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Relevant bibliographies by topics / Missile flight control; Autopilot / Dissertations / Theses

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Dissertations / Theses on the topic 'Missile flight control; Autopilot'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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1

Jones, Campbell Llyr. "Neural control of a sea skimming missile." Thesis, University of Southampton, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.387900.

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2

Vural, Ozgur Ahmet. "Fuzzy Logic Guidance System Design For Guided Missiles." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/1026715/index.pdf.

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This thesis involves modeling, guidance, control, and flight simulations of a canard controlled guided missile. The autopilot is designed by a pole placement technique. Designed autopilot is used with the guidance systems considered in the thesis. Five different guidance methods are applied in the thesis, one of which is the famous proportional navigation guidance. The other four guidance methods are different fuzzy logic guidance systems designed considering different types of guidance inputs. Simulations are done against five different target types and the performances of the five guidance m

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3

Lai, Haoyu. "On the design of nonlinear gain scheduled control systems." Ohio : Ohio University, 1998. http://www.ohiolink.edu/etd/view.cgi?ohiou1176486900.

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4

Doruk, Resat Ozgur. "Missile Autopilot Design By Projective Control Theory." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/4/1089929/index.pdf.

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In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of all the states required for feedback. Because of this fact, the linear quadratic design

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5

Bibel, John Eugene. "Missile autopilot design using Mu-Synthesis." Thesis, This resource online, 1998. http://scholar.lib.vt.edu/theses/available/etd-08252008-161841/.

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6

Counsell, John Mark. "Optimum and safe control algorithim (OSCA) for modern missile autopilot design." Thesis, Lancaster University, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.332382.

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7

White, David Paul. "Missile autopilot design using a gain scheduling technique." Ohio : Ohio University, 1994. http://www.ohiolink.edu/etd/view.cgi?ohiou1179860306.

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8

Ozkan, Bulent. "Dynamic Modeling, Guidance, And Control Of Homing Missiles." Phd thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/12606533/index.pdf.

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DYNAMIC MODELING, GUIDANCE, AND CONTROL OF HOMING MISSILES &Ouml<br>ZKAN, B&uuml<br>lent Ph. D., Department of Mechanical Engineering Supervisor: Prof. Dr. M. Kemal &Ouml<br>ZG&Ouml<br>REN Co-Supervisor: Dr. G&ouml<br>kmen MAHMUTYAZICIOgLU September 2005, 236 pages In this study, the dynamic modeling, guidance, and control of a missile with two relatively rotating parts are dealt with. The two parts of the missile are connected to each other by means of a roller bearing. In the first part of the study, the governing differential equations of motion of the mentioned missile are derived. Then,

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9

Sefastsson, Ulf. "Evaluation of Missile Guidance and Autopilot through a 6 DOF Simulation Model." Thesis, KTH, Optimeringslära och systemteori, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-188897.

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Missile guidance and autopilot have been active fields of research since the second world war. There are lots of literature on the subjects, but the bulk of which are confined to overly simplified models, and therefore the publications of the methods applied to more realistic models are scarce. In this report a nonlinear 6 DOF simulation model of a tail-controlled air-to-air missile is considered. Through several assumptions and simplifications a linearized approximation of the plant is obtained, which then is used in the implementation of 5 guidance laws and 2 autopilots. The guidance laws ar

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10

Sharma, Manu. "A neuro-adaptive autopilot design for guided munitions." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12470.

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11

DeMott, Robert. "Development of a Flexible FPGA-Based Platform for Flight Control System Research." VCU Scholars Compass, 2010. http://scholarscompass.vcu.edu/etd/2321.

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This work is part of ongoing research conducted at Virginia Commonwealth University relating to unmanned aerial vehicles. The primary objective of this thesis was to develop a flexible, high-performance autopilot platform in order to facilitate research on advanced flight control algorithms. A dual FPGA-based system architecture utilizing a stacked, multi-board design was created to meet this goal. Processing tasks were split between the two FPGA devices, allowing for improved system timing and increased throughput. A combination of analog and digital filtering techniques were employed in

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12

Snyder, Mark. "NONLINEAR STABILIZATION AND CONTROL OF MEDIUM RANGE SURFACE TO AIR INTERCEPTOR MISSILES." Master's thesis, University of Central Florida, 2009. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4081.

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Nonlinear stabilization and control autopilots are capable of sustaining nominal performance throughout the entire fight envelope an interceptor missile may encounter during hostile engagements and require no gain scheduling to maintain autopilot stability. Due to non minimum phase conditions characteristic of tail controlled missile airframes, a separation of time scales within the dynamic equations of motion between rotational and translational differential equations was enforced to overcome unstable effects of non minimum phase. Dynamic inversion techniques are then applied to derive linear

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13

Kahvecioglu, Alper. "A Tool For Designing Robust Autopilots For Ramjet Missiles." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607058/index.pdf.

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The study presented in this thesis comprises the development of the longitudinal autopilot algorithm for a ramjet powered air-to-surface missile. Ramjet Missiles have short time-of-flight, however they suffer from limited angle of attack margins due to poor operational-region characteristics of the ramjet engine. Because of such limitations and presence of uncertainties involved, Robust Control Techniques are used for the controller design. Robust Control Techniques not only provide an easy limitation/uncertainty/performance handling for MIMO systems, but also, robust controllers promise stabi

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14

Evcimen, Cagdas. "Development And Comparison Of Autopilot And Guidance Algorithms For Missiles." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/2/12608677/index.pdf.

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In order to have an interception with a target, a missile should be guided with a successful guidance algorithm accompanied with a suitable autopilot structure. In this study, different autopilot and guidance designs for a canard-controlled missile are developed. As a first step, nonlinear missile mathematical model is derived by using the equations of motion with aerodynamic coefficients found by Missile DATCOM program. Autopilot design starts by the linearization of the nonlinear missile model around equilibrium flight conditions. Controllers based on the concepts of optimal control theory r

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15

Aydin, Gunes. "Aerodynamic Parameter Estimation Of A Missile In Closed Loop Control And Validation With Flight Data." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12615044/index.pdf.

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Aerodynamic parameter estimation from closed loop data has been developed as another research area since control and stability augmentation systems have been mandatory for aircrafts. This thesis focuses on aerodynamic parameter estimation of an air to ground missile from closed loop data using separate surface excitations. A design procedure is proposed for designing separate surface excitations. The effect of excitations signals to the system is also analyzed by examining autopilot disturbance rejection performance. Aerodynamic parameters are estimated using two different estimation technique

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16

Ng, Chuk Man 1974. "On the digital re-design of an analogue missile flight control system using PIM method." Thesis, McGill University, 1999. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=30263.

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This research examines some of the ways to design a digital control system with particular reference to the control of yaw plane dynamics of an air-to-air missile model. Specific attention is paid to compare two methods of global digital re-design of validated analogue closed loop control system. These two methods are the multi-input multi-output (MIMO) Plant Input Mapping (PIM) method and multi-loop PIM method. The thesis will first show how a specific class of closed loop MIMO feedback systems with a single-input multi-output (SIMO) plant can be re-structured as multi-loop control systems, w

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17

Ng, Chuk Man. "On the digital re-design of an analogue missile flight control system using PIM method." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape4/PQDD_0030/MQ64239.pdf.

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18

Du, Yongliang. "Development of real-time flight control system for low-cost vehicle." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/8621.

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In recent years, more and more light aircraft enter our daily life, from Agricultural applications, emergency rescue, flight experiment and training to Barriers to entry, light aircraft always have their own advantages. Thus, they have become more and more popular. However, in the process of GDP research about Flight Control System design for the Flying Crane, the author read a lot of literature about Flight Control System design, then noticed that the research in Flight Control System have apparently neglected to Low-cost vehicles. So it is necessary to do some study about Flight Control Syst

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19

Sleeman, William Clifford IV. "The Development of a Linux and FPGA Based Autopilot System for Unmanned Aerial Vehicles." VCU Scholars Compass, 2007. http://scholarscompass.vcu.edu/etd_retro/129.

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This project is part of research funded by NASA Langley in field of Unmanned Aerial Vehicles (UAVs) and is based on past work conducted at Virginia Commonwealth University. Dr. Mark A. Motter of NASA Langley intends to use the new autopilot system to test aircraft with many control surfaces. The goal of this project is to port an existing UAV autopilot system that has more computing power than the previous generation system to allow for more advanced flight control algorithms.The steps taken to complete this project include choosing a new hardware platform, porting C flight control software fr

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20

Kargin, Volkan. "Design Of An Autonomous Landing Control Algorithm For A Fixed Wing Uav." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608996/index.pdf.

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This thesis concerns with the design and development of automatic flight controller strategies for the autonomous landing of fixed wing unmanned aircraft subject to severe environmental conditions. The Tactical Unmanned Aerial Vehicle (TUAV) designed at the Middle East Technical University (METU) is used as the subject platform. In the first part of this thesis, a dynamic model of the TUAV is developed in FORTRAN environment. The dynamic model is used to establish the stability characteristics of the TUAV. The simulation model also incorporates ground reaction and atmospheric models. Based on

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21

Peddle, Iain K. "Acceleration based manoeuvre flight control system for unmanned aerial vehicles." Thesis, Stellenbosch : Stellenbosch University, 2008. http://hdl.handle.net/10019.1/1172.

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Thesis (PhD (Electrical and Electronic Engineering))--Stellenbosch University, 2008.<br>A strategy for the design of an effective, practically feasible, robust, computationally efficient autopilot for three dimensional manoeuvre flight control of Unmanned Aerial Vehicles is presented. The core feature of the strategy is the design of attitude independent inner loop acceleration controllers. With these controllers implemented, the aircraft is reduced to a point mass with a steerable acceleration vector when viewed from an outer loop guidance perspective. Trajectory generation is also simpl

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22

Náglová, Katarína. "Konvenční a adaptivní metody nastavení parametrů regulátoru pro řízení letové výšky letadla s pohyblivou pozicí těžiště v prostředí MATLAB - Simulink." Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2013. http://www.nusl.cz/ntk/nusl-219931.

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The thesis is focused on aircraft flight level control in case when the location of center of gravity changes during flight. The theoretical part of the thesis describes basics of aerodynamics, which are necessary to understand airplane's behavior and its control theory. Basics of state theory and stability of systems, as it is used for design of linear model. This part also mentions mathematical equations of nonlinear model of business jet and discusses conventional and adaptive methods used to design autopilot parameters. Several autopilots were designed in practical part of the thesis. The

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23

Cakir, Zeynep. "Development Of A Uav Testbed." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613209/index.pdf.

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The development and testing for a UAV testbed to be used in academic research and undergraduate education is proposed in this thesis. Analysis on commercial off-the-shelf UAV systems and autopilots lead to the development of a custom, open-architecture and modular UAV testbed. The main focus is to support research in UAV control field and education of the undergraduate students. The integration and use of commercial-off-the-shelf avionics and air vehicle are described in detail. System performance is examined both in flight and on the ground. Results of the system tests show that the develope

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24

DeBoy, Christopher C., Paul D. Schwartz, and Richard K. Huebschman. "Midcourse Space Experiment Spacecraft and Ground Segment Telemetry Design and Implementation." International Foundation for Telemetering, 1996. http://hdl.handle.net/10150/608390.

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International Telemetering Conference Proceedings / October 28-31, 1996 / Town and Country Hotel and Convention Center, San Diego, California<br>This paper reviews the performance requirements that provided the baseline for development of the onboard data system, RF transmission system, and ground segment receiving system of the Midcourse Space Experiment (MSX) spacecraft. The onboard Command and Data Handling (C&DH) System was designed to support the high data outputs of the three imaging sensor systems onboard the spacecraft and the requirement for large volumes of data storage. Because

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25

Tanil, Cagatay. "Optimal External Configuration Design Of Missiles." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12610873/index.pdf.

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The main area of emphasis in this study is to investigate the methods and technology for aerodynamic configuration sizing of missiles and to develop a software platform in MATLAB&reg<br>environment as a design tool which has an ability of optimizing the external configuration of missiles for a set of flight requirements specified by the user through a graphical user interface. A genetic algorithm based optimization tool is prepared by MATLAB is expected to help the designer to find out the best external geometry candidates in the conceptual design stage. Missile DATCOM software package is empl

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26

Mattei, Giovanni. "Robust nonlinear control : from continuous time to sampled-data with aerospace applications." Thesis, Paris 11, 2015. http://www.theses.fr/2015PA112025/document.

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La thèse porte sur le développement des techniques non linéaires robustes de stabilisation et commande des systèmes avec perturbations de model. D’abord, on introduit les concepts de base de stabilité et stabilisabilité robuste dans le contexte des systèmes non linéaires. Ensuite, on présente une méthodologie de stabilisation par retour d’état en présence d’incertitudes qui ne sont pas dans l’image de la commande («unmatched»). L’approche récursive du «backstepping» permet de compenser les perturbations «unmatched» et de construire une fonction de Lyapunov contrôlée robuste, utilisable pour le

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27

Novák, Jiří. "Návrh autopilota a letových řídících módů v prostředí Simulink." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-416616.

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Tato diplomová práce je zaměřena na vývoj simulačního prostředí v Matlab/Simulink zvoleného letadla ve známém letovém režimu. Pozice a orientace letadla pohybujícího se ve vzduchu je popsána pohybovými rovnicemi se šesti stup\v{n}i volnosti. Soustava translačních, rotačních a kinematických rovnic tvoří soustavu devíti nelineárních diferenciálních rovnic prvního řádu. Tyto rovnice lze linearizovat okolo nějakého rovnovážného stavu, který budeme nazývat letovým režimem. Součástí simulačního prostředí je řídící systém letadla založený na PID regulaci. Základem je návrh autopilota, který řídí úhel

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28

Lavergne, Fabien. "Méthodologie de synthèse de lois de commandes non-linéaires et robustes : application au suivi de trajectoire des avions de transport." Toulouse 3, 2005. http://www.theses.fr/2005TOU30248.

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Le travail présenté dans ce mémoire de thèse s'inscrit dans le cadre de la commande non-linéaire et robuste des avions de transport. Le but de cette thèse est de coupler les propriétés de la commande non-linéaire (adaptation aux non-linéarités de l'avion, synthèse de correcteurs explicites, facilité de réglage une fois la synthèse réalisée, généricité des lois de commande obtenues) à des propriétés de robustesse indispensables à l'activité aéronautique. En effet, pour garantir la sécurité des vols tant en pilotage manuel qu'en pilotage automatique, les lois de commande doivent présenter des pr

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29

Roussel, Emmanuel. "Contribution à la modélisation, l'identification et la commande d'un hélicoptère miniature." Thesis, Strasbourg, 2017. http://www.theses.fr/2017STRAD030/document.

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La stabilisation et l’automatisation du vol de tout véhicule aérien nécessite la mise en oeuvre d’algorithmes de commande. La synthèse et la simulation des lois de commande reposent sur un modèle mathématique du véhicule, qui doit être de complexité et de précision appropriées. Cette thèse présente une méthodologie complète d’identification appliquée à un hélicoptère coaxialminiature. L’étude théorique de son comportement en vol permet d’établir plusieurs modèles basés sur la mécanique du vol, qui diffèrent par les phénomènes aérodynamiques pris en compte. Ils sont identifiés, comparés et vali

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30

Powly, A. A. "Variable Structure Control Based Flight Control Systems For Aircraft And Missiles." Thesis, 2004. http://etd.iisc.ernet.in/handle/2005/1136.

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31

Lei, Keng-Lon, and 李勁輪. "Application of Robust Control Theory to Missile Autopilot Design with High Off-Boresight Angle." Thesis, 1999. http://ndltd.ncl.edu.tw/handle/81681921771563892277.

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碩士<br>國立成功大學<br>航空太空工程學系<br>87<br>An autopilot system for the heading reversal maneuvering (HRM) phase in missile engagement with high off-boresight angle up to 180 degrees has been successfully synthesized with the combination of aerodynamic control and thrust vector control (TVC). The application of H∞ control theory has provided the missile robustness (including robust stability and robust performance) properties in the presence of model uncertainty caused by aerodynamic coefficient variation. Simultaneously, autopilot has enabled the missile to resist the maximal possible yawing moment wit

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32

Chen, Wei-Yu, and 陳韋佑. "Integration and Simulations for Mission and Flight Control Systems of a Missile." Thesis, 2002. http://ndltd.ncl.edu.tw/handle/hv2j3f.

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碩士<br>國立成功大學<br>航空太空工程學系碩博士班<br>90<br>The objective of this thesis is to investigate the method of integrating the mission and control systems of a missile. To validate the method, simulations with a 6-d.o.f. rigid body model are conducted. In order to obtain a set of aerodynamic coefficient data, a typical configuration of twin-inlet missile is provided and the data compendium method is used accordingly. With the estimated aerodynamic data, a control system is designed to stabilize the missile and track the output of the guidance system. In this study, the mission is designed to be the maximu

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33

Yu, Tsungte, and 游宗德. "The Study of Appling Support Vector Machines to the Missile Flight Control." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/02253581127040028986.

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碩士<br>國防大學理工學院<br>兵器系統工程碩士班<br>100<br>This thesis applied the support vector regression (SVR) technique to establish an intelligent controller with online training and adaptive controls. This controller can determine the extremely short-term changes of control commands to predict the output of the next time step precisely. This research employed LABVIEW (laboratory virtual instrument engineering workbench), an image programming language, and MATLAB, a support vector machine toolbox. The application of a DC motor speed controller provided good control results. Then we integrated the SVR techniq

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34

Wang, Chun-Bi, and 王俊筆. "Base on Fuzzy PID to Design and Simulate the UAV Longitudinal Autopilot Flight Control System." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/76730328713319491116.

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35

Lin, Hung-Wei, and 林煥巍. "A Study of Parameters Selection for an Integrated Guidance and Flight Control Autopilot Used in UAV." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/65122643883255035998.

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碩士<br>國立成功大學<br>航空太空工程學系碩博士班<br>92<br>A F-16 as the UAV dynamic model and its integrated guidance and flight control autopilot is chosen in this research as the main focus of this study. The objective is to investigate the effect of autopilot parameters to the flight performance of an unmanned aerial vehicle (UAV) and proposes an analysis method for selecting a set of parameters best suited for many different flight conditions. The guidance law of the autopilot transforms the relative position between the UAV and a desired location and the velocity of the UAV into flight control command. Th

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36

Chen, Feng-Wei, and 陳峰緯. "Based on Input Estimator and LQG Control Theory to Design Flight Satbility Controller for Supersonic Cruise Missile." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/37259789151044730553.

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碩士<br>國防大學理工學院<br>兵器系統工程碩士班<br>101<br>In this thesis, the recursive input estimation method and LQG (Linear-Quadratic-Gaussian) control theory are utilized to design high-precision and robustness flight stability controller for supersonic cruise missile. The method for obtaining the disturbance input estimation ability and enhancing flight stability control performance are also proposed. The recursive input estimation with characteristics about faster computation, less measurements and low pass filter. LQG controller is based on optimal control theory has the characteristics of easy to impleme

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37

Kumar, Shashi Ranjan. "Sliding Mode Control Based Guidance Strategies with Terminal Constraints." Thesis, 2015. http://etd.iisc.ernet.in/2005/3876.

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In the guidance literature, minimizing miss distance along with optimizing the energy usage had been an objective for several decades. In current day applications, additional terminal performance such as impact angle and impact time are of paramount importance. These terminal constraints increase warhead effectiveness and survivability of the interceptor. This thesis contributes to the design of guidance laws addressing terminal constraints such as impact angle, impact time, and both impact time as well as impact angle, in addition to interception of targets. In the first part of the thesis,

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38

Saroj, Kumar G. "An Integrated Estimation-Guidance Approach for Seeker-less Interceptors." Thesis, 2015. http://etd.iisc.ernet.in/2005/3828.

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In this thesis, the problem of intercepting highly manoeuvrable threats using seeker-less interceptors that operate in the command guidance mode, is addressed. These systems are more prone to estimation errors than standard seeker-based systems. Several non-linear and optimal estimation and guidance concepts are presented in this thesis for interception of randomly maneuvering targets by seeker-less interceptors. The key contributions of the thesis can be broadly categorized into six groups, namely (i) an optimal selection of bank of lters in interactive multiple model (IMM) scheme to cater to

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