircraft." In Structural Control, 235–49. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3525-9_17.

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Miotto, Piero, Leena Singh, James D. Paduano, Andrew Clare, Mary L. Cummings, and Lesley A. Weitz. "Aircraft Autonomy." In Advances in Control System Technology for Aerospace Applications, 81–107. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-47694-9_3.

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Conference papers on the topic "Aircraft controls"

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Lindberg, Rickard, and Per Fredin. "Identification of fighter aircraft." In Aerospace/Defense Sensing and Controls, edited by Ivan Kadar. SPIE, 1998. http://dx.doi.org/10.1117/12.327100.

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Flint, John R. "System design and aircraft integration." In Aerospace/Defense Sensing and Controls, edited by Ronald J. Lewandowski, Loran A. Haworth, Wendell Stephens, and Henry J. Girolamo. SPIE, 1996. http://dx.doi.org/10.1117/12.241887.

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Mcnally, Patrick J. "Functional Digital Aircraft: Designing Flight Controls." In General Aviation Technology Conference & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2002. http://dx.doi.org/10.4271/2002-01-1512.

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Overstreet, Mark A., and Robert F. Hoskin. "Fiber Optics for Aircraft Engine Controls." In 1988 American Control Conference. IEEE, 1988. http://dx.doi.org/10.23919/acc.1988.4790023.

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Ahmad, Hammad, Trevor Young, Daniel Toal, and Edin Omerdic. "Control Allocation with Actuator Dynamics for Aircraft Flight Controls." In 7th AIAA ATIO Conf, 2nd CEIAT Int'l Conf on Innov and Integr in Aero Sciences,17th LTA Systems Tech Conf; followed by 2nd TEOS Forum. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-7828.

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Walker, Gregory W. "Application of cognitive controls for unmanned aircraft." In Aerospace/Defense Sensing and Controls, edited by Scott A. Speigle. SPIE, 1996. http://dx.doi.org/10.1117/12.241091.

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Wisely, Paul L., and Christopher T. Bartlett. "Head-up display for air transport aircraft." In Aerospace/Defense Sensing and Controls, edited by Darrel G. Hopper. SPIE, 1998. http://dx.doi.org/10.1117/12.321809.

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Craig, David M. "Application of AMLCDs to military aircraft displays." In Aerospace/Defense Sensing and Controls, edited by Darrel G. Hopper. SPIE, 1998. http://dx.doi.org/10.1117/12.321812.

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Dal Toe, S., Paolo G. Bison, Sergio Marinetti, and Ermanno G. Grinzato. "Thermal investigation of real aircraft components." In Aerospace/Defense Sensing, Simulation, and Controls, edited by Andres E. Rozlosnik and Ralph B. Dinwiddie. SPIE, 2001. http://dx.doi.org/10.1117/12.421045.

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Desjardins, Daniel D., and Darrel G. Hopper. "Military display market segment: aircraft cockpits." In Aerospace/Defense Sensing, Simulation, and Controls, edited by Darrel G. Hopper. SPIE, 2001. http://dx.doi.org/10.1117/12.439136.

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Reports on the topic "Aircraft controls"

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Buffington, James M. Tailless Aircraft Control Allocation. Fort Belvoir, VA: Defense Technical Information Center, May 1997. http://dx.doi.org/10.21236/ada327799.

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Wise, Kevin A., Jack L. Sedwick, and Yutaka Ikeda. Nonlinear Control of Fighter Aircraft. Fort Belvoir, VA: Defense Technical Information Center, June 1999. http://dx.doi.org/10.21236/ada386935.

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Teel, Andrew R. Robust Nonlinear Control of Tailless Aircraft. Fort Belvoir, VA: Defense Technical Information Center, February 1999. http://dx.doi.org/10.21236/ada367415.

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Teel, Andrew R. Robust Nonlinear Control of Tailless Fighter Aircraft. Fort Belvoir, VA: Defense Technical Information Center, February 1999. http://dx.doi.org/10.21236/ada367012.

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Hill, R. D. A Survey of Aircraft Integrated Control Technology. Fort Belvoir, VA: Defense Technical Information Center, September 1987. http://dx.doi.org/10.21236/ada186949.

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Williams, David R. Closed-Loop Control of Acoustic Tones in Aircraft Cavities. Fort Belvoir, VA: Defense Technical Information Center, February 2002. http://dx.doi.org/10.21236/ada400135.

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Callaway, Steven P. Aircraft Enroute Command and Control Comms Redesign Mechanical Documentation. Fort Belvoir, VA: Defense Technical Information Center, November 2015. http://dx.doi.org/10.21236/ad1000591.

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Viswanathan, Sivaswamy, and Allen Charkey. Aircraft Battery State of Charge and Charge Control System. Fort Belvoir, VA: Defense Technical Information Center, January 1988. http://dx.doi.org/10.21236/ada194979.

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Viswanathan, Sivaswamy, and Allen Charkey. Aircraft Battery State of Charge and Charge Control System. Fort Belvoir, VA: Defense Technical Information Center, February 1986. http://dx.doi.org/10.21236/ada169411.

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Buffington, James. Modular Control Design for the Innovative Control Effectors (ICE) Tailless Fighter Aircraft Configuration 101-3. Fort Belvoir, VA: Defense Technical Information Center, June 1999. http://dx.doi.org/10.21236/ada375713.

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