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Dissertations / Theses on the topic 'Aircraft - Automatic Control'
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1
Mukherjee, Jason. "Automatic control of an aircraft employing outboard horizontal stabilizers." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape3/PQDD_0027/NQ49523.pdf.
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Benkhedda, Hassen. "Design of a transport aircraft automatic flight control system with analytical redundancy." Thesis, University of Southampton, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.241599.
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Alkhatib, K. Y. "Analytical redundancy scheme for improving reliability of automatic flight control systems for aircraft." Thesis, Loughborough University, 1985. https://dspace.lboro.ac.uk/2134/31989.
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Any redundancy scheme in aircraft control systems is usually considered separately from the control algorithms involved. All feedback control systems are usually designed under the assumption that their sensors will not fail. When the integrity requirements demand it, then a redundancy scheme must be designed to provide any required measurements with only extremely short interruptions to normal service being caused by failures of individual sensors.
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Tang, Yi Rui. "Development, dynamic modeling, and autonomous flight control of small UAV helicopters." Thesis, University of Macau, 2017. http://umaclib3.umac.mo/record=b3691051.
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Lindblom, Markus. "Semi-Automatic Generation of Control Law Parameters for Generic Fighter Aircraft." Thesis, Linköpings universitet, Reglerteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-167725.
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Control law design can be an iterative and time-consuming process. The design procedure can often include manual tuning, not uncommonly in the form of trial and error. Modern software tools may alleviate this process but are generally not developed for use within any specific industry. There is therefore an apparent need to develop field-specific tools to facilitate control law design.The main contribution of this thesis is the investigation of a systematic and simplified approach to semi-automatic generation of control law parameters for generic fighter aircraft. The investigated method aims to reduce human workload and time spent on complex decision making in the early stages of aircraft development. The method presented is based on gain scheduled LQI-control with piece-wise linear interpolation. A solution to the automated tuning problem of the associated weighting matrices Q and R is investigated. The method is based on an LQ-optimal eigenstructure assignment. However, the derived method suffers from problem regarding practical implementation, such as the seemingly narrow LQ-optimal root-loci of the linearized aircraft model.Furthermore, the inherent problem of hidden coupling is discussed in relation to gain scheduled controllers based on conventional series expansion linearization. An alternative linearization method is used in order to circumvent this problem. Moreover, the possible benefits and disadvantages of control allocation is addressed in the context of actuator redundancy. It is concluded that one may achieve a somewhat simpler handling of constraints at the expense of some model accuracy due to the inevitable exclusion of servo dynamics.
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Zhao, Yue. "Automatic Prevention and Recovery of Aircraft Loss-of-Control by a Hybrid Control Approach." Ohio University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1458728101.
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Wagner, Elaine Ann. "On-board automatic aid and advisory for pilots of control-impaired aircraft." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/35940.
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Zaludin, Zairil A. "Flight dynamics and automatic flight control system of an hypersonic transport aircraft." Thesis, University of Southampton, 1999. https://eprints.soton.ac.uk/47120/.
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S, Kulik M., Antonov V. K, Glazok O. M, et al. "Unmanned aircraft with a closed wing." Thesis, IEEE, 2015. http://er.nau.edu.ua/handle/NAU/22133.
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A configuration of an unmanned aircraft with closed wing is considered. The method of identification designed for researching the aerodynamic qualities of the model is proposed.<br>http://ieeexplore.ieee.org/xpl/login.jsp?tp=&arnumber=7346558&url=http%3A%2F%2Fieeexplore.ieee.org%2Fxpls%2Ficp.jsp%3Farnumber%3D7346558
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Lim, Bock-Aeng. "Design and rapid prototyping of flight control and navigation system for an unmanned aerial vehicle." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://sirsi.nps.navy.mil/uhtbin/hyperion-image/02Mar%5FLimBA.pdf.
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Sunnanbo, Albin. "Laser feedback control for robotics in aircraft assembly." Thesis, Linköping University, Department of Electrical Engineering, 2003. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-2097.
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<p>The aim of this thesis is to investigate how the absolute accuracy of an industrial robot can be increased by monitoring the position of the robot. The motive is to automate high precision, low volume production such as aircraft industry. A laser tracker that can measure both position and orientation with very high accuracy isused to monitor the robot tool position. The robot and laser tracker are integrated via a standard computer. </p><p>The abilities and performance of the robot, with and without feedback from the laser tracker, are investigated. Robotic drilling is performed with supervision and control from the laser tracker. </p><p>The system is implemented and tested on parts of a demonstrator for new aircraft assembly techniques. The ability to position components with internal friction to (+/-)0.05 mm absolute accuracy is shown.</p>
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Hektor, Tomas. "Marginalized Particle Filter for Aircraft Navigation in 3-D." Thesis, Linköping University, Department of Electrical Engineering, 2007. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-10193.
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<p>In this thesis Sequential Monte Carlo filters, or particle filters, applied to aircraft navigation is considered. This report consists of two parts. The first part is an illustration of the theory behind this thesis project. The second and most important part evaluates the algorithm by using real flight data.</p><p>Navigation is about determining one's own position, orientation and velocity. The sensor fusion studied combines data from an inertial navigation system (INS) with measurements of the ground elevation below in order to form a terrain aided positioning system (TAP). The ground elevation measurements are compared with a height database. The height database is highly non-linear, which is why a marginalized particle filter (MPF) is used for the sensor fusion.</p><p>Tests have shown that the MPF delivers a stable and good estimate of the position, as long as it receives good data. A comparison with Saab's NINS algorithm showed that the two algorithms perform quite similar, although NINS performs better when data is lacking.</p>
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Wise, Richard. "UAV guidance control laws for autonomous coordinated tracking of a moving ground target /." Thesis, Connect to this title online; UW restricted, 2007. http://hdl.handle.net/1773/9959.
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Atesoglu, Ozgur Mustafa. "High Angle Of Attack Maneuvering And Stabilization Control Of Aircraft." Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608575/index.pdf.
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In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional
aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologies and the stability and robustness analyses are done by using robust performance (RP) analysis techniques. The control
architecture is designed to serve both for the recovery from the undesired stall condition (the stabilization controller) and to perform desired agile maneuvering (the attitude controller). The detailed modeling of the aircraft dynamics, aerodynamics, engines and thrust vectoring paddles, as well as the flight
environment of the aircraft and the on-board sensors is performed. Within the control loop the human pilot model is included and the design of a fly-by-wire controller is also investigated. The performance of the designed stabilization and attitude controllers are simulated using the custom built 6 DoF aircraft flight simulation tool. As for the stabilization controller, a forced deep-stall flight condition is generated and the aircraft is recovered to stable and pilot controllable
flight regimes from that undesired flight state. The performance of the attitude controller is investigated under various high angle of attack agile maneuvering conditions. Finally, the performances of the proposed controller schemes are discussed and the conclusions are made.
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Unnikrishnan, Suraj. "Adaptive Envelope Protection Methods for Aircraft." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/11478.
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Carefree handling refers to the ability of a pilot to operate an aircraft without the need to continuously monitor aircraft operating limits. At the heart of all carefree handling or maneuvering systems, also referred to as envelope protection systems, are algorithms and methods for predicting future limit violations. Recently, envelope protection methods that have gained more acceptance, translate limit proximity information to its equivalent in the control channel. Envelope protection algorithms either use very small prediction horizon or are static methods with no capability to adapt to changes in system configurations. Adaptive approaches maximizing prediction horizon such as dynamic trim, are only applicable to steady-state-response critical limit parameters. In this thesis, a new adaptive envelope protection method is developed that is applicable to steady-state and transient response critical limit parameters. The approach is based upon devising the most aggressive optimal control profile to the limit boundary and using it to compute control limits. Pilot-in-the-loop evaluations of the proposed approach are conducted at the Georgia Tech Carefree Maneuver lab for transient longitudinal hub moment limit protection. Carefree maneuvering is the dual of carefree handling in the realm of autonomous Uninhabited Aerial Vehicles (UAVs). Designing a flight control system to fully and effectively utilize the operational flight envelope is very difficult. With the increasing role and demands for extreme maneuverability there is a need for developing envelope protection methods for autonomous UAVs. In this thesis, a full-authority automatic envelope protection method is proposed for limit protection in UAVs. The approach uses adaptive estimate of limit parameter dynamics and finite-time horizon predictions to detect impending limit boundary violations. Limit violations are prevented by treating the limit boundary as an obstacle and by correcting nominal control/command inputs to track a limit parameter safe-response profile near the limit boundary. The method is evaluated using software-in-the-loop and flight evaluations on the Georgia Tech unmanned rotorcraft platform- GTMax. The thesis also develops and evaluates an extension for calculating control margins based on restricting limit parameter response aggressiveness near the limit boundary.
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Frykman, Petter. "Applied particle filters in integrated aircraft navigation." Thesis, Linköping University, Department of Electrical Engineering, 2003. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1736.
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<p>Navigation is about knowing your own position, orientation and velocity relative to some geographic entities. The sensor fusion considered in this thesis combines data from a dead reckoning system, inertial navigation system (INS), and measurements of the ground elevation. The very fast dynamics of aircraft navigation makes it difficult to estimate the true states. Instead the algorithm studied will estimate the errors of the INS and compensate for them. A height database is used along with the measurements. The height database is highly non-linear why a Rao-Blackwellized particle filter is used for the sensor fusion. This integrated navigation system only uses data from its own sensors and from the height database, which means that it is independent of information from outside the aircraft. </p><p>This report will describe the algorithm and illustrate the theory used. The main purpose is to evaluate the algorithm using real flight data, why the result chapter is the most important.</p>
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Chevrolat, Sofia. "Automatic Fusion of Fidelity sources ofAerodynamic Data : Simulating Aircraft Stability And Control Characteristics for Use in Conceptual Design." Thesis, KTH, Aeroakustik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-30614.
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CFD use has increased signi cantly in airplane conception, and the industry demands more andmore precise and reliable tools. This was the goal of the SimSAC project. The result is CEASIOM,a computerized environment made of several modules for the design and prediction of the aircraft'scharacteristics. It constructs aerodynamic tables used in the prediction of the characteristics of anaircraft. In simple ight conditions, simple computation methods are used, whereas in complex ightconditions,involving turbulences, more advanced methods are used. This reduces the computationalcost, but the tables resulting from di erent delity sources must be fused to obtain a coherent tablecovering the whole ight envelope.The goal of this project was to realize the fusion. Additionally, a lter and a custom-made mapping toenhance the accuracy of the results from the fusion were required. The addition of helpful visualizationtools was suggested. The whole should be integrated in the CEASIOM interface as a Fusion module.For this, 6 functions were coded. The rst one loads the data sets. The second, myplot, allows theengineer by plotting the data in a coherent way, to spot any big mistakes or incompatibility in thedata sets. The third, myvisual, displays the elements spotted as outliers or potentially out of pattern.This is used by the next function, my ltermap, to lter out the erroneous data. This function alsorealizes the custom-made mapping.The fth function, myfusion, fuses the data and saves it in a .xmlCEASIOM formatted structure to be used by the next CEASIOM module. The sixth function ltersout, in the same way as my ltermap, the outliers from the fused data, and saves the ltered fused dataset in a .xml CEASIOM formatted structure. Finally, a Matlab GUI was implemented and integratedinto the main CEASIOM interface.The module works perfectly, except for the mapping part, that needs a few readjustments.
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Lindh, Anders, and Johan Tofte. "Design och implementering av styrlagar för generisk flygplansmodell." Thesis, Linköping University, Department of Electrical Engineering, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1359.
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<p>For research purposes Saab has developed a generic mathematical model denoted VEGAS of an aircraft with a configuration similar to JAS 39 Gripen. Today parts of Gripen backup control system are used also for VEGAS making the system subject to both corporate and defense secrecy. </p><p>The main objective of this master thesis is to design, verify and implement public pitch axis flight control system for VEGAS. Furthermore, simplifications regarding the design process is to be examined. </p><p>Design of pitch axis flight control system for the entire flight envelope has been carried out. Linearization of the dynamic model and programming design environment are used as development tools. The control system has been tested and verified in real-time simulator. </p><p>Linear quadratic optimization (LQ) and gain-scheduling are often used when designing aircraft control system. This method tends to require extensive design effort. This thesis suggests an alternative method combining LQ and scaling of parameters.</p>
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Wang, Chao. "Aircraft autopilot design using a sampled-data gain scheduling technique." Ohio : Ohio University, 1999. http://www.ohiolink.edu/etd/view.cgi?ohiou1175280078.
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Reimann, Johan Michael. "Using Multiplayer Differential Game Theory to Derive Efficient Pursuit-Evasion Strategies for Unmanned Aerial Vehicles." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/16151.
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In recent years, Unmanned Aerial Vehicles (UAVs) have been used extensively in military conflict situations to execute intelligence, surveillance and reconnaissance missions. However, most of the current UAV platforms have limited collaborative capabilities, and consequently they must be controlled individually by operators on the ground. The purpose of the research presented in this thesis is to derive algorithms that can enable multiple UAVs to reason about the movements of multiple ground targets and autonomously coordinate their efforts in real-time to ensure that the targets do not escape. By improving the autonomy of multivehicle systems, the workload placed on the command and control operators is reduced significantly.
To derive effective adversarial control algorithms, the adversarial scenario is modeled as a multiplayer differential game. However, due to the inherent computational complexity of multiplayer differential games, three less computationally demanding differential pursuit-evasion game-based algorithms are presented. The purpose of the algorithms is to quickly derive interception strategies for a team of autonomous vehicles. The algorithms are applicable to scenarios with different base assumptions, that is, the three algorithms are meant to complement one another by addressing different types of adversarial problems.
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Zhou, Yan. "Development of a data collection system for small Unmanned Aerial Vehicles (UAVs)." Thesis, Cape Peninsula University of Technology, 2011. http://hdl.handle.net/20.500.11838/1299.
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Dissertation (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2011<br>This paper presents the development of a data collection system for a small unmanned
Aerial Vehicle (UAV) flight. The following three facets comprise of a UAV system: (1) a UAV
aircraft; (2) onboard avionics; and (3) a ground control station subsystem (Taha et al.,
2010:1). In this project, the UAV aircraft is based on the low-cost autonomous quad-rotator
system named “Arducopter Quad”, where the onboard avionic system utilizes both an
ArduPilot Mega (APM) on-board controller and IMU sensor shield, while the “Mission
Planner” software operates as GCS software to gather essential flight data (Xiang & Tian,
2011:176). The approach provides the UAV system structure and both hardware and
software with a small UAV data collection system, which is examined throughout the study.
And introduce the concept of Arducopter dynamics for better understanding with its flight
control.
The study also considers the communication process between the UAV and the ground
control station. The radio wave is an important aspect in the UAV data collection system
(Austin, 2010:143). The literature review introduced the basis of the radio wave in respect of
its travelling speed, and its characteristics of propagation, including how different frequencies
will affect radio wave propagation.
The aim of this project was to develop a platform for a small UAV real-time data collection
system. The pendulum system was involved to simulate the “Roll” movement of the small
UAV, while real-time IMU sensor data was successfully collected at ground control station
(GCS), both serial communication and wireless communication, which was applied in the
data collection process. The microwave generator interference test proves that the 2.4 GHz
XBee module is capable of establishing reliable indoor communication between the APM
controller and the GCS.
The work of this project is towards development of additional health monitoring technology to
prevent the safety issue of the small UAV. The data collection system can be used as basis
for the future research of real-time health monitoring for various small UAVs.
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Bodin, Camilla. "Automatic Flight Maneuver Identification Using Machine Learning Methods." Thesis, Linköpings universitet, Reglerteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-165844.
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This thesis proposes a general approach to solve the offline flight-maneuver identification problem using machine learning methods. The purpose of the study was to provide means for the aircraft professionals at the flight test and verification department of Saab Aeronautics to automate the procedure of analyzing flight test data. The suggested approach succeeded in generating binary classifiers and multiclass classifiers that identified six flight maneuvers of different complexity from real flight test data. The binary classifiers solved the problem of identifying one maneuver from flight test data at a time, while the multiclass classifiers solved the problem of identifying several maneuvers from flight test data simultaneously. To achieve these results, the difficulties that this time series classification problem entailed were simplified by using different strategies. One strategy was to develop a maneuver extraction algorithm that used handcrafted rules. Another strategy was to represent the time series data by statistical measures. There was also an issue of an imbalanced dataset, where one class far outweighed others in number of samples. This was solved by using a modified oversampling method on the dataset that was used for training. Logistic Regression, Support Vector Machines with both linear and nonlinear kernels, and Artifical Neural Networks were explored, where the hyperparameters for each machine learning algorithm were chosen during model estimation by 4-fold cross-validation and solving an optimization problem based on important performance metrics. A feature selection algorithm was also used during model estimation to evaluate how the performance changes depending on how many features were used. The machine learning models were then evaluated on test data consisting of 24 flight tests. The results given by the test data set showed that the simplifications done were reasonable, but the maneuver extraction algorithm could sometimes fail. Some maneuvers were easier to identify than others and the linear machine learning models resulted in a poor fit to the more complex classes. In conclusion, both binary classifiers and multiclass classifiers could be used to solve the flight maneuver identification problem, and solving a hyperparameter optimization problem boosted the performance of the finalized models. Nonlinear classifiers performed the best on average across all explored maneuvers.
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Hand, Troy S. "Self-organized traffic flows: a sequential conflict resolution approach." Thesis, Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49125.
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This thesis discusses the effect of sequential conflict resolution maneuvers of a continuous flow of agents through a finite control volume. Video analysis of real world traffic flows that exhibit self-organized capabilities is conducted to extract characteristics of those agents. A tool is created which stabilizes the input video and extracts motion from it using the background subtraction method. I discuss the tool in detail as I created it to be user friendly and easily modifiable for other uses. The aim of the video analysis I conduct is to determine characteristics of agents in self-organized traffic flow. Comparisons are made with agents under sequential conflict resolution schemes and those that exhibit these self-organized capabilities to determine if agents under sequential control can approach the behaviors of those in self-organized environment. Flow geometries are studied and generalized with the goal of determining stability characteristics of arbitrary flow geometries. Stability analysis includes analytical proof of bounds on the conflict resolution maneuvers.
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Rosander, Regina. "Sensor fusion between a Synthetic Attitude and Heading Reference System and GPS." Thesis, Linköping University, Department of Electrical Engineering, 2003. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-1766.
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<p>Sensor fusion deals with the merging of several signals into one, extracting a better and more reliable result. Traditionally the Kalmanfilter is used for this purpose and the aircraft navigation has benefited tremendously from its use. This thesis considers the merge of two navigation systems, the GPS positioning system and the Saab developed Synthetic Attitude and Heading Reference System (SAHRS). The purpose is to find a model for such a fusion and to investigate whether the fusion will improve the overall navigation performance. The non-linear nature of the navigation equations will lead to the use of the extended Kalman filter and the model is evaluated against both simulated and real data. The results show that this strategy indeed works but problems will arise when the GPS signal falls away.</p>
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Knoebel, Nathan B. "Adaptive Quaternion Control for a Miniature Tailsitter UAV." Diss., CLICK HERE for online access, 2007. http://contentdm.lib.byu.edu/ETD/image/etd2092.pdf.
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Escamilla, Núñez Héctor. "Contribution au guidage des avions en trafic à haute densité." Thesis, Toulouse 3, 2018. http://www.theses.fr/2018TOU30074/document.
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Ce travail est développé dans le contexte des projets SESAR et Next-Gen, où de nouvelles applications de la gestion du trafic aérien (ATM) comme le concept de gestion d'opérations en 4D, se sont focalisées sur les opérations basées sur la trajectoire (TBO - Trajectory Based Operations). Ces opérations sont en relation avec l'extension de la flexibilité de la séparation entre avions, et par conséquence, avec l'augmentation de la capacité du trafic aérien. En sachant qu'une évolution des routes fixes et autorisations émises par le contrôle du trafic aérien (ATC - Air Traffic Control) vers des trajectoires flexibles est imminente, en s'appuyant en même temps aux niveaux les plus élevés de l'automatique embarquée, ce travail de recherche s'intéresse aux sujets qui aideront à la transition des systèmes actuels vers les systèmes compatibles avec les nouveaux besoins des TBO. Les principaux axes de recherche de ce manuscrit s'articulent en trois points: La génération de trajectoires en 4D, le guidage en 4D, et l'estimation de la masse d'un avion pour l'optimisation des trajectoires. Concernant la génération des trajectoires, le besoin des utilisateurs d'espaces aériens de planifier leurs routes préférées à partir d'un point d'entrée dans l'espace aérien sans être limités par les configurations existantes est considéré. Une solution particulière pour la génération de trajectoires lisses en 4D à partir de points de contrôle prédéfinis est alors explorée. La méthode proposée s'appuie sur les courbes de Bézier, et elle permet de contrôler la distance euclidienne entre le point de contrôle donné et la trajectoire proposée. Ceci est fait en modifiant la trajectoire de telle façon qu'elle reste à l'intérieur des limites des facteurs de charge, en considérant un compromis entre la courbure de la trajectoire et la vitesse voulue de l'avion, ce qui représente une étape importante dans le chemin vers les TBO. Le guidage précis en 4D améliorera la sûreté en diminuant l'occurrence de quasi-collisions aériennes pour des trajectoires en 4D planifiées en avance. En conséquence, deux autopilotes et deux méthodes de guidage sont développées avec l'objectif de réduire la charge de travail des contrôleurs du trafic aérien associée à un vol. Les techniques de backstepping et feedback linearization sont utilisées pour le pilotage, alors que l'inversion non linéaire directe et indirecte sont adoptées pour le guidage. De plus, l'impact de la connaissance inexacte de la masse de l'avion dans le suivi de trajectoires, ses conséquences dans l'optimisation, la consommation de carburant, et la performance de l'avion, a conduit à l'implémentation d'une estimation embarquée de la masse de l'avion. L'approche créée est basée sur les moindres carrées, en fournissant des estimations de la masse initiale et la masse courante, toutes les deux avec une précision suffisante pour atteindre les objectifs liées aux TBO. Les méthodes proposées dans cette thèse sont examinées en utilisant un modèle à six degrés de liberté, dont les paramètres approchent un appareil du type B737-200 ou A320-200. La simulation est basée sur une modélisation complète et non linéaire de la dynamique des avions de transport incluant des perturbations liées au vent. Des réseaux de neurones sont utilisés pour obtenir les différents coefficients aérodynamiques correspondant aux forces et moments de l'avion<br>This work is developed with the perspective of SESAR and Next-Gen projects, where new applications of Air Traffic Management (ATM) such as the Full 4D Management concept, are centered on Trajectory-Based Operations (TBO), deeply related with the extension of the flexibility in separation between aircraft, and hence, with the augmentation of air traffic capacity. Therefore, since a shift from fixed routes and Air Traffic Control (ATC) clearances to flexible trajectories is imminent, while relying on higher levels of onboard automation, the thesis hinges around topics that should enable or ease the transition from current systems to systems compliant with the new expectancies of Trajectory-Based Operations. The main axes of the manuscript can be summarized in three topics: 4D trajectory generation, 4D guidance, and mass estimation for trajectory optimization. Regarding the trajectory generation, the need of airspace users to plan their preferred route from an entry to an exit point of the airspace without being constrained by the existent configurations is considered. Thus, a particular solution for 4D smooth path generation from preexisting control points is explored. The method is based on Bezier curves, and is able to control the Euclidian distance between the given control points and the proposed trajectory. This is done by reshaping the path to remain within load factor limits, taking into account a tradeoff between path curvature and aircraft intended speed, representing a milestone in the road towards Trajectory-Based Operations. It is considered that accurate 4D guidance will improve safety by decreasing the occurrence of near mid-air collisions for planned conflict free 4D trajectories. In consequence, two autopilots and two guidance approaches are developed with the objective of diminishing the workload for air traffic controllers associated to a single flight. The backstepping and feedback linearization techniques are used for attitude control, while direct and indirect nonlinear inversion are adopted for guidance. Furthermore, the impact of inaccurate mass knowledge in trajectory guidance, with consequences in optimization, fuel consumption, and aircraft performance, has led to the implementation of an on-board aircraft mass estimation. The created approach is based on least squares, providing an initial mass estimation, and online computations of the current mass, both with enough accuracy to meet the objectives related to TBO. The methods proposed in this thesis are tested in a six degrees of freedom Matlab model with its parameters chosen similar to an aircraft type B737-200 or A320-200. The simulation is based on a full nonlinear modelling of transport aircraft dynamics under wind disturbances. Trained neural networks are used to obtain the aerodynamic coefficients corresponding the aircraft forces and moments
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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<br>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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Mcfadyen, Aaron. "Visual control for automated aircraft collision avoidance systems." Thesis, Queensland University of Technology, 2015. https://eprints.qut.edu.au/81418/1/Aaron_McFadyen_Thesis.pdf.
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This thesis presents a new vision-based decision and control strategy for automated aircraft collision avoidance that can be realistically applied to the See and Avoid problem. The effectiveness of the control strategy positions the research as a major contribution toward realising the simultaneous operation of manned and unmanned aircraft within civilian airspace.
Key developments include novel classical and visual predictive control frameworks, and a performance evaluation technique aligned with existing aviation practise and applicable to autonomous systems. The overall approach is demonstrated through experimental results on a small multirotor unmanned aircraft, and through high fidelity probabilistic simulation studies.
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Hou, Zhicheng. "Modeling and formation controller design for multi-quadrotor systems with leader-follower configuration." Thesis, Compiègne, 2016. http://www.theses.fr/2016COMP2259/document.
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Cette thèse propose des solutions aux problématiques inhérentes au contrôle de formations aériennes de type leader-suiveur pour des flottes de quadrirotors. Au regard des travaux existants, les stratégies qui sont proposés dans notre travail, considère que le(s) leader{s) a une interaction avec les suiveurs. En outre, les rôles de leader et de suiveur sont interchangeables lors de la formation. Dans un premier temps, la modélisation mathématique d'un seul quadrirotor et celle de la formation de quadrirotors est développée. Ensuite, le problème de suivi de trajectoire pour un seul quadrirotor est étudié. Au travers de l'analyse de 1, dynamique du système pour la conception d'une commande par platitude, il apparait que le suivi de trajectoire pour chaque quadrirotor équivaut à déterminer les sorties plates désirées. Un contrôleur pour système plats permettant l'asservissement des drones pour le suivi de trajectoire est donc proposé. Étant donné la propriété de double-boucle de la dynamique du quadrirotor en boucle fermée, un contrôleur d'attitude avec des grands gains est conçu, selon la théorie « singular perturbation system ». Puisque la dynamique du quadrirotor en boucle fermée fonctionne sur deux échelles de temps, la dynamique de rotation (boundary-layer mode) est contrôlée sur l'échelle de temps la plus rapide. La conception du contrôleur de formation dépend seulement de la dynamique de translation (modèle réduit dans une échelle de temps lente). Ce résultat a simplifié la conception du contrôleur de formation, de telle sorte que le modèle réduit du quadrirotor est utilisé au lieu du modèle complet. Étant donné que le modèle réduit du quadrirotor a une caractéristique de double-intégrateur, un algorithme de consensus pour des systèmes caractérisés par de multiple double-intégrateurs est proposé. Pour traiter le problème de la formation leader-suiveur, une matrice d'interaction est initialement proposée basée sur la matrice de Laplacienne. Nous montrons que la condition de convergence et la vitesse de convergence de l'erreur de formation dépendent de la plus petite valeur propre de la matrice d'interaction. Trois stratégies de contrôle de la formation avec une topologie fixe sont ensuite proposées. Le contrôle de formation par platitude est proposé pour obtenir une formation agressive, tandis que les dérivées de grands ordres de la trajectoire désirée pour chaque UAV sont estimées en utilisant un observateur; la méthode Lyapunov redesign est implémentée pour traiter les non-linéarités de la dynamique de la translation des quadrotors; une loi de commande bornée par l'utilisation, entre autre, de la fonction tangente hyperbolique est développée avec un feedback composite non linéaire, afin d'améliorer les performances de la formation. De plus, une commande de commutation saturée de la formation est étudiée, car la topologie de la formation est variable. La stabilité du système est obtenue grâce aux théories “convex hull » et « common Lyapunov function ». Cette stratégie de commande de commutation permet le changement des leaders dans la formation. Inspirée par certains travaux existants, tels que le contrôle de la formation avec des voisins anonymes, nous proposons, finalement, une loi de commande avec des voisins pondérés, qui montre une meilleure robustesse que le contrôle avec des voisins anonymes. Les résultats de simulation obtenus avec Matlab illustrent premièrement nos stratégies de contrôle que nous proposons De plus, en utilisant le langage de programmation C ++, nos stratégies sont mises en œuvre dans un framework de simulation et d'expérimentation développé au laboratoire Heudiasyc. Grâce aux nombreux tests variés que nous avons réalisés en simulation et en temps-réel, l'efficacité et les avantages de nos stratégies de contrôle de la formation proposées sont présentés<br>In this thesis, we address a leader-follower (L-F) formation control problem for multiple UAVs, especially quadrotors. Different from existing works, the strategies, which are proposed in our work, consider that the leader(s) have interaction with the followers. Additionally, the leader(s) are changeable during the formation. First, the mathematical modeling of a single quadrotor and of the formation of quadrotors is developed. The trajectory tracking problem for a single quadrotor is investigated. Through the analysis of the flatness of the quadrotor dynamical model, the desired trajectory for each quadrotor is transferred to the design of the desired at outputs. A flatness-based trajectory tracking controller is, then, proposed. Considering the double-loop property of the closed-loop quadrotor dynamics, a high-gain attitude controller is designed, according to the singular perturbation system theory. Since the closed-loop quadrotor dynamics performs in two time scales, the rotational dynamics (boundary-layer model) is controlled in a fast time scale. The formation controller design is then only considered for the translational dynamics: reduced model in a slow time scale. This result has simplified the formation controller design such that the reduced model of the quadrotor is considered instead of the complete model. Since the reduced model of the quadrotor has a double-integrator characteristic, consensus algorithm for multiple double-integrator systems is proposed. Dealing with the leader-follower formation problem, an interaction matrix is originally proposed based on the Laplacian matrix. We prove that the convergence condition and convergence speed of the formation error are in terms of the smallest eigenvalue of the interaction matrix. Three formation control strategies with fixed formation topology are then proposed. The flatness-based formation control is proposed to deal with the aggressive formation problem, while the high-order derivatives of the desired trajectory for each UAV are estimated by using an observer; the Lyapunov redesign is developed to deal with the nonlinearities of the translational dynamics of the quadrotors; the hyperbolic tangent-based bounded control with composite nonlinear feedback is developed in order to improve the performance of the formation. In an additional way, a saturated switching control of the formation is investigated, where the formation topology is switching. The stability of the system is obtained by introducing the convex hull theory and the common Lyapunov function. This switching control strategy permits the change of the leaders in the formation. Inspired by some existing works, such as the anonymous neighbor-based formation control, we finally propose a weighted neighbor-based control, which shows better robustness than the anonymous neighbor-based control. Simulation results using Matlab primarily illustrate our proposed formation control strategies. Furthermore, using C++ programming, our strategies are implemented on the simulator-experiment framework, developed at Heudiasyc laboratory. Through a variety of tests on the simulator and real-time experiments, the efficiency and the advantages of our proposed formation control strategies are shown. Finally, a vision-based inter-distance detection system is developed. This system is composed by an on-board camera, infrared LEDs and an infrared filter. The idea is to detect the UAVs and calculate the inter-distance by calculating the area of the special LEDs patterns. This algorithm is validated on a PC, with a webcam and primarily implemented on a real quadrotor
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Herrera, Jason (Jason Richard). "Evaluation of control systems for automated aircraft wing manufacturing." Thesis, Massachusetts Institute of Technology, 2013. http://hdl.handle.net/1721.1/82484.
Full textAbstract:
Thesis (M.B.A.)--Massachusetts Institute of Technology, Sloan School of Management; and, (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics; in conjunction with the Leaders for Global Operations Program at MIT, 2013.<br>This electronic version was submitted and approved by the author's academic department as part of an electronic thesis pilot project. The certified thesis is available in the Institute Archives and Special Collections.<br>Cataloged from department-submitted PDF version of thesis<br>Includes bibliographical references (p. 62-64).<br>The Boeing Company is looking to bring aircraft manufacturing technology into the 21st century. As part of this process, several projects have been started to develop the technologies required to achieve Boeing's vision for the future of aircraft manufacturing. To date, much of this work has focused on hardware, including robotic and other automation technologies. However, in order to use this hardware, a significant effort must also be made in the area of factory control and coordination. This thesis advances knowledge in this area by evaluating the suitability of different control system approaches for aircraft wing box assembly. First, general classes of control systems are discussed and several criteria are proposed for evaluating their performance in an aircraft manufacturing environment. The current wing box assembly process is then examined in order to develop simplified but representative task networks to which various algorithms can be applied. The Tercio algorithm, developed at MIT, is used to generate schedules for several problem structures of interest in order to characterize the algorithm's performance in this context. The Tercio algorithm is then benchmarked against the Aurora scheduling tool, showing that Tercio can generate more efficient schedules than Aurora, but at the cost of increased computation time. Next, management considerations with respect to product design, manufacturing technology development, and implementation associated with advanced manufacturing technologies are discussed. Finally, recommendations are provided for how Boeing can accelerate the development of useful and practical advanced, automated manufacturing systems.<br>by Jason Herrera.<br>S.M.<br>M.B.A.
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Dierker, Dominic J. "An Automated Controller Design Methodology for Six Degree-of-Freedom Aircraft Models." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright151610728419557.
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Aguilar, Cortés Carlos Ezequiel. "Air carrier liability and automation issues." Thesis, McGill University, 2002. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=78196.
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Our intended topic is a general discussion of the basic elements of liability related to airline accidents to which fully automated cockpits have constituted an associated contributory factor. In addition we addressed the liability of air carriers arising from injuries or death caused to passengers traveling on international flights. For this purpose, we reviewed the Warsaw System and the different international instruments that constitute it. We also reviewed principles of common law applicable to aircraft manufacturers and the "Free Flight" as an example of the growing automation environment, which is a general benefit to commercial aviation but also a likely contributory cause for accidents in particular cases. In the last part we briefly discuss a personal view regarding the interplay between manufacturers and airlines under the 1999 Montreal Convention, which is an international treaty unifying the desegregated Warsaw System into one single instrument that is expected to enter into force in a few years.
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Nguyen, Van Cuong. "Système de commande embarqué pour le pilotage d'un lanceur aéroporté automatisé." Thesis, Evry-Val d'Essonne, 2013. http://www.theses.fr/2013EVRY0003/document.
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Cette thèse traite du problème de la stabilisation d'un système de lancement aéroporté (éventuellement non habité) pour satellites. Le lancement aéroporté consiste à ramener, à l'aide d'un avion, un satellite et son lanceur (fusée) à une certaine hauteur, et d'exécuter son lancement dans les airs (souvent en larguant la fusée). Ceci est similaire au lancement d'un missile par un avion chasseur. La plus grande différence réside dans le rapport de masse entre l'avion et le lanceur qui est beaucoup plus proche de l'unité (fusée lourde comparée à la masse de l'avion). Le système est composé de deux étages: le premier étage est dit avion porteur qui est un véhicule aérien automatisé. Il porte le lanceur qui constitue le deuxième étage (la fusée). Dans la première partie, sont proposées des approches de modélisation pour le système de largage pendant et après le largage. La première approche considère que la phase de séparation est instantanée, mais imparfaite. Par conséquent le système est vu comme un modèle d'aéroplane dont les variables d'état sont avec des larges conditions initiales dues à la séparation imparfaite. Une deuxième approche considère la séparation elle-même, représentée par une forte perturbation (un extrême cas) sur les forces et couples aérodynamiques du modèle au cours d'un intervalle de temps. Dans la deuxième partie, afin de stabiliser le système de largage après la séparation, la commande à intégrateur conditionnel modifié est développée dans un premier temps pour une classe des systèmes non-linéaires multi-entrées multi-sorties, avec comme point de départ la théorie introduite par Khalil et co-auteurs pour des systèmes mono entrée mono sortie. Cette commande a été ensuite étendue pour la commande à servo-compensateur conditionnel modifié pour une classe de systèmes non-linéaires multi-entrées multi-sorties. Les deux stratégies ont été appliquées pour stabiliser le système de largage pendant et après la phase de séparation. Ces techniques ont l'avantage d'être robustes et de pouvoir utiliser des modèles approximatifs. D'un autre côté, il était important d'examiner la possibilité d'obtenir de meilleures performances en utilisant de meilleurs modèles. Pour cette raison, la commande de linéarisation par bouclage dynamique a été étudiée. Finalement, les performances de toutes ces méthodes de commande (ainsi que certaines commandes de base additionnelles) ont été illustrées par des simulations sous Matlab/Simulink sur un modèle non-linéaire de F-16<br>This thesis addresses the problem of the stabilization of an (unmanned) airlaunch system. Air launching consists in bringing a satellite and its launcher (rocket) to a certain height using an aircraft, and then launching it from the air (often by dropping the rocket), in a similar way of launching a missile from a fighter. The main difference is that the envisaged mass ratio is much closer to one (heavy rocket compared to aircraft mass). It is then composed of two stages: the first stage called carrier aircraft consists of an aerial vehicle that carries the launcher which constitutes the second stage (rocket). This thesis starts by introducing the problem and objectives, continues by presenting several approaches to model the airlaunch system, and ends by developing different advanced control methods to stabilize it after the launching phase. In the modeling part we propose a firstly approach called the initial condition model which assumes that the separation phase is instantaneous, and then the airlaunch system is composed of an aircraft model after the launching phase but with large initial conditions on its state variables, caused by a non-perfect split phase. A second approach assumes that the separation phase itself is modeled by a disturbance on aerodynamic forces and moments (from a worst case) during a time interval. In the control part a modified conditional integrator controller for a class of nonlinear multi-input multi-output systems is first developed starting from the conditional integrator theory developed by Khalil and co-workers. It is then extended to a modified conditional servocompensator control for a class of nonlinear multi-input multi-output systems. Both control strategies were then applied to stabilize the airlaunch system after the separation phase. They have the advantage of being very robust, and they don't depend so much on reliable models. Even if these control strategies gave good results, it was investigated in this thesis another control approach much more dependent on detailed and reliable models. This approach was based on dynamic feedback linearization theory, and the main idea is to obtain better performance in trade off better models. Finally, all proposed control methods (plus some standard ones) were compared and illustrated by simulations under Matlab/Simulink on a nonlinear F-16 model. These simulations have shown that the results were as expected, and that each control strategy was well fit for a particular situation
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Querry, Stephane. "Stochastic optimization by evolutionary methods applied to autonomous aircraft flight control." Thesis, Strasbourg, 2014. http://www.theses.fr/2014STRAD031.
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Le but de ce doctorat est de déterminer dans quelle mesure les algorithmes issus de l’intelligence artificielle, principalement les Algorithmes Evolutionnaires et la Programmation Génétique, pourraient aider les algorithmes de l’automatique classique afin de permettre aux engins autonomes de disposer de capacités bien supérieures, et ce dans les domaines de l’identification, de la planification de trajectoire, du pilotage et de la navigation.De nouveaux algorithmes ont été développés, dans les domaines de l’identification, de la planification de trajectoire, de la navigation et du contrôle, et ont été testés sur des systèmes de simulation et des aéronefs du monde réel (Oktokopter du ST2I, Bebop.Drone de la société Parrot, Twin Otter et F-16 de la NASA) de manière à évaluer les apports de ces nouvelles approches par rapport à l’état de l’art.La plupart de ces nouvelles approches ont permis d’obtenir de très bons résultats comparés à l’état de l’art, notamment dans le domaine de l’identification et de la commande, et un approfondissement des travaux devraient être engagé afin de développer le potentiel applicatifs de certains algorithmes<br>The object of this PhD has consisted in elaborating evolutionary computing algorithms to find interesting solutions to important problems in several domains of automation science, applied to aircrafts mission conduction and to understand what could be the advantages of using such approaches, compared to the state-of-the-art, in terms of efficiency, robustness, and effort of implementation.New algorithms have been developed, in Identification, Path planning, Navigation and Control and have been tested on simulation and on real world platforms (AR.Drone 3.0 UAV (Parrot), Oktokopter UAV, Twin Otter and military fighter F-16 (NASA LaRC)), to assess the performances improvements, given by the new proposed approaches.Most of these new approaches provide very interesting results; and research work (on control by evolutionary algorithms, identification by genetic programming and relative navigation) should be engaged to plan potential applications in different real world technologies
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Claase, Etienne H. "Robust multi-H2 output-feedback approach to aerial refuelling automation of large aircraft via linear matrix inequalities." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80195.
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Thesis (MScEng)--Stellenbosch University, 2013.<br>ENGLISH ABSTRACT: In recent years the aviation industry has shown an interest in the airborne refuelling
of large transport aircraft to enable increased payload mass at take-off and
to extend aircraft range. Due to the large volume of fuel to be transferred, a boom
and receptacle refuelling system with a larger fuel transfer rate is employed. The
refuelling operation is particularly difficult and strenuous for the pilot of the receiver
aircraft, because the position of the receptacle relative to the tanker aircraft must
be maintained within a narrow window for a relatively long period of time. The
airborne refuelling of a large aircraft is typically much more difficult than that of a
fighter aircraft, since the large aircraft is more sluggish, takes much longer to refuel,
and has a relatively large distance between its refuelling receptacle and its centre of
mass. These difficulties provide the motivation for developing flight control laws for
Autonomous In-Flight Refuelling (AIFR) to alleviate the workload on the pilot.
The objective of the research is to design a flight control system that can regulate
the receptacle of a receiver aircraft to remain within the boom envelope of a tanker
aircraft in light and medium turbulence. The flight control system must be robust
to uncertainties in the aircraft dynamic model, and must obey actuator deflection
and slew rate limits.
Literature on AIFR shows a wide range of approaches, including Linear Quadratic
Regulator (LQR), μ-synthesis and neural-network based adaptive control, none of
which explicitly includes constraints on actuator amplitudes, actuator rates and
regulation errors in the design/synthesis. A new approach to designing AIFR flight
control laws is proposed, based on Linear Matrix Inequality (LMI) optimisation.
The relatively new LMI technique enables optimised regulation of stochastic systems
subject to time-varying uncertainties and coloured noise disturbance, while simultaneously
constraining transient behaviour and multiple outputs and actuators to
operate within their amplitude, saturation and slew rate limits. These constraints
are achieved by directly formulating them as inequalities.<br>AFRIKAANSE OPSOMMING: Die lugvaart industrie toon huidiglik ’n belangstelling in die brandstof oordrag
tussen twee groot vervoervliegtuie gedurende vlug, met die doel om die maksimum
opstyggewig kapasiteit sowel as die maksimum ononderbroke vlugafstand vermoë
van die hervulde vliegtuig te vermeerder. ’n Boom hervulling-stelsel word geïmplementeer
om die hoë spoed van brandstof oordrag te voorsien. Die verrigting van
vluggebonde hervulling van ’n groot, trae vliegtuig is moeiliker en meer veeleisend
as bv. van ’n vegvliegtuig, veral vir die vlieënier van die hervulde vliegtuig, wat
sy boom-skakel moet reguleer binne ’n relatiewe klein boom bewegingsruimte vir ’n
relatiewe lang tydperk. Die kinematika betrokke speel ook ’n groter rol in ’n groot
hervulde vliegtuig a.g.v. die langer afstand tussen die boom-skakel en die massa middelpunt/
draaipunt. Hierdie bied die motivering om ’n beheerstelsel te ontwikkel wat
die taak outomaties uitvoer.
Die doel van die navorsing is om ’n beheerstelsel te ontwerp wat die boom-skakel
van die hervulde vliegtuig outomaties reguleer binne die bewegingsruimte van die
boom, gedurende ligte en matige turbulensie. Daar word van die beheerder vereis
om robuust te wees teen onsekerhede in die vliegtuig se meganika, sowel as om die
beheer oppervlaktes en turbines van die vliegtuig binne hul defleksie-, wringkrag- en
sleurtempo-perke te hou.
Daar bestaan reeds ’n groot verskeidenheid van benaderings tot die outomatisering
van luggebonde hervulling, onder andere LQR, μ-sintese en neurale-netwerk
gebaseerde aanpasbare beheer, waarvan geeneen perke op aktueerders en regulasie
foute direk in die ontwerp insluit nie. ’n Nuwe benadering word voorgestel wat
gebaseer is op Linear Matrix Inequality (LMI) optimering. Die LMI tegniek is relatief
nuut in die gebruik van beheerstelsel ontwerp. Dit stel die ontwerper in staat
om ’n stogastiese stelsel, onderworpe aan tydvariante-stelsel-variasie en gekleurde
ruis versteurings, optimaal te reguleer, terwyl aktueerders en stelsel gedrag direk
beperk word.
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Topsakal, Julide Julie. "Robust Motion Planning in the Presence of Uncertainties using a Maneuver Automaton." Thesis, Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/6904.
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One of the basic problems which have to be solved by Unmanned Automated Vehicles (UAV) involves the computation of a motion plan
that would enable the system to reach a target given a set of initial conditions in presence of uncertainties on the vehicle dynamics and in the environment. Recent research efforts in this
area have relied on deterministic models. To address the problem of inevitable uncertainties, a low-level control layer is typically used to ensure proper robust trajectory tracking. Such
decision-tracking algorithms correct model disturbances a posteriori, while the whole movement planning is done in a purely
deterministic fashion.
We argue that the decision making process that takes place during movement planning, as performed by experienced human pilots, is not
a purely deterministic operation, but is heavily influenced by the presence of uncertainties and reflects a risk-management policy. This research aims at addressing these uncertainties and developing an optimal control strategy that would account for the presence of
system uncertainties.
The underlying description of UAV trajectories will be based on a modeling language, the Maneuver Automaton, that takes into full
account the vehicle dynamics, and hence guarantees flyable and trackable paths and results in a discretized solution space. Two
optimal control problems, a nominal problem omitting uncertainties and a robust problem addressing the presence of uncertainties,
will be defined and compared throughout this work. The incorporation of uncertainties, will ensure that the generated motion planning policies will maximize the probability to meet
mission goals, weighing risks against performance.
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Carmody, Meghan A. "Task-Dependent Effects of Automation: The Role of Internal Models in Performance, Workload, and Situational Awareness in a Semi-Automated Cockpit." Ft. Belvoir Defense Technical Information Center, 1994. http://handle.dtic.mil/100.2/ADA292538.
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Hvězda, Michal. "Model systému automatického řízení přesného přiblížení a přistání civilního dopravního letadla za použití informací DGNSS." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-438882.
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LPV approaches are being published in the Czech Republic nowadays. Their usage is enabled by the EGNOS European satellite augmentation system. However, published decision heights do not allow equivalence with the ILS CAT I precision approach yet. This work presents the model of automated control of aircraft precision approach. Verification of its functionality shows that applicable airspace requirements can be fulfilled for lower values of decision heights than values already published. The model is developed using contemporary methods of model-based development in the tool supporting common processing of both continuous and discrete signals. Although model architecture follows the structure of commonly used ILS system in definition of coordinate system and in establishing control in two separate directions it allows curved approach. Usage of digital navigation data provided by satellite system opens further opportunities in its usage, expansion and improvements. Model functionality in control of flight course, position and height control is verified in the scenarios covering detailed thesis goals. The goals were defined based on definition of precision approach process and include navigation signal drop-out, impact of wind, various flight path angles and curved approach. Analysis of behavior of controlled aircraft dynamics was a stimulator for research of specific system modules up to the application level, i.e. specific simulations of successful precision approaches.
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Eklund, Adam, and Jesper Karner. "Development of a Framework for Concept Selection and Design Automation : Utilizing hybrid modeling for indirect parametric control of subdivision surfaces." Thesis, Linköpings universitet, Maskinkonstruktion, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-147755.
Full textAbstract:
Saab Aeronautics’ section Overall Design and Survivability develops early aircraft concepts and utilizes Computer Aided Design (CAD) to ensure the feasibility of principal- and critical characteristics. Saab has over the years developed several start models of aircrafts in CAD from pre-defined aircraft configurations, which are to some extent non-generic. When new configurations are to be explored, manual- and repetitive work is required if the new configuration cannot be attained solely through parametric modifications of a start model. The complexity of these CAD models also demands great knowledge of how aircraft components interact with each other to ensure compatibility. The project covered in this thesis was thus carried out to develop a more effective way for Saab to create and explore a larger design space. This by creating a framework that consists of a product configurator coupled with a library of generic CAD models. The product configurator that was created is the Saab Tradespace Analyzer & Reconfigurator (STAR), which takes compatibility relationships into consideration to facilitate concept selection. The STAR also provides a dynamic design space calculation to indicate how close the user is to a final concept selection. Two generic CAD models were created, a fuselage model and an air inlet model. A skeleton model was also created in order to reduce model dependencies and to control the main geometry of the aircraft product. In addition to these, an already existing wing model was implemented to form the library of generic CAD models. The framework coupling the STAR with the CAD library utilizes design automation to allow automatic CAD model generation of a concept that has been selected within the STAR. It was concluded through extrapolation that the created framework would allow Saab to create and explore a larger design space in a more effective way than what is done today, provided the library of CAD models were to contain the same number of components as today’s start models.
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Alonso, Tabares Diego. "Contribution à l'automatisation des opérations au sol des aéroports." Thesis, Toulouse 3, 2018. http://www.theses.fr/2018TOU30225.
Full textAbstract:
The sustainability of air transport relies on proper and timely aircraft ground handling. Lack of manpower and current ground handling industry conditions makes innovation and automation the only way to support existing growth rates. This research presents the state of the art of aircraft ground handling at airports, identifying the challenges to overcome in building safe, efficient and environmental friendly automated ground operations. The greatest opportunity lies with automated docking of ground support equipment to aircraft, with further autonomous vehicles moving around the aircraft and automated systems within the aircraft later on. The problem formulation for resources assignment for ground handling in a fully automated environment is undertaken. On-line solutions for the fleet assignment problem are proposed and applied to an airport case<br>La durabilité du transport aérien est basée sur le bon déroulement de la manutention des avions. Le manque de main d’œuvre et les conditions existantes sur l’industrie de la manutention au sol fait que l’innovation et l’automatisation sont la seule façon de maintenir le rythme de croissance actuel. Cette recherche présente l’état de l’art de la manutention au sol des avions, identifie les défis à résoudre pour parvenir à des opérations au sol sécurisées, efficaces et respectueuses de l’environnement. La meilleure opportunité est dans l’accostage automatique des matériels au sol à l’avion, avec des véhicules autonomes qui vont évoluer autour de l’avion et des systèmes automatisés dans l’avion lui-même. La formulation du problème pour l’allocation des ressources pour la manutention au sol des avions dans le cadre totalement automatisé est entreprise. Des solutions en ligne pour le problème d’assignation des flottes sont proposées et appliquées dans un aéroport
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Нощенко, Сергій Петрович. "Автоматизований вихрострумовий дефектоскоп для моніторингу стану елементів конструкцій літальних апаратів". Master's thesis, КПІ ім. Ігоря Сікорського, 2020. https://ela.kpi.ua/handle/123456789/38193.
Full textAbstract:
Магістерська дисертація містить 112 листа, 25 рисунків, 23 таблиць, 18 джерел за переліком посилань.
У дисертації приведений аналіз елементів конструкцій, як об’єкта НК контролю. Підтверджена доцільність використання вихрострумового неруйнівного контролю для виявлення дефектів типу поверхневих та підповерхневих утомних тріщин та оцінки їх параметрів.
Проведений огляд можливих методів опрацювання прийнятих сигналів за наявними годографами відносної внесеної напруги. Розглянуто типи накладних та прохідних вихрострумових перетворювачів. Проведений аналіз підтвердив доцільність використання вихрострумового перетворювача трансформаторного типу з диференційно з’єднаними вимірювальними котушками.
Підчас аналізу годографів внесеної напруги від дефекту було виявлено можливості більш детального кількісного оцінювання параметрів дефекту за вихідним сигналом ВСП. Отримані за годографом внесеної напруги від дефекту орієнтовні градуювальні характеристики для параметрів дефектів дали змогу прослідкувати особливості зміни фази та амплітуди прийнятого сигналу ВСП від глибини залягання та глибини дефекту. . Запропоновані технічні рішення дають змогу автоматизувати процес контролю щодо прийняття рішення про наявність дефекту та оцінювання числових показників дефектів.<br>The master's dissertation contains 82 letters, 25 figures, 23 tables, 18 sources according to the list of references.
The dissertation presents an analysis of structural elements as an object of NC control. The expediency of using eddy current non-destructive testing to detect defects such as surface and subsurface fatigue cracks and evaluate their parameters has been confirmed.
A review of possible methods of processing the received signals according to the available hodographs of the relative applied voltage. Types of overhead and through-flow eddy current converters are considered. The analysis confirmed the feasibility of using an eddy current transducer of the transformer type with differentially connected measuring coils.
During the analysis of hodographs of the applied stress from the defect, the possibilities of a more detailed quantitative assessment of the defect parameters according to the VSP output signal were revealed. The approximate calibration characteristics for the defect parameters obtained from the hodograph of the applied stress from the defect made it possible to trace the peculiarities of the phase and amplitude change of the received GSP signal from the depth and depth of the defect. . The proposed technical solutions make it possible to automate the process of control over the decision on the presence of a defect and the evaluation of numerical indicators of defects.
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Chiu, Jen-Chun, and 邱仁君. "Applications of Fuzzy Neural Networks to Aircraft Automatic Landing Control." Thesis, 2002. http://ndltd.ncl.edu.tw/handle/71958502154828437937.
Full textAbstract:
碩士<br>國立海洋大學<br>航運技術研究所<br>90<br>Fuzzy neural networks have been applied to flight control for their better adaptability and robustness for unmodeled systems and hardware implementation capability. Fuzzy neural networks can increase the flight controller’s adaptation to different environments. Currently, most of the improvements in the Automatic Landing System (ALS) have involved the guidance instruments. Using improved calculation methods and highly accurate instruments, these systems provide more accurate flight data to the ALS to make the landing smoother. However, these researches do not include weather factors such as wind shear. There have not been many researches on the problem of intelligent landing control. The purpose of this thesis is to apply a fuzzy neural network controller to an aircraft automatic landing system. In this research, we investigate a fuzzy neural network system that combines the advantages of the fuzzy logic and neural network systems. The Backpropagation Through Time algorithm is implemented into the network learning process. A complete landing phase is divided into several stages (intervals). Each stage uses the same fuzzy neural network controller. The Linearized Inverse Aircraft Model calculates the error signals that will be used to back propagate through the controller to obtain the weight changes in each stage. The error continues to be back propagated through all of the stages and weight changes for the controller are computed at each stage. The weight changes from all obtained stages from the delta learning rule are added together for the overall update. Simulation results show that the trained controller can guide the aircraft to land safely through wind disturbances and successfully expand the controllable environment in severe wind disturbances.
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Collins, David C. (David Charles) 1969. "Adaptive model reference control of highly maneuverable high performance aircraft." Thesis, 1993. http://hdl.handle.net/1957/37416.
Full textAbstract:
This thesis presents an adaptive model reference controller for a highly
maneuverable high performance aircraft, in particular, a modified F18. An adaptive
controller is developed to maneuver an aircraft at a high angle of attack. Thus, the
aircraft is required to fly over a highly nonlinear flight regime. The adaptive controller
presented in this thesis can be viewed as a combination of a linear and a nonlinear
controller. Around a fixed flight condition the adaptive controller converges to a linear
controller; however, the controller remains a nonlinear controller during maneuvers.
The contributions of this thesis lie in two areas. The first area is in control.
A successful application of linear adaptive control is presented for a highly nonlinear
system. A new method is used to generate the reference trajectory. The reference
model uses output feedback to improve the reference trajectory. It is shown that this
improvement is necessary because of the control limitations. This work is also
important to the control of highly maneuverable high performance aircraft. A
successful adaptive controller has been developed to rapidly maneuver an aircraft to
a high angle of attack. The main focus of this thesis is adaptive control.<br>Graduation date: 1993
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Bean, Ronnie A. "Nonlinear control of high performance aircraft." Thesis, 1994. http://hdl.handle.net/1957/35260.
Full textAbstract:
This thesis presents the design of various controllers for a highly maneuverable,
high performance aircraft, namely the modified F-18. The aircraft
was required to perform high angle-of-attack maneuvers, for which the aircraft
behaves in as a highly nonlinear system. An adaptive PID controller
was used to control the aircraft through these high angle-of-attack maneuvers.
Several nonlinear controllers were then developed based on the adaptive PID
control, and were tested for robustness. This thesis also looks at an improvement
in the aircraft which may improve performance in high angle-of-attack
maneuvers.
The contributions of this thesis are in the areas of control, in general, and
specifically in the area of aircraft control. Successful application of linear
adaptive control and nonlinear control were presented. In the area of aircraft
control, controllers were presented which produce good performance for high
angle-of-attack maneuvers, while maintaining implementability. Also, some
insight is gained into what aircraft changes could improve performance.<br>Graduation date: 1995
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Chawla, Charu. "Robust Partial Integrated Guidance And Control Of UAVs For Reactive Obstacle Avoidance." Thesis, 2010. https://etd.iisc.ac.in/handle/2005/1659.
Full textAbstract:
UAVs employed for low altitude jobs are more liable to collide with the urban structures on their way to the goal point. In this thesis, the problem of reactive obstacle avoidance is addressed by an innovative partial integrated guidance and control (PIGC) approach using the Six-DOF model of real UAV unlike the kinematic models used in the existing literatures. The guidance algorithm is designed which uses the collision cone approach to predict any possible collision with the obstacle and computes an alternate aiming direction for the vehicle. The aiming direction of the vehicle is the line of sight line tangent to the safety ball surrounding the obstacle. The point where the tangent touches the safety ball is the aiming point. Once the aiming point is known, the obstacle is avoided by directing the vehicle (on the principles of pursuit guidance) along the tangent to the safety ball. First, the guidance algorithm is applied successfully to the point mass model of UAV to verify the proposed collision avoidance concept. Next, PIGC approach is proposed for reactive obstacle avoidance of UAVs.
The reactive nature of the avoidance problem within the available time window demands simultaneous reaction from the guidance and control loop structures of the system i.e, in the IGC framework (executes in single loop). However, such quick maneuvers cause the faster dynamics of the system to go unstable due to inherent separation between the faster and slower dynamics. On the contrary, in the conventional design (executes in three loops), the settling time of the response of different loops will not be able to match with the stringent time-to-go window for obstacle avoidance. This causes delay in tracking in all the loops which will affect the system performance adversely and hence UAV will fail to avoid the obstacle. However, in the PIGC framework, it overcomes the disadvantage of both the IGC design and the conventional design, by introducing one more loop compared to the IGC approach and reducing a loop compared to the conventional approach, hence named as Partial IGC.
Nonlinear dynamic inversion technique based PIGC approach utilizes the faster and slower dynamics of the full nonlinear Six-DOF model of UAV and executes the avoidance maneuver in two loops. In the outer loop, the vehicle guidance strategy attempts to reorient the velocity vector of the vehicle along the aiming point within a fraction of the available time-to-go. The orientation of the velocity vector is achieved by enforcing the angular correction in the horizontal and vertical flight path angles and enforcing turn coordination. The outer loop generates the body angular rates which are tracked as the commanded signal in the inner loop. The enforcement of the desired body rates generates the necessary control surface deflections required to stir the UAV. Control surface deflections are realized by the vehicle through the first order actuator dynamics. A controller for the first order actuator model is also proposed in order to reduce the actuator delay.
Every loop of the PIGC technique uses nonlinear dynamic inversion technique which has critical issues like sensitiveness to the modeling inaccuracies of the plant model. To make it robust against the parameter inaccuracies of the system, it is reinforced with the neuro-adaptive design in the inner loop of the PIGC design. In the NA design, weight update rule based on Lyapunov’s theory provides online training of the weights. To enhance fast and stable training of the weights, preflight maneuvers are proposed. Preflight maneuvers provide stabilized pre-trained weights which prevents any misapprehensions in the obstacle avoidance scenario.
Simulation studies have been carried out with the point mass model and with the Six-DOF model of the real fixed wing UAV in the PIGC framework to test the performance of the nonlinear reactive guidance scheme. Various simulations have been executed with different number and size of the obstacles. NA augmented PIGC design is validated with different levels of uncertainties in the plant model. A comparative study in NA augmented PIGC design was performed between the pre-trained weights and zero weights as used for weight initialization in online training. Various comparative study shows that the NA augmented PIGC design is quite effective in avoiding collisions in different scenarios. Since the NDI technique involved in the PIGC design gives a closed loop solution and does not operate with iterative steps, therefore the reactive obstacle avoidance is achieved in a computationally efficient manner.
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Chawla, Charu. "Robust Partial Integrated Guidance And Control Of UAVs For Reactive Obstacle Avoidance." Thesis, 2010. http://etd.iisc.ernet.in/handle/2005/1659.
Full textAbstract:
UAVs employed for low altitude jobs are more liable to collide with the urban structures on their way to the goal point. In this thesis, the problem of reactive obstacle avoidance is addressed by an innovative partial integrated guidance and control (PIGC) approach using the Six-DOF model of real UAV unlike the kinematic models used in the existing literatures. The guidance algorithm is designed which uses the collision cone approach to predict any possible collision with the obstacle and computes an alternate aiming direction for the vehicle. The aiming direction of the vehicle is the line of sight line tangent to the safety ball surrounding the obstacle. The point where the tangent touches the safety ball is the aiming point. Once the aiming point is known, the obstacle is avoided by directing the vehicle (on the principles of pursuit guidance) along the tangent to the safety ball. First, the guidance algorithm is applied successfully to the point mass model of UAV to verify the proposed collision avoidance concept. Next, PIGC approach is proposed for reactive obstacle avoidance of UAVs.
The reactive nature of the avoidance problem within the available time window demands simultaneous reaction from the guidance and control loop structures of the system i.e, in the IGC framework (executes in single loop). However, such quick maneuvers cause the faster dynamics of the system to go unstable due to inherent separation between the faster and slower dynamics. On the contrary, in the conventional design (executes in three loops), the settling time of the response of different loops will not be able to match with the stringent time-to-go window for obstacle avoidance. This causes delay in tracking in all the loops which will affect the system performance adversely and hence UAV will fail to avoid the obstacle. However, in the PIGC framework, it overcomes the disadvantage of both the IGC design and the conventional design, by introducing one more loop compared to the IGC approach and reducing a loop compared to the conventional approach, hence named as Partial IGC.
Nonlinear dynamic inversion technique based PIGC approach utilizes the faster and slower dynamics of the full nonlinear Six-DOF model of UAV and executes the avoidance maneuver in two loops. In the outer loop, the vehicle guidance strategy attempts to reorient the velocity vector of the vehicle along the aiming point within a fraction of the available time-to-go. The orientation of the velocity vector is achieved by enforcing the angular correction in the horizontal and vertical flight path angles and enforcing turn coordination. The outer loop generates the body angular rates which are tracked as the commanded signal in the inner loop. The enforcement of the desired body rates generates the necessary control surface deflections required to stir the UAV. Control surface deflections are realized by the vehicle through the first order actuator dynamics. A controller for the first order actuator model is also proposed in order to reduce the actuator delay.
Every loop of the PIGC technique uses nonlinear dynamic inversion technique which has critical issues like sensitiveness to the modeling inaccuracies of the plant model. To make it robust against the parameter inaccuracies of the system, it is reinforced with the neuro-adaptive design in the inner loop of the PIGC design. In the NA design, weight update rule based on Lyapunov’s theory provides online training of the weights. To enhance fast and stable training of the weights, preflight maneuvers are proposed. Preflight maneuvers provide stabilized pre-trained weights which prevents any misapprehensions in the obstacle avoidance scenario.
Simulation studies have been carried out with the point mass model and with the Six-DOF model of the real fixed wing UAV in the PIGC framework to test the performance of the nonlinear reactive guidance scheme. Various simulations have been executed with different number and size of the obstacles. NA augmented PIGC design is validated with different levels of uncertainties in the plant model. A comparative study in NA augmented PIGC design was performed between the pre-trained weights and zero weights as used for weight initialization in online training. Various comparative study shows that the NA augmented PIGC design is quite effective in avoiding collisions in different scenarios. Since the NDI technique involved in the PIGC design gives a closed loop solution and does not operate with iterative steps, therefore the reactive obstacle avoidance is achieved in a computationally efficient manner.
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Chiang, Pu-Hai, and 蔣步海. "A study of the integrated aircraft maintenance information system for automated scheduling and control management." Thesis, 2016. http://ndltd.ncl.edu.tw/handle/2m9m5c.
Full textAbstract:
博士<br>國立雲林科技大學<br>工業工程與管理系<br>104<br>This paper is to develop an integrated information platform of aircraft maintenance management (AMM) for optimization of scheduling planning and control management in the aircraft maintenance plant. The AMM system is offering the environments which maintenance resources are shared to improve the efficiency of production control, and as a result also is enhancing the effectiveness of the whole aircraft production and maintenance management.
Because any relevant maintenance jobs of the aircraft components should follow the existing procedures, it is identified as a category of job shop maintenance mode. In this research, we adopt an iterated greedy (IG) algorithm to solve the maintenance scheduling problems and to find an optimized solution; we also study the job shop scheduling problems (JSSP) with the objective of minimizing the total weighted tardiness (TWT), and the computations in effectiveness of IG algorithm are compared by benchmark test instances from the literature. Finally, the computational results show this proposed scheduling optimization model has a better performance.
In this paper, we also provided the practical application of the automated AMM information system, and the advantages are presented in the conclusions. The optimized maintenance scheduling results in reducing production cost and manpower; moreover, it also improves the relevant resources utilization and overall efficiency, and the AMM information system electronization can be not only effectively applied to the logistic engineering analysis but also relatively used to enhance the competitiveness of the whole aircraft production and maintenance management, the beneficial effect on striving for fleet management and maintenance business will be founded in the future for aircraft maintenance plants.
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(8660301), Chiyu Zhang. "MULTI-TARGET TRACKING AND IDENTITY MANAGEMENT USING MULTIPLE MOBILE SENSORS." Thesis, 2020.
Find full textAbstract:
<p>Due to their rapid
technological advancement, mobile sensors such as unmanned aerial vehicles (UAVs) are
seeing growing application in the area of multi-target tracking and identity management
(MTIM). For efficient and sustainable performance of a MTIM system with mobile
sensors, proper algorithms are needed to both effectively estimate the
states/identities of targets from sensing data and optimally guide the mobile sensors based
on the target estimates. One major challenge in MTIM is that a target may be
temporarily lost due to line-of-sight breaks or corrupted sensing data in cluttered
environments. It is desired that these targets are kept tracking and identification, especially
when they reappear after the temporary loss of detection. Another challenging task
in MTIM is to correctly track and identify targets during track coalescence,
where multiple targets get close to each other and could be hardly distinguishable.
In addition, while the number of targets in the sensors’ surveillance region is
usually unknown and time-varying in practice, many existing MTIM algorithms assume
their number of targets to be known and constant, thus those algorithms could not
be directly applied to real scenarios.</p>
<p>In this research, a set of
solutions is developed to address three particular issues in MTIM that involves the
above challenges: 1) using a single mobile sensor with a limited sensing range to
track multiple targets, where the targets may occasionally lose detection; 2) using a
network of mobile sensors to actively seek and identify targets to improve the accuracy of
multi-target identity management; and 3) tracking and managing the identities of an unknown and
time-varying number of targets in clutter.</p>
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(8063924), Austin L. Nash. "Hierarchical Combined Plant and Control Design for Thermal Management Systems." Thesis, 2019.
Find full textAbstract:
Over the last few decades, many factors, including increased electrification, have led to a critical need for fast and efficient transient cooling. Thermal management systems (TMSs) are typically designed using steady-state assumptions and to accommodate the most extreme operating conditions that could be encountered, such as maximum expected heat loads. Unfortunately, by designing systems in this manner, closed-loop transient performance is neglected and often constrained. If not constrained, conventional design approaches result in oversized systems that are less efficient under nominal operation. Therefore, it is imperative that \emph{transient} component modeling and subsystem interactions be considered at the design stage to avoid costly future redesigns. Simply put, as technological advances create the need for rapid transient cooling, a new design paradigm is needed to realize next generation systems to meet these demands. <br><br>In this thesis, I develop a new design approach for TMSs called hierarchical control co-design (HCCD). More specifically, I develop a HCCD algorithm aimed at optimizing high-fidelity design and control for a TMS across a system hierarchy. This is accomplished in part by integrating system level (SL) CCD with detailed component level (CL) design optimization. The lower-fidelity SL CCD algorithm incorporates feedback control into the design of a TMS to ensure controllability and robust transient response to exogenous disturbances, and the higher-fidelity CL design optimization algorithms provide a way of designing detailed components to achieve the desired performance needed at the SL. Key specifications are passed back and forth between levels of the hierarchy at each iteration to converge on an optimal design that is responsive to desired objectives at each level. The resulting HCCD algorithm permits the design and control of a TMS that is not only optimized for steady-state efficiency, but that can be designed for robustness to transient disturbances while achieving said disturbance rejection with minimal compromise to system efficiency. Several case studies are used to demonstrate the utility of the algorithm in designing systems with different objectives. Additionally, high-fidelity thermal modeling software is used to validate a solution to the proposed model-based design process. <br>