Artykuły w czasopismach: „Automatic landing”

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Liu, Mao Han, Chun Tao Li i Yi Wang. "UAV Automatic Landing Control Law". Advanced Materials Research 383-390 (listopad 2011): 1452–57. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.1452.

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Landing is the most important stage of the Flight of UAV, the study of automatic landing of UAVs has important engineering significance. In this paper, the UAV landing trajectory is divided into approach phase, steep glide phase and flare phase; a cascade control structure controller of height tracking was applied and the landing control law was designed. The digital simulation was done in the MATLAB / simulink environment. The results of simulation indicated that UAV can track the designed landing trajectory very well under the control law of automatic landing and safe landing can be achieved.

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Ghous, Hamid, Mubasher H. Malik, Dania Majeed, Fathima Nuzha Mohamed i Ayesha Nasir. "Evaluation of Safe Landing Site Detection Methods for Unmanned Aerial Vehicles". VAWKUM Transactions on Computer Sciences 11, nr 1 (28.06.2023): 281–94. http://dx.doi.org/10.21015/vtcs.v11i1.1474.

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Nowadays, aerial vehicles (drones) are becoming more popular. Over the past few years, Unmanned Aerial Vehicles (UAVs) have been used in various remote sensing applications. Every aerial vehicle is now either partially or completely automated. The tiniest type of aerial vehicle is the UAV. The widespread use of aerial drones requires numerous safe landing site detection techniques. The paper aims to review literature on techniques for automatic safe landing of aerial drone vehicles by detecting suitable landing sites, considering factors such as ground surfaces and using image processing methods. A drone must determine whether the landing zones are safe for automatic landing. Onboard visual sensors provide potential information on outdoor and indoor ground surfaces through signals or images. The optimal landing locations are then determined from the input data using various image processing and safe landing area detection (SLAD) methods. UAVs are acquisition systems that are quick, efficient, and adaptable. We discuss existing safe landing detection approaches and their achievements. Furthermore, we focus on possible areas for improvement, strength, and future approaches for safe landing site detection. The research addresses the increasing need for safe landing site detection techniques in the widespread use of aerial drones, allowing for automated and secure landing operations.

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Rashmi Koushik et al.,, Rashmi Koushik et al ,. "Automatic Landing Control System". International Journal of Mechanical and Production Engineering Research and Development 10, nr 3 (2020): 7639–50. http://dx.doi.org/10.24247/ijmperdjun2020726.

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Caro Fuentes, Vincenzo, Ariel Torres, Danny Luarte, Jorge E. Pezoa, Sebastián E. Godoy, Sergio N. Torres i Mauricio A. Urbina. "Digital Classification of Chilean Pelagic Species in Fishing Landing Lines". Sensors 23, nr 19 (29.09.2023): 8163. http://dx.doi.org/10.3390/s23198163.

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Fishing landings in Chile are inspected to control fisheries that are subject to catch quotas. The control process is not easy since the volumes extracted are large and the numbers of landings and artisan shipowners are high. Moreover, the number of inspectors is limited, and a non-automated method is utilized that normally requires months of training. In this work, we propose, design, and implement an automated fish landing control system. The system consists of a custom gate with a camera array and controlled illumination that performs automatic video acquisition once the fish landing starts. The imagery is sent to the cloud in real time and processed by a custom-designed detection algorithm based on deep convolutional networks. The detection algorithm identifies and classifies different pelagic species in real time, and it has been tuned to identify the specific species found in landings of two fishing industries in the Biobío region in Chile. A web-based industrial software was also developed to display a list of fish detections, record relevant statistical summaries, and create landing reports in a user interface. All the records are stored in the cloud for future analyses and possible Chilean government audits. The system can automatically, remotely, and continuously identify and classify the following species: anchovy, jack mackerel, jumbo squid, mackerel, sardine, and snoek, considerably outperforming the current manual procedure.

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Bykov, V. A., S. M. Velikovskiy, A. E. Parnenkov i S. M. Shulgin. "Approach to forming of assessment of probability of making a landing of the unmanned aerial vehicle of helicopter type on the runway platform of the ship taking into account different operational modes". Radio industry (Russia) 31, nr 2 (7.07.2021): 7–14. http://dx.doi.org/10.21778/2413-9599-2021-31-2-7-14.

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Problem statement. Now taking-off and landings of human powered helicopters to runway site of the ship, provides the Palubnik-1 complex interacting with other systems of the ship. At the same time creation of system of take off and landing of unmanned aerial vehicles of helicopter type should be made about use of regular aerotechnical means of the ship. In article proposed options of use of the automatic and automated landing system as for piloted, and unmanned aerial vehicles of helicopter type in different operational modes.Objective. To offer approach to forming of technique of assessment of probability of making a landing of the unmanned aerial vehicle of helicopter type depending on its technical appearance that will allow to lower development costs and carrying out natural tests.Results. On the basis of proposed options of ensuring landing the analysis of several appearances of unmanned aerial vehicles of helicopter type is carried out, some of their parameters are provided and also landing probability depending on the angle of rolling motion is evaluated.Practical implications. The offered approach allows to evaluate making a landing probability depending on the made technical solutions and also at set of enough statistical data to make adaptation of these decisions on other flight vehicles.

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Plinge, Walter R. "Automatic Approach and Landing Systems". Measurement and Control 36, nr 6 (lipiec 2003): 176–80. http://dx.doi.org/10.1177/002029400303600603.

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Nowak, Dariusz, Grzegorz Kopecki, Damian Kordos i Tomasz Rogalski. "The PAPI Lights-Based Vision System for Aircraft Automatic Control during Approach and Landing". Aerospace 9, nr 6 (25.05.2022): 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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Parkinson, B. W., i K. T. Fitzgibbon. "Aircraft Automatic Landing Systems Using GPS". Journal of Navigation 42, nr 1 (styczeń 1989): 47–59. http://dx.doi.org/10.1017/s0373463300015083.

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abstractThis paper is based on a presentation made at the IAIN International Navigation Congress held in Sydney, Australia, in February 1988.The global positioning system (GPS) offers a new opportunity for the automation of aircraft landing systems. The position and velocity measurements provided by a state-of-the-art GPS receiver using the C/A code and working in a normal or differential mode (D-GPS) and aided by one or two ground-based PseudoLites (PLS), may be able to satisfy the landing accuracy requirements of the FA A.This paper describes the design and simulation of an aircraft automatic landing system. Aircraft position and velocity are assumed to be measured using a (carrier-tracking) GPS receiver. The hypothesized capability is based on measurements taken at Stanford and elsewhere, using the Trimble 4000SX, five-channel receiver in an integrated-doppler-aiding mode. For some of the autopilot designs, either ground-based GPS transmitters (pseudolites) or a radar altimeter have also been incorporated.Included in the landing simulations are wind shears and a gust model, creating realistic landing situations. The performances of the lateral and vertical displacements are presented with their 1σ r.m.s. estimation errors during the glide-slope and flare phases. Included are different wind conditions, GPS configurations and controllers. The results are compared with the FAA requirements for various categories of automatic landing systems.

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Bubeev, Yu A., V. M. Usov, B. I. Kryuchkov, A. A. Oboznov, M. V. Mikhaylyuk i V. I. Zhelonkin. "VIRTUAL PROTOTYPING OF HELICOPTER-TYPE SPACECRAFT RADAR LANDING FOR UNDERSTANDING WHEN COSMONAUTS MAY TAKE A DECISION TO LAND A LUNAR MODULE MANUALLY". Aerospace and Environmental Medicine 56, nr 1 (2022): 32–46. http://dx.doi.org/10.21687/0233-528x-2022-56-1-32-46.

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The paper presents a computer toolset to simulate situations in which a cosmonaut has to decide on whether to choose an automated or vision assisted manual landing. A computer experiment was designed to reproduce lunar landscapes observed by cosmonauts from the landing module. Methodology of the virtual prototyping of landing on to the Moon was formulated in terms of visual environment mapping to the information need of cosmonauts. The mission critical point of decision-making on how to control landing was specified. Analysis of vertical takeoff and landing of both piloted and automatic space vehicles made possible description of navigation in low visibility, and substantiation of the use of 2D/3D synthetic vision systems in simulation of manual landing a helicopter-type vehicle in low visibility.

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Liu, Hengxi, Yongzhi Wang, Shibo Wen, Jianzhong Liu, Jiaxiang Wang, Yaqin Cao, Zhiguo Meng i Yuanzhi Zhang. "A New Blind Selection Approach for Lunar Landing Zones Based on Engineering Constraints Using Sliding Window". Remote Sensing 15, nr 12 (19.06.2023): 3184. http://dx.doi.org/10.3390/rs15123184.

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Deep space exploration has risen in interest among scientists in recent years, with soft landings being one of the most straightforward ways to acquire knowledge about the Moon. In general, landing mission success depends on the selection of landing zones, and there are currently few effective quantitative models that can be used to select suitable landing zones. When automatic landing zones are selected, the grid method used for data partitioning tends to miss potentially suitable landing sites between grids. Therefore, this study proposes a new engineering-constrained approach for landing zone selection using LRO LOLA-based slope data as original data based on the sliding window method, which solves the spatial omission problem of the grid method. Using the threshold ratio, mean, coefficient of variation, Moran’s I, and overall rating, this method quantifies the suitability of each sliding window. The k-means clustering algorithm is adopted to determine the suitability threshold for the overall rating. The results show that 20 of 22 lunar soft landing sites are suitable for landing. Additionally, 43 of 50 landing sites preselected by the experts (suitable landing sites considering a combination of conditions) are suitable for landing, accounting for 90.9% and 86% of the total number, respectively, for a window size of 0.5° × 0.5°. Among them, there are four soft landing sites: Surveyor 3, 6, 7, and Apollo 15, which are not suitable for landing in the evaluation results of the grid method. However, they are suitable for landing in the overall evaluation results of the sliding window method, which significantly reduces the spatial omission problem of the grid method. In addition, four candidate landing regions, including Aristarchus Crater, Marius Hills, Moscoviense Basin, and Orientale Basin, were evaluated for landing suitability using the sliding window method. The suitability of the landing area within the candidate range of small window sizes was 0.90, 0.97, 0.49, and 0.55. This indicates the capacity of the method to analyze an arbitrary range during blind landing zone selection. The results can quantify the slope suitability of the landing zones from an engineering perspective and provide different landing window options. The proposed method for selecting lunar landing zones is clearly superior to the gridding method. It enhances data processing for automatic lunar landing zone selection and progresses the selection process from qualitative to quantitative.

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Brukarczyk, Bartłomiej, Dariusz Nowak, Piotr Kot, Tomasz Rogalski i Paweł Rzucidło. "Fixed Wing Aircraft Automatic Landing with the Use of a Dedicated Ground Sign System". Aerospace 8, nr 6 (16.06.2021): 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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Essuri, M., K. Alkurmaji i A. Ghmmam. "Developing a Dynamic Model for Unmanned Aerial Vehicle Motion on Ground during Takeoff Phase". Applied Mechanics and Materials 232 (listopad 2012): 561–67. http://dx.doi.org/10.4028/www.scientific.net/amm.232.561.

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Modeling of take-off and landing motion for a fixed wing (UAV) is necessary for developing an automatic take off and landing control system (ATOL). Automatic take off and landing system becomes an important system due to wide spread of unmanned aerial vehicles in different applications ranging from intelligence, surveillance, up to missile firing. Automatic take off and landing system reduces damage to an unmanned aerial vehicle and its payload that may be caused by human pilot errors. Furthermore, training human pilot to a sufficient level of skill and experience for takeoff and landing may take several years and significant cost. A human pilot also may impose additional restrictions for UAV operation especially at night time or dusty desert conditions. Although, ATOL adds complexity to the system, it reduces the long run cost and risk caused by takeoff and landing process, and makes UAV takeoff from different runways and at different atmospheric conditions. A mathematical model for takeoff is successfully developed for a small fixed wing UAV. A Matlab/Simulink simulation model is prepared for the ground roll phase, and some simulation results are also shown.

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Petrishchev, V. F. "Energy-Saving Algorithm of Automatic Control of Compulsory Passenger Carrier Landing. Part 1". Mekhatronika, Avtomatizatsiya, Upravlenie 19, nr 11 (8.11.2018): 725–33. http://dx.doi.org/10.17587/mau.19.725-733.

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The task was to develop an automatic landing system (ALS) for a passenger carrier that can be externally activated and excludes the possibility of the crew’s interference into the landing process, for example, when a carrier alters its nominal course or there is no contact with the crew. The air crush history saw a lot of cases that could have been prevented if the planes had had an ALS system and airports had had possibilities to activate that system and suspend the crew from flight control. One of such unforgettable examples is the New-York tragedy of September 11, 2001. State-of-the-art technology allows solving the problem of automatic carrier landing. The most remarkable example demonstrating solution of this problem is the automatic landing of the Buran orbiter 30 years ago on November 15, 1988. The article consists of two sections. The first section of the article deals with conditions of effective solution of autoland problem. It describes in short, the flight modes during automatic landing control. To solve the problem of automatic longitudinal control in the most crucial final landing mode, the author proposes an energy-saving control algorithm that provides control in the mode of negative feedback. The system status vector comprises six parameters: range, altitude, pitch angle, and their first-order derivatives. The control algorithm is developed for the Tupolev TU-154M airliner. In development of the algorithm, the following assumptions were used: a) a linear model of dependence of aerodynamic data on the angle of attack; b) a linear model of programmed switch of engine thrust to the idle mode on the interval of 3 seconds from the beginning of the flareout; c) a pitch angular acceleration, occurring at elevator rate reversal, as a control signal; d) the frequency of the control algorithm operation equal to 200 Hz. The second section further analyzes characteristics of the energy-saving algorithm of automatic control of compulsory passenger carrier landing during the final landing phase, which was developed in the first section. The author developed a model program of control and mathematically modeled the carrier landing phases. When switching from one phase to another, the motion parameters were concatenated so that the final motion parameters of the previous phase became the initial motion parameters of the next phase. The author also studied the influence of errors in aerodynamic data on the landing conditions. The modeling revealed that if a pitch deflection direction is used for the determination of phases, then in a general case, the landing mode consists not of two traditionally determined phases, but of the following three: pitch angle increase (flareout), pitch angle decrease (float), and again, pitch angle increase (this phase is called ‘maintenance’). The necessity to introduce the third phase is determined by the presence of errors in the aerodynamic data of the airplane. On the whole, it is confirmed that the energy saving control algorithm provides successful solution of the problem of automatic landing of a passenger carrier at its final flight phase. At that, it is determined that the landing mode does not exceed 5s.

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Petrishchev, V. F. "Energy-Saving Algorithm of Automatic Control of Compulsory Passenger Carrier Landing. Part II". Mekhatronika, Avtomatizatsiya, Upravlenie 19, nr 12 (8.12.2018): 788–96. http://dx.doi.org/10.17587/mau.19.788-796.

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The task was to develop an automatic landing system (ALS) for a passenger carrier that can be externally activated and excludes the possibility of the crew’s interference into the landing process, for example, when a carrier alters its nominal course or there is no contact with the crew. The air crush history saw a lot of cases that could have been prevented if the planes had had an ALS system and airports had had possibilities to activate that system and suspend the crew from flight control. One of such unforgettable examples is the New-York tragedy of September 11, 2001. State-of-the-art technology allows solving the problem of automatic carrier landing. The most remarkable example demonstrating solution of this problem is the automatic landing of the Buran orbiter 30 years ago on November 15, 1988. The article consists of two sections. The first section of the article deals with conditions of effective solution of autoland problem. It describes in short, the flight modes during automatic landing control. To solve the problem of automatic longitudinal control in the most crucial final landing mode, the author proposes an energy-saving control algorithm that provides control in the mode of negative feedback. The system status vector comprises six parameters: range, altitude, pitch angle, and their first-order derivatives. The control algorithm is developed for the Tupolev TU-154M airliner. In development of the algorithm, the following assumptions were used: a) a linear model of dependence of aerodynamic data on the angle of attack; b) a linear model of programmed switch of engine thrust to the idle mode on the interval of 3 seconds from the beginning of the flareout; c) a pitch angular acceleration, occurring at elevator rate reversal, as a control signal; d) the frequency of the control algorithm operation equal to 200 Hz.The second section further analyzes characteristics of the energy-saving algorithm of automatic control of compulsory passenger carrier landing during the final landing phase, which was developed in the first section. The author developed a model program of control and mathematically modeled the carrier landing phases. When switching from one phase to another, the motion parameters were concatenated so that the final motion parameters of the previous phase became the initial motion parameters of the next phase. The author also studied the influence of errors in aerodynamic data on the landing conditions. The modeling revealed that if a pitch deflection direction is used for the determination of phases, then in a general case, the landing mode consists not of two traditionally determined phases, but of the following three: pitch angle increase (flareout), pitch angle decrease (float), and again, pitch angle increase (this phase is called ‘maintenance’). The necessity to introduce the third phase is determined by the presence of errors in the aerodynamic data of the airplane. On the whole, it is confirmed that the energy saving control algorithm provides successful solution of the problem of automatic landing of a passenger carrier at its final flight phase. At that, it is determined that the landing mode does not exceed 5 s.

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Juang, Jih Gau, i Shuai Ting Yu. "A Hybrid Intelligent System for Wind Shear Encountered Aircraft Landing Control". Applied Mechanics and Materials 764-765 (maj 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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Jiang, Xing Wei, Qi Dan Zhu i Zi Xia Wen. "Receding Horizon Control on Automatic Landing Lateral Loop of Carrier-Based Aircraft". Applied Mechanics and Materials 300-301 (luty 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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Ryabinov, Artyom V., Anton I. Saveliev i Dmitriy A. Anikin. "Modeling the influence of external influences on the process of automated landing of a UAV-quadcopter on a moving platform using technical vision". Modeling and Analysis of Information Systems 30, nr 4 (11.12.2023): 366–81. http://dx.doi.org/10.18255/1818-1015-2023-4-366-381.

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This article describes a series of experiments in the Gazebo simulation environment aimed at studying the influence of external weather conditions on the automatic landing of an unmanned aerial vehicle (UAV) on a moving platform using computer vision and a previously developed control system based on PID and polynomial controllers. As part of the research, methods for modeling external weather conditions were developed and landing tests were carried out simulating weather conditions such as wind, light, fog and precipitation, including their combinations. In all experiments, successful landing on the platform was achieved; during the experiments, landing time and its accuracy were measured. The graphical and statistical analysis of the obtained results revealed the influence of illumination, precipitation and wind on the UAV landing time, and the introduction of wind into the simulation under any other external conditions led to the most significant increase in landing time. At the same time, the study failed to identify a systemic negative influence of external conditions on landing accuracy. The results obtained provide valuable information for further improvement of autonomous automatic landing systems for UAVs without the use of satellite navigation systems.

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Cristiana Voicu, Serena, i Florentin Alin Buţu. "H-Infinity Design for Automatic Landing System". International Journal of Modeling and Optimization 7, nr 3 (czerwiec 2017): 173–78. http://dx.doi.org/10.7763/ijmo.2017.v7.579.

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Saiki, H., T. Fukao i T. Kohno. "Automatic Landing Control of Outdoor Blimp Robots". IFAC Proceedings Volumes 42, nr 16 (2009): 32–37. http://dx.doi.org/10.3182/20090909-4-jp-2010.00008.

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Liao, Fang, Jian Liang Wang, Eng Kee Poh i Dong Li. "Fault-Tolerant Robust Automatic Landing Control Design". Journal of Guidance, Control, and Dynamics 28, nr 5 (wrzesień 2005): 854–71. http://dx.doi.org/10.2514/1.12611.

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Rithirun, Chart, i Pitikhate Sooraksa. "Automatic Landing Controller of Unmanned Aerial Vehicle". Advanced Materials Research 677 (marzec 2013): 442–48. http://dx.doi.org/10.4028/www.scientific.net/amr.677.442.

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This paper presents the soft control strategies for automatic landing of Unmanned Aerial Vehicle and simulation the result of controller. The soft controller parameters can be modify and show off the results response of control surface of Unmanned Aerial Vehicle which can fly to the desirable waypoints along the flight plan, one may freely select a control scheme to stabilize and perform the target tracking with robustness. The main control system of Unmanned Aerial Vehicle is developed from Fuzzy PD+I controller with auto-tuning gain parameters and the simulation is carried out by Matlab/Simulink simulation program including with Aerosim toolbox software. The model of Unmanned Aerial Vehicle for simulation in this paper is selected the model of Aerosonde UAV from Aerosonde PTY LTD., which is developed mathematical model by Unmanned Dynamics.

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Nho, Kyungmoon, i Ramesh K. Agarwal. "Automatic Landing System Design Using Fuzzy Logic". Journal of Guidance, Control, and Dynamics 23, nr 2 (marzec 2000): 298–304. http://dx.doi.org/10.2514/2.4522.

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Crassidis, John L., D. Joseph Mook i James M. McGrath. "Automatic carrier landing system utilizing aircraft sensors". Journal of Guidance, Control, and Dynamics 16, nr 5 (wrzesień 1993): 914–21. http://dx.doi.org/10.2514/3.21101.

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Aagten-Murphy, David, i Paul M. Bays. "Automatic and intentional influences on saccade landing". Journal of Neurophysiology 118, nr 2 (1.08.2017): 1105–22. http://dx.doi.org/10.1152/jn.00141.2017.

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When making an eye movement to a target location, the presence of a nearby distractor can cause the saccade to unintentionally terminate at the distractor itself or the average position in between stimuli. With probabilistic mixture models, we quantified how both unavoidable capture and goal-directed targeting were influenced by changing the task and the target-distractor separation. Using this novel technique, we could extract the time course over which automatic and intentional processes compete for control of saccades.

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Wang, Chang, Jiaqing Wang, Changyun Wei, Yi Zhu, Dong Yin i Jie Li. "Vision-Based Deep Reinforcement Learning of UAV-UGV Collaborative Landing Policy Using Automatic Curriculum". Drones 7, nr 11 (13.11.2023): 676. http://dx.doi.org/10.3390/drones7110676.

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Collaborative autonomous landing of a quadrotor Unmanned Aerial Vehicle (UAV) on a moving Unmanned Ground Vehicle (UGV) presents challenges due to the need for accurate real-time tracking of the UGV and the adjustment for the landing policy. To address this challenge, we propose a progressive learning framework for generating an optimal landing policy based on vision without the need of communication between the UAV and the UGV. First, we propose the Landing Vision System (LVS) to offer rapid localization and pose estimation of the UGV. Then, we design an Automatic Curriculum Learning (ACL) approach to learn the landing tasks under different conditions of UGV motions and wind interference. Specifically, we introduce a neural network-based difficulty discriminator to schedule the landing tasks according to their levels of difficulty. Our method achieves a higher landing success rate and accuracy compared with the state-of-the-art TD3 reinforcement learning algorithm.

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Jia, Baoxu, Liguo Sun, Xiaoyu Liu, Shuting Xu, Wenqian Tan i Junkai Jiao. "Carrier Aircraft Flight Controller Design by Synthesizing Preview and Nonlinear Control Laws". Drones 7, nr 3 (15.03.2023): 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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Yang, Wenqi, Siyu Zhou, Jianhua Lu i Liting Song. "Longitudinal Control Technology for Automatic Carrier Landing Based on Model-compensated Active Disturbance Rejection Control". Journal of Physics: Conference Series 2477, nr 1 (1.04.2023): 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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Li, Hui Jie, Ling Yu Yang i Gong Zhang Shen. "CAT III Autoland Control Laws Design Based on Multi-Objective Optimization". Advanced Materials Research 452-453 (styczeń 2012): 548–52. http://dx.doi.org/10.4028/www.scientific.net/amr.452-453.548.

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The CAT III longitudinal automatic landing control laws based on multi-objective optimization is discussed. Firstly summarized the CAT III airworthiness criteria and transformed into the specifications of control system. The configuration of the longitudinal automatic landing controllers is proposed secondly and multi-objective optimization is used to tradeoff free parameters of the controllers. The Monte Carlo simulation results show the designed control laws fulfill the CAT III requirements, when there are uncertainties of structure, measurement error and disturbances.

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Anh, Trung Vuong, Hong Son Tran, Dinh-dung Nguyen, Truong-thanh Nguyen, Trong-son Phan i Hong Tien Nguyen. "An investigation of the Control Quality of the Automatic Control System for Fixed-wing UAVs During Landing Process". Volume 03 Issue 02 vm03, is02 (29.12.2022): 61–69. http://dx.doi.org/10.23890/ijast.vm03is02.0201.

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This study presents an investigation and evaluation of the control quality of the automatic control system for UAVs in the vertical plane under windy conditions. For the operational stages of UAVs in general, the landing stage is one of the high-probability stages that pose a threat to flight safety, especially at the time of landing. Therefore, to evaluate the control quality of the system, the authors investigated the parameters during UAV landing. The automatic control system uses a PID controller with optimal parameters selected by the Signal Constraint tool in Matlab Simulink. The predetermined wind model was used to verify at the most extreme times. The programs proposed in the paper are simulated on Matlab Simulink software.

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30

Wang, Lipeng, Zhi Zhang i Qidan Zhu. "Automatic flight control design considering objective and subjective risks during carrier landing". Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 234, nr 4 (14.08.2019): 446–61. http://dx.doi.org/10.1177/0959651819868039.

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In this article, a design scheme of automatic carrier landing system control law based on combination of the objective risk and the subjective risk is proposed, in order to improve the safety and flying quality of the landing. The nonlinear longitudinal mathematical model is constructed in the air wake turbulence condition during carrier landing, which is transformed into a linear perturbed model by the state-space equations with deviation state variables. The concepts of the objective risk and the subjective risk in the recovery of an aircraft aboard a carrier are addressed. A principle of predicting the future states based on the current ones is put forward so that a mathematic model for the objective risk is established, synthetically considering the current and future landing state deviations. For the other risk, the corresponding model is obtained by the subjective experiences of the pilots in the flight simulation tests. Furthermore, a novel model predictive control algorithm, which contains the additional subjective risk and the time-varying weights of the state terms, is proposed. Automatic carrier landing control law is built by introducing the objective risk, the subjective risk, and the effect of carrier air wake disturbance. In the rolling optimization progress, these time-varying weights are dynamically tuned according to the constantly changing objective risk to control the state deviations and suppress this risk, while the subjective risk is handled by the additional risk terms. Besides, the action of carrier air wake disturbance is considered and compensated in the derivation of the linear matrix inequalities. Test results based on a semi-physical simulation platform indicate that the new automatic carrier landing system control algorithm proposed by this article brings about an excellent carrier landing performance as well as an improved flying quality.

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Ngoua Ndong Avele, J. B., i V. S. Goryainov. "UAV Docking Station: Study on Building an Autonomous Takeoff and Landing Platform for Unmanned Aerial Vehicles". LETI Transactions on Electrical Engineering & Computer Science 16, nr 9 (2023): 38–48. http://dx.doi.org/10.32603/2071-8985-2023-16-9-38-48.

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Studies how to increase the efficiency of autonomous operation of drones using an intelligent docking station for unmanned aerial vehicles (UAVs), which improves charging and maintenance, reducing the need for human intervention in these processes. Known examples of designs for an automatic drone recharging system have been considered. The results present a system developed for automatic landing of drones on the platform and concepts for systems for automatically positioning the drone after landing and for wireless charging or replacing the drone battery.

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32

Liang, Jianjian, Shoukun Wang i Bo Wang. "Online Motion Planning for Fixed-Wing Aircraft in Precise Automatic Landing on Mobile Platforms". Drones 7, nr 5 (18.05.2023): 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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Mook, D. Joseph, Douglas A. Swanson, Michael J. Roemer i Roger Noury. "Improved noise rejection in automatic carrier landing systems". Journal of Guidance, Control, and Dynamics 15, nr 2 (marzec 1992): 509–19. http://dx.doi.org/10.2514/3.20864.

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Zhao, Lin, Xuebo Yang, Huijun Gao i Peng Shi. "Automatic Landing System Design Using Multiobjective Robust Control". Journal of Aerospace Engineering 26, nr 3 (lipiec 2013): 603–17. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000174.

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Juang *, Jih-Gau, i Jern-Zuin Chio. "Fuzzy modelling control for aircraft automatic landing system". International Journal of Systems Science 36, nr 2 (10.02.2005): 77–87. http://dx.doi.org/10.1080/0020772042000325961.

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Venkateswara Rao, D. M. K. K., i Tiauw Hiong Go. "Automatic landing system design using sliding mode control". Aerospace Science and Technology 32, nr 1 (styczeń 2014): 180–87. http://dx.doi.org/10.1016/j.ast.2013.10.001.

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Wang, Lipeng, Zhi Zhang, Qidan Zhu i Ran Dong. "Longitudinal automatic carrier landing system guidance law using model predictive control with an additional landing risk term". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, nr 3 (20.12.2017): 1089–105. http://dx.doi.org/10.1177/0954410017746432.

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This paper used a model predictive control with an additional term to develop a modified longitudinal guidance law to reduce landing risk in an automatic carrier landing system. The landing risk model was established by using a longitudinal trajectory and touchdown point predictive principle. A traditional MPC was then involved in designing a modified automatic carrier landing system guidance law for the proposed model. The nonlinear landing mathematic model of an F/A-18 carrier-based aircraft was initially established. Considering the processed procedure in the model predictive control algorithm, the corresponding linear landing model was derived on the basis of the equilibrium states of the F/A-18. Second, landing trajectory in the longitudinal plane was analysed so that the predictive principle of the trajectory trend was reasonably addressed. Depending on the experimental sample data of a pilot model, some linear imitating envelopes are transformed from the corresponding nonlinear trajectory clusters. Furthermore, a touchdown point prediction model was further established based on the predicted trajectory and touchdown point. Third, the traditional model predictive control was introduced to integrate the landing risk term in the performance cost function to develop a novel modified algorithm that not only guides the aircraft to automatically approach and land on the carrier, but also eliminates landing risk during the final carrier approach. Linear matrix inequalities were imported to substitute algebraic inequalities derived from this new algorithm to increase calculating speed. A simulation mission was conducted on a semi-physical platform and compared with the traditional model predictive control without the additional term. The theoretical results validated the correctness and robustness of the modified algorithm and its capability to eliminate landing risk during terminal carrier approach.

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38

Ruiyang, Zhou, i K. A. Neusypin. "Model predictive control for automatic carrier landing considering ship motion". Journal of Physics: Conference Series 2235, nr 1 (1.05.2022): 012005. http://dx.doi.org/10.1088/1742-6596/2235/1/012005.

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Abstract This paper studies a control problem of UAV automatic landing on carrier considering carrier heave motion, which is given by an empirical model based on spectral density function. A linearized UAV dynamics model is applied as the predictive model, a MPC controller is then proposed for the flight dynamics control. Simulation is conducted with real parameters of the UAV “Silver Fox”, the results exhibit the great landing performance of MPC method.

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39

Galimov, Musa, Roman Fedorenko i Alexander Klimchik. "UAV Positioning Mechanisms in Landing Stations: Classification and Engineering Design Review". Sensors 20, nr 13 (29.06.2020): 3648. http://dx.doi.org/10.3390/s20133648.

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Landing platforms’ automation is aimed at servicing vertical take-off and landing UAVs between flights and maintaining their airworthiness. Over the last few years, different designs for the landing platforms have been proposed. This shows a strong development and establishment of automatic landing platforms with UAV positioning devices on the landing site. Positioning and safe fixation of the UAV are some of the main features of the landing platform, especially if it is mounted on a movable vehicle. This article focuses exclusively on the landing platform and its elements that provide the positioning of the UAV by affecting it during and after the landing. Both active devices and mechanisms and passive elements used for positioning are considered. This article, based on the review of recent patents and publications, gives the classification of positioning approaches used in landing stations with the analysis of the required landing precision, as well as the pros and cons of each type of approach.

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40

Korikov, Anatoly M., i Van Тruc Tran. "Detection of the landing site and development of algorithms for automatic landing of an unmanned aerial vehicle". Proceedings of Tomsk State University of Control Systems and Radioelectronics 26, nr 2 (2023): 72–80. http://dx.doi.org/10.21293/1818-0442-2023-26-2-72-80.

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In the article, for a dual-circuit navigation and control system (NKS) of an unmanned aerial vehicle (UAV), the following tasks are solved: detection (recognition) of a landing pad (LP) for a UAV using a convolutional neural network; determining the coordinates of the LP in the frame of the UAV camera; tracking the LP in the frame through the channels of roll, yaw and pitch of the UAV triaxial gimbal; simulation of the UAV flight in space along a given trajectory and automatic landing of the UAV on the detected LP; synthesis of sliding control by the positional and angular coordinates of the UAV. MATLAB SIMULINK software was used to implement the developed algorithms for solving these problems. The created algorithms provide automatic landing of the UAV on the detected LP.

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41

Cui, Kaikai, Wei Han, Yujie Liu, Xinwei Wang, Xichao Su i Jie Liu. "Model Predictive Control for Automatic Carrier Landing with Time Delay". International Journal of Aerospace Engineering 2021 (17.08.2021): 1–19. http://dx.doi.org/10.1155/2021/8613498.

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This paper focuses on the problem of automatic carrier landing control with time delay, and an antidelay model predictive control (AD-MPC) scheme for carrier landing based on the symplectic pseudospectral (SP) method and a prediction error method with particle swarm optimization (PE-PSO) is designed. Firstly, the mathematical model for carrier landing control with time delay is given, and based on the Padé approximation (PA) principle, the model with time delay is transformed into an equivalent nondelay one. Furthermore, a guidance trajectory based on the predicted trajectory shape and position deviation is designed in the MPC framework to eliminate the influence of carrier deck motion and real-time error. At the same time, a rolling optimal control block is designed based on the SP algorithm, in which the steady-state carrier air wake compensation is introduced to suppress the interference of the air wake. On this basis, the PE-PSO delay estimation algorithm is proposed to estimate the unknown delay parameter in the equivalent control model. The simulation results show that the delay estimation error of the PE-PSO algorithm is smaller than 2 ms, and the AD-MPC algorithm proposed in this paper can limit the landing height error within ±0.14 m under the condition of multiple disturbances and system input delay. The control accuracy of AD-MPC is much higher than that of the traditional pole assignment algorithm, and its computational efficiency meets the requirement of real-time online tracking.

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42

Cheng, Chen, Zian Wang, Zheng Gong, Pengcheng Cai i Chengxi Zhang. "Prediction and Compensation Model of Longitudinal and Lateral Deck Motion for Automatic Landing Guidance System". Mathematics 10, nr 19 (21.09.2022): 3440. http://dx.doi.org/10.3390/math10193440.

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This paper mainly studies the longitudinal and lateral deck motion compensation technology. In order to ensure the safe landing of the carrier-based aircrafts on the flight decks of carriers during the landing process, it is necessary to introduce deck motion information into the guidance law information of the automatic landing guidance system when the aircraft is about to land so that the aircraft can track the deck motion. To compensate the influence of the height change in the ideal landing point on the landing process, the compensation effects of the deck motion compensators with different design parameters are verified by simulation. For further phase-lead compensation for the longitudinal automatic landing guidance system, a deck motion predictor is designed based on the particle filter optimal prediction theory and the AR model time series analysis method. Because the influence of up and down motions on the vertical motion of the ideal landing point is the largest, the compensation effects of the designed predictor and compensator are simulated and verified based on the up and down motion of the power spectrum. For the compensation for the lateral motion, a tracking strategy of the horizontal measurement axis of the inertial stability coordinate system to the horizontal axis of the hull coordinate system (center line of the deck) is proposed. The tracking effects of the horizontal measurement axis of the designed integral and inertial tracking strategies are simulated and compared. Secondly, the lateral deck motion compensation commands are designed, and the compensation effects of different forms of compensation commands are verified by simulations. Finally, the compensation effects for the lateral deck motion under integral and inertial tracking strategies are simulated and analyzed.

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43

Kelner, Jan M., i Cezary Ziółkowski. "Doppler Effect-Based Automatic Landing Procedure for UAV in Difficult Access Environments". Journal of Advanced Transportation 2017 (2017): 1–9. http://dx.doi.org/10.1155/2017/8092718.

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Currently, almost unrestricted access to low-lying areas of airspace creates an opportunity to use unmanned aerial vehicles (UAVs), especially those capable of vertical take-off and landing (VTOL), in transport services. UAVs become increasingly popular for transporting postal items over small, medium, and large distances. It is forecasted that, in the near future, VTOL UAVs with a high take-off weight will also deliver goods to very distant and hard-to-reach locations. Therefore, UAV navigation plays a very important role in the process of carrying out transport services. At present, during the flight phase, drones make use of the integrated global navigation satellite system (GNSS) and the inertial navigation system (INS). However, the inaccuracy of GNSS + INS makes it unsuitable for landing and take-off, necessitating the guidance of a human UAV operator during those phases. Available navigation systems do not provide sufficiently high positioning accuracy for an UAV. For this reason, full automation of the landing approach is not possible. This paper puts forward a proposal to solve this problem. The authors show the structure of an autonomous system and a Doppler-based navigation procedure that allows for automatic landing approaches. An accuracy evaluation of the developed solution for VTOL is made on the basis of simulation studies.

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Bian, Qi, Brett Nener, Ting Li i Xinmin Wang. "Multimodal control parameter optimization for aircraft longitudinal automatic landing via the hybrid particle swarm-BFGS algorithm". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, nr 12 (14.02.2019): 4482–91. http://dx.doi.org/10.1177/0954410019825946.

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The airborne automatic landing system needs to provide both accurate trajectory tracking and constant sink rate. In this article, a hybrid optimizer combining a modified particle swarm algorithm with the damped Broyden–Fletcher–Goldfarb–Shanno (BFGS) method is presented to not only solve the parameter tuning problem for the automatic landing system design, but also explore the hidden properties of the multimodal optimization problem. In doing so, the quasi-random sequence-based particle initialization method is adopted to let the particles cover the problem domain more evenly. Then, the damped BFGS-based searching method is used to calculate the local minimum of each particle. A three-point searching method is adopted as a substitution method if the damped BFGS method fails. By using the modified niching method, each particle is updated and converges to an estimated local minimum point. Finally, a range of optimized solutions is analysed and presented to the engineer for the automatic landing system design. A series of simulations are carried out on a test bed based on a 6 degrees of freedom (DoF) non-linear model of the F/A-18. Comparative results verify the effectiveness of the proposed method.

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45

Makarenko, A. A., A. D. Makarov, A. A. Vlasov i E. A. Motorin. "OPTION OF CONSTRUCTION OF AUTOMATIC LANDING SYSTEM FOR UNMANNED AIRCRAFT WITH VERTICAL TAKEOFF AND LANDING". Radio industry, nr 1 (1.01.2017): 96–103. http://dx.doi.org/10.21778/2413-9599-2017-1-96-103.

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Krammer, Christoph, Markus Rosenbauer i Florian Holzapfel. "Flight Guidance for Vision-Augmented Automatic Landing of Electric Vertical Take-off and Landing Vehicles". IFAC-PapersOnLine 55, nr 22 (2022): 248–54. http://dx.doi.org/10.1016/j.ifacol.2023.03.042.

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Suhih, Nikolai, i Valentin Rukavishnikov. "Research of the Processes of Aircraft Director Control at Board Calculator Failure". Automation on transport 8, nr 2 (14.06.2022): 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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Kolosov, Kirill, Alexander Miller i Boris Miller. "Robust Data Fusion of UAV Navigation Measurements with Application to the Landing System". Remote Sensing 12, nr 23 (24.11.2020): 3849. http://dx.doi.org/10.3390/rs12233849.

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To perform precise approach and landing concerning an aircraft in automatic mode, local airfield-based landing systems are used. For joint processing of measurements of the onboard inertial navigation systems (INS), altimeters and local landing systems, the Kalman filter is usually used. The application of the quadratic criterion in the Kalman filter entails the well-known problem of high sensitivity of the estimate to anomalous measurement errors. During the automatic approach phase, abnormal navigation errors can lead to disaster, so the data fusion algorithm must automatically identify and isolate abnormal measurements. This paper presents a recurrent filtering algorithm that is resistant to anomalous errors in measurements and considers its application in the data fusion problem for landing system measurements with onboard sensor measurements—INS and altimeters. The robustness of the estimate is achieved through the combined use of the least modulus method and the Kalman filter. To detect and isolate failures the chi-square criterion is used. It makes possible the customization of the algorithm in accordance with the requirements for false alarm probability and the alarm missing probability. Testing results of the robust filtering algorithm are given both for synthesized data and for real measurements.

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Tseng, Stephen, Ji Hung Lou i Wang Ting Liao. "Development of a Vision Recognition System for Unmanned Aerial Helicopter Automatic Landing System". Applied Mechanics and Materials 411-414 (wrzesień 2013): 1815–20. http://dx.doi.org/10.4028/www.scientific.net/amm.411-414.1815.

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An embedded vision recognition system is developed for a regular UAH to provide guidance information during hovering and landing. An innovative landing mark has been designed to facilitate the image processing while provide relative heading, height, and coordinate for navigation. The system can provide 30 Hz updating rate to the UAH avionic system. Simulation and real-world tests have shown promising performance and results for future applications.

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Choi, Ji-Wook, Do-Kyung Hwang, Jong-Woo An i Jang-Myung Lee. "Object Detection Using CNN for Automatic Landing of drones". Journal of the Institute of Electronics and Information Engineers 56, nr 5 (31.05.2019): 82–90. http://dx.doi.org/10.5573/ieie.2019.56.5.82.

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