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1
Febbo, Marco. "Advanced 4DT flight guidance and control software system." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2016. http://amslaurea.unibo.it/11239/.
Повний текст джерелаАнотація:
The work presented in this thesis has been part of a Cranfield University research project. This thesis aims to design a flight control law for large cargo aircraft by using predictive control, which can assure flight motion along the flight path exactly and on time. In particular this work involves the modelling of a Boeing C-17 Globemaster III 6DOF model (used as study case), by using DATCOM and Matlab Simulink software. Then a predictive control algorithm has been developed. The majority of the work is done in a Matlab/Simulink environment. Finally the predictive control algorithm has been applied on the aircraft model and its performances, in tracking given trajectory optimized through a 4DT Research Software, have been evaluated.
2
Moon, Jongki. "Mission-based guidance system design for autonomous UAVs." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/31797.
Повний текст джерелаАнотація:
Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2010.Committee Chair: Prasad, JVR; Committee Member: Costello, Mark; Committee Member: Johnson, Eric; Committee Member: Schrage, Daniel; Committee Member: Vela, Patricio. Part of the SMARTech Electronic Thesis and Dissertation Collection.
3
Cloutier, Michael John. "Guidance and control system for an Autonomous Underwater Vehicle." Thesis, Monterey, California. Naval Postgraduate School, 1990. http://hdl.handle.net/10945/30635.
Повний текст джерелаАнотація:
Approved for public release, distribution is unlimitedThe Naval Postgraduate School (NPS) is currently involved in a long-term project to investigate and develop real-time control software, artificial intelligence, computer architecture and control systems theory as they pertain to U.S. Navy autonomous vehicle programs. In support of this goal, the NPS is currently designing and fabricating a testbed autonomous underwater vehicle. This work describes the design, development, and testing of a Guidance Subsystem for this testbed vehicle which uses portions of cubic spirals as the desired path to follow between waypoints. In addition, data translation firmware and real-time software for the control surfaces and main motors is designed, implemented and tested. The process of selecting and implementing an appropriate computer architecture in support of these goals is also discussed and detailed, along with the choice of associated computer hardware and real-time operating system software.
4
Bouzid, Yasser. "Guidance and control system for autonomous aerial vehicles navigation." Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLE014.
Повний текст джерелаАнотація:
Cette thèse traite du guidage et du pilotage de véhicules aériens qui peuvent assurer des missions dans des lieux particulièrement hostiles, dangereux ou inaccessibles avec des véhicules conventionnels. Nous sommes tout d'abord motivés par le scénario de couverture, qui est généralement un processus long pouvant utiliser un grand nombre de personnes et d'équipements. Or, la nature de la couverture nécessite un véhicule aérien avec des capacités de vol stationnaire. Pour cela, nous nous intéressons alors aux multirotors, qui sont considérés comme une bonne étude de cas pour concevoir, analyser et mettre en œuvre des stratégies de contrôle de vol.En réalité, de nombreux défis sont encore ouverts pour ce qui concerne le scénario de couverture comme la faisabilité, l’optimalité en visitant tous les points d’intérêts. De plus, un système de contrôle robuste est indispensable pour contrer des effets néfastes tel le vent. Par ailleurs, la conception d'un algorithme de contrôle répondant à certaines exigences (structure simple, précision, énergie minimale consommée) constitue un défi supplémentaire. Ensuite, notre travail introduit un modèle mathématique générique pour les multi-rotors en considérant l’effet du vent.Dans la première partie du manuscrit, nous proposons des planificateurs en utilisant comme base l'algorithme RRT* (optimal Rapidly-exploring Random Tree). En fait, dans les grands espaces, un grand nombre de nœuds est généré augmentant alors le temps de calcul et la mémoire consommée. Pour y remédier, une procédure de suppression est impliquée pendant le processus « ReWire » pour les réduire. De plus, un planificateur multidirectionnel qui renvoie un ensemble de chemins optimaux à partir d'un point de départ et d'un ensemble de points objectifs est proposé. Notre travail introduit également une stratégie CPP (Coverage path-planning) optimale dans un espace contraint. Celle-ci consiste à procéder par un algorithme en deux phases. Dans la première, un planificateur multidirectionnel est utilisé pour définir les chemins les plus courts de chaque point à ses voisins. Dans la seconde phase, au moyen des coûts entre les points, le chemin global le plus court est obtenu en résolvant un problème de voyageur en utilisant des algorithmes génétiques. Puis, compte tenu de l'énergie embarquée limitée, un problème de routage est adapté et est résolu par la méthode de savings. Dans une seconde partie, nous nous sommes penchés sur la conception d'un système de pilotage efficace permettant au véhicule de suivre une trajectoire paramétrée dans le temps. D’une part nous proposons une extension de la commande par modèle interne au non-linéaire (NLIMC). Notre technique repose sur l’utilisation du principe de base IMC pour synthétiser un contrôleur non linéaire qui fait intervenir la propriété de platitude. D’autre part, nous proposons une autre forme de contrôleur dont la structure apparente est un PID mais dans lequel est incorporée la technique des modes glissants que l'on appellera aussi PID non linéaire bien qu’il diffère de l’existant. Cette combinaison a l’avantage de conduire à un bon niveau de robustesse fourni par les modes glissants et en même temps à un bon comportement spécifié par la structure PID. En outre, en guise de complément, nous proposons deux contrôleurs redondants basés sur deux principes distincts afin de booster et d’améliorer les capacités de tout contrôleur. Le premier est basé sur l’approche MFC (Model-Free Control) tandis que le second est basé sur les modes glissants dynamiques DSMC (Dynamic Sliding Mode Controller). Enfin, pour montrer les performances de ces contrôleurs, nous avons effectué une série de tests avec plusieurs illustrations et scénarios, nous avons dressé un tableau de comparaison avec les approches conventionnelles. Les résultats issus des simulations numériques et ceux des tests expérimentaux réalisés sur un drone quadrotor se sont avérés cohérents et semblent bien prometteursThis thesis deals with the guidance and control of aerial vehicles, which can also ensure missions in hostile, dangerous environments, or inaccessible workspaces with conventional vehicles. First, we are motivated by the coverage scenario, which is in general a long process, requiring a large number of individuals and specific equipment. However, the nature of sensing coverage requires an aerial vehicle with hovering capabilities. For this purpose, we are interested in multirotors that are considered as a good case study to design, analyze and implement flight control strategies.As matter of fact, many challenges are still open with respect to the coverage scenario such as for instance the feasibility and the optimality when passing through the Points of Interest. In addition, a robust control system is essential to mitigate the adverse effects such as the wind. Moreover, designing a control algorithm, which meet some requirements (simplicity, accuracy, consumed energy, etc.) constitutes a complementary challenge. Then, our work introduces a generic mathematical model for multirotors flying under the effect of wind.In a first part, we propose planners using as a basis the optimal Rapidly-exploring Random Tree (RRT*) algorithm. In fact, in large workspaces, a large number of nodes is generated and then increasing the computation time and the consumed memory. To counter these latter, a removal procedure is involved during the rewiring process. In addition, a multidirectional planner that returns a set of optimal paths from a starting point and a set of objective points is proposed. Our work also introduces an optimal Coverage path-planning (CPP) strategy in a constrained workspace. This one proceeds through a two-phases algorithm. In the first one, a Connected Multi-directional planner is used to define the shortest paths from each point to its neighbors. In the second phase, by means of the pair-wise costs between points, the overall shortest path is obtained by solving a Traveling Salesman Problem using Genetic Algorithms. Then, taking into account the limited on-board energy, a Capacitated-Vehicle Routing Problem is adapted and solved by the savings approach.In a second part, we study the design of an effective control system allowing the vehicle to track a trajectory parameterized in time. On the one hand, we propose an extension to nonlinear systems of the Internal Model Control (NLIMC). Our technique is based on the use of the basic IMC principle to synthesize a nonlinear controller that involves the property of flatness. On the other hand, we propose another form of controller whose apparent structure is a PID but in which the technique of sliding modes is incorporated that will also call the nonlinear PID (NLPID). This combination has the advantage to lead to a good level of robustness provided by the sliding modes and at the same time to a good behavior specified by the PID structure. Besides, as a complement, we present two redundant controllers based on two distinct principles in order to boost and to improve the capabilities of any controller. The first one is based on the Model-Free Control (MFC) approach while the second one is based on Dynamic Sliding Mode Controller (DSMC).Finally, to highlight the performance of these controllers, we have performed a series of tests with several illustrations and scenarios and we have drawn up a comparison table with conventional approaches. The results of both the numerical simulations and the experimentation that are performed on a quadrotor are consistent and seem to be quite promising
5
Li, Ming-Yan. "Performance analysis and enhancement of proportional navigation guidance systems /." Title page, table of contents and abstract only, 1999. http://web4.library.adelaide.edu.au/theses/09ENS/09ensl693.pdf.
Повний текст джерела
6
Roddy, D. J. "Application of optimal control to bank-to-turn CLOS guidance." Thesis, Queen's University Belfast, 1985. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.373543.
Повний текст джерела
7
Richter, Ralph. "A predictive fuzzy-neural autopilot for the guidance of small motorised marine craft." Thesis, University of Plymouth, 2000. http://hdl.handle.net/10026.1/2665.
Повний текст джерелаАнотація:
This thesis investigates the design and evaluation of a control system, that is able to adapt quickly to changes in environment and steering characteristics. This type of controller is particularly suited for applications with wide-ranging working conditions such as those experienced by small motorised craft. A small motorised craft is assumed to be highly agile and prone to disturbances, being thrown off-course very easily when travelling at high speed 'but rather heavy and sluggish at low speeds. Unlike large vessels, the steering characteristics of the craft will change tremendously with a change in forward speed. Any new design of autopilot needs to be to compensate for these changes in dynamic characteristics to maintain near optimal levels of performance. This study identities the problems that need to be overcome and the variables involved. A self-organising fuzzy logic controller is developed and tested in simulation. This type of controller learns on-line but has certain performance limitations. The major original contribution of this research investigation is the development of an improved self-adaptive and predictive control concept, the Predictive Self-organising Fuzzy Logic Controller (PSoFLC). The novel feature of the control algorithm is that is uses a neural network as a predictive simulator of the boat's future response and this network is then incorporated into the control loop to improve the course changing, as well as course keeping capabilities of the autopilot investigated. The autopilot is tested in simulation to validate the working principle of the concept and to demonstrate the self-tuning of the control parameters. Further work is required to establish the suitability of the proposed novel concept to other control.
8
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.
Повний текст джерелаАнотація:
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 methods are compared and discussed.
9
Brake, Nicholas J. "Control System Development for small UAV Gimbal." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/838.
Повний текст джерелаАнотація:
The design process of unmanned ISR systems has typically driven in the direction of increasing system mass to increase stabilization performance and imagery quality. However, through the use of new sensor and processor technology high performance stabilization feedback is being made available for control on new small and low mass stabilized platforms that can be placed on small UAVs. This project develops and implements a LOS stabilization controller design, typically seen on larger gimbals, onto a new small stabilized gimbal, the Tigereye, and demonstrates the application on several small UAV aircraft. The Tigereye gimbal is a new 2lb, 2-axis, gimbal intended to provided high performance closed loop LOS stabilization through the utilization of inertial rate gyro, electronic video stabilization, and host platform state information. Ground and flight tests results of the LOS stabilization controller on the Tigereye gimbal have shown stabilization performance improvements over legacy systems. However, system characteristics identified in testing still limit stabilization performance, these include: host system vibration, gimbal joint friction and backlash, joint actuation compliance, payload CG asymmetry, and gyro noise and drift. The control system design has been highly modularized in anticipation of future algorithm and hardware upgrades to address the remaining issues and extend the system's capabilities.
10
Ding, Ting. "Advanced surface movement guidance and control system investigation and implementation in simulation." Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/6767.
Повний текст джерелаАнотація:
The Surface Movement Guidance and Control System (SMGCS) is a system
providing the surveillance, routing, guidance and control supports to the airport
traffic. The moving objects being managed include all the aircraft and vehicles
in the interested area on the surface; the personnel making use of this system
are the pilots, vehicle drivers, and ground controllers.
The airport surface traffic management has long been discussed because of the
operational challenges; this includes the increasing complexity of the field
movement management and the density of airport traffic. To improve airport
operation qualities, the Advanced Surface Movement Control and Guidance
System (A-SMGCS) was introduced. In terms of architecture and capability
differences, there are two levels of the A-SMGCS, which are A-SMGCS I & II.
The positive impacts on the airport surface operation are: safety, capacity,
efficiency, human factor conditions, and economic issues.
This project deals with an investigation on SMGCS baseline and the A-SMGCS,
covering the system conception, background, current developments and relative
technologies. The applications in practical operations are discussed as well.
There is also an analysis about the airport surface incursion classification and
severity. Based on this, a simulation is presented to illustrate the practical
applications of the A-SMGCS. The simulation results show the functions of
Human Machine Interface (HMI) in A-SMGCS, including the designation and
diversion for clearance, the real-time view of surface target movements and the
indications for contracted incursions.
Over all, the research aims are to work on an investigation and explanation of
A-SMGCS, and to implement a simulation of the system functions. The
implementation includes the image processing, system architecture definition in
Simulink, Graphical User Interface (GUI) design for the HMI, and the
corresponding Matlab programming for simulation environment establishment.
11
Plew, Jason. "Development of a flight avionics system for an autonomous Micro Air Vehicle." [Gainesville, Fla.] : University of Florida, 2004. http://purl.fcla.edu/fcla/etd/UFE0008540.
Повний текст джерела
12
Gadala, Ibrahim M. "A design expert system for guidance and assessment of the design evolution of motion control systems." Thesis, University of British Columbia, 2012. http://hdl.handle.net/2429/41894.
Повний текст джерелаАнотація:
The automation of engineering design is of great significance in the development of machinery and products in competitive industries. Using an automated and “optimal” design process to redesign the faulty components and poorly performing regions of an existing engineering system will facilitate the realization of realistic design alternatives, with benefits such as improved quality, reliability, and cost effectiveness. Motivated by such needs, this thesis develops a Design Expert System (DES) for motion control (MC) applications. The developed DES is expected to be integrated into a multi-system Evolutionary Design Framework (EDF) which is being developed in our laboratory. The EDF integrates techniques of condition monitoring, modeling, and evolutionary optimization for autonomous identification, diagnosis, and redesign of poorly performing aspects of an existing machine. Through integration with optimization routines and the use of a comprehensive knowledge base (KB) in the MC domain, the DES developed in this work is able to guide the evolution of optimal design alternatives and assess their feasibility and effectiveness.
Due to the prevalence of electric motors as actuators in many industrial applications, MC design and actuator (motor) selection represent the application domain of the DES developed in the present research. The KB of the DES includes knowledge of typical mechanical structures used in industrial MC systems, common profiles of load speed or position (duty cycles), and the effect of practical issues such as s-curve profiling, geometric trajectory blending, intermittent duty cycles, rms torque, and the thermal response of motors. A systematic methodology for detailed design analysis and subsequent selection of commercially available motors, their drive systems, and transmission devices (e.g., gears) from an external database is developed. Selections by the DES are compared to those by a human designer for both hypothetical and actual designs, thereby verifying the DES procedure. To facilitate the interaction between different systems in the EDF, a graphical user interface (GUI) is created for the DES in Excel®. The DES is synchronized with Matlab® to guide optimization routines based on its built-in human expertise and heuristic design knowledge. A guided optimization case study is presented and benefits of the guidance process are discussed.
13
Williams, Timothy Alphonzo. "Optimal parachute guidance, navigation, and control for the Affordable Guided Airdrop System (AGAS)." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2000. http://handle.dtic.mil/100.2/ADA380301.
Повний текст джерелаАнотація:
Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, June 2000.Thesis advisor(s): Kaminer, Isaac I.; Yakimenko, Oleg A. "June 2000." Includes bibliographical references (p. 81-82). Also available in print.
14
Dong, Zhilin. "The development of electrohydraulic steering control system for off-road vehicle automatic guidance." Diss., Columbia, Mo. : University of Missouri-Columbia, 2007. http://hdl.handle.net/10355/5981.
Повний текст джерелаАнотація:
Thesis (M.S.)--University of Missouri-Columbia, 2007.The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on November 9, 2007) Vita. Includes bibliographical references.
15
Hallberg, Eric N. "Design of a GPS aided guidance, navigation, and control system for trajectory control of an air vehicle." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA281034.
Повний текст джерела
16
Purnell, Graham. "Implementation of a robotic system for deboning of a beef forequarter for process meat." Thesis, University of Bristol, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.240579.
Повний текст джерела
17
Nygaard, Andreas. "High-Level Control System for Remote Controlled Surgical Robots : Haptic Guidance of Surgical Robot." Thesis, Norwegian University of Science and Technology, Department of Engineering Cybernetics, 2008. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-8864.
Повний текст джерелаАнотація:
This report considers the work to improve the autonomy of surgical teleoperated systems, by introducing haptic guidance. The use of surgical robots in surgical procedures have become more common the recent years, but still it is in its infancy. Some advantages when using robots is scalability of movements, reduced tremor, better visualisation systems and greater range of motions than with conventional minimally invasive surgery. On the contrary, lack of tactile feedback and highly unstructured medical environment restricts the use of teleoperated robots to specific tasks within specific procedures. A way of improving autonomy of the teleoperated system is to introduce predefined constraints in the surgical environment, to create a trajectory or forbidden area, in order to guide the movements of the surgeon. This is often called haptic guidance. This report introduces the basics of teleoperated systems, with control schemes, models and analytical tools. Algorithms for haptic guidance have been developed, and the entire control and guidance system have been modified and suited for implementation on a real teleoperated system. Theoretical analysis of the position position (PP) control scheme reveals some general stability and performance characteristics, later used as a basis for tuning the real system parameters. The teleoperated system consists of a Phantom Omni device, from SensAble-Technologies, used as master manipulator, and AESOP 3000DS, from Computer Motions Inc., as the slave manipulator. The control system is implemented on a regular PC, connecting the complete system. Tests reveal that the slave manipulator is not suited for this task due to a significant communication time delay, limited velocity and inadequate control possibilities. The consequences makes force feedback based on the PP control scheme impossible, and limits performance of the entire teleoperated system. The guidance system is implemented in two variations, one based on slave positions and one based on master positions. This is motivated to give a performance comparison for variations of position error/tracking between the two manipulators. Slave based guidance appears to be stable only for limited values of the gains, and thus, it generates no strict constraints. It can be used to guide the operator away from forbidden areas, but is not suitable for high precision guiding. The master based guidance is stabile for very high gains, and the guidance have the accuracy to improve the surgeons precision during procedures. In the case of line guidance, the master based guidance gives a deviation of up to $1.3mm$ from the given trajectory. The work has shown the possibilities of using haptic guidance to improve accuracy and precision in surgical procedures, but among others, hardware limitations give room for several improvements in order to develop a teleoperated system that works.
18
Soto, Manuel. "Unmanned aerial vehicle real-time guidance system via state space heuristic search." To access this resource online via ProQuest Dissertations and Theses @ UTEP, 2007. http://0-proquest.umi.com.lib.utep.edu/login?COPT=REJTPTU0YmImSU5UPTAmVkVSPTI=&clientId=2515.
Повний текст джерела
19
Silva, Seth F. "Applied System Identification for a Four Wheel Reaction Wheel Platform." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/328.
Повний текст джерелаАнотація:
Applied System Identification for a Four Wheel Reaction Wheel Platform
By
Seth Franklyn Silva
At the California Polytechnic State University, San Luis Obispo there is a four-wheel reaction wheel pyramidal simulator platform supported by an air-bearing. This simulator has the current capability to measure the wheel speeds and angular velocity of the platform, and with these measurements, the system identification process was used to obtain the mass properties of this simulator. A handling algorithm was developed to allow wireless data acquisition and command to the spacecraft simulator from a “ground” computer allowing the simulator to be free of induced torques due to wiring. The system identification algorithm using a least squares estimation scheme was tested on this simulator and compared to theoretical analysis. The resultant principle inertia about the z-axis from the experimental analysis was 3.5 percent off the theoretical, while the other inertias had an error of up to 187 percent. The error is explained as noise attributed to noise in the measurement, averaging inconsistencies, low bandwidth, and derivation of accelerations from measured data.
20
KATO, TOMOYUKI. "Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification." DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1201.
Повний текст джерелаАнотація:
The Cal Poly Spacecraft Dynamics Simulator, also known as the Pyramidal Reaction Wheel Platform (PRWP), is an air-bearing four reaction wheel spacecraft simulator designed to simulate the low-gravity, frictionless condition of the space environment and to test and validate spacecraft attitude control hardware and control laws through real-time motion tests. The PRWP system was modified to the new Mk.III configuration, which adopted the MATLAB xPC kernel for better real-time hardware control. Also the Litton LN-200 IMU was integrated onto the PRWP and replaced the previous attitude sensor. Through the comparison of various control laws through motion tests the Mk.III configuration was tested for robust control law verification capability. Two fixed-gain controllers, full-state feedback (FSFB) and linear quadratic regulator with set-point control(LQRSP), and two adaptive controllers, nonlinear direct model reference adaptive controller (NDMRAC) and the adaptive output feedback (AOF), were each tested in three different cases of varying plant parameters to test controller robustness through real-time motion tests. The first two test cases simulate PRWP inertia tensor variations. The third test case simulates uncertainty of the reaction wheel dynamic by slowing down the response time for one of the four reaction wheels. The Mk.III motion tests were also compared with numerical simulations as well as the older Mk.II motion tests to confirm controller validation capability. The Mk.III test results confirmed certain patterns from the numerical simulations and the Mk.II test results. The test case in which actuator dynamics uncertainty was simulated had the most effect on controller performance, as all four control laws experienced an increase in steady-state error. The Mk.III test results also confirmed that the NDMRAC outperformed the fixed-gain controllers.
21
Jalasutram, Srikanth. "Design of an intelligent posture guidance system for workspace seating." Thesis, Georgia Institute of Technology, 2011. http://hdl.handle.net/1853/41117.
Повний текст джерелаАнотація:
Seating is an integral part of work environment. When people are at work, they often sit in chairs for long periods of time without changing postures. This results in reduced blood circulation in the body, especially in the buttock-thigh area causing muscle fatigue, pain and discomfort. Ergonomically designed task chairs adopt a passive approach to guiding people into better postures by providing adjustability inside the chair. However most people do not adjust their chairs because they fail to sense the need for changing posture. They are left to sensing the need to change posture through guesswork or extreme discomfort. This thesis proposes a new system to address this problem by sensing static posture in a seated person with the use of electronic sensors embedded in the seat, and by providing interactive feedback to static posture via sound, light and tactile channels. The new technology is an sensing-feedback mechanism embedded in a chair, that allows people to receive postural information and make body adjustments periodically to avoid pain and discomfort caused by prolonged seating.The feedback mechanism was tested with four subjects to determine its efficacy in generating posture change through pressure relief and user feedback was gathered in order to design the final prototype.
22
Layshot, Nicholas Joseph. "MODELING OF A GYRO-STABILIZED HELICOPTER CAMERA SYSTEM USING NEURAL NETWORKS." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/421.
Повний текст джерелаАнотація:
On-board gimbal systems for camera stabilization in helicopters are typically based on linear models. Such models, however, are inaccurate due to system nonlinearities and complexities. As an alternative approach, artificial neural networks can provide a more accurate model of the gimbal system based on their non-linear mapping and generalization capabilities.
This thesis investigates the applications of artificial neural networks to model the inertial characteristics (on the azimuth axis) of the inner gimbal in a gyro-stabilized multi-gimbal system. The neural network is trained with time-domain data obtained from gyro rate sensors of an actual camera system. The network performance is evaluated and compared with measured data and a traditional linear model. Computer simulation results show the neural network model fits well with the measured data and significantly outperforms a traditional model.
23
Petrich, Jan. "Improved Guidance, Navigation, and Control for Autonomous Underwater Vehicles: Theory and Experiment." Diss., Virginia Tech, 2009. http://hdl.handle.net/10919/27222.
Повний текст джерелаАнотація:
This dissertation addresses attitude control and inertial navigation of autonomous underwater vehicles (AUVs). We present theoretical justification for using simplified models, derive system identification algorithms, and verify our results through extensive field trials. Although this research focuses on small AUVs with limited instrumentation, the results are useful for underwater vehicles of any size.
For attitude control of aircraft systems, second-order equivalent pitch-axis models are common and extensively studied. However, similar analysis has not been performed for the pitch-axis motion of underwater vehicles. In this dissertation, we study the utility and the limitations of second-order approximate models for AUVs. We seek to improve the flight performance and shorten the time required to re-design a control algorithm when the shape, mass-distribution, and/or net buoyancy of an AUV/payload configuration changes.
In comparison to commonly implemented AUV attitude controllers, which neglect roll motion and address pitch and yaw dynamics separately, we derive a novel linear time-varying model that explicitly displays the coupling between pitch and yaw motion due to nonzero roll angle and/or roll rate. The model facilitates an Hâ control design approach that explicitly addresses robustness against those coupling terms and significantly reduces the effect of pitch and yaw coupling.
To improve AUV navigation, we investigate algorithms for calibrating a triaxial gyroscope using angular orientation measurements and formally define AUV trajectories that are persistently exciting and for which the calibration coefficients are uniformly observable. To improve AUV guidance, we propose a near real-time ocean current identification method that estimates a non-uniform flow-field using only sparse flow measurements.Ph. D.
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Bijker, Johan. "Development of an attitude heading reference system for an airship." Thesis, Stellenbosch : University of Stellenbosch, 2006. http://hdl.handle.net/10019/502.
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Rose, Michael Benjamin. "Statistical Methods for Launch Vehicle Guidance, Navigation, and Control (GN&C) System Design and Analysis." DigitalCommons@USU, 2012. https://digitalcommons.usu.edu/etd/1278.
Повний текст джерелаАнотація:
A novel trajectory and attitude control and navigation analysis tool for powered ascent is developed. The tool is capable of rapid trade-space analysis and is designed to ultimately reduce turnaround time for launch vehicle design, mission planning, and redesign work. It is streamlined to quickly determine trajectory and attitude control dispersions, propellant dispersions, orbit insertion dispersions, and navigation errors and their sensitivities to sensor errors, actuator execution uncertainties, and random disturbances. The tool is developed by applying both Monte Carlo and linear covariance analysis techniques to a closed-loop, launch vehicle guidance, navigation, and control (GN&C) system. The nonlinear dynamics and flight GN&C software models of a closed-loop, six-degree-of-freedom (6-DOF), Monte Carlo simulation are formulated and developed. The nominal reference trajectory (NRT) for the proposed lunar ascent trajectory is defined and generated. The Monte Carlo truth models and GN&C algorithms are linearized about the NRT, the linear covariance equations are formulated, and the linear covariance simulation is developed. The performance of the launch vehicle GN&C system is evaluated using both Monte Carlo and linear covariance techniques and their trajectory and attitude control dispersion, propellant dispersion, orbit insertion dispersion, and navigation error results are validated and compared. Statistical results from linear covariance analysis are generally within 10% of Monte Carlo results, and in most cases the differences are less than 5%. This is an excellent result given the many complex nonlinearities that are embedded in the ascent GN&C problem. Moreover, the real value of this tool lies in its speed, where the linear covariance simulation is 1036.62 times faster than the Monte Carlo simulation. Although the application and results presented are for a lunar, single-stage-to-orbit (SSTO), ascent vehicle, the tools, techniques, and mathematical formulations that are discussed are applicable to ascent on Earth or other planets as well as other rocket-powered systems such as sounding rockets and ballistic missiles.
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Sellers, Ryan J. "A Gravity Gradient, Momentum-Biased Attitude Control System for A CubeSat." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/974.
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ExoCube is the latest National Science Foundation (NSF) funded space weather CubeSat and is a collaboration between PolySat, Scientific Solutions Inc. (SSI), the University of Wisconsin, NASA Goddard and SRI International. The 3U will carry a mass spectrometer sensor suite, EXOS, in to low earth orbit (LEO) to measure neutral and ionized particles in the exosphere and thermosphere. Measurements of neutral and ion particles are directly impacted by the angle at which they enter EXOS and which leads to pointing requirements. A combination of a gravity gradient system with a momentum bias wheel is proposed to meet pointing requirements while reducing power requirements and overall system complexity. A MATLAB simulation of dynamic and kinematic behavior of the system in orbit is implemented to guide system design and verify that the pointing requirements will be met. The problem of achieving the required three-axis pointing is broken into four phases: detumbling, initial attitude acquisition, wheel spin-up, and attitude maintenance. Ultimately, this configuration for attitude control in a CubeSat could be applied to many future missions with the simulation serving as a design tool for CubeSat developers.
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Wise, Evan Dale. "Design, analysis, and testing of a precision guidance, navigation, and control system for a dual-spinning Cubesat." Thesis, Massachusetts Institute of Technology, 2013. http://hdl.handle.net/1721.1/82509.
Повний текст джерелаАнотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, June 2013.This thesis was scanned as part of an electronic thesis pilot project.
"May 2013." Cataloged from PDF version of thesis.
Includes bibliographical references (p. [81]-85).
The Microsized Microwave Atmospheric Satellite (MicroMAS) combines two traditional control approaches: a dual spinner and a three-axis gyrostat. Unlike typical dual spinners, the purpose of MicroMAS 's 2U bus and spinner assembly is to actuate a iu payload, not to add gyroscopic stiffness. An orthogonal triple reaction wheel assembly from Maryland Aerospace, Inc., will both counter the angular momentum from the payload and rotate the satellite's bus about its orbit-normal vector to maintain bus alignment with the orbital frame. The payload spins about the spacecraft velocity axis to scan successive swaths of the Earth. However, the CubeSat form factor restricts the velocity axis to be along the spacecraft minor axis of inertia. This orientation leaves the spacecraft at a gravity-gradient-unstable equilibrium. Further, imperfect cancellation of the payload's angular momentum induces nutation behavior. An extended Kalman filter is implemented on a 16-bit P1C24 microcontroller to combine gyroscope, limb sensor, and magnetometer data to provide attitude estimation accuracy of approximately 20 arcminutes. Simulations show that the reaction wheels can consistently maintain pointing to within 30 arcminutes for orbits above 400 kilometers with the payload rotating at 0.83 hertz.
by Evan Dale Wise.
S.M.
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Rothman, Keith Eric. "Validation of Linearized Flight Models using Automated System-Identification." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/81.
Повний текст джерелаАнотація:
Optimization based flight control design tools depend on automatic linearization tools, such as Simulink®’s LINMOD, to extract linear models. In order to ensure the usefulness and correctness of the generated linear model, this linearization must be accurate. So a method of independently verifying the linearized model is needed. This thesis covers the automation of a system identification tool, CIFER®, for use as a verification tool integrated with CONDUIT®, an optimization based design tool. Several test cases are built up to demonstrate the accuracy of the verification tool with respect to analytical results and matches with LINMOD. Several common nonlinearities are tested, comparing the results from CIFER and LINMOD, as well as analytical results where possible. The CIFER results show excellent agreement with analytical results. LINMOD treated most nonlinearity as a unit gain, but some nonlinearities linearized to a zero, causing the linearized model to omit that path. Although these effects are documented within Simulink, their presence may be missed by a user. The verification tool is successful in identifying these problems when present. A section is dedicated to the diagnosis of linearization errors, suggesting solutions where possible.
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MacLean, Steven M. "Modeling and Simulation of a Sounding Rocket Active Stabilization System." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1735.
Повний текст джерелаАнотація:
The Horizon Simulation Framework is a modeling and simulation framework developed to verify system level requirements. In this thesis, the framework is extended to include the Dynamic position type that existed in the early development phase of the framework. The Dynamic position type is tested through the modeling and simulation of a sounding rocket. An active control system based on linear-quadratic regulator (LQR) control theory is implemented and tested in the simulation to determine the overall effect on altitude. A first order aerodynamics and aeroprediction model are created within the framework to allow for rapid changes early in the design process of the sounding rocket. The flight dynamics are compared to two different sounding rocket flights and the aeroprediction model is validated against public wind tunnel test data.
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Kamaldar, Mohammadreza. "DISCRETE-TIME ADAPTIVE CONTROL ALGORITHMS FOR REJECTION OF SINUSOIDAL DISTURBANCES." UKnowledge, 2018. https://uknowledge.uky.edu/me_etds/129.
Повний текст джерелаАнотація:
We present new adaptive control algorithms that address the problem of rejecting sinusoids with known frequencies that act on an unknown asymptotically stable linear time-invariant system. To achieve asymptotic disturbance rejection, adaptive control algorithms of this dissertation rely on limited or no system model information. These algorithms are developed in discrete time, meaning that the control computations use sampled-data measurements. We demonstrate the effectiveness of algorithms via analysis, numerical simulations, and experimental testings. We also present extensions to these algorithms that address systems with decentralized control architecture and systems subject to disturbances with unknown frequencies.
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George, Douglas B. (Douglas Brooks) Carleton University Dissertation Engineering Electrical. "A computer-driven astronomical telescope guidance and control system with superimposed star field and celestial coordinate grahics display." Ottawa, 1987.
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Bruno, Liam T. "Three Axis Attitude Control System Design and Analysis Tool Development for the Cal Poly CubeSat Laboratory." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2288.
Повний текст джерелаАнотація:
The Cal Poly CubeSat Laboratory (CPCL) is currently facing unprecedented engineering challenges—both technically and programmatically—due to the increasing cost and complexity of CubeSat flight missions. In responding to recent RFPs, the CPCL has been forced to find commercially available solutions to entire mission critical spacecraft subsystems such as propulsion and attitude determination & control, because currently no in-house options exist for consideration. The commercially available solutions for these subsystems are often extremely expensive and sometimes provide excessively good performance with respect to mission requirements. Furthermore, use of entire commercial subsystems detracts from the hands-on learning objectives of the CPCL by removing engineering responsibility from students. Therefore, if these particular subsystems can be designed, tested, and integrated in-house at Cal Poly, the result would be twofold: 1) the space of missions supportable by the CPCL under tight budget constraints will grow, and 2) students will be provided with unique, hands-on guidance, navigation, and control learning opportunities. In this thesis, the CPCL’s attitude determination and control system design and analysis toolkit is significantly improved to support in-house ADCS development. The toolkit—including the improvements presented in this work—is then used to complete the existing, partially complete CPCL ADCS design. To fill in missing gaps, particular emphasis is placed on guidance and control algorithm design and selection of attitude actuators. Simulation results show that the completed design is competitive for use in a large class of small satellite missions for which pointing accuracy requirements are on the order of a few degrees.
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Bezold, Maxwell. "AN ATTITUDE DETERMINATION SYSTEM WITH MEMS GYROSCOPE DRIFT COMPENSATION FOR SMALL SATELLITES." UKnowledge, 2013. http://uknowledge.uky.edu/ece_etds/29.
Повний текст джерелаАнотація:
This thesis presents the design of an attitude determination system for small satellites that automatically corrects for attitude drift. Existing attitude determination systems suffer from attitude drift due to the integration of noisy rate gyro sensors used to measure the change in attitude. This attitude drift leads to a gradual loss in attitude knowledge, as error between the estimated attitude and the actual attitude increases.
In this thesis a Kalman filter is used to complete sensor fusion which combines sensor observations with a projected attitude based on the dynamics of the satellite. The system proposed in this thesis also utilizes a novel sensor called the stellar gyro to correct for the drift. The stellar gyro compares star field images taken at different times to determine orientation, and works in the presence of the sun and during eclipse. This device provides a relative attitude fix that can be used to update the attitude estimate provided by the Kalman filter, effectively compensating for drift. Simulink models are developed of the hardware and algorithms to model the effectiveness of the system. The Simulink models show that the attitude determination system is highly accurate, with steady state errors of less than 1 degree.
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Kinnett, Ryan L. "System Integration and Attitude Control of a Low-Cost Spacecraft Attitude Dynamics Simulator." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/271.
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The CalPoly Spacecraft Attitude Dynamics Simulator mimics the rotational dynamics of a spacecraft in orbit and acts as a testbed for spacecraft attitude control system development and demonstration. Prior to this thesis, the simulator platform and several subsystems had been designed and manufactured, but the total simulator system was not yet capable of closed-loop attitude control. Previous attempts to make the system controllable were primarily mired by data transport performance. Rather than exporting data to an external command computer, the strategy implemented in this thesis relies on a compact computer onboard the simulator platform to handle both attitude control processing and data acquisition responsibilities. Software drivers were created to interface the computer’s data acquisition boards with Matlab, and a Simulink library was developed to handle hardware interface functions and simplify the composition of attitude control schemes. To improve the usability of the system, a variety of actuator control, hardware testing, and data visualization utilities were also created. A closedloop attitude control strategy was adapted to facilitate future sensor installations, and was tested in numerical simulation. The control model was then updated to interface with the simulator hardware, and for the first time in the project history, attitude control was performed onboard the CalPoly spacecraft attitude dynamics simulator. The demonstration served to validate the numerical model and to verify the functionality of the entire simulator system.
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Podhradský, Michal. "A Multi-Agent System for Adaptive Control of a Flapping-Wing Micro Air Vehicle." PDXScholar, 2016. https://pdxscholar.library.pdx.edu/open_access_etds/3291.
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Biomimetic flapping-wing vehicles have attracted recent interest because of their numerous potential military and civilian applications. In this dissertation is described the design of a multi-agent adaptive controller for such a vehicle. This controller is responsible for estimating the vehicle pose (position and orientation) and then generating four parameters needed for split-cycle control of wing movements to correct pose errors. These parameters are produced via a subsumption architecture rule base. The control strategy is fault tolerant. Using an online learning process, an agent continuously monitors the vehicle's behavior and initiates diagnostics if the behavior has degraded. This agent can then autonomously adapt the rule base if necessary. Each rule base is constructed using a combination of extrinsic and intrinsic evolution. Details of the vehicle, the multi-agent system architecture, agent task scheduling, rule base design, and vehicle control are provided.
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Brown, Sean M. "Determination of Human Powered Helicopter Stability Characteristics using Multi-Body System Simulation Techniques." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/874.
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Multi-Body System Simulation combined with System Identification was developed as a method for determining the stability characteristics of a human powered helicopter(HPH) configurations. HPH stability remains a key component for meeting competition requirements, but has not been properly treated. Traditional helicopter dynamic analysis is not suited to the HPH due to its low rotation speeds and light weight. Multi-Body System Simulation is able to generate dynamic response data for any HPH configuration. System identification and linear stability theory are used to determine the stability characteristics from the dynamic response. This thesis focuses on the method development and doesn't present any HPH analysis results.
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De, Hart Ruan Dirk. "Advanced take-off and flight control algorithms for fixed wing unmanned aerial vehicles." Thesis, Stellenbosch : University of Stellenbosch, 2010. http://hdl.handle.net/10019.1/4179.
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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2010.ENGLISH ABSTRACT: This thesis presents the development and implementation of a position based kinematic guidance system, the derivation and testing of a Dynamic Pursuit Navigation algorithm and a thorough analysis of an aircraft’s runway interactions, which is used to implement automated take-off of a fixed wing UAV. The analysis of the runway is focussed on the aircraft’s lateral modes. Undercarriage and aerodynamic effects are first analysed individually, after which the combined system is analysed. The various types of feedback control are investigated and the best solution suggested. Supporting controllers are designed and combined to successfully implement autonomous take-off, with acceleration based guidance. A computationally efficient position based kinematic guidance architecture is designed and implemented that allows a large percentage of the flight envelope to be utilised. An airspeed controller that allows for aggressive flight is designed and implemented by applying Feedback Linearisation techniques. A Dynamic Pursuit Navigation algorithm is derived that allows following of a moving ground based object at a constant distance (radius). This algorithm is implemented and verified through non-linear simulation.
AFRIKAANSE OPSOMMING: Hierdie tesis handel oor die ontwikkeling en toepassing van posisie-afhanklike, kinematiese leidings-algoritmes, die ontwikkeling van ’n Dinamiese Volgings-navigasie-algoritme en ’n deeglike analise van die interaksie van ’n lugraam met ’n aanloopbaan sodat outonome opstygprosedure van ’n vastevlerk vliegtuig bewerkstellig kan word. Die bogenoemde analise het gefokus op die laterale modus van ’n vastevlerk vliegtuig en is tweeledig behartig. Die eerste gedeelte het gefokus op die analise van die onderstel, terwyl die lugraam en die aerodinamiese effekte in die tweede gedeelte ondersoek is. Verskillende tipes terugvoerbeheer vir die outonome opstygprosedure is ondersoek om die mees geskikte tegniek te bepaal. Addisionele beheerders, wat deur die versnellingsbeheer gebaseerde opstygprosedure benodig word, is ontwerp. ’n Posisie gebaseerde kinematiese leidingsbeheerstruktuur om ’n groot persentasie van die vlugvermoë te benut, is ontwikkel. Terugvoer linearisering is toegepas om ’n lugspoedbeheerder , wat in staat is tot aggressiewe vlug, te ontwerp. ’n Dinamiese Volgingsnavigasie-algoritme wat in staat is om ’n bewegende grondvoorwerp te volg, is ontwikkel. Hierdie algoritme is geïmplementeer en bevestig deur nie-lineêre simulasie.
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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.
Повний текст джерелаАнотація:
Thesis (PhD (Electrical and Electronic Engineering))--Stellenbosch University, 2008.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 simplified with reference trajectories only required to be kinematically feasible. Robustness is achieved through uncertainty encapsulation and disturbance rejection at an acceleration level. The detailed design and associated analysis of the inner loop acceleration controllers is carried out for the case where the airflow incidence angles are small. For this case it is shown that under mild practically feasible conditions the inner loop dynamics decouple and become linear, thereby allowing the derivation of closed form pole placement solutions. Dimensional and normalised non-dimensional time variants of the inner loop controllers are designed and their respective advantages highlighted. Pole placement constraints that arise due to the typically weak non-minimum phase nature of aircraft dynamics are developed. A generic, aircraft independent guidance control algorithm, well suited for use with the inner loop acceleration controllers, is also presented. The guidance algorithm regulates the aircraft about a kinematically feasible reference trajectory. A number of fundamental basis trajectories are presented which are easily linkable to form complex three dimensional manoeuvres. Results from simulations with a number of different aircraft and reference trajectories illustrate the versatility and functionality of the autopilot. Key words: Aircraft control, Autonomous vehicles, UAV flight control, Acceleration control, Aircraft guidance, Trajectory tracking, Manoeuvre flight control.
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Kirkpatrick, Daniel Eugene. "Design of a Hardware Platform for GPS-Based Orientation Sensing." PDXScholar, 2015. https://pdxscholar.library.pdx.edu/open_access_etds/2197.
Повний текст джерелаАнотація:
Unmanned aerial vehicles (UAV's) have recently gained popularity in military, civil service, agriculture, commercial, and hobby use. This is due in part to their affordability, which comes from advances in component technology. That technology includes microelectromechanical systems (MEMS) for inertial sensing, microprocessor technology for sequential algorithm processing, field programmable gate arrays (FPGA's) for parallel data processing, camera technology, global navigation satellite systems (GNSS's) for navigation, and battery technology such as the high energy density of lithium polymer batteries.
Despite the success of the technology to date, there remains development before UAV's should be flying alongside manned aircraft or over populated areas. One concern is that UAV electronics are not as safe, reliable or robust as manned-aircraft electronics because UAV's are not certified by the FAA. Another concern for UAV operation is with control algorithms and sensors, particularly in the estimation of the aircraft state, which is the position, velocity, and orientation of the aircraft. Some problems, such as numerical stability of a control algorithm or flight in windy and turbulent conditions have only been solved for certain conditions of wind, weather, or maneuvers. Outside those conditions, the actual orientation of a flying craft can mislead to the control system, and the control system may not be able to recover without a crash. When pilots fly manned aircraft in instrument meteorological conditions, or conditions of limited visibility of the ground, terrain, and obstacles, the pilot must fly in a manner which avoids abrupt maneuvers which could disturb accuracy of the aircraft's instruments. In a UAV without a pilot, there is a need to estimate the position and orientation of a UAV in an absolute manner unambiguous relative to the Earth. The position and orientation estimate must not depend on carefully controlled flight paths, but instead the estimate must be robust in the presence of UAV flight dynamics.
This thesis describes the design, implementation, and evaluation of a hardware platform for GPS based orientation sensing research. In this work, we considered a receiver with three or four RF sections, each connected to an antenna in a triangular or tetrahedral pyramid constellation. Specific requirements for the receiver hardware and functionality were created. Circuitry was designed to meet the requirements using commercial off-the-shelf (COTS) radio frequency (RF) modules, a mid-sized microcontroller, an FPGA, and other supporting components. A printed circuit board (PCB) was designed, fabricated, assembled, and tested. A GPS baseband processor was designed and coded in Verilog hardware description language. The design was synthesized and loaded to the FPGA, and the microcontroller was programmed to track satellites.
With the hardware platform implemented, live satellite signals were found and tracked, and experiments were performed to explore the validity of GPS based orientation sensing using short antenna baselines. The platform successfully allows the user to develop correlator designs and explore carrier phase based orientation measurement using only software/Verilog modifications. Initial results of carrier phase based orientation sensing are promising, but the presence of multipath signal interference shows room for improvement to the baseband processing code.
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Meier, Kevin Christopher. "Developing a Guidance Law for a Small-Scale Controllable Projectile Using Backstepping and Adaptive Control Techniques and a Hardware System Implementation for a UAV and a UGV to Track a Moving Ground Target." BYU ScholarsArchive, 2012. https://scholarsarchive.byu.edu/etd/3378.
Повний текст джерелаАнотація:
The work in this thesis is on two topics. The first topic focuses on collaboration between a UAV and a UGV to track a moving ground target. The second topic focuses on deriving a guidance law for a small-scale controllable projectile to be guided into a target. For the first topic, we implement a path planning algorithm in a hardware system for a UAV and UGV to track a ground target. The algorithm is designed for urban environments where it is common for objects to obstruct sensors located on the UAV and the UGV. During the hardware system's implementation, multiple problems prevented the hardware system from functioning properly. We will describe solutions to these problems. For the second topic, we develop a guidance law for a small-scale controllable projectile using Lyapunov analysis techniques. We implement a PID controller on the body-axes pitch rate and yaw rate of the projectile such that the behavior of the pitch rate and yaw rate can be approximated as a second order system. We derive inputs for the pitch rate and yaw rate using backstepping and adaptive control techniques. The guidance law we develop guarantees the rocket will point at its intended destination. Additionally, we present expressions for the kinematics and dynamics of the rocket's motion and define the forces and moments that act on the rocket's body.
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Wenger, Jason Christopher. "Development of a synthetic vision system for general aviation." Thesis, University of Iowa, 2007. http://ir.uiowa.edu/etd/162.
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Nichols, Joseph Walter. "Vision-Based Guidance for Air-to-Air Tracking and Rendezvous of Unmanned Aircraft Systems." BYU ScholarsArchive, 2013. https://scholarsarchive.byu.edu/etd/3764.
Повний текст джерелаАнотація:
This dissertation develops the visual pursuit method for air-to-air tracking and rendezvous of unmanned aircraft systems. It also shows the development of vector-field and proportional-integral methods for controlling UAS flight in formation with other aircraft. The visual pursuit method is a nonlinear guidance method that uses vision-based line of sight angles as inputs to the algorithm that produces pitch rate, bank angle and airspeed commands for the autopilot to use in aircraft control. The method is shown to be convergent about the center of the camera image frame and to be stable in the sense of Lyapunov. In the lateral direction, the guidance method is optimized to balance the pursuit heading with respect to the prevailing wind and the location of the target on the image plane to improve tracking performance in high winds and reduce bank angle effort. In both simulation and flight experimentation, visual pursuit is shown to be effective in providing flight guidance in strong winds. Visual pursuit is also shown to be effective in guiding the seeker while performing aerial docking with a towed aerial drogue. Flight trials demonstrated the ability to guide to within a few meters of the drogue. Further research developed a method to improve docking performance by artificially increasing the length of the line of sight vector at close range to the target to prevent flight control saturation. This improvement to visual pursuit was shown to be an effective method for providing guidance during aerial docking simulations. An analysis of the visual pursuit method is provided using the method of adjoints to evaluate the effects of airspeed, closing velocity, system time constant, sensor delay and target motion on docking performance. A method for predicting docking accuracy is developed and shown to be useful for predicting docking performance for small and large unmanned aircraft systems.
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Krantz, Elias. "Experiment Design for System Identification on Satellite Hardware Demonstrator." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71351.
Повний текст джерелаАнотація:
The subject of this thesis covers the process of online parameter estimation of agile satellites. Accurate knowledge of parameters such as moment of inertia and centre of mass play a crucial role in satellite attitude control and pointing performance. Typically, identification of parameters such as these is performed on-ground using post-processing algorithms. This thesis investigates the potential of performing the identification procedures in real-time on-board operating satellites, using only measurements available from typical satellite attitude sensors. The thesis covers the areas of system identification and modelling of spacecraft attitude dynamics. An algorithm based on the Unscented Kalman Filter is developed for online parameter estimation of spacecraft moment of inertia parameters. The proposed method is successfully validated, both through simulation environments, and in practice using Airbus’ satellite hardware demonstrator INTREPID, a three-axis air-bearing table equipped with CMG actuators and typical attitude sensors.
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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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Dam, Long H. "Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator." DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1175.
Повний текст джерелаАнотація:
The Cal Poly Spacecraft Simulator is currently being developed for future testing and verifying theoretical control applications. This paper details the effort to balance the platform and remove undesired external torque from the system using System Identification technique developed by Patrick Healy. Since the relationship between the input and output of the system is linear, the least square method is proposed to identify the mass properties and location of center of mass of the system. The tests use four sine wave generators that are out of phase with different amplitudes as the inputs to excite various structural modes of the system. The outputs, angular rates of the platform, are measured by the newly implemented LN-200 Inertial Measurement Unit that helps reducing the measurement noise. Two test cases of 90o yaw rotations with the identified inertia were performed and validated against the computer simulation model; and the result shows that the test cases trajectories followed closely with the computer simulation model.
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O-larnnithipong, Nonnarit. "Hand Motion Tracking System using Inertial Measurement Units and Infrared Cameras." FIU Digital Commons, 2018. https://digitalcommons.fiu.edu/etd/3905.
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This dissertation presents a novel approach to develop a system for real-time tracking of the position and orientation of the human hand in three-dimensional space, using MEMS inertial measurement units (IMUs) and infrared cameras. This research focuses on the study and implementation of an algorithm to correct the gyroscope drift, which is a major problem in orientation tracking using commercial-grade IMUs. An algorithm to improve the orientation estimation is proposed. It consists of: 1.) Prediction of the bias offset error while the sensor is static, 2.) Estimation of a quaternion orientation from the unbiased angular velocity, 3.) Correction of the orientation quaternion utilizing the gravity vector and the magnetic North vector, and 4.) Adaptive quaternion interpolation, which determines the final quaternion estimate based upon the current conditions of the sensor.
The results verified that the implementation of the orientation correction algorithm using the gravity vector and the magnetic North vector is able to reduce the amount of drift in orientation tracking and is compatible with position tracking using infrared cameras for real-time human hand motion tracking. Thirty human subjects participated in an experiment to validate the performance of the hand motion tracking system. The statistical analysis shows that the error of position tracking is, on average, 1.7 cm in the x-axis, 1.0 cm in the y-axis, and 3.5 cm in the z-axis. The Kruskal-Wallis tests show that the orientation correction algorithm using gravity vector and magnetic North vector can significantly reduce the errors in orientation tracking in comparison to fixed offset compensation. Statistical analyses show that the orientation correction algorithm using gravity vector and magnetic North vector and the on-board Kalman-based orientation filtering produced orientation errors that were not significantly different in the Euler angles, Phi, Theta and Psi, with the p-values of 0.632, 0.262 and 0.728, respectively.
The proposed orientation correction algorithm represents a contribution to the emerging approaches to obtain reliable orientation estimates from MEMS IMUs. The development of a hand motion tracking system using IMUs and infrared cameras in this dissertation enables future improvements in natural human-computer interactions within a 3D virtual environment.
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Ilg, Mark Dean Chang Bor-Chin. "Guidance, navigation, and control for munitions /." Philadelphia, Pa. : Drexel University, 2008. http://hdl.handle.net/1860/2831.
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McConnell, George. "Digital bank-to-turn control and guidance." Thesis, Queen's University Belfast, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303013.
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Annamalai, Andy S. K. "An adaptive autopilot design for an uninhabited surface vehicle." Thesis, University of Plymouth, 2014. http://hdl.handle.net/10026.1/3100.
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An adaptive autopilot design for an uninhabited surface vehicle Andy SK Annamalai The work described herein concerns the development of an innovative approach to the design of autopilot for uninhabited surface vehicles. In order to fulfil the requirements of autonomous missions, uninhabited surface vehicles must be able to operate with a minimum of external intervention. Existing strategies are limited by their dependence on a fixed model of the vessel. Thus, any change in plant dynamics has a non-trivial, deleterious effect on performance. This thesis presents an approach based on an adaptive model predictive control that is capable of retaining full functionality even in the face of sudden changes in dynamics. In the first part of this work recent developments in the field of uninhabited surface vehicles and trends in marine control are discussed. Historical developments and different strategies for model predictive control as applicable to surface vehicles are also explored. This thesis also presents innovative work done to improve the hardware on existing Springer uninhabited surface vehicle to serve as an effective test and research platform. Advanced controllers such as a model predictive controller are reliant on the accuracy of the model to accomplish the missions successfully. Hence, different techniques to obtain the model of Springer are investigated. Data obtained from experiments at Roadford Reservoir, United Kingdom are utilised to derive a generalised model of Springer by employing an innovative hybrid modelling technique that incorporates the different forward speeds and variable payload on-board the vehicle. Waypoint line of sight guidance provides the reference trajectory essential to complete missions successfully. The performances of traditional autopilots such as proportional integral and derivative controllers when applied to Springer are analysed. Autopilots based on modern controllers such as linear quadratic Gaussian and its innovative variants are integrated with the navigation and guidance systems on-board Springer. The modified linear quadratic Gaussian is obtained by combining various state estimators based on the Interval Kalman filter and the weighted Interval Kalman filter. Change in system dynamics is a challenge faced by uninhabited surface vehicles that result in erroneous autopilot behaviour. To overcome this challenge different adaptive algorithms are analysed and an innovative, adaptive autopilot based on model predictive control is designed. The acronym ‘aMPC’ is coined to refer to adaptive model predictive control that is obtained by combining the advances made to weighted least squares during this research and is used in conjunction with model predictive control. Successful experimentation is undertaken to validate the performance and autonomous mission capabilities of the adaptive autopilot despite change in system dynamics.
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Corban, J. Eric. "Real-time guidance and propulsion control for single-stage-to-orbit airbreathing vehicles." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12889.
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