Relevant bibliographies by topics / Fly-by-wire primary flight control

Academic literature on the topic 'Fly-by-wire primary flight control'

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Published: 14 March 2023

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Journal articles on the topic "Fly-by-wire primary flight control"

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McLean, D. "Aircraft flight control systems." Aeronautical Journal 103, no. 1021 (March 1999): 159–66. http://dx.doi.org/10.1017/s0001924000064976.

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Abstract This paper presents a short account of the flight control systems used in commercial transport, military combat and general aviation aircraft. The effects of aircraft safety, reliability and weather delays on satisfactory aircraft operations are shown to be significant reasons for the extensive use of flight control systems. The principles of flight control, the sensors and actuators required and the various modes which can be selected are treated, together with a short account of the primary flying controls and the use of manual reversion in emergency situations. The paper concludes with a consideration of the fly-by-wire (FBW) and fly-fby-light concepts, and covers relaxed static stability, carefree manoeuvring and the use of canards before discussing some FBW flight control systems which are used in passenger aircraft.
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Di Rito, G., and R. Galatolo. "Experimental assessment of the dynamic stiffness of a fault-tolerant fly-by-wire hydraulic actuator." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, no. 6 (June 2012): 679–90. http://dx.doi.org/10.1177/0954410011413986.

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The stiffness of an actuator depends on the closed-loop position control (architecture and parameters), on the load frequency, and, for fault-tolerant actuators, on the operative mode. The stiffness response is of basic importance for the design of actuators for primary flight controls, especially for high-performance aircrafts. Actually, during flight conditions characterized by high speed and high angle-of-attack, the dynamic interactions between aircraft structure, actuator, and aerodynamic loads can induce aeroservoelastic effects, which, if not controlled, can imply performance degradation and even instability. The study and the compensation of such concerns require the assessment of the resonant frequencies of the aeroservoelastic system, which can be performed only by characterizing the dynamic stiffness of the actuator. This article reports the experimental activities carried out for the characterization of the stiffness response of a fault-tolerant fly-by-wire actuator for the primary flight controls of a modern jet trainer, starting from the feasibility studies of the experiments up to the execution of the vibration tests. The actuator stiffness performance is evaluated in different fail-operative modes by artificially injecting hydraulic and electrical failures, and the experimental data are interpreted by means of an LTI model of the flight actuator, highlighting and discussing the effects that the failures induce on the stiffness performance.
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Wang, Xiao-Hui, Wei-Qian Yu, Chen-Bo Gu, and Yi Jiang. "PFCS Four-redundant Sidestick Randomly Dynamically Grouping Vote Technology." Journal of Physics: Conference Series 2281, no. 1 (June 1, 2022): 012016. http://dx.doi.org/10.1088/1742-6596/2281/1/012016.

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Abstract For civil aircraft, the reliability of control device sensors in flight control system is very important for aircraft control and safe flight. Redundancy signal voting and monitoring technology can improve the availability and integrity of sensor signals in fly by wire primary flight control system of civil aircraft. In this paper, a simplified four-redundant signal voting and monitoring method is proposed which randomly and dynamically divides the four redundant signals into two groups for comparison. The safety analysis and simulation results reveal that this simplified method meets the safety requirements and has advantages in robustness and availability.
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Permenter, Kathryn E., and Clifford C. Baker. "Task-Operator Study for the Primary Flight Control Center of Tarawa Class (LHA) Ships." Proceedings of the Human Factors Society Annual Meeting 33, no. 16 (October 1989): 1119–23. http://dx.doi.org/10.1177/154193128903301618.

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This report presents the findings of a Task-Operator study for the Primary Flight Control (Pri-Fly) major operating stations aboard Tarawa class (LHA) ships. The LHA carries a variety of attack and cargo helicopters, plus AV-8A Sea Harrier jet aircraft. Pri-Fly is the area of the ship which controls the landing and recovery of aircraft, as well as flight control when aircraft are in the immediate vicinity of the ship. Two main positions were examined by this study, the Air Administrator (Air-Boss) and the Assistant Air Administrator (Mini-Boss). The purposes of this study were to perform a task-operator study of Pri-Fly personnel task requirements, to identify human-equipment interface design problems given the existing configuration of Pri-Fly within LHAs, and to provide general design recommendations based on the findings of the study. Seven tasks were undertaken to meet the objectives of the project. Overall, the review identified numerous human engineering design problems in Pri-Fly, many of which severely limit the performance of Pri-Fly personnel. Based on this review, it is asserted that significant improvement can be realized, in terms of air operations safety and efficiency, by instituting a Pri-Fly improvement program.
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Muthard, Emily K. "The Contaminating Influence of Display Size on Flight Control, Risk Assessment, and Route Selection." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 49, no. 1 (September 2005): 73–77. http://dx.doi.org/10.1177/154193120504900117.

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The present experiment was designed to examine the effect of display size on distance estimates used for flight control and in assessing risk for route selection. Sixteen pilots were asked to select and fly along a route using integrated hazard and primary flight displays. Display size was manipulated by altering the physical size of a two-dimensional display and through axis compression in a three-dimensional display. Display minification resulted in poorer flight control. When the display was enlarged, pilots were found to overestimate the distance from the flight path to impending hazards and subsequently choose riskier routes. Pilots also exhibited greater confidence in their route choices with the large display, even though their choices were more dangerous. Results suggest that display size must be considered when designing displays for spatial tasks.
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Crowder, R., and C. Maxwell. "Simulation of a prototype electrically powered integrated actuator for civil aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 6 (June 1, 1997): 381–94. http://dx.doi.org/10.1243/0954410971532749.

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Developments in the design and proposed operation of large civil aircraft have resulted in aircraft manufacturers and equipment suppliers developing new system concepts, one of which is the all or more electric aircraft. In the all or more electric aircraft the distribution of power for flight actuation will be through the electrical system, as opposed to the currently used bulk hydraulic system. In order to implement power-by-wire, high-performance electrically powered actuators will be required. The paper discusses the design details, and the simulation of an electrohydrostatic actuator suitable for use in primary flight control systems of a civil aircraft. The paper presents experimental and simulation results, and identifies the parameters that will critically affect the performance of an actuator.
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Collinson, R. P. G. "Fly-by-wire flight control." Computing & Control Engineering Journal 10, no. 4 (August 1, 1999): 141–52. http://dx.doi.org/10.1049/cce:19990403.

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Kuenen, L. P. S., and P. J. Silk. "Sex-biased trap capture and odor-stimulated upwind flight in the field by Rhagoletis mendax (Diptera: Tephritidae)." Canadian Entomologist 133, no. 2 (April 2001): 293–95. http://dx.doi.org/10.4039/ent133293-2.

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The bluebeny maggot, Rhagoletis mendax Curran, is a primary insect pest of low bush blueberries, Vaccinium angustifolium Ait. (Ericaceae), in eastern Canada. Eggs are laid in ripening berries and mature larvae emerge from the berries to pupate in the soil. Adult flies can be controlled with insecticides (Wood et al. 1983) and (or) cultural control by bum or flail-mow pruning of bushes. Pruned plants do not bear fruit the season after pruning, and this rotation of fruit and nonfruit years is believed to reduce fly populations by limiting food availability (Lathrop 1952). Adult flies can be monitored by capture on yellow-panel sticky traps or red-sphere traps (Prokopy and Coli 1978; Wood et al. 1983; Neilson et al. 1984). In this study, we focused on the sex ratio of R. mendax flies captured on baited and unbaited yellow-panel sticky traps (Pheroco® AM traps) and on the orientation behavior of flies toward wind-vane traps.
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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "The fly-by-wire system." INCAS BULLETIN 11, no. 4 (December 8, 2019): 217–22. http://dx.doi.org/10.13111/2066-8201.2019.11.4.19.

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This report shows the execution and evolution of airplane flight control systems. The report describes the development of airplane flight control systems and gives a survey of the principal phases of the flight control systems that assure the finding and execution of the fly-by-wire system. The development of flight control systems, from human control with mechanical links to a wire-driven computer, is a remarkable representation of the development of aeronautical technologies. The fly-by-wire system constitutes a fast-forwarding in aircraft design, from mechanical linkage to large hydraulic actuators to computer-assisted fly-by-wire system. The use of the fly-by-wire system has generated huge satisfaction for the aircraft industry by lessening the weight of the flight control system, by creating multiple redundancy flight control systems, which increases the flight safety of all aircraft equipped with the fly-by-wire system. The passage from analog to digital is another fast-forwarding in the development of fly-by-wire systems.
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Cranshaw, Whitney, and Matthew Camper. "Management of Poplar Twiggall Fly on Nursery-grown Aspen." Journal of Environmental Horticulture 25, no. 1 (March 1, 2007): 33–35. http://dx.doi.org/10.24266/0738-2898-25.1.33.

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Abstract The poplar twiggall fly (PTGF), Hexomyza schineri (Giraud) (Diptera: Agromyzidae), makes smoothly rounded galls on current season twigs of aspen that persist and continue to expand into large swellings years after insect emergence. Early season observations noted that adults make feeding puncture wounds in foliage with their ovipositor that are good indicators of early season activity. Oviposition in twigs results in an observable swelling of tissues within days. However, full development of galls does not occur until approximately two months following oviposition. Adults typically were active for a period of about two to three weeks subsequent to bud break and its primary parasitoid, the eurytomid Eurytoma contractura Bugbee, was trapped at the end of the PTGF flight period. Efforts to prevent adult emergence by painting galls two weeks prior to adult emergence with either sealants (shellac, polyurethane) or insecticides (imidacloprid, abamectin) did not reduce adult emergence. Soil drench treatments of imidacloprid prior to and immediately following bud break significantly reduced PTGF gall production. High rates of thiamethoxam also provided suppression of galling. Foliar applications tested were ineffective in control of gall production by this insect.
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Dissertations / Theses on the topic "Fly-by-wire primary flight control"

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MORNACCHI, ANDREA. "Design and development of prognostic and health management system for fly-by-wire primary flight control." Doctoral thesis, Politecnico di Torino, 2016. http://hdl.handle.net/11583/2651742.

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Electro-Hydraulic Servo Actuators (EHSA) is the principal technology used for primary flight control in new aircrafts and legacy platforms. The development of Prognostic and Health Management technologies and their application to EHSA systems is of great interest in both the aerospace industry and the air fleet operators. This Ph.D. thesis is the results of research activity focused on the development of a PHM system for servovalve of fly-by-wire primary flight EHSA. One of the key features of the research is the implementation of a PHM system without the addition of new sensors, taking advantage of sensing and information already available. This choice allows extending the PHM capability to the EHSAs of legacy platforms and not only to new aircrafts. The enabling technologies borrow from the area of Bayesian estimation theory and specifically particle filtering and the information acquired from EHSA during pre-flight check is processed by appropriate algorithms in order to obtain relevant features, detect the degradation and estimate the Remaining Useful Life (RUL). The results are evaluated through appropriate metrics in order to assess the performance and effectiveness of the implemented PHM system. The major objective of this contribution is to develop an innovative fault diagnosis and failure prognosis framework for critical aircraft components that integrates effectively mathematically rigorous and validated signal processing, feature extraction, diagnostic and prognostic algorithms with novel uncertainty representation and management tools in a platform that is computationally efficient and ready to be transitioned on-board an aircraft.
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GENTILE, ROCCO. "Advanced Diagnostic for Fly-By-Wire Flight Control Systems." Doctoral thesis, Politecnico di Torino, 2021. http://hdl.handle.net/11583/2934682.

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Gautrey, Jim. "Flying qualities and flight control system design for a fly-by-wire transport aircraft." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/9594.

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Fly-by-wire flight control systems are becoming more common in both civil and military aircraft. These systems give many benefits, but also present a new set of problems due to their increased complexity compared to conventional systems and the larger choice of options that they provide. The work presented here considers the application of fly-by-wire to a generic regional transport aircraft. The flying qualities criteria used for typical flying qualities evaluations are described briefly followed by analysis of several past transport aircraft flying qualities programmes against these criteria. From these results, some control law independent design requirements are formulated for a civil aircraft for the approach and landing task. These control law independent flying qualities criteria are intended to be used with any generic rate-like control law for a transport aircraft and enabled a number of different control laws to be designed. The results of a number of flying qualities evaluations are presented. Both an ILS approach task and a formation flying task were used. The effects of windshear were also considered. It was found that control laws which maintain flight path are suitable for the ILS approach task, while most rate-like response characteristics give good flying qualities for the formation flying task. Finally, the conclusions drawn from these evaluations are presented, and both the Civil and Military current airworthiness requirements are assessed. In addition to the flying qualities work, a study is made of the management issues associated with fly-by-wire design. A fly-by-wire aircraft design programme was proposed and the project management issues associated with this were considered. A timescale was proposed for the design process for a generic regional aircraft, and the critical path for this process is presented.
EPSRC; Avro International Aerospace.
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Cochoy, Olaf. "Investigations for the synchronized operation of a hybrid actuator configuration in redundant flight control systems." Aachen Shaker, 2009. http://d-nb.info/999024698/04.

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Griffin, Stuart James. "Helicopter control law design using eigenstructure assignment." Thesis, University of York, 1997. http://etheses.whiterose.ac.uk/21041/.

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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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Del, Gobbo Diego. "Formal specification of requirements for analytical redundancy based fault tolerant flight control systems." Morgantown, W. Va. : [West Virginia University Libraries], 2000. http://etd.wvu.edu/templates/showETD.cfm?recnum=1629.

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Thesis (Ph. D.)--West Virginia University, 2000.
Title from document title page. Document formatted into pages; contains ix, 185 p. : ill. Includes abstract. Includes bibliographical references (p. 87-91).
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Chandramohan, Rajeev. "Adaptive critic flight control for a general aviation aircraft: Simulations for the beech bonanza fly-by-wire testbed." Thesis, Wichita State University, 2007. http://hdl.handle.net/10057/1509.

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An adaptive and reconfigurable flight control system is developed for a general aviation aircraft. The flight control system consisting of two neural networks is developed using a two phase procedure called the pre-training phase and the online training phase. The adaptive critic method used in this thesis was developed by Ferrari and Stengel. In the pre-training phase the architecture and initial weights of the neural network are determined based on linear control. A set of local gains for the linearized model of the plant is obtained at different design points on the velocity v/s altitude envelope using an LQR method. The pre-training phase guarantees that the neural network controller meets the performance specifications of the linear controllers at the design points. Online training uses a dual heuristic adaptive critic architecture that trains the two networks to meet performance specifications in the presence of nonlinearities and control failures. The control system developed is implemented for a three-degree-of-freedom longitudinal aircraft simulation. As observed from the results the adaptive control system meets performance requirements, specified in terms of the damping ratio of the phugoid and short period modes, in the presence of nonlinearities. The neural network controller also compensates for partial elevator and thrust failures. It is also observed that the neural network controller meets the performance specification for large variations in the parameters of the assumed and actual models.
Thesis (M.S)--Wichita State University, College of Engineering, Dept. of Aerospace Engineering
"July 2007."
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Chandramohan, Rajeev Steck James E. "Adaptive critic flight control for a general aviation aircraft: Simulations for the beech bonanza fly-by-wire testbed /." Thesis, A link to full text of this thesis in SOAR, 2007. http://hdl.handle.net/10057/1509.

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Venter, Jeanne Marie. "Autonomous air-to-air refueling : a comparison of control strategies." Thesis, Stellenbosch : Stellenbosch University, 2012. http://hdl.handle.net/10019.1/20239.

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Thesis (MScEng)--Stellenbosch University, 2012.
ENGLISH ABSTRACT: The air-to-air refuelling of large aircraft presents challenges such as a long fuel transfer time, slow aircraft responses and a large distance between the aircraft CG and the receptacle position. This project addresses some of these issues by adding a control system to keep the receiver aircraft in the correct position relative to the tanker to enable fuel transfer. This project investigates different control strategies which are designed to control the A330-300 during refuelling at one trim condition. The controllers are based on a mathematical aircraft model which was derived from a simulation model received from Airbus. The first set of controllers uses the aircraft actuators directly. Controllers that are based on the CG dynamics and the receptacle dynamics are compared. Due to the large distance between the CG and the receptacle it was found to be essential to control the receptacle position, and not only the CG position. Also, a controller that is based on a model of the receptacle dynamics performs better. The second set of controllers uses the aircraft manual control laws as an inner loop controller. This set of controllers and the last direct actuator controller use the same axial controller that uses the engine thrust to control axial position. It was found that both the direct actuator controller and the manual control laws controller are able to keep the receptacle within the disconnect envelope in moderate turbulence. In both sets of controllers the axial controller fails to keep the receptacle reliably within the disconnect envelope in light turbulence. From the results it is concluded that both the direct actuator control and manual control laws can be used to successfully control the receptacle position in the normal and lateral positions as long as the receptacle kinematics are included in the control design. Using only the engine thrust for axial control is insufficient. Several recommendations are made to improve the axial control and also how these results can be used in future work.
AFRIKAANSE OPSOMMING: Die lug-tot-lug brandstof hervulling van groot vliegtuie het uitdagings soos ’n lang hervullingstyd, stadige vliegtuig dinamika en ’n groot afstand tussen die hervullingspoort en die vliegtuig massamiddelpunt. Hierdie projek spreek sommige van hierdie uitdagings aan deur ’n beheerstelsel by te voeg wat die vliegtuig in die korrekte posisie relatief tot die tenker hou vir brandstofoordrag om plaas te vind. Hierdie projek ondersoek verskillende beheerstrategieë wat ontwerp is om die A330- 300 te beheer by ’n enkele gestadigde toestand. Die beheerders is gebaseer op ’n wiskundige vliegtuigmodel wat vanaf ’n simulasiemodel afgelei is. Die simulasiemodel is vanaf Airbus verkry. Die eerste stel beheerders beheer direk die vliegtuig se beheeroppervlakke. Beheerders wat onderskeidelik die massamiddelpunt en die hervullingspoort beheer word vergelyk. Daar is gevind dat dit essensieel is om die hervullingspoort te beheer en nie slegs die massamiddelpunt nie, as gevolg van die groot afstand tussen hierdie twee punte. Die tweede stel beheerders gebruik die vliegtuig se eie beheerwette as ’n binnelusbeheerder en vorm self die buitelus. Albei stelle beheerders gebruik dieselfde aksiale beheerder wat enjin stukrag gebruik om die aksiale posisie te beheer. Daar is gevind dat beide stelle beheerders die hervullingspoort binne die ontkoppelingsbestek kan hou in die normale en laterale rigtings tydens matige turbulensie. In beide stelle beheerders is dit die aksiale beheerder wat faal om die hervullingspoort betroubaar in posisie te hou, selfs in ligte turbulensie. Vanaf die resultate word afgelei dat beide die direkte beheerder en die buitelusbeheerder gepas is om die laterale en normale posisiebeheer toe te pas mits die dinamika van die hervullingspoort in ag geneem word. Om slegs stukrag te gebruik vir aksiale beheer is nie voldoende nie, en verskeie voorstelle word gemaak om die aksiale beheer te verbeter in toekomstige navorsing.
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Books on the topic "Fly-by-wire primary flight control"

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Dian chuan fei xing kong zhi xi tong: Fly-by-wire flight control system. Beijing: Guo fang gong ye chu ban she, 2003.

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Gautrey, J. Flight control system architecture analysis and design for a fly-by-wire generic regional aircraft. Cranfield, Bedford, England: Cranfield University, College of Aeronautics, 1996.

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Droste, Carl S. A case study on the F-16 fly-by-wire flight control system. New York]: American Institute of Aeronautics and Astronautics, 1985.

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F, Wanamaker Michael, and United States. National Aeronautics and Space Administration., eds. Optical closed-loop flight control demonstration: Fly-by-Light Aircraft Closed Loop Test (FACT) Program and Fly-by-Light Installation and Test (FIT) Program : under contract NAS3-25965. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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F, Wanamaker Michael, and United States. National Aeronautics and Space Administration., eds. Optical closed-loop flight control demonstration: Fly-by-Light Aircraft Closed Loop Test (FACT) Program and Fly-by-Light Installation and Test (FIT) Program : under contract NAS3-25965. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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F, Wanamaker Michael, and United States. National Aeronautics and Space Administration., eds. Optical closed-loop flight control demonstration: Fly-by-Light Aircraft Closed Loop Test (FACT) Program and Fly-by-Light Installation and Test (FIT) Program : under contract NAS3-25965. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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Gibson, J. C. Development of a methodology for excellence in handling qualities design for fly by wire aircraft. Delft, Netherlands: Delft University Press, 1999.

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Tomayko, J. E. Computers take flight: A history of NASA's pioneering digital fly-by-wire project. Washington, D.C: NASA, 2000.

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Sundberg, Gale R. Civil air transport: A fresh look at power-by-wire and fly-by-light. [Washington, D.C.]: NASA, 1990.

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Fault tolerant flight control: A benchmark challenge. Berlin: Springer, 2010.

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Book chapters on the topic "Fly-by-wire primary flight control"

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Collinson, R. P. G. "Fly-by-wire flight control." In Introduction to Avionics, 119–76. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0007-6_4.

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Collinson, R. P. G. "Fly-by-Wire Flight Control." In Introduction to Avionics Systems, 179–253. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-0708-5_4.

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Collinson, R. P. G. "Fly-by-Wire Flight Control." In Introduction to Avionics Systems, 159–224. Boston, MA: Springer US, 2003. http://dx.doi.org/10.1007/978-1-4419-7466-2_4.

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Luo, Xin. "Research on Control Characteristics of Civil Aircraft Module Integration Fly by Wire Flight Control System." In Lecture Notes in Electrical Engineering, 345–54. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_35.

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Favre, C. "Fly-by-wire for commercial aircraft: the Airbus experience." In Advances in Aircraft Flight Control, 211–29. Routledge, 2018. http://dx.doi.org/10.1201/9781315136820-8.

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Nae, Cătălin, Ilie Nicolin, and Bogdan Adrian Nicolin. "Military Aircraft Flight Control." In Aeronautics - New Advances [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.105491.

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This chapter presents major stages in the evolution of military aircraft flight control systems. As the flight speed steadily increased, it was necessary to develop new flight control systems to replace the old pilot control with mechanical connections to the control surfaces. The first major step is the pilot with a side stick/rudder pedal or an autopilot, who sends commands converted to electrical signals to a flight control computer and, in turn, interprets and sends wired electrical commands to the electrohydraulic actuators of each control surface and receives electrical signals from the motion transducer of each control surface. This stage of development of aeronautical technologies has been called the fly-by-wire flight control system. The latest major step in the evolution of military aircraft flight control systems is the replacement of copper wires with the fiber-optic cables, which have a much lower weight and a much higher capacity to carry digital information (light or photons). The command imposed by the pilot with a side stick/rudder pedal or autopilot is converted into light signals to the flight control computer and to the electrical or electrohydraulic actuators of each control surface and receives light signals from the motion transducer of each control surface. The latest flight control system is called fly-by-light system.
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Conference papers on the topic "Fly-by-wire primary flight control"

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Ferrara, Davide, Giovanni Jacazio, Andrea Mornacchi, and Massimo Sorli. "Robust Mechatronic Actuation System for UAV Primary Flight Controls." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85339.

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The paper describes the initial results of a research activity aimed at developing a high integrity mechatronic system for UAVs primary flight controls able to ensure the necessary flight safety and to enhance the system availability by implementing appropriate prognostic functions. In this system a flight control surface is driven by two parallel rollerscrews, on their turn driven by brushless motors equipped with gearhead and clutch; the motors electric drives are controlled by dual redundant electronic units performing closed loop position control as a function of the commands received from the flight control computer. Provisions are taken in the motor drives to provide damping in the event of simultaneous failure of both actuators. The electronic units perform control, diagnosis and prognosis of the actuation system and mutually exchange data via a cross channel data link. System prognosis is made by dedicated algorithms processing the control and feedback signals obtained in flight and during preflight checks. As a whole, a smart mechatronic system is obtained providing high integrity control of an aerodynamic surface with dual mechanical link, dual power source and quadruplex control, similarly to a fly-by-wire hydraulic flight control. The paper first addresses the critical design issues associated with the electromechanical actuation of flight control surfaces, briefly reviews alternative solutions proposed for jam-tolerant electromechanical actuators, then outlines configuration, characteristics and performance of the mechatronic actuation system, and presents a summary of its behaviour under normal, degraded, fault developing and failure conditions.
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Ma, Carlton Y. "Fly-By-Wire Dual-Dual Flight Control Actuation System." In Aerospace Power Systems Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/981252.

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3

Lyle, B. S. "Reducing Complexity in Fly-By-Wire Flight Control Actuators." In A-6 Symposium Program Advanced Actuation, Controls, and Integration for Aerospace Vehicles. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1985. http://dx.doi.org/10.4271/851752.

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4

WALTER, CHRIS. "MAFT - An architecture for reliable fly-by-wire flight control." In Digital Avionics Systems Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3902.

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VIETEN, K. "High-performance fighter fly-by-wire flight control actuation system." In Aerospace Design Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1123.

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Tameh, Tahereh Ahmadi, Mohamad Sawan, and Raman Kashyap. "Fly-by-wire flight control smart optical rotary sensor for aircraft." In 2016 Photonics North (PN). IEEE, 2016. http://dx.doi.org/10.1109/pn.2016.7537895.

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Xue, Ying, Zhenqiang Yao, and Wei Niu. "The Distributed Dissimilar Redundancy Architecture of Fly-by-Wire Flight Control System." In 2016 12th International Conference on Computational Intelligence and Security (CIS). IEEE, 2016. http://dx.doi.org/10.1109/cis.2016.0072.

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8

Shetty, Devdas, and Louis Manzione. "Unmanned Aerial Vehicles (UAV): Design Trends." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-64518.

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This paper looks at the trends in design procedures in Unmanned Aerial Vehicles (UAVs). Rapid advances in technology are enabling more and more capability to be placed on smaller airframes which is spurring a large increase in the number of UAVs being deployed in the army. The military role of UAV is growing at unprecedented rates. The UAV is an acronym for Unmanned Aerial Vehicle, which is an aircraft with no pilot on board. UAVs can be remote controlled aircraft (e.g. flown by a pilot at a ground control station) or can fly autonomously based on pre-programmed flight plans or more complex dynamic automation systems. A variety of design configurations are in use. The primary driving parameters in all UAVs is the need for maximizing available wing area and wing effectiveness, while minimizing the required storage volume. The major factors in determining the relative merit of the different concepts are the evaluation of structural viability, mechanical complexity and overall system survivability by G forces. This paper examines some of the design methodologies and hardware-in-the loop simulation environment to support and validate the UAV hardware and software development.
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Berger, Tom, Mark Tischler, and Steven G. Hagerott. "Piloted Simulation Handling Qualities Assessment of a Business Jet Fly-By-Wire Flight Control System." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0019.

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Alvarez, Daniel J., David H. Klyde, Marco Lotterio, and Tony Lambregts. "Fixed-Base Piloted Simulation Evaluation of Pitch Axis Fly-By-Wire Flight Control System Characteristics." In AIAA Atmospheric Flight Mechanics (AFM) Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-4508.

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