Journal articles: 'Aircraft - Automatic Control'

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Suhih, Nikolai, and Valentin Rukavishnikov. "Research of the Processes of Aircraft Director Control at Board Calculator Failure." Automation on transport 8, no. 2 (2022): 121–32. http://dx.doi.org/10.20295/2412-9186-2022-8-2-121-132.

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It’s accepted to divide aircraft automatic control into semi-automatic (director) and automatic. Semi-automatic (director) systems provide for the collection and analysis of information, delivered from navigation equipment. On aircraft position in space and give a command to a pilot. Aircraft management with the help of such piloting-navigational systems is called semi-automatic because information collection and processing on aircraft condition is automated but the control’s left to be manual. Automatic control systems provide not just for information collection and processing on aircraft state but also for management laws as well as for control process itself. A man implements functions on automatic system work control, on identifying, making decisions on inclusion of this or that program, function of "hot" reserve. Present article shows experiment organization and obtained results on research of the processes of airplane director management while failures of board calculator of trajectory control system with real pilot inclusion into circuit. The research is held on the stage of aircraft approach and landing. The experiment was held on special bench of half-real modeling.

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Šlihta, Mareks, Vladimirs Šestakovs, and Ramachandran Karunanidhi. "Aircraft Automatic Control System Failure and Flight Safety." Transport and Aerospace Engineering 3, no. 1 (2016): 15–23. http://dx.doi.org/10.1515/tae-2016-0002.

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Abstract This article presents a mathematical model estimating the probability of successful completion of the aircraft’s flight in case of aviation equipment failure in flight. This paper shows the relationship between the aircraft’s automatic control system and flight safety. The calculations of probability are made for the successful completion of the flight on Boeing 737 aircraft when the automatic control system has failed.

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Yamasaki, Takeshi, Keisuke Enomoto, Daiki Tanaka, Daiki Tanaka, and Yoriaki Baba. "Automatic Control for Chase Aircraft." International Journal of Aeronautical and Space Sciences 7, no. 2 (2006): 145–54. http://dx.doi.org/10.5139/ijass.2006.7.2.145.

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Zajdel, Albert, Cezary Szczepański, Mariusz Krawczyk, Jerzy Graffstein, and Piotr Masłowski. "Selected Aspects of the Low Level Automatic Taxi Control System Concept." Transactions on Aerospace Research 2017, no. 2 (2017): 69–79. http://dx.doi.org/10.2478/tar-2017-0016.

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Abstract Taxiing of manned and remotely piloted aircraft is still performed by pilots without using a system of automatic control of direction and speed. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge. The reasons are: decreased airport capacity due to the growing number of aircraft, poor ground operation conditions during poor visibility conditions, an increase in workload of pilots and air traffic controllers and the integration of simultaneous ground operations of manned and remotely piloted air vehicles. This paper presents selected aspects of the concept of a Low Level Automatic Taxi Control System. In particular, it emphasizes the means of controlling an aircraft during taxiing, accuracy requirements of the system and proposes control techniques. The resulting controller of the system is adaptable for different aircrafts. The actuators and their mechanical connections to available controls are the aircraft specific part and are designed for the particular type – in this case – a general aviation light airplane.

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Krawczyk, Mariusz, Cezary Szczepański, and Albert Zajdel. "Automatic Taxiing Direction Control System for Carrier-Based Aircraft." Transactions on Maritime Science 8, no. 2 (2019): 171–79. http://dx.doi.org/10.7225/toms.v08.n02.002.

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This paper solves the problem of automatic taxiing direction control of carrier-based aircraft. On modern aircraft carriers, taxiing aircraft either propel themselves using their own engines or are towed by specialised tugs, which requires dedicated personnel and assets. The automatization of this process would simultaneously increase aircraft flow and decrease the number of personnel and assets required. The key challenge in the automatization of this type of process is the development of an automatic control system capable of performing the requisite tasks, which our researchers managed to do. First, the specific conditions of taxiing on-board carriers were analysed and modelled. The model of a fixed-wing aircraft best suited to this purpose was identified and the proper method of automatic control – ADRC – chosen. The algorithm used in the methodto facilitate effective direction control of a taxiing aircraft was formulated and extensively tested. The results of automatic taxiing simulation for F/A-18 aircraft have been presented. The conclusion is that the ADRC type control algorithm can ensure effective automatic control of taxiing aircraft.

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Zhen, Ziyang, Ju Jiang, Xinhua Wang, and Kangwei Li. "Modeling, control design, and influence analysis of catapult-assisted take-off process for carrier-based aircrafts." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 13 (2017): 2527–40. http://dx.doi.org/10.1177/0954410017715278.

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This paper addresses the problems of modeling, control design, and influence analysis of the steam catapult-assisted take-off process of the carrier-based aircrafts. The mathematical models of the carrier-based aircraft, steam catapult, landing gears, and the environmental factors including deck motion and bow airflow have been established to express the aircraft dynamics in the take-off process. An engineering method based automatic flight control system has been designed, which is divided into the longitudinal channel and lateral channel. The influences of the preset control surface, ship deck motion, ship bow airflow, and automatic flight control system system are tested by a series of simulations. The simulation results show that the elevator angle preset is necessary in the stage of accelerated running on the ship deck and the deck motion is the most important factor for safe take-off, while the ship bow airflow is beneficial for climbing up of the aircraft. The automatic flight control system gives the guarantee of safety and performance in the take-off process of the carrier-based aircraft.

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Rogalski, Tomasz. "Unmanned aircraft automatic flight control algorithm in loop manoeuvre." Aircraft Engineering and Aerospace Technology 90, no. 6 (2018): 877–84. http://dx.doi.org/10.1108/aeat-02-2018-0088.

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Purpose This paper aims to present the idea of an automatic control system dedicated to small manned and unmanned aircraft performing manoeuvres other than those necessary to perform a so-called standard flight. The character of these manoeuvres and the range of aircraft flight parameter changes restrict application of standard control algorithms. In many cases, they also limit the possibility to acquire complete information about aircraft flight parameters. This paper analyses an alternative solution that can be applied in such cases. The loop manoeuvre, an element of aerobatic flight, was selected as a working example. Design/methodology/approach This paper used theoretical discussion and breakdowns to create basics for designing structures of control algorithms. A simplified analytical approach was then applied to tune regulators. Research results were verified in a series of computer-based software-in-the-loop rig test computer simulations. Findings The structure of the control system enabling aerobatic flight was found and the method for tuning regulators was also created. Practical implications The findings could be a foundation for autopilots working in non-conventional flight scenarios and automatic aircraft recovery systems. Originality/value This paper presents the author’s original approach to aircraft automated control where high precision control is not the priority and flight parameters cannot be precisely measured or determined.

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Bobin, A. V., V. A. Azarov, S. A. Bulgakov, and D. A. Savin. "Technique for recognition of aircrafts and radar traps in the control circuit of airspace control system based on neural network technology." Izvestiya MGTU MAMI 7, no. 1-4 (2013): 124–30. http://dx.doi.org/10.17816/2074-0530-67843.

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The paper proposes a method for building of automatic recognizers of aircrafts on a set of radar measurements based on the cascade of multilayer feedforward neural networks. The practical application of this technique in recognizing of three types of aircraft is presented as well.

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TUDOSIE, Alexandru Nicolae, and Mádálina Luciana PĂUNESCU. "AUTOMATIC CONTROL SYSTEM FOR AN AIRCRAFT PLAN SUPERSONIC INLET WITH MOBILE PANEL." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 19, no. 1 (2017): 243–52. http://dx.doi.org/10.19062/2247-3173.2017.19.1.27.

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Zajdel, Albert, Mariusz Krawczyk, and Cezary Szczepański. "Trim Tab Flight Stabilisation System Performance Assessment under Degraded Actuator Speeds." Aerospace 10, no. 5 (2023): 429. http://dx.doi.org/10.3390/aerospace10050429.

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One of the areas involved in changing current aircraft into more electric ones is decreasing energy consumption by the aircraft’s automatic flight control. Therefore, some aircraft types have tested the possibility of controlling the flight in automatic mode or stabilising the flight with trimmers. Previous research on cost-effective and less electrical-energy-consuming automatic stabilisation systems for an aircraft resulted in constructing a laboratory model of the system. Such a feature is beneficial for initiatives like Future Sky, electric aircraft and aircraft stabilisation system retrofits. The system was developed using model-based design and next tuned and tested in model, pilot and hardware-in-the-loop simulations. The implementation of this system does not modify the pilot’s primary manual controls. Instead, the electrical trim system is used for automatic stabilisation or manual trimming, depending on the chosen operation mode. The paper presents the development process of the laboratory model of the system and its simulation under degraded actuator speeds. The results were the basis for its control performance assessment. First, the control performance measure was defined. Then the simulation scenarios that compare system behaviour in stabilisation mode after aerodynamic disturbance with three different trim tab actuator speeds were described. The performance measure is highly degraded by the slower actuator speeds, although altitude and heading are finally stabilised in all cases. Moreover, the performance of stabilisation in a lateral channel is less affected by the slowest actuator than in a longitudinal channel.

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Sukhov, Z. S., and G. A. Timofeev. "Automatic Aircraft Cabin Pressurization Systems." Proceedings of Higher Educational Institutions. Маchine Building, no. 9 (714) (September 2019): 20–25. http://dx.doi.org/10.18698/0536-1044-2019-9-20-25.

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This article presents a review of pneumatic, electro-pneumatic and digital systems for automatic pressure control in an airtight cabin and lists the types of aircraft where such systems are installed. Advanced algorithms for controlling the pressure in an airtight cabin are analyzed and literature on this topic is surveyed. The work of a Russian author that describes optimal control based on Pontryagin’s maximum principle is examined. The works of foreign authors on fuzzy PID-controller, L1-adaptive controller and other methods of adaptive pressurization are analyzed and brief results of these works are presented. The performed analysis indicates the need to use new methods and approaches to the synthesis of automatic pressure control systems for various types of aircraft. One of the most promising solutions is the use of adaptive regulators. The relevance of developing a virtual testing environment to reduce the cost of full-scale testing is shown.

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Rogalski, Tomasz, Mariusz Dojka, Kamila Jakubik, and Lukasz Walek. "Automatic take-off control system." Aeronautics and Aerospace Open Access Journal 7, no. 2 (2023): 93–97. http://dx.doi.org/10.15406/aaoaj.2023.07.00175.

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The purpose of the work is to present a solution that will significantly contribute to the technological development of the European defense sector. The proposed solution raises the issue of controlling autonomous vehicles. This paper presents the concept of an algorithm that allows for automatic take-off of unmanned aircraft. Arguments are presented which justify the need for developing and applying such a system. The socioeconomic and environmental aspects of the project are also discussed. The automatic take-off algorithm complements existing aircraft flight control systems. The considered solution takes into account take-off as a maneuver made of three phases. The control on a runway is possible due to data fusion from the INS and GNSS systems. Data fusion may be supported by using the runway image processing system. The concept of an automatic take-off algorithm is presented along with the most appropriate testing methods, including software-in-the-loop and hardware-in-the-loop simulations.

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Nowak, Dariusz, Grzegorz Kopecki, Damian Kordos, and Tomasz Rogalski. "The PAPI Lights-Based Vision System for Aircraft Automatic Control during Approach and Landing." Aerospace 9, no. 6 (2022): 285. http://dx.doi.org/10.3390/aerospace9060285.

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The paper presents the concept of a component of an aircraft’s automatic flight control system, controlling the airplane when in longitudinal motion (i.e., pitch angle, sink rate, airspeed channels) during automatic landing, from a final approach until a touchdown. It is composed of two key parts: a vision system and an automatic landing system. The first part exploits dedicated image-processing algorithms to identify the number of red and white PAPI lights appearing on an onboard video camera. Its output data—information about an aircraft’s position on a vertical profile of a landing trajectory—is used as one of the crucial inputs to the automatic landing system (the second part), which uses them to control the landing. The control algorithms implemented by the automatic landing system are based on the fuzzy logic expert system and were developed to imitate the pilot’s control actions during landing an aircraft. These two parts were teamed together as a component of a laboratory rig, first as pure software algorithms only, then as real hardware modules with downloaded algorithms. In two test campaigns (software in the loop and hardware in the loop) they controlled an aircraft model in a simulation environment. Selected results, presenting both control efficiency and flight precision, are given in the final section of the paper.

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BOIKO, Sergey, Alona HEBDA, Yurii STUSHCHANSKY, Serhiy GOLOVANOV, and Myhailo RUZHUK. "APPROACH TO THE IMPROVEMENT OF THE CONTROL SYSTEM OF THE ELECTRIC POWER PLANT OF THE AIRCRAFT." Herald of Khmelnytskyi National University. Technical sciences 315, no. 6 (2022): 20–24. http://dx.doi.org/10.31891/2307-5732-2022-315-6(2)-20-24.

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The paper proposes an approach to improving the adaptive system of aircraft with an electric propulsion system. Modern aircraft are inextricably linked with electronics that ensure the functioning of the entire air transport system. Modern aircraft avionics is a complex of hardware and software that is part of the automatic control system of the aircraft and functionally combines the glider with the drive of the executive body. One of the main functions of modern avionics is the automation of aircraft control processes, which aims to ensure the proper execution of a safe flight with the smallest number of crew members. this fact encourages the continuous improvement of the existing on-board avionics complexes of aircraft. Among other things, the adaptive control system should determine the dynamic characteristics of the controlled aircraft during the flight, the assessment of the state of the functional systems of the aircraft and the formation of control signals. An approach to the construction of an aircraft control system is proposed, which involves a double determination of the characteristics of the object under study. The structure of the control system of an aircraft with an electric power plant is proposed. Its construction was influenced by the operating features of the aircraft’s electric power plant, the approach to the dual determination of the aircraft’s characteristics, and the principle of dual control of the aircraft’s flight parameters. The paper proposes an approach to improving the adaptive system of aircraft with an electric propulsion system. There are the following factors: 1) height, accuracy and reliability of sensors of all parameters, regardless of operating conditions; 2) a simple and at the same time reliable and functional interface; 3) timely detection of deviations in the operation of aircraft systems during its operation and transmission of relevant information to the crew and the control system; 4) operational determination of the dynamic characteristics of the aircraft during flight and adaptive optimization of controlled signals taking into account the purpose of control and the specified optimization criteria.

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Zhang, Hui, Hong Jie Guo, and Shu Sheng Zhang. "Manufacture of Flexible Automatic Assembly Platform for Aircraft Component Level." Applied Mechanics and Materials 635-637 (September 2014): 1857–60. http://dx.doi.org/10.4028/www.scientific.net/amm.635-637.1857.

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This paper describes the composition and working principle of aircraft parts flexible automatic assembly platform, and gives the detailed analysis and design of flexible automatic assembly platform of mechanical structure and motion adjusting control system. The two types of multi plane assembly shows that automatic assembly platform automatic adjusting is reliable, operation control system and motion mechanism runs stable, this system can meet the various needs of automatic assembly platform of aircraft components, and it realizes the work mode of assembly and products in one to many during the aircraft components Assembly process.

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Zaitseva, Alina, Nikolai Dudayev, and Konstantin Shcherbakov. "MICROPROCESSOR SYSTEM FOR AUTOMATIC CONTROL OF AIRCRAFT FIRE PROTECTION MEANS." Electrical and data processing facilities and systems 18, no. 1 (2022): 131–42. http://dx.doi.org/10.17122/1999-5458-2022-18-1-131-142.

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Relevance The ever-increasing requirements for the safety of the use of aviation technology are inextricably linked with the problem of providing fire protection for aircraft, both military and civilian. The complexity of the problem of ensuring the fire safety of flights is associated with an increase in the intensity of the use of aviation equipment and the expansion of the range of functional tasks performed by it. The resulting complication of on-board equipment and an increase in the number of energy-intensive devices creates the prerequisites for the occurrence of fires on board the aircraft. At the same time, the remoteness of places where fires are possible, the variety of causes leading to fires, as well as the ambiguity of the conditions for the onset and spread, increase the likelihood of equipment failures, but also complicate the crew's activities. The purpose of the study is to implement a prospective aircraft fire protection system that will increase the effectiveness of existing fire extinguishing equipment. The relevance of this research project lies in the creation of an aircraft fire-fighting system that will provide timely detection of overheating/fire in the nacelles of the main power unit, in the compartments of the auxiliary power unit, baggage and cargo compartments and aircraft toilets; reliability of information from fire detection and elimination systems; increase the effectiveness of existing firefighting equipment. Aim of research The aim of the study is to develop a future aircraft fire protection system that will increase the effectiveness of existing fire extinguishing equipment. The objectives of the research project are: 1. Choosing a hardware complex for electronic indication and signaling of the aircraft fire-fighting system; 2. Integration of the fire protection complex into the general aircraft equipment control system. Research methods Analysis of modern high-performance aircraft fire protection systems and creation of a promising fire protection system based on the data obtained Results In the course of this research project, a hardware complex for electronic indication and signaling of the aircraft fire system was selected, and the integration of the fire protection complex into the control system of general aircraft equipment was carried out.

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Smith, G. Allan, and George Meyer. "Aircraft automatic flight control system with model inversion." Journal of Guidance, Control, and Dynamics 10, no. 3 (1987): 269–75. http://dx.doi.org/10.2514/3.20213.

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Juang *, Jih-Gau, and Jern-Zuin Chio. "Fuzzy modelling control for aircraft automatic landing system." International Journal of Systems Science 36, no. 2 (2005): 77–87. http://dx.doi.org/10.1080/0020772042000325961.

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Juang, Jih Gau, and Shuai Ting Yu. "A Hybrid Intelligent System for Wind Shear Encountered Aircraft Landing Control." Applied Mechanics and Materials 764-765 (May 2015): 592–96. http://dx.doi.org/10.4028/www.scientific.net/amm.764-765.592.

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This paper presents sliding mode control (SMC) to aircraft automatic landing system (ALS), and uses genetic algorithm (GA), particle swarm optimization (PSO) and chaos particle swarm optimization (CPSO) to adjust controller parameters. When wind shear is encountered, the aircraft automatic landing system can not be used in such environment during serious wind speed changes. The proposed intelligent control scheme can help the pilots guide the aircraft to a safe landing in wind shear condition. PID control and cerebella model articulation controller (CMAC) are applied to the controller design.

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Tovkach, Serhii. "CUDA-інтеграція контурів керування авіаційного газотурбінного двигуна". Aerospace Technic and Technology, № 6 (27 листопада 2023): 31–39. http://dx.doi.org/10.32620/aktt.2022.6.04.

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The problem of accelerating the process of designing aircraft gas turbine engines and their control systems, the system "AIRCRAFT-AVIATION ENGINE-FUEL", and forming the technical type of an aircraft engine, adapting to new operating conditions within the framework of experimental design bureaus (EDB) and the industry is using automated systems with low computing performance and incomplete description. Information technologies for developing engines allow duplication and mismatch of data, loss of information and time during transmission and processing for making parametric and structural decisions. To better adaptation of the characteristics of an aviation engine (AE) to the tasks solved by an aircraft in flight, it is necessary to integrate control systems. Integrated control systems are especially effective for managing today's multi-mode aircraft. On the basis of their control, optimal control programs for the power plant (PP) are formed using the criteria for evaluating the effectiveness of the aircraft. This article proposes a paradigm for building integrated control loops for an aircraft gas turbine engine, which can be formed by automating control processes, an automatic control system, and combined control programs. The objective of this research is the processes of constructing adaptive control loops for aircraft gas turbine engines. The subject of this study is the adaptive control of aircraft gas turbine engines using embedded control loops and CUDA architecture. The goal is to improve the dynamic characteristics of an aircraft gas turbine engine through adaptive control using control loops, considering various aircraft flight modes and engine operating modes. Objectives: to determine the main controllable elements of an aircraft engine, adjustable parameters and factors for constructing control loops according to the principle of adaptation; describe the mechanism of joint management of gas turbine engines; to study the processes of building an integration circuit "aircraft - power plant" and develop the concept of an integrated ACS; define the CUDA paradigm for parallel computing of control loops. Conclusions. The scientific novelty lies in the formation of a paradigm for developing adaptive control models for gas turbine engines, considering different aircraft flight modes and engine operation modes.

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Lu, Ke, Hongyuan Tian, Pan Zhen, Senkui Lu, and Renliang Chen. "Conversion Flight Control for Tiltrotor Aircraft via Active Disturbance Rejection Control." Aerospace 9, no. 3 (2022): 155. http://dx.doi.org/10.3390/aerospace9030155.

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The tiltrotor aircraft consists of three primary flight modes, which are helicopter flight mode in low forward speed flight, airplane flight mode in high forward speed flight and conversion flight mode. This paper presents an active disturbance rejection controller for tiltrotor aircraft conversion flight. First, a tiltrotor aircraft flight dynamics model is developed and verified. Then, conversion flight control laws, designed via the active disturbance rejection control (ADRC) and sliding mode control (SMC) techniques, are proposed for the tiltrotor aircraft with model uncertainties and external disturbance, which are estimated with an extended state observer. Finally, the simulation of automatic conversion flight is carried out, which shows the effectiveness of the developed controller.

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Rogalski, Tomasz, Paweł Rzucidło, and Jacek Prusik. "Unmanned aircraft automatic flight control algorithm in a spin maneuver." Aircraft Engineering and Aerospace Technology 92, no. 8 (2020): 1215–24. http://dx.doi.org/10.1108/aeat-05-2019-0099.

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Purpose The paper aims to present an idea of automatic control algorithms dedicated to both small manned and unmanned aircraft, capable to perform spin maneuver automatically. This is a case of maneuver far away from so-called standard flight. The character of this maneuver and the range of aircraft flight parameters changes restrict application of standard control algorithms. Possibility of acquisition full information about aircraft flight parameters is limited as well in such cases. This paper analyses an alternative solution that can be applied in some specific cases. Design/methodology/approach The paper uses theoretical discussion and breakdowns to create basics for development of structures of control algorithms. Simplified analytical approach was applied to tune regulators. Results of research were verified in series of software-in-the loop, computer simulations. Findings The structure of the control system enabling aerobatic flight (spin flight as example selected) was found and the method how to tune regulators was presented as well. Practical implications It could be a fundament for autopilots working in non-conventional flight states and aircraft automatic recovery systems. Originality/value The paper presents author’s original approach to aircraft automatic control when high control precision is not the priority, and not all flight parameters can be precisely measured.

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Jiang, Xing Wei, Qi Dan Zhu, and Zi Xia Wen. "Receding Horizon Control on Automatic Landing Lateral Loop of Carrier-Based Aircraft." Applied Mechanics and Materials 300-301 (February 2013): 1610–16. http://dx.doi.org/10.4028/www.scientific.net/amm.300-301.1610.

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Since the angled deck is only tens miles width, the task of landing an aircraft on an aircraft carrier requires precise control, especially lateral loop. For this problem, this paper focuses on researching the aircraft automatic landing lateral control. In lateral control, the most crucial parts are controlling the off center distance and keeping the desired landing attitude. So firstly a nonlinear kinetic model of aircraft landing in lateral directional axis is established, and then transformed into error states. The controller is designed for an angle of attack of 11.7 deg and an airspeed of 40m/s, the equilibrium point. Receding horizon control methodology is employed to solve the aircraft lateral control problem. This controller is solved in MATLAB, and sent to the 3D simulation environment by network communication, to control the aircraft landing lateral loop. The simulation environment is programmed based on VC++ software. The simulation results show that receding horizon control method can achieve trajectory tracking and attitude tracking of nonlinear aircraft landing system.

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Szczepanski, Cezary, Mariusz Krawczyk, and Albert Zajdel. "The airplane trim system – new functionalities." Aircraft Engineering and Aerospace Technology 92, no. 9 (2020): 1401–6. http://dx.doi.org/10.1108/aeat-12-2019-0241.

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Purpose A standard automatic flight control system – autopilot – will become required equipment of the future aircraft, operating in the common sky. For a specific group of aircraft, they are too expensive and too energy-consuming solutions. This paper aims to present the concept of an automatic flight control system that overcomes those limitations. Design/methodology/approach The proposed automatic flight control system uses the trim tabs in all prime flight controlling surfaces: elevator, ailerons and rudder, for stabilizing and controlling the steady flights of an aircraft. Findings The results of an aeroplane flight controlled with the use of trim tabs simulation tests and remarks have been presented and discussed. The simulation was conducted in real-time hardware in the loop environment. The stabilization of the flight was achieved in performed test scenarios. Originality/value The possibility to control an aircraft with coordinated deflections of the trimming surfaces is a beneficial alternate to those currently used and can be recommended for use in the next-generation aircraft.

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Krawczyk, Mariusz, Cezary Jerzy Szczepanski, and Albert Zajdel. "Aircraft model for the automatic taxi directional control design." Aircraft Engineering and Aerospace Technology 91, no. 2 (2019): 289–95. http://dx.doi.org/10.1108/aeat-01-2018-0025.

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PurposeThis paper aims to present a concept of an automatic directional control system of remotely piloted aerial system (RPAS) during the taxiing phase. In particular, it shows the initial stages of the control laws synthesis-mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload.Design/methodology/approachThe adapted methodology follows the model-based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis. The computer simulations are carried out to analyse the model behaviour.FindingsChosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxiing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. Simulations allowed to compute the critical speeds for different taxiway conditions in a 90° turn.Practical implicationsThe results can be used for the taxi directional control law synthesis and simulation of the control system. The computed critical speeds can be treated as a safety limits.Originality/valueThe taxi directional control system has not been introduced to the RPAS yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle has a big value in the process of design and implementation of the future auto taxi systems. Moreover, computed speed safety limits can be used by designers and standards creators.

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Krawczyk, Mariusz, Cezary Jerzy Szczepanski, and Albert Zajdel. "Aircraft model for automatic taxi directional control system design." Aircraft Engineering and Aerospace Technology 91, no. 3 (2019): 477–83. http://dx.doi.org/10.1108/aeat-06-2018-0161.

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Purpose This paper aims to present a concept of an automatic directional control system of remotely piloted aerial system (RPAS) during the taxiing phase. In particular, it shows the initial stages of the control laws synthesis – mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload. Design/methodology/approach The adapted methodology follows the model-based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis. The computer simulations are carried out to analyse the model behaviour. Findings Chosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. Simulations allowed to compute the critical speeds for different taxiway conditions in a 90° turn. Practical implications The results can be used for the taxi directional control law synthesis and simulation of the control system. The computed critical speeds can be treated as safety limits. Originality/value The taxi directional control system has not been introduced to the RPAS yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle has a big value in the process of design and implementation of the future auto taxi systems. Moreover, computed speed safety limits can be used by designers and standard creators.

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Nee Jones, Lim Jen, Rini Akmeliawati, and Chee Pin Tan. "Aircraft Automatic Maneouvering System Using Energy-based Control Technique." IFAC Proceedings Volumes 41, no. 2 (2008): 1200–1205. http://dx.doi.org/10.3182/20080706-5-kr-1001.00207.

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Zhao, Yue, and J. Jim Zhu. "Automatic Aircraft Loss-of-Control Prevention by Bandwidth Adaptation." Journal of Guidance, Control, and Dynamics 40, no. 4 (2017): 878–89. http://dx.doi.org/10.2514/1.g001835.

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Cristian, VIDAN, and BADEA Silviu Ionut. "Longitudinal automatic control system for a light weight aircraft." INCAS BULLETIN 8, no. 4 (2016): 157–64. http://dx.doi.org/10.13111/2066-8201.2016.8.4.13.

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Lungu, Romulus, Mihai Lungu, and Lucian Teodor Grigorie. "Automatic Control of Aircraft in Longitudinal Plane During Landing." IEEE Transactions on Aerospace and Electronic Systems 49, no. 2 (2013): 1338–50. http://dx.doi.org/10.1109/taes.2013.6494418.

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Buryak, Yu I., M. P. Lyubovnikov, and K. A. Kolesnikov. "REAL-TIME CONTROL OF OPERATIONAL AND TECHNICAL PERFORMANCES OF THE AIRCRAFT GROUP." Vestnik komp'iuternykh i informatsionnykh tekhnologii, no. 188 (2020): 12–22. http://dx.doi.org/10.14489/vkit.2020.02.pp.012-022.

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The article deals with the issues of improving the efficiency of control of operational and technical characteristics of the aircraft group by ensuring the completeness, reliability and relevance of data collection on the results of their operation. Proposals have been formed to combine aircraft maintenance work and collect the necessary data in a single automated real-time process. New approaches to automation of information processes of aircraft technical operation on the basis of wide use of mobile computer devices, document flow in electronic form and means of automatic identification United by the corresponding software components are offered. Mathematical models, algorithms and supporting software have been developed. The methodical approach for the automated creation of software applications using the tools of the software and technology platform is considered. A software and hardware complex for collecting and monitoring real-time parameters of the technical condition and operational and technical characteristics of the aircraft group was developed, the main functions of its components and the scheme of interaction were determined. It is shown that the proposed methodological and software-technical solutions allow to provide an increase in the reliability and efficiency of the assessment of operational and technical characteristics of aircraft using both single and integrated (complex) indicators.

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Shibanov, G. P. "Automatic Control of Aircraft Engine in Conditions of Stand Test." Mekhatronika, Avtomatizatsiya, Upravlenie 21, no. 2 (2020): 86–92. http://dx.doi.org/10.17587/mau.21.86-92.

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The general principles of automatic control of aircraft engines and functionally related systems in the conditions of their stand tests are suggested. These principles are prospectively reduced to six sequentially implemented procedures or steps. In accordance with these principles, the control of aircraft engine parameters is carried out by a computer-aided test equipment (CTE) based on a computer complex that implements algorithms based on Boolean algebra and the algebra of events and states. These algorithms allow control procedures to be carried out in dynamic mode in accordance with the schedule of testing an aircraft engine. With this control, the specified sequence of operating modes of the aircraft engine undergoing testing is observed without fixing them in time and with the possibility of skipping or repeating individual modes. Parameters are monitored at each of the next aircraft engine operating modes only after all parameters are checked in the previous mode and the value of the main determining parameter reaches the value determined for this mode. During the period of transient processes, parameters are controlled only at the points of extremum of the values of the main determining parameter with fixing the time of transient processes and determining that. "In the tolerance" or "not in the tolerance" is the checked parameter and the fixed time interval. Upon arrival of the signals from the monitoring object, the time of occurrence of which is unknown, and only the time interval during which they can appear is known, any of the CTE operation modes are terminated, tolerance control of the parameters provided by the program is performed, and the previously interrupted mode is restored. Simultaneously with the tolerance control of the parameters, the time of arrival of the above signals is recorded. The group of emergency parameters is monitored continuously throughout the entire period of stand test.

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Yang, Wenqi, Siyu Zhou, Jianhua Lu, and Liting Song. "Longitudinal Control Technology for Automatic Carrier Landing Based on Model-compensated Active Disturbance Rejection Control." Journal of Physics: Conference Series 2477, no. 1 (2023): 012095. http://dx.doi.org/10.1088/1742-6596/2477/1/012095.

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Abstract Carrier aircraft landing is a system engineering with strong nonlinear, strong coupling, and complex environmental interference. Landing control is one of the key technologies for carrier aircraft landing, which directly affects the success of the landing. A longitudinal decoupling control method based on Model Compensated Linear Active Disturbance Rejection Control (MCC-LADRC) is proposed for tracking the deck motion and maintaining the attack angle in the final stage of the carrier landing. The simulation results show that compared with the PID control and traditional LADRC strategy, the MCC-LADRC method can not only control the carrier aircraft to track the deck motion synchronously and accurately, improve the landing accuracy and anti-disturbance capability but also has a good attack angle retention effect and eliminate the coupling between the pitch angle and the attack angle.

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Brukarczyk, Bartłomiej, Dariusz Nowak, Piotr Kot, Tomasz Rogalski, and Paweł Rzucidło. "Fixed Wing Aircraft Automatic Landing with the Use of a Dedicated Ground Sign System." Aerospace 8, no. 6 (2021): 167. http://dx.doi.org/10.3390/aerospace8060167.

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The paper presents automatic control of an aircraft in the longitudinal channel during automatic landing. There are two crucial components of the system presented in the paper: a vision system and an automatic landing system. The vision system processes pictures of dedicated on-ground signs which appear to an on-board video camera to determine a glide path. Image processing algorithms used by the system were implemented into an embedded system and tested under laboratory conditions according to the hardware-in-the-loop method. An output from the vision system was used as one of the input signals to an automatic landing system. The major components are control algorithms based on the fuzzy logic expert system. They were created to imitate pilot actions while landing the aircraft. Both systems were connected with one another for cooperation and to control an aircraft model in a simulation environment. Selected results of tests presenting control efficiency and precision are shown in the final section of the paper.

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Wu, Jian Jun, Wei Wan, and Peng Wu. "Design of Aircraft Electrical Load Management Center." Advanced Materials Research 268-270 (July 2011): 546–51. http://dx.doi.org/10.4028/www.scientific.net/amr.268-270.546.

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Aircraft Electrical Load Management Center, an important part of the aircraft power supply system, solves the automatic management of aircraft load via a multi-channel transmission bus and a solid-state power controller. Using micro-computer technology, instead of manual operation, for automatic control and management of the load has improved the existing method of distribution and load management, which has enhanced performance of aircraft and its maintenance of power system. This paper studies the overall structure and composition principle of ELMC and details ELMC’s functions of each component modules and the implementation of hardware and software. System test results show that the automatic load management techniques greatly improve the aircraft power system reliability and maintainability.

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Su, Te-Jen, Kun-Liang Lo, Feng-Chun Lee, and Yuan-Hsiu Chang. "Aircraft approaching service of terminal control based on fuzzy control." International Journal of Modern Physics B 34, no. 22n24 (2020): 2040142. http://dx.doi.org/10.1142/s0217979220401426.

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Aircraft approaching is the most dangerous phase in every complete flight. To solve the pressure of air traffic controllers and the landings delayed problems caused by the huge air traffic flow in Terminal Control Area (TCA), an automatic Air Traffic Control (ATC) instructions system is initially designed in this paper. It applies the fuzzy theory to make instant and appropriate decisions which can be transmitted via Controller-Pilot Datalink Communications (CPDLC). By means of the designed system, the decision-making time can be saved and the human factors can be reduced to avoid the flight accidents and further delays in aircraft approaching.

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Gallimore, Jennie J., James McCracken, and Janet Gerace. "Hardware and Human Factors Issues for Military Automatic Brightness Controls." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 39, no. 1 (1995): 89–92. http://dx.doi.org/10.1177/154193129503900121.

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Electronic displays have replaced many mechanical displays in aircraft. The “glass” cockpit continues to advance. Electronic displays required adjustment of luminance (often referred to as brightness) and contrast as the ambient environment changes. Requiring pilots to manually control brightness creates additional pilot workload. Instead, automatic brightness controls (ABCs) have been suggested. The purpose of this paper is to summarize a research plan for the development of an ABC for military aircraft.

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Juang, Jih Gau, Chung Ju Cheng, and Teng Chieh Yang. "Wind Shear Encountered Landing Control Based on CMACs." Applied Mechanics and Materials 284-287 (January 2013): 2351–55. http://dx.doi.org/10.4028/www.scientific.net/amm.284-287.2351.

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This paper presents an intelligent control scheme that uses different cerebellar model articulation controllers (CMACs) in aircraft automatic landing control. The proposed intelligent control system can act as an experienced pilot and guide the aircraft landed safely in wind shear condition. Lyapunov theory is applied to obtain adaptive learning rule and stability analysis is also provided. Furthermore, the proposed controllers are implemented in a DSP. The simulations by MatLab are demonstrated.

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Liang, Jianjian, Shoukun Wang, and Bo Wang. "Online Motion Planning for Fixed-Wing Aircraft in Precise Automatic Landing on Mobile Platforms." Drones 7, no. 5 (2023): 324. http://dx.doi.org/10.3390/drones7050324.

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This paper proposes the creative idea that an unmanned fixed-wing aircraft should automatically adjust its 3D landing trajectory online to land on a given touchdown point, instead of following a pre-designed fixed glide slope angle or a landing path composed of two waypoints. A fixed-wing aircraft is a typical under-actuated and nonholonomic constrained system, and its landing procedure—which involves complex kinematic and dynamic constraints—is challenging, especially in some scenarios such as landing on an aircraft carrier, which has a runway that is very short and narrow. The conventional solution of setting a very conservative landing path in advance and controlling the aircraft to follow it without dynamic adjustment of the reference path has not performed satisfactorily due to the variation in initial states and widespread environmental uncertainties. The motion planner shown in this study can adjust an aircraft’s landing trajectory online and guide the aircraft to land at a given fixed or moving point while conforming to the strict constraints. Such a planner is composed of two parts: one is used to generate a series of motion primitives which conform to the dynamic constraints, and the other is used to evaluate those primitives and choose the best one for the aircraft to execute. In this paper, numerical simulations demonstrate that when given a landing configuration composed of position, altitude, and direction, the planner can provide a feasible guidance path for the aircraft to land accurately.

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Jiang, Junxia, Chen Bian, Yunbo Bi, and Yinglin Ke. "A new type of inner-side working head for automatic drilling and riveting system." Assembly Automation 39, no. 1 (2019): 154–64. http://dx.doi.org/10.1108/aa-09-2017-107.

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PurposeThe purpose of this paper is to design, analyze and optimize a new type of inner-side working head for automatic horizontal dual-machine cooperative drilling and riveting system. The inner-side working head is the key component of automatic drilling and riveting system, and it is a challenge to design an inner-side working head which must be stiffness and stable with a compact structure to realize its functions.Design/methodology/approachAccording to the assembly structure features of large aircraft panels and riveting process requirements, a new type of inner-side working head is designed for pressure riveting. The force condition of the inner-side working head during the riveting process is analyzed and the deformation model is established. Design optimization is performed based on genetic algorithm and finite element analysis. The optimized inner-side working head is tested with automatic horizontal dual-machine cooperative drilling and riveting system.FindingsThe deformation model provides the precision compensation basis for control system. Application test results show that the automatic drilling and riveting system can realize assembly of large aircraft panel with high efficiency and quality through the inner-side working head.Research limitations/implicationsThe inner-side working head has been used in aircraft panel assembly.Practical implicationsThe inner-side working head has been used in aircraft panel assembly.Originality/valueThis paper presents the design, analysis and optimization of a new type of inner-side working head which can realize automatic riveting for aircraft panel. The research will promote the automation of aircraft panel assembly.

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Yepifanov, Sergiy. "Aircraft Turbine Engine Automatic Control Based on Adaptive Dynamic Models." Transactions on Aerospace Research 2020, no. 4 (2020): 61–70. http://dx.doi.org/10.2478/tar-2020-0021.

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Abstract One of the most perspective development directions of the aircraft engine is the application of adaptive digital automatic control systems (ACS). The significant element of the adaptation is the correction of mathematical models of both engine and its executive, measuring devices. These models help to solve tasks of control and are a combination of static models and dynamic models, as static models describe relations between parameters at steady-state modes, and dynamic ones characterize deviations of the parameters from static values. The work considers problems of the models’ correction using parametric identification methods. It is shown that the main problem of the precise engine simulation is the correction of the static model. A robust procedure that is based on a wide application of a priori information about performances of the engine and its measuring system is proposed for this purpose. One of many variants of this procedure provides an application of the non-linear thermodynamic model of the working process and estimation of individual corrections to the engine components’ characteristics with further substitution of the thermodynamic model by approximating on-board static model. Physically grounded estimates are obtained based on a priori information setting about the estimated parameters and engine performances, using fuzzy sets. Executive devices (actuators) and the most inertial temperature sensors require correction to their dynamic models. Researches showed, in case that the data for identification are collected during regular operation of ACS, the estimates of dynamic model parameters can be strongly correlated that reasons inadmissible errors. The reason is inside the substantial limitations on transients’ intensity that contain regular algorithms of acceleration/deceleration control. Therefore, test actions on the engine are required. Their character and minimum composition are determined using the derived relations between errors in model coefficients, measurement process, and control action parameters.

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Tianchang, Liu. "Composition and Application of Aircraft Towing Tractor Automatic Control System." Engineering and Applied Sciences 4, no. 6 (2019): 190. http://dx.doi.org/10.11648/j.eas.20190406.17.

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Zhen, Ziyang, Chaojun Yu, Shuoying Jiang, and Ju Jiang. "Adaptive Super-Twisting Control for Automatic Carrier Landing of Aircraft." IEEE Transactions on Aerospace and Electronic Systems 56, no. 2 (2020): 984–97. http://dx.doi.org/10.1109/taes.2019.2924134.

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Akmeliawati, Rini, and Iven M. Y. Mareels. "Nonlinear Energy-Based Control Method for Aircraft Automatic Landing Systems." IEEE Transactions on Control Systems Technology 18, no. 4 (2010): 871–84. http://dx.doi.org/10.1109/tcst.2009.2030788.

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Lungu, Romulus, and Mihai Lungu. "Automatic Control of Aircraft in Lateral-Directional Plane During Landing." Asian Journal of Control 18, no. 2 (2015): 433–46. http://dx.doi.org/10.1002/asjc.1133.

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Wang, Xudong, Yuanjun Sang, and Guangrui Zhou. "Combining Stable Inversion and H∞ Synthesis for Trajectory Tracking and Disturbance Rejection Control of Civil Aircraft Autolanding." Applied Sciences 10, no. 4 (2020): 1224. http://dx.doi.org/10.3390/app10041224.

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The landing phase during a flight probably is the most dangerous part, as most of the accidents occur in this phase. A robust trajectory tracking controller is presented to autoland a civil aircraft subjected to severe wind disturbances to improve the aircraft’s safety. Firstly, the dynamic models of the aircraft and windshear are built. Secondly, a stable inversion (SI) based robust autolanding controller (SIRAC) is proposed. In this architecture, the SI algorithm is used to improve the output tracking precision, while the H ∞ synthesis is applied for enhancing robust stability against uncertainties caused by wind disturbances. Finally, two scenario simulations are carried out for the automatic landing control of a large civil aircraft. Significant performances on the system have been achieved without any disturbance. In addition to that, the proposed SIRAC can also track the desired autolanding trajectory with high precision, even under large wind condition.

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Pachter, M., and E. B. Nelson. "Reconfigurable flight control." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 4 (2005): 287–319. http://dx.doi.org/10.1243/095441005x30243.

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Indirect adaptive control for reconfigurable flight control is advocated. Specifically, online static system identification using a moving window/batch estimation is implemented. The ensuing linear regression is augmented with an intercept. The intercept parameter is included to address the effects of trim change associated with the occurrence of a control surface failure. Parameter estimate information is used to adjust the inner loop's control gains, and a command derived from the intercept estimate is fed forward to automatically retrim the aircraft. The tracking performance of this automatic retrimming method, which relies on system identification, surpasses the conventional approach of exclusively relying on integral action for retrimming. These adaptive and reconfigurable flight control concepts are illustrated in the context of a fighter aircraft's pitch plane dynamics. The novel adaptive and reconfigurable flight control system successfully handles a 50 per cent horizontal tail control surface loss.

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Prusik, Jacek, and Tomasz Rogalski. "Automatic removal of the plane from a spin using fuzzy logic controller." Transportation Overview - Przeglad Komunikacyjny 2019, no. 2 (2019): 45–53. http://dx.doi.org/10.35117/a_eng_19_02_04.

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The paper presents a concept of automatic control system recovering an aircraft from the spin using fuzzy logic controller. Control system causing: stall, spin, spin recovery, dive recovery and switching on classic heading and altitude autopilots, was created in Matlab – Simulink software, which was connected to the flight simulator X-Plane. During tests developed control algorithms were checked and tuned. At the end graphs of flight parameters recorded during simulation were analyzed, and properties of designed control system were evaluated. Particular attention was paid to the design of a fuzzy logic controller stopping autorotation of the aircraft. On the output it controlled the position of the rudder, while on input it received a signal being a function of the angular velocity of the aircraft.

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Jia, Baoxu, Liguo Sun, Xiaoyu Liu, Shuting Xu, Wenqian Tan, and Junkai Jiao. "Carrier Aircraft Flight Controller Design by Synthesizing Preview and Nonlinear Control Laws." Drones 7, no. 3 (2023): 200. http://dx.doi.org/10.3390/drones7030200.

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This paper proposes an innovative automatic carrier landing control law for carrier-based aircraft considering complex ship motion and wind environment. Specifically, a strategy is proposed to synthesize preview control with an adaptive nonlinear control scheme. Firstly, incremental nonlinear backstepping control law is adopted in the attitude control loop to enhance the anti-disturbance capability of the aircraft. Secondly, to enhance the glide slope tracking performance under severe sea conditions, the carrier motion is predicted, and the forecasted motion is adopted in an optimal preview control guidance law to compensate influences induced by carrier motion. However, synthesizing the inner-loop and outer-loop control is not that straightforward since the preview control is naturally an optimal control law which requires a state-space model. Therefore, low-order equivalent fitting of the attitude-to-altitude high-order system model needs to be performed; furthermore, a state observer needs to be designed for the low-order equivalent system to supply required states to the landing controller. Finally, to validate the proposed methodology, an unmanned tailless aircraft model is used to perform the automatic landing tasks under variant sea conditions. Results show that the automatic carrier landing system can lead to satisfactory landing precision and success rate even under severe sea conditions.

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SHAO Min min, 邵敏敏, 龚华军 GONG Hua jun, 甄子洋 ZHEN Zi yang, and 江. 驹. JIANG Ju. "An H2 Preview Control Based Automatic Landing Control Method for Carrier Based Aircraft." Electronics Optics & Control 22, no. 9 (2015): 68–71. http://dx.doi.org/10.3788/m0005220152209.0068.

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Journal articles on the topic 'Aircraft - Automatic Control'

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