Journal articles: '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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Reichel, Reinhard. "Steuersysteme im Flugzeug – Fly-By-Wire (Flight Control Systems – Fly-By-Wire)." at - Automatisierungstechnik 52, no. 12-2004 (December 2004): 588–95. http://dx.doi.org/10.1524/auto.52.12.588.53458.

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12

Fielding, C. "The design of fly-by-wire flight control systems." Aeronautical Journal 105, no. 1051 (September 2001): 543–49. http://dx.doi.org/10.1017/s0001924000018005.

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The design of an advanced flight control system (FCS) is a technically challenging task for which a range of engineering disciplines have to align their skills and efforts in order to achieve a successful system design. This paper presents an overview of some of the factors which need to be considered and is intended to serve as an introduction to this stimulating subject. Specific aspects covered are: flight dynamics and handling qualities, mechanical and fly-by-wire systems, control laws and air data systems, stores carriage, actuation systems, flight control computer implementation, flexible airframe dynamics, and ground and flight testing. The flight control system challenges and expected future developments are reviewed and a comprehensive set of references is provided for further reading.

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Cervia, Fabio, Eugenio Denti, Roberto Galatolo, and Francesco Schettini. "Air Data Computation in Fly-By-Wire Flight-Control Systems." Journal of Aircraft 43, no. 2 (March 2006): 450–55. http://dx.doi.org/10.2514/1.16270.

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Bauer, Christophe, Kristen Lagadec, Christian Bès, and Marcel Mongeau. "Flight Control System Architecture Optimization for Fly-By-Wire Airliners." Journal of Guidance, Control, and Dynamics 30, no. 4 (July 2007): 1023–29. http://dx.doi.org/10.2514/1.26311.

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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "The Fly-by-Light system for military aircraft." INCAS BULLETIN 14, no. 1 (March 7, 2021): 237–41. http://dx.doi.org/10.13111/2066-8201.2022.14.1.19.

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This paper presents the authors’ recent documentary research on the benefits of using the Fly-by-Light system in Military aircraft and the understanding of why Fly-by-Light (FBL) is very promising for the further development of military aircraft. The Fly-by-Light flight system is characterized by the fact that the input control signals from the pilot, motion data, and air data sensors are sent to the flight control computer and from there to the actuators of the control surfaces through a fiber optic cable and the feedback from actuators sensors or other signals is received in the same way, through fiber optic cable connected to the aircraft flight control computer. The first major step in the evolution of flight control systems was the replacement of mechanical flight control systems with a Fly-by-Wire (FBW) flight control system. The next major step is the replacement of Fly-by-Wire (FBW) flight control system with a Fly-by-Light (FBL) flight control system which has some significant advantages such as: reducing the weight of the system, increasing the speed and volume of information transmitted through fiber-optic cable (input and feedback signals), keeping intact the accuracy of the signals along the entire length of the circuit; also, the optical fibers do not present any risk of fire, as they carry only light signals, and the temperature, humidity, and severe weather conditions do not affect the fiber optic cable, which can withstand a pressure of about 0.69 - 1.38 MPa without damaging the cable, unaffected by Electromagnetic Interference (EMI) and the Electromagnetic Pulse (EMP) generated by nuclear blasts. All the advantages listed above provide tactical and safety advantages for the military aircraft and its crew.

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Zhang, Ya Ni, Yan Li, and Ya Kui Gao. "Commercial Transport Aircraft Flight Simulator Flying Qualities Airworthiness Verification." Applied Mechanics and Materials 235 (November 2012): 170–75. http://dx.doi.org/10.4028/www.scientific.net/amm.235.170.

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Flight simulation is a simulation of flight and various aspects of the flight environment. Flight simulation is used for a variety of reasons, including aircraft development and flight training. The engineering flight simulator is used for a certain commercial transport aircraft development. The aircraft adopts fly-by-wire flight control technology. The engineering flight simulator was mainly used as a platform to test flying quality of the aircraft. The simulator has actual aircraft cockpit with wide-field visual system mounted on large six degree of freedom(DOF) motion platform that feature comprehensive flight and systems models. In order to demonstrate the flying quality of the aircraft, Flying quality verification experiments were carried out on the simulator. This test provided a means by which one may evaluate flight characteristics for fly-by-wire flight control commercial transport aircraft. Experiment results were evaluated .

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Berger, Tom, Mark B. Tischler, Steven G. Hagerott, M. Christopher Cotting, James L. Gresham, Justin E. George, Kyle J. Krogh, Alessandro d’Argenio, and Justin D. Howland. "Business Jet Fly-by-Wire Control Laws Handling Qualities Flight Test Assessment." Journal of Guidance, Control, and Dynamics 44, no. 8 (August 2021): 1498–516. http://dx.doi.org/10.2514/1.g005768.

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Jacazio, a. Giovanni, and b. Lorenzo Borello. "Mathematical models of electrohydraulic servovalves for fly-by-wire flight control systems." Mathematical and Computer Modelling 11 (1988): 563–69. http://dx.doi.org/10.1016/0895-7177(88)90556-0.

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Mulder, M., A. R. Veldhuijzen, M. M. van Paassen, and J. A. Mulder. "Integrating Fly-by-Wire Controls with Perspective Flight-Path Displays." Journal of Guidance, Control, and Dynamics 28, no. 6 (November 2005): 1263–74. http://dx.doi.org/10.2514/1.12617.

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Dołęga, Boguslaw, and Tomasz Rogalski. "DIAGNOSTICS OF FLY-BY-WIRE CONTROL SYSTEM/KOMPIUTERIU REGULIUOJAMOS VALDYMO SISTEMOS DIAGNOSTIKA." Aviation 12, no. 2 (June 30, 2008): 41–45. http://dx.doi.org/10.3846/1648-7788.2008.12.41-45.

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The paper describes the diagnostics of a fly‐by‐wire control system taken during the creation of this system. Special attention is paid to laboratory tests, which should prove the system could be tested in‐flight. An important kind of verification of the system is testing and reconfiguring fault detection and localization methods. The human factor is also taken into consideration. Santrauka Straipsnyje apibūdinama kompiuteriu reguliuojamos valdymo sistemos diagnostika šios sistemos kūrimo metu. Ypatingas dėmesys skirtas laboratoriniams bandymams, kurių rezultatai turi būti patikrinti skrydžio metu. Vienas svarbiausių sistemos verifikavimo būdų yra gedimų nustatymo ir lokalizavimo metodų bandymas. Taip pat įvertinamas ir žmogiškasis faktorius.

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Rzucidło, Paweł. "MONITORING AND DATA ACQUISITION SYSTEM FOR EXPERIMENTAL GENERAL AVIATION FLY‐BY‐WIRE AIRCRAFT." Aviation 10, no. 3 (September 30, 2006): 16–20. http://dx.doi.org/10.3846/16487788.2006.9635935.

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A CAN data bus was used in a project of an experimental Fly‐by‐Wire control system (SPS‐1) mounted on board a PZL‐110 “Koliber” general aviation aircraft. This solution allows the free communication between flight control computers and individual modules of the system. The monitoring of the bus state and data frames is useful during particular hardware tests, system integration, laboratory and in‐flight tests. This report intends to present the specific monitor tool developed with the to SPS‐1. The main part of the CAN monitoring system is software. It realizes acquisition, visualization and conversion of stored data. The monitoring software operates with devices used by an experimental control system and connected to the bus. Particular devices are assigned to separate windows. The operator can control the SPS‐1 system through specialized windows or by virtual cockpit. Apart from this, the CAN monitor controls and simulates selected modules of the SPS‐1 system and works as the bus diagnostics tool.

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Feder, Judy. "Drones Move From "Nice To Have" to Strategic Resources for Projects." Journal of Petroleum Technology 72, no. 12 (December 1, 2020): 29–30. http://dx.doi.org/10.2118/1220-0029-jpt.

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While drones have been used on oil and gas facilities for video inspections and other tasks, they have been operated by an on-site pilot or one positioned on a bobbing workboat adjacent to an offshore platform. Now a proof-of-concept study conducted by TechnipFMC has tested the feasibility of a global drone system with drones operated remotely by pilots based anywhere in the world. The study is the subject of a paper (OTC 30241) presented at the Offshore Technology Conference Asia in Kuala Lumpur in November. Construction supervision and health, safety, and environmental (HSE) monitoring were the main drivers of the study. The construction supervision application is part of a larger digitalization ambition to monitor and manage construction activities with data generated from the drone ultimately feeding an internal software dedicated to this business process. Potential HSE applications include crisis management, human safety, evacuation assistance, hazardous-area identification, traffic control, carbon-footprint reduction, and environmental surveys. One of the study’s main objectives was to move from traditional unmanned autonomous vehicles (UAV) to resident systems and to investigate the possibilities they could offer. Aerial views have been used extensively to reduce personnel exposure in specific situations such as difficult access or potentially dangerous inspection areas like active flares, confined spaces, or high structures. In these cases, the drones are controlled by an on-site pilot who is either within their line of sight or a short distance away. Combining AUV technology with embedded and associated intelligence from the internet of things (IoT), artificial intelligence (AI), and cloud and edge computing should enable drones to fly safely in complex and dynamic environments, resulting in integrated, resident systems that are permanently deployed at construction sites and available 24/7 without the need for an on-site certified pilot. Implementing these technologies will make data accessible and available in real time to people working on the project worldwide and it will also generate new work processes for project management and execution. Flight and Operations Testing According to the paper’s primary author, Nicolas Tcherniguin, manager of offshore business and technology with TechnipFMC, digital tools such as image recognition, machine learning, and simulation of digital twins based on the drone’s flight have been tested. Remaining bottlenecks have been identified, and some have been addressed while others will require additional efforts. AI development will offer additional features, especially if they can be integrated with other ground monitoring devices.

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Kim, Chong-Sup, In-Je Cho, Seung-Duck Lee, and Han-Ju Lee. "Design and Validation of Model Inversion Flight Control Law for Fly By Wire Helicopter." Journal of the Korean Society for Aeronautical & Space Sciences 40, no. 8 (August 1, 2012): 678–87. http://dx.doi.org/10.5139/jksas.2012.40.8.678.

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Kun, Zhou, Wang Lixin, and Tan Xiangsheng. "Flying qualities reduction of fly-by-wire commercial aircraft with reconfiguration flight control laws." Procedia Engineering 17 (2011): 179–96. http://dx.doi.org/10.1016/j.proeng.2011.10.021.

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Hind, Sam. "On ‘Living in a Box’. Distributed Control and Automation Surprises / „Living in a Box“. Verteilte Steuerung und Automatisierungsüberraschungen in Verkehrsﬂugzeugen." Technikgeschichte 87, no. 1 (2020): 43–68. http://dx.doi.org/10.5771/0040-117x-2020-1-43.

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This article interrogates an aircraft control system referred to as ‘fly-by-wire’. First developed in the 1960s, fly-by-wire replaced mechanical and hydraulic aircraft control systems with an electronic, computer-mediated system capable of relaying, responding to, and sometimes restricting, human inputs from pilots. In so doing, fly-by-wire enabled an entirely new world of flight in which human decisions were subject to machinic, and electronic, approval. The article examines the effects of fly-by-wire on the socio-technical control of aircraft, with repercussions for how one considers contemporary questions regarding the interweaving of automation, control, knowledge and safety. It proceeds in two parts. Firstly, it argues that fly-by-wire is a form of ‘distributed control’. Dependent upon situated automation, the ability to control, steer and manoeuvre the aircraft is variously distributed beyond the cockpit and human pilots, to integrated components, sensors, physical surfaces, and systems throughout the aircraft itself. In so doing, new and novel operational capacities are reached depending on the situation; shifting and re-calibrating the relationship between pilots and aircraft. Secondly, and more specifically, I suggest that distributed forms of control in the shape of aircraft fly-by-wire systems yield so-called ‘automation surprises’. The effect of distributing decision-making to a wider assemblage of components, sensors, surfaces, and systems is that operational asymmetries occur in the otherwise smooth collaboration between pilot and machine. I discuss recent Boeing 737 accidents in order to evidence this argument, contending that recent additions to fly- by-wire have led to novel re-distributive control effects. As the development of prototype autonomous vehicles abounds, historical lessons drawn from aircraft control, decision-making and safety should be of critical importance.

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Dlamini, Z., and T. Jones. "Fly-by-wire robustness to flight dynamics change under horizontal stabiliser damage." Aeronautical Journal 120, no. 1228 (May 10, 2016): 1005–23. http://dx.doi.org/10.1017/aer.2016.42.

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ABSTRACTAircraft damage modelling was conducted on a Boeing 747 to examine the effects of asymmetric horizontal stabiliser loss on the flight dynamics of a commercial Fly-by-Wire (FBW) aircraft. Robustness of the control system is investigated by analysing how characteristic eigenvalues move as a result of damage and comparison to the non-FBW aircraft is made. Furthermore, the extent of stabiliser loss that the system can successfully handle without loss of stability and acceptable performance is identified. The presented analysis of the results gives insightful knowledge to aid in the design of an improved FBW system with increased damage tolerance. A handling qualities evaluation is presented to provide an understanding of how the pilot perceives the damaged aircraft. The results of the study show that a generic FBW system improves robustness such that the aircraft is stable with 50% horizontal stabiliser loss. With 50% damage, the aircraft is controllable but unsafe to fly and may be unable to effectively complete its mission task.

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Zhang, Chao, Yi Nan Liu, and Jian Hui Xu. "Integrated Aircraft Modeling Research for Accurate Flight Control System Design." Advanced Materials Research 791-793 (September 2013): 658–62. http://dx.doi.org/10.4028/www.scientific.net/amr.791-793.658.

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In order to realize accurate flight control system design and simulation, an integrated scheme of aircraft model which consists of flight dynamics, fly-by-wire (FBW) platform and flight environment is proposed. Flight environment includes gravity, wind, and atmosphere. And the actuator and sensors such as gyroscope and accelerometer models are considered in the FBW platform. All parts of the integrated model are closely connected and interacted with each other. Simulation results confirm the effectiveness of the integrated aircraft model and also indicate that the (Flight Control Law) FCL must be designed with robustness to sensor noise and time delays with the FBW platform in addition to the required robustness to model uncertainty in flight dynamics.

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Shen, Yingchun, Shuo Chang, and Qiang Wei. "Fly-by-wire Flight Control Comparative Analysis of Resident and Detached Application Sources of Civil Aircraft." Journal of Physics: Conference Series 2338, no. 1 (September 1, 2022): 012092. http://dx.doi.org/10.1088/1742-6596/2338/1/012092.

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Abstract Starting from the current multifunctional integration and architecture design development status of the flight control system for the mainstream civil aircraft, this paper proposes the system design concepts of “In and Out as a Whole”, “Direct Connection and Transmission”, and “Same Sources and Routes” for the external sensors application sources of the fight control system. External application sources are air data, inertial Reference data and angle of attack sensors in this paper, specifically. This paper analyzes and compares the functional residence and separation processing of external application sources for fly-by-wire flight control system. In addition, it demonstrates the correctness of this design concept and its practical engineering value, systematically. This work has provided a significant reference for future civil aircraft design.

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Gautrey, J. E., and M. V. Cook. "A generic control anticipation parameter for aircraft handling qualities evaluation." Aeronautical Journal 102, no. 1013 (March 1998): 151–60. http://dx.doi.org/10.1017/s000192400006543x.

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AbstractThe established control anticipation parameter longitudinal handling qualities criterion is based on the assumption that the short term dynamic response of the aeroplane is classical, or second-order-like. Modern fly-by-wire aircraft often have longitudinal short term dynamics which are not second-order-like and to which it is difficult to apply the criterion. This paper presents a proposed generic control anticipation parameter which is a modified version of the control anticipation parameter and which may be applicable to both unaugmented and augmented aircraft of all types. The appropriateness of the modified criterion was illustrated by designing a number of command and stability augmentation control laws, constrained to meet the criterion, for application to a medium weight fly-by-wire civil transport aircraft. The handling characteristics conferred by the control laws were assessed in a series of flight simulator trials, the results of which are briefly presented.

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Lee, R. N. "Development of Active Control Technology for the Next Generation of Combat Aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 206, no. 1 (January 1992): 15–25. http://dx.doi.org/10.1243/pime_proc_1992_206_235_02.

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In the mid 1970s British Aerospace recognized that active control technology offered considerable benefits in terms of improved performance and combat effectiveness for future combat aircraft. However, the introduction of such technology carried with it a significant development risk. In order to minimize that risk, a series of flight demonstrator programmes were initiated. This paper describes the principles of active control and the very successful fly-by-wire Jaguar and experimental aircraft demonstrator flight test programmes which progressively demonstrated the viability and benefits of active controls to the extent that this technology is being fully utilized on the new European fighter aircraft.

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Rzucidło, Paweł. "THE DETECTION OF PILOT‐INDUCED OSCILLATIONS." Aviation 11, no. 1 (March 31, 2007): 15–22. http://dx.doi.org/10.3846/16487788.2007.9635950.

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Fly‐by‐wire systems enable superior control of chosen flight parameters. A pilot can modify stabilized parameters by adequate movement of control inceptors such as a side‐stick or trust lever. Fly‐by‐wire control reduces the load on a pilot and allows a pilot to focus on the main tasks. Unfortunately, the use of more complicated interfaces between human and machine can cause incorrect pilot behavior and in many cases lead to erroneous interactions between the operator and effective aircraft dynamics. The structure of control laws and dynamics of electromechanical actuators are especially important factors. They can influence unfavorable aircraft‐pilot coupling and can lead to pilot‐induced oscillations (PIO) in certain cases. The automatic detection of PIOs is presented in this paper. The practical realization of a PIO‐detector and examples of diagnostics of human‐machine systems are reported on in this article.

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Kuderko, Dmitry, Vladimir Tselischev, and Dmitry Tselischev. "PROSPECTS FOR DEVELOPMENT OF FLIGHT CONTROL SURFACES ACTUATORS OF CIVIL AIRCRAFT." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 67 (2021): 70–84. http://dx.doi.org/10.15593/2224-9982/2021.67.07.

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The main problems arising in the development of systems of actuators with remote control for promising aircraft are considered. The tasks of the fly-by-wire control system for actuators of the aircraft are determined. The directions of development of improving the mass-dimensional and dynamic characteristics, improving the design and layout of circuit solutions, control systems and improving operational characteristics, which provide an increase in the quality and safety of the aircraft operation, are given. A concept for the development of actuators for the control surfaces of a passenger aircraft has been formulated, including the main directions of scientific and experimental work carried out by technical design companies, scientific organizations and manufacturers of hydraulic units both in Russia and abroad. The improvement of weight and size characteristics is possible due to the energy perfection of actuators and ensuring synchronization of their operation, the use of autonomous actuator circuits, and pumping stations of variable capacity. The issues of improving the dynamic characteristics of actuators involve the problems of increasing speed, accuracy, stability, and controllability. When considering promising design and layout schemes of actuators, the features of the use of electrohydrostatic actuators, integrated layout, electrohydraulic control and the advantage of an autonomous electrohydraulic actuator are shown. The section devoted to control systems characterizes fly-by-wire system, the use of Load Sensing (LS)-regulation of volumetric hydraulic machines, issues of performance management and integration with an intelligent computer control system. When considering the performance characteristics of perspective actuators, the possibilities of reducing heat losses, problems of increasing reliability and resource, and features of bench testing are highlighted. New directions for the development of actuators are considered, such as the use of fiber-optic control wiring instead of electric, as well as the use of plasma technologies for control surfaces.

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Rzucidło, Paweł, and Peter Chudy. "Analysis of Interactions between Pilot-Operator and Advanced Flight Control System." Solid State Phenomena 180 (November 2011): 101–8. http://dx.doi.org/10.4028/www.scientific.net/ssp.180.101.

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This work discusses the application of techniques serving the purpose of prediction and detection of unfavorable man-machine interactions. Prediction criteria of Pilot Induced Oscillations (PIO) were applied during design process of experimental multi-modal fly-by-wire control system for small light aircraft. Estimated PIO susceptibility was further verified during real-time simulations and flight tests. The verification process included subjective pilot/operator expert opinions and the results obtained from the automatic detectors, used for the PIO identification in long sets of recorded data. The general idea of the detection algorithms is based on the Fast Fourier Transform (FFT). These are being presented in this paper in a form of detection applications along with the results of the flight experiments.

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Fadel, Mohamed, Mahmoud Rabie, and Ahmed Youssef. "Modeling, Simulation and Control of a Fly-by-wire Flight Control System Using Classical PID and Modified PI-D Controllers." Journal Européen des Systèmes Automatisés 52, no. 3 (August 31, 2019): 267–76. http://dx.doi.org/10.18280/jesa.520307.

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Weiser, Christian, Daniel Ossmann, and Gertjan Looye. "Design and flight test of a linear parameter varying flight controller." CEAS Aeronautical Journal 11, no. 4 (August 28, 2020): 955–69. http://dx.doi.org/10.1007/s13272-020-00461-y.

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Abstract Future aircraft generations require improved performance and efficiency to enable a reduced environmental footprint. To acquire this goal, for example new material and wing concepts are perused at the moment by the aircraft industry. These developments, which include aspects such as over-actuation and lowly damped flexible modes, give rise to more complex, multi-objective control problems. One candidate method, which delivers a solution to these problems for the whole flight envelope, is linear parameter varying (LPV) control. It naturally incorporates the controller scheduling in the synthesis process, guarantees stability and robustness over the entire parameter envelope, and enables intuitive multi-objective, multiple-input multiple-output (MIMO) controller designs. This paper proves the concept of LPV control in practice: The paper presents and discusses the LPV controller design process, simulation results, motion simulator test and finally, the in-flight validation of the control system on a Cessna Citation II aircraft. The developed inner loop controller structures are inspired by classical flight controllers used on state-of-the-art fly-by-wire airliners. The longitudinal aircraft motion is augmented with load-factor command and the lateral motion controller features a roll rate command with attitude hold behavior. The control laws are validated in flight by automated and actual pilot inputs with respect to functionality, flying and handling qualities. Test results are encouraging with the provided key findings and lessons learned aiming to provide a simplification for future LPV flight controller development and testing campaigns.

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Müller, Simon, Karolin Schreiter, Robert Luckner, and Dietrich Manzey. "Manual Flying and Energy Awareness." Aviation Psychology and Applied Human Factors 7, no. 1 (April 2017): 18–27. http://dx.doi.org/10.1027/2192-0923/a000111.

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Abstract. In order to enable pilots to better maintain energy awareness and energy management in manual flight, a new concept has been proposed, which transfers the demand control principle of fly-by-wire control laws also to the control of thrust. It includes a total-energy-related augmented thrust controller combined with a modified cockpit instrumentation enriched by specific energy displays. In order to empirically evaluate the human performance consequences of this new approach, an experimental study was conducted in a flight simulator investigating its effects on pilots’ performance, workload, and situation awareness. A total of 24 commercial aircraft pilots performed a landing and approach on a complex flight trajectory with and without the new system elements. The results confirm the expected beneficial effects of the new system on flight precision and lowered effort involved in thrust control as compared with conventional raw data flying. No negative side effects, for example, impaired situation awareness, were found.

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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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Steer, A. J. "Supersonic transport aircraft longitudinal flight control law design." Aeronautical Journal 108, no. 1084 (June 2004): 319–29. http://dx.doi.org/10.1017/s000192400000018x.

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Abstract Modern civil transport aircraft utilise increasingly complex command and stability augmentation systems to restore stability, optimise aerodynamic performance and provide the pilot with the optimum handling qualities. Provided it has sufficient control power a second generation fly-by-wire supersonic transport aircraft should be capable of exhibiting similarly desirable low-speed handling qualities. However, successful flight control law design requires identification of the ideal command response type for a particular phase of flight, a set of valid handling quality design criteria and piloted simulation evaluation tasks and metrics. A non-linear mathematical model of the European supersonic transport aircraft has been synthesized on the final approach to land. Specific handling quality design criteria have been proposed to enable the non-linear dynamic inversion flight control laws to be designed, with piloted simulation used for validation. A pitch rate command system, with dynamics matched to the aircraft’s flight path response, will consistently provide Level 1 handling qualities. Nevertheless, pre-filtering the pilot’s input to provide a second order pitch rate response, using the author’s suggested revised constraints on the control anticipation parameter will generate the best handling qualities during the terminal phase of flight. The resulting pre-filter can be easily applied to non-linear dynamic inversion inner loop controllers and has simple and flight proven sensor requirements.

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Rogalski, Tomasz. "THE IDEA OF A SYSTEM INCREASING FLIGHT SAFETY." Aviation 14, no. 4 (December 31, 2010): 112–16. http://dx.doi.org/10.3846/aviation.2010.17.

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This paper presents a conception of an airborne control system that can increase the safety of a general aviation aircraft. Sample threats appear on board the general aviation airplane discussed in the paper. The system monitors some events and flight parameters in the cockpit and can take some actions protecting the plane against threats if recognised as necessary. The paper presents sample actions fly‐by‐wire control systems can take to protect a plane against some threats on board. The system can modify a pilot's controls to correct flight and if it is not enough the system can disengage the pilot to autonomously fly the plane to the nearest safe airport Santrauka Straipsnyje pateikta valdymo iš oro sistemos koncepcija, kuri gali padidinti bendrosios aviacijos orlaiviu sauguma bei aptartos pavyzdines gresmes bendrosios aviacijos orlaiviuose. Aprašoma sistema stebi lakūno kabinoje rodomus ivairius skrydžio parametrus ir, kilus bet kokiai gresmei orlaivio saugumui, gali ji apsaugoti. Darbe pateikiami ir kompiuterizuoto elektrodistancinio valdymo sistemos pavyzdžiai, kurie taip pat gali apsaugoti orlaivi nuo jam kylančiu gresmiu. Ši sistema gali modifikuoti piloto valdyma taip, kad būtu pakoreguotas skrydis, o jei ir to neužtenka – sistema pajegi ir autonominiam skrydžiui, kuomet orlaivis yra nukreipiamas i artimiausia ir saugiausia oro uosta be piloto pagalbos.

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Ömürlü, Vasfi, and İbrahim Yildiz. "A Stewart Platform as a FBW Flight Control Unit." Journal of Electrical Engineering 62, no. 4 (July 1, 2011): 213–19. http://dx.doi.org/10.2478/v10187-011-0034-y.

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A Stewart Platform as a FBW Flight Control UnitA variety of flight control units have been put into realization for navigational purposes of spatially moving vehicles (SMV), which is mostly manipulated by 2 or 3 degrees-of-freedom (DOF) joysticks. Since motion in space consists of three translational motions in forward, side and vertical directions and three rotational motions about these axis; with present joystick interfaces, spatial vehicles has to employ more than one navigational control unit to be able to navigate on all required directions. In this study, a 3 × 3 Stewart-Platform-based FBW (Fly-By-Wire) flight control unit with force feedback is presented which will provide single point manipulation of any SMVs along three translational and about three rotational axis. Within the frame of this paper, design, capability and the advantages of the novel system is mentioned. Kinematics of a Stewart Platform (SP) mechanism employed and its motion potentials is presented by simulations and workspace of the system is evaluated. Dynamic analysis by Bond-Graph approach will be mentioned. Mechatronic design of the complete structure is discussed and force reflection capability of the system with simulations is pointed out using stiffness control. Finally, the possible future work of the subject is discussed which may include the feasible solutions of the SP in terms of size and safety when implementing inside a cockpit.

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Di Rito, G., E. Denti, and R. Galatolo. "Development and experimental validation of real-time executable models of primary fly-by-wire actuators." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 222, no. 6 (September 2008): 523–42. http://dx.doi.org/10.1243/09596518jsce546.

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Wang, Lixin, Kun Yang, Peng Zhao, and Ting Yue. "Aircraft Configuration Parameter Boundaries Based on Closed-Loop Flying Qualities Requirements." Aerospace 8, no. 12 (November 24, 2021): 360. http://dx.doi.org/10.3390/aerospace8120360.

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For aircraft employing the fly-by-wire technique, the closed-loop dynamic characteristics are determined by both the configuration design and the flight control system. As the capacity of the control system has certain limitations, the configuration parameters are also constrained by the requirements of the closed-loop flying qualities. This paper presents an aircraft configuration parameter boundaries determination method based on closed-loop flying qualities requirements independent of the actual flight control law design, mainly aiming at the parameters that affect the stability and control characteristics. First, a nonlinear dynamic inversion-based flight control law is adopted to decouple the control law gains from the configuration parameters and to study the relationship between the configuration parameters and closed-loop flying qualities. Second, a flying qualities evaluation scheme is established by selecting the most severe flight conditions and the evaluation criteria that are most sensitive to changes in the parameters. Finally, the parameter boundaries according to the requirements of Level 1 flying qualities are determined by searching for the critical values that lead to degradation of the flying qualities. The proposed method is verified by an application example of the design ranges of a sample aircraft’s wing position, horizontal tail area, center of gravity, vertical tail area and vertical tail position.

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Miller, Nicole D., Theodore J. Yoder, Nicholas C. Manoukis, Lori A. F. N. Carvalho, and Matthew S. Siderhurst. "Harmonic radar tracking of individual melon flies, Zeugodacus cucurbitae, in Hawaii: Determining movement parameters in cage and field settings." PLOS ONE 17, no. 11 (November 16, 2022): e0276987. http://dx.doi.org/10.1371/journal.pone.0276987.

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Tephritid fruit flies, such as the melon fly, Zeugodacus cucurbitae, are major horticultural pests worldwide and pose invasion risks due primarily to international trade. Determining movement parameters for fruit flies is critical to effective surveillance and control strategies, from setting quarantine boundaries after incursions to development of agent-based models for management. While mark-release-recapture, flight mills, and visual observations have been used to study tephritid movement, none of these techniques give a full picture of fruit fly movement in nature. Tracking tagged flies offers an alternative method which has the potential to observe individual fly movements in the field, mirroring studies conducted by ecologists on larger animals. In this study, harmonic radar (HR) tags were fabricated using superelastic nitinol wire which is light (tags weighed less than 1 mg), flexible, and does not tangle. Flight tests with wild melon flies showed no obvious adverse effects of HR tag attachment. Subsequent experiments successfully tracked HR tagged flies in large field cages, a papaya field, and open parkland. Unexpectedly, a majority of tagged flies showed strong flight directional biases with these biases varying between flies, similar to what has been observed in the migratory butterfly Pieris brassicae. In field cage experiments, 30 of the 36 flies observed (83%) showed directionally biased flights while similar biases were observed in roughly half the flies tracked in a papaya field. Turning angles from both cage and field experiments were non-random and indicate a strong bias toward continued “forward” movement. At least some of the observed direction bias can be explained by wind direction with a correlation observed between collective melon fly flight directions in field cage, papaya field, and open field experiments. However, individual mean flight directions coincided with the observed wind direction for only 9 out of the 25 flies in the cage experiment and half of the flies in the papaya field, suggesting wind is unlikely to be the only factor affecting flight direction. Individual flight distances (meters per flight) differed between the field cage, papaya field, and open field experiments with longer mean step-distances observed in the open field. Data on flight directionality and step-distances determined in this study might assist in the development of more effective control and better parametrize models of pest tephritid fruit fly movement.

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Ivler, Christina M., J. David Powell, Mark B. Tischler, Jay W. Fletcher, and Carl Ott. "Design and Flight Test of a Cable Angle Feedback Flight Control System for the RASCAL JUH-60 Helicopter." Journal of the American Helicopter Society 59, no. 4 (October 1, 2014): 1–15. http://dx.doi.org/10.4050/jahs.59.042008.

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The ability of a helicopter to carry externally slung loads makes it very versatile for many civil and military operations. However, the piloted handling qualities of the helicopter are degraded by the presence of the slung load. A control system is developed that uses measurements of the slung load motions as well as conventional fuselage feedback to improve the handling qualities for hover/low-speed operations. Prior research has shown a fundamental trade-off between load damping and piloted handling qualities for a feedback control system with cable angle/rate feedback. A new task-tailored approach proposed and implemented herein uses a method of switching between a load damping mode and a piloted handling qualities mode. These modes provide appropriate load feedback depending on the piloting task and flight regime. This provides improved handling qualities for maneuvering flight and for improved precision load control at hover. A new mission task element for precision load placement is developed (for possible inclusion into ADS-33E-PRF) to test the ability of the cable feedback system to improve load placement task performance. The improvements provided by this control system are demonstrated in a piloted flight test on the JUH-60A RASCAL fly-by-wire helicopter. The average load set-down time was reduced by a factor of two for the 1000-lb load on a 56-ft sling.

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Granzoto, R. M., L. A. Algodoal, G. J. Zambrano, and G. G. Becker. "Horizontal tail local angle-of-attack and total pressure measurements through static pressure ports and Kiel pitot." Aeronautical Journal 123, no. 1268 (October 2019): 1476–91. http://dx.doi.org/10.1017/aer.2019.68.

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ABSTRACTAircraft handling qualities may be influenced by wing-tip flow separations and horizontal tail (HT) reduced efficiency caused by loss of local dynamic pressure or local tailplane flow separations in high angle-of-attack manoeuvres. From the flight tester’s perspective, provided that the test aircraft presents sufficient longitudinal control authority to overcome an uncommanded nose-up motion, this characteristic should not be a safety factor. Monitoring and measuring the local airflow in the aircraft’s HT provides information for safe flight-test envelope expansion and data for early aerodynamic knowledge and model validation. This work presents the development, installation and pre-flight calibration using computational fluid dynamics (CFD), flight-test calibration, results and benefits of differential pressure based local angle-of-attack and total pressure measurements through 20 static pressure ports and a Kiel pitot. These sensors were installed in a single-aisle, four-abreast, full fly-by-wire medium-range jet airliner with twin turbofan engines and conventional HT (low vertical position).

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Seher-Weiß, Susanne. "ACT/FHS System Identification Including Rotor and Engine Dynamics." Journal of the American Helicopter Society 64, no. 2 (April 1, 2019): 1–12. http://dx.doi.org/10.4050/jahs.64.022003.

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At the German Aerospace Center (DLR) Institute of Flight Systems, models of the Active Control Technology/Flying Helicopter Simulator (ACT/FHS), an EC135 with a fly-by-wire/light flight control system, are needed for control law development and simulation. Thus, models are sought that cover the whole flight envelope and are valid over a broad range of frequencies. Furthermore, if the models are to be used in the feedforward loop of the model following the control system, they have to be invertible and thus should not have any positive transmission zeros. For rotor flapping, the explicit formulation with flapping angles was modified slightly to avoid positive transmission zeros. For the regressive lead–lag, a simple model formulation was found that needs only one dipole with two states. The engine dynamics were first modeled separately and then coupled to the body/rotor model. The final integrated model has 17 states and yields a good match for frequencies up to 30 rad/s. All system identification was performed using the maximum likelihood method in the frequency domain.

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XUE, Ying, and Zhen Qiang YAO. "A Way to Mitigate Force-Fight Oscillation Based on Pressure and Position Compensation for Fly-by-Wire Flight Control Systems." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 63, no. 1 (2020): 1–7. http://dx.doi.org/10.2322/tjsass.63.1.

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Warzocha, Krzysztof, Jerzy Szura, Piotr Bąk, Paweł Rzucidło, and Tomasz Rogalski. "Transformative Use of Additive Technology in Design and Manufacture of Hydraulic Actuator for Fly-by-Wire System." Applied Sciences 11, no. 11 (May 22, 2021): 4772. http://dx.doi.org/10.3390/app11114772.

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In this paper, the results of research on additively manufactured aerospace parts made of maraging steel are presented. This state-of-the-art technology seems to have the highest potential for practical use in the field of ultra-light and high-performance aerospace hydraulic parts. The strength properties of representative specimens made with steel 1.2709 were investigated. The researchers conducted static tensile testing, fatigue tensile testing, and pressure impulse testing. A Goodman diagram was plotted to visualize the impact of the building orientation vs. load character on the fatigue strength of the additive manufacturing (AM) specimens. Based on the research carried out on the strength of the AM samples, an aircraft flight control actuator was designed to achieve the highest level of safety integrity along with the greatest simplicity and lowest weight relative to hydraulic actuators manufactured using classical methods. The entire design process was integrated with the manufacturing process to achieve this target.

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Kim, Chong-Sup, Chang-Ho Ji, and Byoung Soo Kim. "Development of a control law to improve the handling qualities for short-range air-to-air combat maneuvers." Advances in Mechanical Engineering 12, no. 7 (July 2020): 168781402093679. http://dx.doi.org/10.1177/1687814020936790.

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Modern fighter aircraft have been designed to have high maneuverability in order to preoccupy strategic superiority in short-range air-to-air combat between fighter aircraft in warfare. Digital fly-by-wire flight control system design is aimed at providing good handling qualities for all mission task elements over the entire flight envelope. To provide both excellent gross acquisition and fine tracking compatibility, simultaneously for air-to-air combat maneuvers, this article presents a common longitudinal control law design of a task-dependent self-adjusting command-path pilot prefilter gain scheduler within the same control law design architecture and response type based on nonlinear dynamic inversion control. We perform the frequency- and time-domain analyses based on the mathematical model of T-50 advanced trainer aircraft to evaluate the basic flying qualities of the proposed control method. Furthermore, the pilot evaluation is performed to evaluate the gross acquisition and fine tracking capability for air-to-air tracking maneuvers in a handling quality simulator. The evaluation results reveal that the proposed control method improves the fine tracking capability without the degradation of gross acquisition.

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Zhang, Jing Kai, Peng Hui Li, Xiao Xiong Liu, and Wei Guo Zhang. "An Autopilot Fault Diagnosis Method Based on Hybrid Case and Fault Trees." Applied Mechanics and Materials 373-375 (August 2013): 829–32. http://dx.doi.org/10.4028/www.scientific.net/amm.373-375.829.

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Targeted at the faults of autopilot in fly-by-wire flight control system, a method based on integration of case and fault tree is proposed to quickly diagnose faults and provide the maintenance of autopilot system. In the process of diagnosis, according to the characteristics of fault information about autopilot system, the Build-in-test data was used to quickly search similar fault in the case base and accurately point out the fault location. For complex fault, the fault tree method is used to traverse to complete the reasoning and diagnosis procedure, and simultaneously add the results to the case base. The simulation results show the method is achieved.

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

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