Gotowe bibliografie tematyczne / Automatic landing

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Gotowa bibliografia na temat „Automatic landing”

Autor: Grafiati
Data publikacji: 10 sierpnia 2024

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Artykuły w czasopismach na temat "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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Rozprawy doktorskie na temat "Automatic landing"

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Bole, Michael. "Design of an automatic landing system for twin rotor vertical take-off and landing unmanned air vehicle". Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape3/PQDD_0015/MQ47834.pdf.

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Gising, Andreas. "MALLS - Mobile Automatic Launch and Landing Station for VTOL UAVs". Thesis, Linköping University, Department of Electrical Engineering, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-15980.

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The market for vertical takeoff and landing unmanned aerial vehicles, VTOL UAVs, is growing rapidly. To reciprocate the demand of VTOL UAVs in offshore applications, CybAero has developed a novel concept for landing on moving objects called MALLS, Mobile Automatic Launch and Landing Station. MALLS can tilt its helipad and is supposed to align to either the horizontal plane with an operator adjusted offset or to the helicopter skids. Doing so, eliminates the gyroscopic forces otherwise induced in the rotordisc as the helicopter is forced to change attitude when the skids align to the ground during landing or when standing on a jolting boat with the rotor spun up. This master’s thesis project is an attempt to get the concept of MALLS closer to a quarter scale implementation. The main focus lies on the development of the measurement methods for achieving the references needed by MALLS, the hori- zontal plane and the plane of the helicopter skids. The control of MALLS is also discussed. The measurement methods developed have been proved by tested implementations or simulations. The theories behind them contain among other things signal filtering, Kalman filtering, sensor fusion and search algorithms. The project have led to that the MALLS prototype can align its helipad to the horizontal plane and that a method for measuring the relative attitude between the helipad and the helicopter skids have been developed. Also suggestions for future improvements are presented.

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Caldeira, Fabrício Reis. "Design of an automatic landing system using linear quadratic tracker". Instituto Tecnológico de Aeronáutica, 2008. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=725.

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This work presents the application of the Linear Quadratic Tracker (LQT) for the automatic landing system of passenger transport airplanes. The design method to achieve an autoland flare law with improved performance and disturbance rejection is described. With this method the design is direct and more formal thus avoiding the somewhat time consuming and more ad-hoc design iterations currently practice in industry. Although the design technique has been used for a autoland system, the approach is general enough to be used in other control applications. The structure of a traditional flare controller used for transport airplane and the LQT flare controller are presented. The performance of the flare control law designed based on LQT is compared against the performance of a traditional flare control law. Simulation time histories and Monte Carlo simulation results are presented. The time histories simulations cover the nominal and the most adverse conditions anticipated during the operation of the autoland system. The results show that the LQT law provides a more accurate path control and better disturbance rejection. The Monte Carlo simulation was made according to the certification requirements of an autoland system. The results show that the LQT controller provides reduced touchdown dispersion for the sink rate and distance at touchdown. The automatic landing system using LQT complies easily with the certification requirements, whereas the traditional system based on the classical design of autopilot inner loop/outer loop meets the certification requirements with smaller margins.
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Lai, Khai Ping. "A deep learning model for automatic image texture classification: Application to vision-based automatic aircraft landing". Thesis, Queensland University of Technology, 2016. https://eprints.qut.edu.au/97992/4/Khai_Ping_Lai_Thesis.pdf.

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This project aims to investigate a robust Deep Learning architecture to classify different type of textural imagery. The findings will eventually be part of a central processing algorithm used for Automatic Image Classification for Automatic Aircraft Landing.
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Hill, Steven James. "DGPS/ILS integration for an automatic landing system using Kalman Filtering". Ohio University / OhioLINK, 1996. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1178311128.

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Aribal, Seckin. "Development Of An Autopilot For Automatic Landing Of An Unmanned Aerial Vehicle". Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613391/index.pdf.

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This thesis presents the design of an autopilot and guidance system for an unmanned aerial vehicle. Classical (PID) and modern control (LQT, Sliding Mode) methods for autonomous navigation and landing in adverse weather conditions are implemented. Two different guidance systems are designed in order to navigate through waypoints during normal and/or emergency flight. The nonlinear Pioneer UAV model is used in controller development and simulations. Aircraft is linearized at different trim points and total airspeed, altitude, roll and yaw autopilots are designed using Matlab/Simulink environment for lateral and longitudinal control of the aircraft. Gain scheduling is used to combine controllers designed for different trim points. An optimal landing trajectory is determined using &ldquo
Steepest Descent&rdquo
Algorithm according to the dynamic characteristics of the aircraft. Optimal altitude trajectory is used together with a lateral guidance against cross-wind disturbance. Finally, simulations including landing under crosswind, tailwind, etc., are run and the results are analyzed in order to demonstrate the performance and effectiveness of the controllers.
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Magnus, Vestergren. "Automatic Takeoff and Landing of Unmanned Fixed Wing Aircrafts : A Systems Engineering Approach". Thesis, Linköpings universitet, Datorteknik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-133078.

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The purpose of this thesis is to extend an existing autopilot with automatic takeoff and landing algorithms for small fixed wing unmanned aircrafts. The work has been done from a systems engineering perspective and as for solution candidates this thesis has a bias towards solutions utilizing fuzzy logic. The coveted promises of fuzzy logic was primarily the idea to have a design that was easily tunable with very little knowledge beyond flight experience for a particular aircraft. The systems engineering perspective provided a way to structure and reason about the project where the problem has been decoupled from different solutions and the work has been divided in a way that would allow multiple aspects of the project to be pursued simultaneously. Though the fuzzy logic controllers delivered functional solutions the promises related to ease of tuning was not fulfilled in a landing context. This might have been a consequence of the designs attempted but in the end a simpler solution outperformed the implemented fuzzy logic controllers. Takeoff did not present the same issues in tuning but did require some special care to handle the initial low airspeeds in an hand launch.
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Trittler, Martin [Verfasser]. "Automatic Landing for Fixed-Wing Unmanned Aerial Vehicles with Optical Sensors / Martin Trittler". Aachen : Shaker, 2018. http://d-nb.info/1162794321/34.

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Hermansson, Joel. "Vision and GPS based autonomous landing of an unmanned aerial vehicle". Thesis, Linköping University, Automatic Control, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-57735.

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A control system for autonomous landing of an unmanned aerial vehicle (UAV)with high precision has been developed. The UAV is a medium sized model he-licopter. Measurements from a GPS, a camera and a compass are fused with anextended Kalman filter for state estimation of the helicopter. Four PID-controllers,one for each control signal of the helicopter, are used for the helicopter control.During the final test flights fifteen landings were performed with an average land-ing accuracy of 35 cm.    A bias in the GPS measurements makes it impossible to land the helicopter withhigh precision using only the GPS. Therefore, a vision system using a camera anda pattern provided landing platform has been developed. The vision system givesaccurate measurement of the 6-DOF pose of the helicopter relative the platform.These measurements are used to guide the helicopter to the landing target. Inorder to use the vision system in real time, fast image processing algorithms havebeen developed. The vision system can easily match up the with the camera framerate of 30 Hz.


Ett kontrolsystem för att autonomt landa en modellhelikopter har utvecklats.Mätdata från en GPS, en kamera samt en kompass fusioneras med ett Extend-ed Kalman Filter för tillståndsestimering av helikoptern. Fyra PID-regulatorer,en för varje kontrolsignal på helikoptern, har används för regleringen. Under densista provflygningen gjordes tre landingar av vilken den minst lyckade slutade35 cm från målet.    På grund av en drift i GPS-mätningarna är det omöjligt att landa helikopternmed hög precision med bara en GPS. Därför har ett bildbehandlingssystem som an-vänder en kamera samt ett mönster på platformen utvecklats. Bidbehandlingssys-temet mäter positionen och orienteringen av helikoptern relativt platformen. Dessamätningar används kompensera för GPS-mätningarnas drift. Snabba bildbehan-dlingsalgoritmer har utvecklats för att kunna använda bildbehandlingssystemet irealtid. Systemet är mycket snabbare än 30 bilder per sekund vilket är kameranshastighet.

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Lugo, Cárdenas Israel. "Autonomous take-off and landing for a fixed wing UAV". Thesis, Compiègne, 2017. http://www.theses.fr/2017COMP2364/document.

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Ce travail étudie certains des problèmes les plus pertinents dans le sens de la navigation et contrôle présentés dans une classe particulière de mini-véhicules aériens. L'un des principaux objectifs c'est à réaliser un véhicule léger et facile à déployer dans un court laps de temps, un véhicule sans pilote drone capable de suivre une mission complète, du décollage aux points de cheminement suivants et de terminer la mission avec un atterrissage autonome à l'intérieur d'une zone délimitée en utilisant une interface graphique dans un ordinateur ou une tablette. La génération de trajectoire II est la partie qui dit le drone où il doit voyager et sont générés par un algorithme intégré sur le drone. Le résultat classique de Dubins est utilisé comme base pour la génération de trajectoire en 2D et nous avons étendu à la génération de trajectoire 3D. Une stratégie de suivi de trajectoire développée en utilisant l'approche de Lyapunov, est présentée pour piloter un drone à voilure fixe à travers tout le chemin désiré. Le concept clé derrière le contrôleur de suivi de trajectoire s'appuie sur la réduction de la distance entre le centre de masse de l'avion p et le point sur la trajectoire q à zéro, ainsi que l'angle entre le vecteur vitesse et la tangente à la trajectoire. Afin de tester les techniques mises au point au cours de la thèse une application C# -Net personnalisée a été développé nommé MAV3DSim (Multi-Aerial Vehicle 3D Simulator). Le MAV3DSim permet une opération de lecture/écriture de/vers le moteur de simulation à partir de laquelle nous pourrions recevoir toutes les informations de capteurs émulés et envoyés par le simulateur. Le système complet est capable d'effectuer un décollage et d'atterrissage autonome, à travers des points de suivi. Ceci est accompli en utilisant chacune des stratégies développées au cours de la thèse. Nous avons une stratégie pour le décollage et l'atterrissage, ce qui est généré par la partie de navigation qui est le générateur de trajectoire. Une fois que nous avons généré le chemin, il est utilisé par la stratégie de suivi de trajectoire et avec ce que nous avons l'atterrissage et le décollage autonome
This work studies some of the most relevant problems in the direction of navigation and control presented in a particular class of mini‐aircraft. One of the main objectives is to build a lightweight and easy to deploy vehicle in a short period of time, an unmanned aerial vehicle capable of following a complete mission from take‐o⁄ to the following waypoints and complete the mission with an autonomous landing within a delimitated area using a graphical interface in a computer. The Trajectory Generation It is the part that tells the drone where it must travel and are generated by an algorithm built into the drone. The classic result of Dubins is used as a basis for the trajectory generation in 2D and we have extended it to the 3D trajectory generation. A path following strategy developed using the Lyapunov approach is presented to pilot a fixed wing drone across the desired path. The key concept behind the tracking controller is the reduction of the distance between the center of mass of the aircraft p and the point q on the path to zero, as well as the angle between the velocity vector and the vector tangent to the path. In order to test the techniques developed during the thesis a customized C # .Net application was developed called MAV3DSim (Multi‐Aerial Vehicle 3D Simulator). The MAV3DSim allows a read / write operation from / to the simulation engine from which we could receive all emulated sensor information and sent to the simulator. The MAV3DSim consists of three main elements, the simulation engine, the computation of the control law and the visualization interface. The simulation engine is in charge of the numeric integration of the dynamic equations of the vehicle, we can choose between a quadrotor and a xed wing drone for use in simulation. The visualization interface resembles a ground station type of application, where all variables of the vehicle s state vector can be represented on the same screen. The experimental platform functions as a test bed for the control law prototyping. The platform consists of a xed wing aircraft with a PX4 which has the autopilot function as well as a Raspberry PI mini‐computer which to the implementation of the generation and trajectory tracking. The complete system is capable of performing an autonomous take‐o⁄and landing, through waypoints. This is accomplished by using each of the strategies developed during the thesis. We have a strategy for take‐o⁄ and landing, which is generated by the navigationon part that is the trajectory generator. Once we have generated the path, it is used by the trajectory tracking strategy and withthat we have landing and take‐o⁄ autonomously
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Książki na temat "Automatic landing"

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Hueschen, Richard M. Implementation and flight tests for the digital integrated automatic landing system (DIALS). Hampton, Va: National Aeronautics and Space Administration ,Langley Research Center, 1986.

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Zhu, Shangxiang. Automatic landing through the turbulent planetary boundary layer. [Downsview, Ont.]: Institute for Aerospace Studies, 1985.

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Center, Langley Research, red. Implementation and flight tests for the Digital Integrated Automatic Landing System (DIALS). Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

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David, McNally B., i Ames Research Center, red. Flight test evaluation of the Stanford University/United Airlines differential GPS category III automatic landing system. Moffett Field, Calif: National Aeronautics Administration, Ames Research Center, 1995.

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Germany) International Symposium on Precision Approach and Automatic Landing (2000 Munich. International Symposium on Precision Approach and Automatic Landing, ISPA 2000, Munich, Germany, 18-20 July 2000: Symposium proceedings. Bonn: German Institute of Navigation, 2000.

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Bundick, W. Thomas. Results of aircraft open-loop tests of an experimental magnetic leader cable system for guidance during roll-out and turnoff. Hampton, Va: Langley Research Center, 1990.

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B, Middleton David, Poole William L i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. Results of aircraft open-loop tests of an experimental magnetic leader cable system for guidance during roll-out and turnoff. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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B, Middleton David, Poole William L i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. Results of aircraft open-loop tests of an experimental magnetic leader cable system for guidance during roll-out and turnoff. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Erkelens, L. J. J. Investigation on MLS approach path interception and transition techniques, Part II: Flight simulator investigation. Amsterdam: National Aerospace Laboratory, 1985.

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Center, Langley Research, red. Automatic braking system modification for the Advanced Transport Operating System (ATOPS) Transportation System Research Vehicle (TSRV). Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

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Części książek na temat "Automatic landing"

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Georghiou, Luke, J. Stanley Metcalfe, Michael Gibbons, Tim Ray i Janet Evans. "Smiths Industries: Aircraft Automatic Landing Equipment". W Post-Innovation Performance, 279–84. London: Palgrave Macmillan UK, 1986. http://dx.doi.org/10.1007/978-1-349-07455-6_35.

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Murray-Smith, D. J. "Case Study II — An Aircraft Automatic Landing System". W Continuous System Simulation, 163–73. Boston, MA: Springer US, 1995. http://dx.doi.org/10.1007/978-1-4615-2504-2_11.

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Anand, Amitesh, Subhabrata Barman, Nemani Sathya Prakash, Naba Kumar Peyada i Jayashri Deb Sinha. "Vision Based Automatic Landing of Unmanned Aerial Vehicle". W Recent Advances in Intelligent Information Systems and Applied Mathematics, 102–13. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-34152-7_8.

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Juang, Jih-Gau, i Li-Hsiang Chien. "Adaptive Fuzzy Neural Network Control for Automatic Landing System". W Computational Collective Intelligence. Technologies and Applications, 520–30. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-16693-8_53.

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Nagothu, Sudheer Kumar, i G. Anitha. "Automatic Landing Site Detection for UAV Using Supervised Classification". W Springer Series in Geomechanics and Geoengineering, 309–16. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-77276-9_27.

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Huh, Sungsik, i David Hyunchul Shim. "A Vision-Based Automatic Landing Method for Fixed-Wing UAVs". W Selected papers from the 2nd International Symposium on UAVs, Reno, Nevada, U.S.A. June 8–10, 2009, 217–31. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-8764-5_11.

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Suzuki, Satoshi. "Automatic Take-Off and Landing Control for Small Unmanned Helicopter". W Advances in Intelligent Systems and Computing, 155–67. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-37374-9_16.

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Suzuki, Satoshi. "Control Scheme for Automatic Takeoff and Landing of Small Electric Helicopter". W Intelligent Systems, Control and Automation: Science and Engineering, 73–83. Tokyo: Springer Japan, 2013. http://dx.doi.org/10.1007/978-4-431-54276-6_5.

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Subrahmanyam, M. Bala. "H ∞ Design of the F/A-18A Automatic Carrier Landing System". W Finite Horizon H∞ and Related Control Problems, 93–116. Boston, MA: Birkhäuser Boston, 1995. http://dx.doi.org/10.1007/978-1-4612-4272-7_6.

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Shrestha, Manish, Sanjeeb Prasad Panday, Basanta Joshi, Aman Shakya i Rom Kant Pandey. "Automatic Pose Estimation of Micro Unmanned Aerial Vehicle for Autonomous Landing". W Intelligent Computing Methodologies, 3–15. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-60796-8_1.

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Streszczenia konferencji na temat "Automatic landing"

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Zhimin, Han, i Hong Guanxin. "Landing Error Analysis of the Automatic Carrier Landing System". W AIAA Guidance, Navigation and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-6335.

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Gribanov, A. S. "Automatic Landing of a Helicopter". W 2019 International Multi-Conference on Industrial Engineering and Modern Technologies (FarEastCon). IEEE, 2019. http://dx.doi.org/10.1109/fareastcon.2019.8934014.

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Wang, Rongshun, Liaoni Wu i Fuqiang Bing. "Automatic Landing Control Design of Gyroplane". W 2019 IEEE 3rd Advanced Information Management, Communicates, Electronic and Automation Control Conference (IMCEC). IEEE, 2019. http://dx.doi.org/10.1109/imcec46724.2019.8984061.

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Meng, Lin, Yang Gao, Jiachao Zhang i Liangbao Jiao. "Automatic longitudinal landing control of FanWing". W 2nd International Conference on Mechanical, Electronics, and Electrical and Automation Control (METMS 2022), redaktor Xuexia Ye. SPIE, 2022. http://dx.doi.org/10.1117/12.2635153.

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Nho, Kyungmoon, i Ramesh Agarwal. "Automatic landing system design using fuzzy logic". W Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-4484.

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Shen, Yu-Fei, Zia-ur Rahman, Dean Krusienski i Jiang Li. "Automatic detection of aircraft emergency landing sites". W SPIE Defense, Security, and Sensing, redaktorzy Zia-ur Rahman, Stephen E. Reichenbach i Mark A. Neifeld. SPIE, 2011. http://dx.doi.org/10.1117/12.882506.

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Atmeh, Ghassan M., Wahba I. Al-Taq i Zeaid Hasan. "A Nonlinear Automatic Landing Control System for a UAV". W ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-63264.

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An automatic landing system for an unmanned aerial vehicle (UAV) is presented in the following paper. The nonlinear aircraft model with thrust, elevator, rudder and aileron deflections as control inputs is established using the appropriate aerodynamic data. The flight trajectory the airplane is expected to travel during landing is then defined. A nonlinear control law, using feedback linearization method, is designed to develop the automatic landing controller for the UAV aircraft. A linear state-feedback control law is also designed for means of comparison with the nonlinear controller. The elevator is employed for longitudinal control whereas the rudder and aileron aid in lateral control. Thrust is the control input for velocity control, which is held constant during landing. A nonlinear simulation, incorporating wind shear and ground effects, is run using MATLAB/Simulink to assess the controllers’ integrity. The auto-landing system designed in this paper is meant to increase the autonomy of the UAV to eventually reach a fully autonomous system. Simulation results show the importance of designing the controller considering such effects. Landing trajectory tracking performance by the nonlinear controller is of great tone.
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Shoouri, Sara, Shayan Jalili, Jiahong Xu, Isabelle Gallagher, Yuhao Zhang, Joshua Wilhelm, Jean-Baptiste Jeannin i Necmiye Ozay. "Falsification of a Vision-based Automatic Landing System". W AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-0998.

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prasad B., Biju, i S. Pradeep. "Automatic Landing System Design using Feedback Linearization Method". W AIAA Infotech@Aerospace 2007 Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2733.

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MOOK, D., DOUGLAS SWANSON i MICHAEL ROEMER. "Improved noise rejection in automatic carrier landing systems". W Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3374.

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Raporty organizacyjne na temat "Automatic landing"

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Sinclair, Samantha, i Sally Shoop. Automated detection of austere entry landing zones : a “GRAIL Tools” validation assessment. Engineer Research and Development Center (U.S.), sierpień 2022. http://dx.doi.org/10.21079/11681/45265.

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The Geospatial Remote Assessment for Ingress Locations (GRAIL) Tools software is a geospatial product developed to locate austere entry landing zones (LZs) for military aircraft. Using spatial datasets like land classification and slope, along with predefined LZ geometry specifications, GRAIL Tools generates binary suitability filters that distinguish between suitable and unsuitable terrain. GRAIL Tools combines input suitability filters, searches for LZs at user‐defined orientations, and plots results. To refine GRAIL Tools, we: (a) verified software output; (b) conducted validation assessments using five unpaved LZ sites; and (c) assessed input dataset resolution on outcomes using 30 and 1‐m datasets. The software was verified and validated in California and the Baltics, and all five LZs were correctly identified in either the 30 or the 1‐m data. The 30‐m data provided numerous LZs for consideration, while the 1‐m data highlighted hazardous conditions undetected in the 30‐m data. Digital elevation model grid size affected results, as 1‐m data produced overestimated slope values. Resampling the data to 5 m resulted in more realistic slopes. Results indicate GRAIL Tools is an asset the military can use to rapidly assess terrain conditions.
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McQueen, Bob, red. Unsettled Issues Concerning Urban Air Mobility Infrastructure. SAE International, listopad 2021. http://dx.doi.org/10.4271/epr2021025.

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Urban air mobility (UAM) refers to urban transportation systems that move people by air. UAM offers the potential for reducing traffic congestion in cities and providing an integrated approach to urban mobility. With the emergence of electric vertical takeoff and landing (eVTOL) aircraft, drone technology, and the possibility of automated aircraft, interest in this topic has grown considerably for private sector solution providers—including aerospace and technology companies—as well as urban planners and transportation professionals. Unsettled Issues Concerning Urban Air Mobility Infrastructure discusses the infrastructure requirements to effectively integrate UAM services into the overarching urban transportation system to enable multimodal trips and complete origin to destination travel.
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Tzonev, Nick, i Eric Pesty. PR-396-113704-R02 Methods for Detection of Gases and VOCs from Floating Roofs of Aboveground Storage Tanks. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), czerwiec 2013. http://dx.doi.org/10.55274/r0010794.

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Describes the development of an automated system that can effectively replace the EPA-mandated in-service and out-of-service inspections of the Internal Floating Roofs (IFR) in Aboveground Storage Tanks (ASTs). The ultimate goal is to increase the internal inspection interval to twenty (20) years, which would coincide with the interval used by the American Petroleum Institute's (API) Standard 653 for out-of-service general mechanical inspection of the entire tank. Extending the IFR internal inspection interval will eliminate the negative elements associated with additional AST entry events and will reduce VOC emissions associated with IFR landing and tank degassing/cleaning, while minimizing safety risks and saving operating capital.
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