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  • About
  • The Global ETD Search service is a free service for researchers to find electronic theses and dissertations. This service is provided by the Networked Digital Library of Theses and Dissertations.
    Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
71

System level airborne avionics prognostics for maintenance, repair and overhaul

Aman Shah, Shahani January 2016 (has links)
The aim of this study is to propose an alternative approach in prognostics for airborne avionics system in order to enhance maintenance process and aircraft availability. The objectives are to analyse the dependency of avionic systems for fault propagation behaviour degradation, research and develop methods to predict the remaining useful life of avionics Line Replaceable Units (LRU), research and develop methods to evaluate and predict the degradation performances of avionic systems, and lastly to develop software simulation systems to evaluate methods developed. One of the many stakeholders in the aircraft lifecycle includes the Maintenance, Repair and Overhaul (MRO) industry. The predictable logistics process to some degree as an outcome of IVHM gives benefit to the MRO industry. In this thesis, a new integrated numerical methodology called ‘System Level Airborne Avionic Prognostics’ or SLAAP is developed; looking at a top level solution in prognostics. Overall, this research consists of two main elements. One is to thoroughly understand and analyse data that could be utilised. Secondly, is to apply the developed methodology using the enhanced prognostic methodology. Readily available fault tree data is used to analyse the dependencies of each component within the LRUs, and performance were simulated using the linear Markov Model to estimate the time to failure. A hybrid approach prognostics model is then integrated with the prognostics measures that include environmental factors that contribute to the failure of a system, such as temperature. This research attempts to use data that is closest to the data available in the maintenance repair and overhaul industry. Based on a case study on Enhanced Ground Proximity Warning System (EGPWS), the prognostics methodology developed showed a sufficiently close approximation to the Mean Time Before Failure (MTBF) data supplied by the Original Equipment Manufacturer (OEM). This validation gives confidence that the proposed methodology will achieve its objectives and it should be further developed for use in the systems design process.
72

Fault management via dynamic reconfiguration for integrated modular avionics

Hubbard, Peter D. January 2015 (has links)
The purpose of this research is to investigate fault management methodologies within Integrated Modular Avionics (IMA) systems, and develop techniques by which the use of dynamic reconfiguration can be implemented to restore higher levels of systems redundancy in the event of a systems fault. A proposed concept of dynamic configuration has been implemented on a test facility that allows controlled injection of common faults to a representative IMA system. This facility allows not only the observation of the response of the system management activities to manage the fault, but also analysis of real time data across the network to ensure distributed control activities are maintained. IMS technologies have evolved as a feasible direction for the next generation of avionic systems. Although federated systems are logical to design, certify and implement, they have some inherent limitations that are not cost beneficial to the customer over long life-cycles of complex systems, and hence the fundamental modular design, i.e. common processors running modular software functions, provides a flexibility in terms of configuration, implementation and upgradability that cannot be matched by well-established federated avionic system architectures. For example, rapid advances of computing technology means that dedicated hardware can become outmoded by component obsolescence which almost inevitably makes replacements unavailable during normal life-cycles of most avionic systems. To replace the obsolete part with a newer design involves a costly re-design and re-certification of any relevant or interacting functions with this unit. As such, aircraft are often known to go through expensive mid-life updates to upgrade all avionics systems. In contrast, a higher frequency of small capability upgrades would maximise the product performance, including cost of development and procurement, in constantly changing platform deployment environments. IMA is by no means a new concept and work has been carried out globally in order to mature the capability. There are even examples where this technology has been implemented as subsystems on service aircraft. However, IMA flexible configuration properties are yet to be exploited to their full extent; it is feasible that identification of faults or failures within the system would lead to the exploitation of these properties in order to dynamically reconfigure and maintain high levels of redundancy in the event of component failure. It is also conceivable to install redundant components such that an IMS can go through a process of graceful degradation, whereby the system accommodates a number of active failures, but can still maintain appropriate levels of reliability and service. This property extends the average maintenance-free operating period, ensuring that the platform has considerably less unscheduled down time and therefore increased availability. The content of this research work involved a number of key activities in order to investigate the feasibility of the issues outlined above. The first was the creation of a representative IMA system and the development of a systems management capability that performs the required configuration controls. The second aspect was the development of hardware test rig in order to facilitate a tangible demonstration of the IMA capability. A representative IMA was created using LabVIEW Embedded Tool Suit (ETS) real time operating system for minimal PC systems. Although this required further code written to perform IMS middleware functions and does not match up to the stringent air safety requirements, it provided a suitable test bed to demonstrate systems management capabilities. The overall IMA was demonstrated with a 100kg scale Maglev vehicle as a test subject. This platform provides a challenging real-time control problem, analogous to an aircraft flight control system, requiring the calculation of parallel control loops at a high sampling rate in order to maintain magnetic suspension. Although the dynamic properties of the test rig are not as complex as a modern aircraft, it has much less stringent operating requirements and therefore substantially less risk associated with failure to provide service. The main research contributions for the PhD are: 1. A solution for the dynamic reconfiguration problem for assigning required systems functions (namely a distributed, real-time control function with redundant processing channels) to available computing resources whilst protecting the functional concurrency and time critical needs of the control actions. 2. A systems management strategy that utilises the dynamic reconfiguration properties of an IMA System to restore high levels of redundancy in the presence of failures. The conclusion summarises the level of success of the implemented system in terms of an appropriate dynamic reconfiguration to the response of a fault signal. In addition, it highlights the issues with using an IMA to as a solution to operational goals of the target hardware, in terms of design and build complexity, overhead and resources.
73

Unified modelling of aerospace systems : a bond graph approach

Diston, Dominic John January 1999 (has links)
Systems Integration is widely accepted as the basis for improving the efficiency and performance of many engineering products. The aim is to build a unified optimised system not a collection of subsystems that are combined in some ad hoc manner. This moves traditional design boundaries and, in so doing, enables a structured evolution from an integrated system concept to an integrated system product. It is recognised that the inherent complexity cannot be handled effectively without mathematical modelling. The problem is not so much the large number of components but rather the very large number of functional interfaces that result. The costs involved are high and, if the claims of improved efficiency and performance are to be affordable (or even achievable), predictive modelling and analysis will play a major role in reducing risk. A modelling framework is required which can support integrated system development from concept through to certification. This means building a 'system' inside a computer and demonstrating the feasibility of an entire development cycle. The objective is to provide complete coverage of system functionality so as to gain confidence in the design before becoming locked into a full development programme with associated capital investment and contractual arrangements. With these points in mind the purpose of this thesis is threefold. First, to demonstrate the application of bond graphs as a unified modelling framework for aerospace systems. Second, to review the main principles involved with the modelling of engineering systems and to justify the selection of the bond graph notation as a suitable means of representing the power flow (i.e. the dynamics) of physical systems. Third, to present an exposition of the bond graph method and to evolve it into a versatile notation for integrated systems. The originality of the work is based on the recognition that systems integration is a relatively new field of interest without a mature body of academic literature or reported research. Apparently, there is no open literature on the modelling of complete air vehicles plus their embedded vehicle systems which deals with issues of integrated dynamics and control. To this end, bond graph concepts need to be developed and extended in new direction in order to facilitate an intuitive approach to the modelling of integrated systems.
74

Addressing Security Challenges in Emerging Data-based Aeronautical Communications / Sécurisation des futures communications aéronautiques de données

Ben Mahmoud, Mohamed Slim 17 February 2012 (has links)
Ce travail de thèse s'intéresse à la sécurité des futures communications aéronautiques de donnée. Le travail est divisé en trois grandes parties. La première contribution est une architecture de sécurité adaptative pour les communications aéronautiques intégrant un segment sol-bord par satellite. Un module de gestion de la sécurité a été conçu, développé, puis validé lors de la phase finale d'intégration du projet FAST (Fibre-like Aircraft Satellite Communications). La deuxième contribution est une méthodologie quantitative d'estimation du risque lié à la sécurité réseau. L'originalité de notre approche est d'être basée sur la notion de propagation du risque au sein des différents noeuds du réseau. Commecas d'étude, un réseau de communication aéroportuaire utilisant le protocole AeroMACS a été étudié dans le cadre du projet SESAR (Single European Sky ATM Research). La troisième contribution est une infrastructure à clés publiques (PKI) qui permet d'optimiser les échanges de signalisation (échanges de clés, certificats, vérification des signatures) entre l'avion et l'autorité de certification au sol. Le modèle de PKI proposé est un modèle hiérarchique utilisant la certification croisée entre les autorités de certification mères / This research work deals with the information and network security in the aeronautical communication domain. Three fundamental research axes are explored. First, a quantitative network security risk assessment methodology is proposed. Our approach is based on the risk propagation within the network nodes. As study cases, the algorithm has been validated in the scope of the European industrial project entitled SESAR (Single European Sky ATM Research) and the Aerospace Valley FAST (Fibrelike Aircraft Satellite Communications). Particularly, experimental results relative to the case study devoted to the FAST project shown that the global network risk in the non secured system architecture is relatively high, meaning the system needs more consideration from a security point of view. To cope with this issue, an adaptive security management framework for a satellite-based aeronauticalcommunication architecture has been proposed as a second contribution. A security manager module has been designed, implemented, then tested in the scope of the FAST project. Finally, as the security primitives used in the adaptive security management framework need to be efficiently exchanged, the last contribution consists in a scalable PKI adapted for the upcoming network-enabled aircraft. The idea is to minimize the air-ground additional overhead induced by the security procedures (keys, digital certificates, revocation/verification procedures). The PKI model we propose is a cross-certified multirooted hierarchical model
75

Combinaison des aspects temps réel et sûreté de fonctionnement pour la conception des plateformes avioniques / Combination of real-time and safety aspects for the design of avionic platforms

Many, Florian 18 February 2013 (has links)
La conception des plateformes aéronautiques s’effectue en tenant compte des aspects fonctionnels et dysfonctionnels prévus dans les scénarios d’emploi des aéronefs qui les embarquent. Ces plateformes aéronautiques sont composées de systèmes informatiques temps réel qui doivent à la fois être précises dans leurs calculs, exactes dans l’instant de délivrance des résultats des calculs, et robustes à tout évènement pouvant compromettre le bon fonctionnement de la plateforme.Dans ce contexte, ces travaux de thèse abordent les ordonnancements temps réel tolérants aux fautes. Partant du fait que les systèmes informatiques embarqués sont perturbés par les ondes électromagnétiques des radars, notamment dans la phase d’approche des aéronefs, ces travaux proposent une modélisation des effets des ondes, dite en rafales de fautes. Après avoir exploré le comportement de l’ordonnanceur à la détection d’erreurs au sein d’une tâche, une technique de validation, reposant sur le calcul de pire temps de réponse des tâches, est présentée. Il devient alors possible d’effectuer des analyses d’ordonnançabilité sous l’hypothèse de la présence de rafales de fautes. Ainsi, cette technique de validation permet de conclure sur la faisabilité d’un ensemble de tâches en tenant compte de la durée de la rafale de fautes et de la stratégie de gestion des erreurs détectées dans les tâches.Sur la base de ces résultats, les travaux décrits montre comment envisager l’analyse au niveau système. L’idée sous-jacente est de mettre en évidence le rôle des ordonnancements temps réel tolérants aux fautes dans la gestion des données erronées causées par des perturbations extérieures au système.Ainsi, le comportement de chaque équipement est modélisé, ainsi que les flots de données échangés et la dynamique du système. Le comportement de chaque équipement est fonction de la perturbation subie, et donne lieu à l’établissement de la perturbation résultante, véritable réponse dysfonctionnelle de l’équipement à une agression extérieure. / The design of avionic platforms takes into account the functional and dysfunctional aspects, which depend on the aircraft operation concept. These avionic platforms embed computer resources that must produce accurate results at the right time, and must be dependable whatever the disturbance.In this specific context, we address the topic of fault tolerant real time scheduling. Since the embedded computer resources are disturbed by electromagnetic waves produced by radar, especially during the aircraft approach, we suggest a model of these wave effects named fault bursts. Afterthe analysis of scheduler behaviour when an error is dectected inside a task, we present a validation technique based on the evaluation of the worst case response time. By this way, we are able to study the task set feasibility under fault burst assumption and according to the error recovery strategy.Then, based on these results, we show a way to analyse the effects of disturbances such as electromagnetic waves at system level. The underlining idea is to demonstrate the main role of fault tolerant real time scheduler in the management of erroneous data. To do that, we suggest an equipment model which integrates the behaviour of the equipement when a disturbance occurs. We also describe thedata flows in order to describe the avionics platform dynamics.
76

Electro-mechanical interaction in gas turbine-generator systems for more-electric aircraft

Feehally, Thomas January 2012 (has links)
Modern 'more-electric' aircraft demand increased levels of electrical power as non-propulsive power systems are replaced with electrical equivalents. This electrical power is provided by electrical generators, driven via a mechanical transmission system, from a rotating spool in the gas turbine core. A wide range of electrical loads exist throughout the aircraft, which may be pulsating and high powered, and this electrical power demand is transferred though the generators to produce a torque load on the drivetrain. The mechanical components of the drivetrain are designed for minimum mass and so are susceptible to fatigue, therefore the electrical loading existing on modern airframes may induce fatigue in key mechanical components and excite system resonances in both mechanical and electrical domains. This electro-mechanical interaction could lead to a reduced lifespan for mechanical components and electrical network instability.This project investigates electro-mechanical interaction in the electrical power offtake from large diameter aero gas turbines. High fidelity modelling of the drivetrain, and generator, allow the prediction of system resonances for a generic gas turbine-generator system. A Doubly-Fed Induction Generator (DFIG) is considered and modelled. DFIGs offer opportunities due to their fast dynamics and their ability to decouple electrical and mechanical frequencies (e.g. enabling a constant frequency electrical system with a variable speed mechanical drive). A test platform is produced which is representative of a large diameter gas turbine and reproduces the electro-mechanical system behaviour. The test platform is scaled with respect to speed and power but maintains realistic sizing between component dimensions which include: a gas turbine mechanical spool emulation, transmission driveshafts and gearbox, and accessory loads such as a generator. This test platform is used to validate theoretical understanding and suggest alternative mechanical configurations, and generator control schemes, for the mitigation of electro-mechanical interaction.The novel use of a DFIG and an understanding of electro-mechanical interaction allow future aircraft designs to benefit from the increased electrification of systems by ensuring that sufficient electrical power can be provided by a robust gas turbine-generator system.
77

Analyse de vulnérabilités de systèmes avioniques embarqués : classification et expérimentation / Vulnerabilities analysis of embedded avionic systems : classification and experiment

Dessiatnikoff, Anthony 17 July 2014 (has links)
L’évolution actuelle des systèmes embarqués à bord des systèmes complexes (avions,satellites, navires, automobiles, etc.) les rend de plus en plus vulnérables à des attaques,en raison de : (1) la complexité croissante des applications ; (2) l’ouverture des systèmes vers des réseaux et systèmes qui ne sont pas totalement contrôlés ; (3) l’utilisation de composants sur étagère qui ne sont pas développés selon les méthodes exigées pour les systèmes embarqués critiques ; (4) le partage de ressources informatiques entre applications, qui va de pair avec l’accroissement de puissance des processeurs. Pour faire face aux risques de malveillances ciblant les systèmes embarqués, il est nécessaire d’appliquer ou d’adapter les méthodes et techniques de sécurité qui ont fait leurs preuves dans d’autres contextes : Méthodes formelles de spécification, développement et vérification ;Mécanismes et outils de sécurité (pare-feux, VPNs, etc.) ; Analyse de vulnérabilités et contre-mesures. C’est sur ce dernier point que portent nos travaux de thèse.En effet, cet aspect de la sécurité a peu fait l’objet de recherche, contrairement aux méthodes formelles. Cependant, il n’existe pas actuellement de modèle formel capable de couvrir à la fois des niveaux d’abstraction suffisamment élevés pour permettre d’exprimer les propriétés de sécurité désirées, et les détails d’implémentation où se situent la plupart des vulnérabilités susceptibles d’être exploitées par des attaquants : fonctions des noyaux d’OS dédiées à la protection des espaces d’adressage, à la gestion des interruptions et au changement de contextes, etc. ; implémentation matérielle des mécanismes de protection et d’autres fonctions ancillaires. C’est sur ces vulnérabilités de bas niveau que se focalise notre étude.Nos contributions sont résumées par la suite. Nous avons proposé une classification des attaques possibles sur un système temps-réel. En nous basant sur cette classification,nous avons effectué une analyse de vulnérabilité sur un système réaliste : une plateforme avionique expérimentale fournie par Airbus. Il s’agit d’un noyau temps-réel critique ordonnancé avec plusieurs autres applications, le tout exécuté sur une plateforme Freescale QorIQ P4080. C’est à travers une application dite « malveillante », présente parmi l’en-semble des applications, que nous essayons de modifier le comportement des autres applications ou du système global pour détecter des vulnérabilités. Cette méthode d’analyse de vulnérabilités a permis de détecter plusieurs problèmes concernant les accès mémoire,la communication entre applications, la gestion du temps et la gestion des erreurs qui pouvaient conduire à la défaillance du système global. Enfin, nous avons proposé des contre-mesures spécifiques à certaines attaques et des contre-mesures génériques pour le noyau temps-réel qui permet d’empêcher une application d’obtenir des accès privilégiés ou encore de perturber le comportement du système. / Security is becoming a major concern for embedded computing systems in variouscritical industrial sectors (aerospace, satellites, automotive, etc.). Indeed, recent trendsin the development and operation of such systems, have made them more and morevulnerable to potential attacks, for the following reasons : 1) increasing complexity of theapplications ; 2) openness to applications and networks that are note completely undercontrol ; 3) Use Commercial-Off-The-Shelf (COTS) hardware and software components ;4) Resource sharing among different applications, driven by the increase of processorscapabilities.To improve the security of such systems, it is necessary to apply or adapt methodsand techniques that have proven their efficiency in other contexts : Formal methods forspecification, development and verification ; Security mechanisms and tools (firewalls,VPNs, etc.) ; Vulnerability assessment and countermeasure provision.The research carried out in this thesis adresses the latter technique. This aspect ofsecurity analysis cannot be easily covered by current formal methods, since no exist-ing model is able to cover both high-level abstractions, where security properties canbe defined, and low-level implementation details, where most vulnerabilities that couldbe exploited by attackers lie : OS kernel implementation of address space protection,interrupt management, context switching, etc. ; hardware implementation of protectionmechanisms and other ancillary functions. Very few research projects are addressing thisaspect of security, which is the main objective of this thesis. In particular, our researchfocuses on low-level vulnerabilities, but contrarily with common practice, we aim todiscover and analyze them during the development process.Our contributions are summarized as follows. We elaborated a classification of low-level vulnerabilities for different implementations of real-time embedded systems. Basedon this classification, we carried out a vulnerability analysis study on a realistic system :An experimental avionic platform provided by Airbus. It consists of a critical real-timekernel scheduling the execution of different applications on a freescale QorIQ P4080platform. The identification and analysis of vulnerabilities is carried out based on a“malicious” application hosted on the platform that attempts to corrupt the behavior ofthe other applications or the global system considering different types of low level attacks.Such experiments allowed us to identify some problems related to the management ofmemory accesses, the communication between applications, time management and errorhandling that could lead to the global system failure.We have also proposed genericcounter measures to protect the real-time kernel against specific attacks, and to preventa given application from escalating its privileges or trying to compromise the systembehavior
78

De l'usage d'architectures Ethernet commutées embarquées dans les lanceurs spatiaux / On the use of switched Ethernet embedded in space launchers

Robert, Jérémy 23 October 2012 (has links)
Les lanceurs spatiaux actuels, et en particulier Ariane 5, utilisent le réseau déterministe MIL-STD-1553B. Compte tenu des nouveaux objectifs de réduction des coûts et de la masse du système global ainsi que du support de trafic de télémesure multimédia, cette technologie n'est plus forcément optimale. Parmi les différents candidats de remplacement, cette thèse met en évidence les capacités du standard Ethernet à répondre à ces nouveaux objectifs tout en s'appuyant sur une utilisation de composants matériels et d'outils de développement existants à moindre coût (COTS). La première contribution porte sur l'évaluation de performances temporelles des architectures commutées. Les travaux mettent ainsi en évidence les gains et limites liés au choix d'une part du mode de communication (de maître/esclaves à producteurs/consommateur) et d'autre part à une future distribution de l'avionique. Pour cela, cette étude s'appuie sur une évaluation déterministe des délais de bout en bout par calcul réseau, simulations et expérimentations. Ces résultats ont été validés pour deux architectures commutées pour un scénario représentatif des vols actuels. La seconde contribution concerne l'amélioration de la disponibilité du système de communication. Il est proposé une stratégie de reconfiguration "temps réel" des chemins par supervision active du réseau. Dans le cadre d'exigences critiques, il est également proposé l'utilisation d'arbres couvrants multiples permettant d'anticiper la défaillance d'éléments d'interconnexion. Enfin, le choix d'architectures commutées et segmentées ne permet plus d'observer en tout point le réseau comme sur un bus. Pour cela, cette thèse met en avant les conditions et performances dans lesquelles un protocole de synchronisation d'horloges pourra contribuer à générer à partir de plusieurs points de captures une trace unique des échanges sur le réseau. Ce travail permettra d'identifier les tests pour une future validation du standard Ethernet pour les lanceurs spatiaux / Current space launchers, and particularly Ariane 5, use the deterministic network MIL-STD-1553B. According to the new objectives of cost and system mass reduction and of multimedia traffic support, this technology is not optimal anymore. Among the potential candidates, this thesis highlights the fact that such objectives can be achieved through the use of Ethernet standard based on components-on-the-shelf. The first contribution focuses on time performance evaluation of switched architectures. The gain and limits related to the communication mode (from master/slaves to producers/consummers) and future avionic distribution are studied. This study relies on a deterministic evaluation of the end-to-end delay by using network calculus, simulations and experiments. These results are validated with two switched architectures by using a scenario considered as representative of current flights. The second contribution is the network availability improvement. A real-time path reconfiguration strategy is proposed through active network supervision. Based on critical requirements, it is also suggested to use multiple spanning-trees for anticipating network element failures. The last contribution deals with the issue that in switched and segmented architectures it is not possible to collect all the traffic as in a bus. In order to do so, this thesis introduces the configurations under which a clock synchronization protocol could contribute to generate a single network trace from many collecting points. This work will enable to identify the tests for a future Ethernet standard validation in the framework of space launchers
79

Control of cooperative unmanned aerial vehicles / Έλεγχος συνεργαζόμενων ρομποτικών οχημάτων

Αλέξης, Κώστας 06 October 2011 (has links)
This thesis addresses the problems of design and control of small cooperative unmanned autonomous quadrotor aerial vehicles. A new approach is proposed, for the modeling of the system’s dynamics using linearized Piecewise AffineModels. The Piecewise Affine dynamic–models cover a large part of the quadrotor’s flight envelope while also taking into account the additive effects of environmental disturbances. The effects of aerodynamic forces and moments were also examined. A small quadrotor is designed and developed that emphasizes in the areas of increased on–board computational capabilities, state estimation and modular connectivity. Based on the translational and rotational system’s dynamics: a) a switching model predictive controller, b) an explicitly solved constrained finite time optimal control strategy, and c) a cascade control scheme comprised of classical Proportional Integral Derivative control scheme augmented with angular acceleration feedback, were designed and experimentally tested in order to achieve trajectory tracking under the presence of wind–gusts. The efficiency of the proposed control methods was verified through extended experimental studies. The final quadrotor design utilizes a powerful control unit, a sensor system that provides state estimation based on inertial sensors, ultrasound sonars, GPS and vision chips, and an efficient actuating system. The research effort extended in the field of unmanned aerial vehicles cooperation. Cooperation strategies were proposed in order to address the problems of: a) Forest Fire Monitoring and b) Unknown Area Exploration and Target Acquisition. The Forest FireMonitoring algorithm is formulated based on consensus systems theory formulated as a spatiotemporal rendezvous problem in between the quadrotors. The Area Exploration and Target Acquisition algorithm is formulated based on market–based approaches. / Η συγκεκριμένη διατριβή καταπιάνεται με τα προβλήματα της σχεδίασης και ελέγχου μικρού μεγέθους συνεργαζόμενων μη επανδρωμένων αεροσκαφών με έμφαση στα συστήματα Κάθετης Απογείωσης και Προσγείωσης και ιδιαίτερα στη συστήματα τύπου Quadrotor. Μια νέα προσέγγιση για την μοντελοποίηση της δυναμικής του συστήματος η οποία βασίζεται στη θεωρία των Piecewise Affine συστημάτων προτείνεται. Η μοντελοποίηση με βάση τη θεωρία των Piecewise Affine συστημάτων καλύπτει ένα μεγάλο μέρος του φακέλου πτήσης του αεροσκάφους καθότι συνυπολογίζει μέρος της μη-γραμμικότητας του συστήματος ενώ παράλληλα δίνει τη δυνατότητα να χρησιμοποιηθούν τα ιδιαίτερα ανεπτυγμένα εργαλεία του γραμμικού ελέγχου. Αναπτύσσεται νέα πειραματική πλατφόρμα αεροσκάφους τύπου quadrotor η οποία χαρακτηρίζεται από ιδιαίτερες ικανότητες υπολογιστικής ισχύος, αυτόνομη εκτίμηση κατάστασης, πολλαπλή συνδεσιμότητα και αποδοτικό σύστημα πρόωσης. Η τελική πλατφόρμα quadrotor ελικοπτέρου UPATcopter ενσωματώνει μικρουπολογιστικό σύστημα υψηλών δυνατοτήτων, ειδικά συστήματα εκτίμησης κατάστασης τόσο σε εσωτερικούς όσο και σε εξωτερικούς χώρους μέρος των οποίων αναπτύχθηκε στα πλαίσια της διατριβής και αποδοτικό υποσύστημα πρόωσης. Τρεις διαφορετικοί νόμοι ελέγχου αναπτύχθηκαν και δοκιμάστηκαν πειραματικά. Αρχικά δοκιμάσθηκε ένας Constrained Finite Time Optimal Controller, ο οποίος υπολογίζεται πολύ-παραμετρικά και συνυπολογίζει την επίδραση των περιορισμών εισόδου και κατάστασης. Ο συγκεκριμένος ελεγκτής υπολογίσθηκε με βάση μια οικογένεια Piecewise Affine αναπαραστάσεων του υποσυστήματος προσανατολισμού και δοκιμάσθηκε επιτυγχάνοντας αποδοτικό έλεγχο του προσανατολισμού του σκάφους. Ακολούθως δοκιμάσθηκε ένας Switching Model Predictive Control βασισμένος στην Piecewise Affine μοντελοποίηση του συστήματος ο οποίος επίσης συνυπολογίζει την επίδραση των περιορισμών του συστήματος και του ρόλου των διαταραχών. Με τη χρήση αυτού του ελεγκτή επιτεύχθηκε έλεγχος προσανατολισμού και θέσης του αεροσκάφους τόσο σε άπνοια όσο και υπό την επίδραση ισχυρών διαταραχών ανέμου. Επιπρόσθετα, δοκιμάσθηκε ελεγκτής βασισμένος στη θεωρία PID ελέγχου επαυξημένος με ανάδραση γωνιακής επιτάχυνσης του συστήματος. Τέλος, η έρευνα επεκτάθηκε και στις στρατηγικές συνεργασίας μη επανδρωμένων αεροσκαφών προτείνοντας δύο αλγόριθμους. Συγκεκριμένα προτάθηκε αλγόριθμος για την αντιμετώπιση των προβλημάτων επιθεώρησης δασικής πυρκαγιάς και αλγόριθμος εξερεύνησης μιας άγνωστης περιοχής από ομάδα ετερογενών αεροσκαφών.
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Component-led integrative optimisation methodology for avionic thermal management

Jones, Andy January 2017 (has links)
The modern military aircraft can be defined as a System of Systems (SoS); several distinct systems operating simultaneously across boundary interfaces. As the on-board subsystems have become more complex and diverse, the development process has become more isolated. When considering thermal management of distributed heat loads, the aircraft has become a collection of individually optimised components and subsystems, rather than the implementation of a single system to perform a given task. Avionic thermal management is quickly becoming a limiting factor of aircraft performance, reliability and effectiveness. The challenge of avionic thermal management is growing with the increasing complexity and power density of avionic packages. The aircraft relies on a heat rejection growth capacity to accommodate the additional through-life avionic heat loads. Growth capacity is defined as an allowable thermal loading growth designed into the system by the underutilisation of spatial and cooling supply at aircraft introduction; however, this is a limited resource and aircraft subsystem cooling capability is reaching a critical point. The depleted growth capacity coupled with increased avionic power demands has led to component thermal failure. However, due to the poor resolution of existing data acquisition, experimental facilities or thermodynamic modeling, the exact inflight-operating conditions remain relatively unknown. The knowledge gap identified in this work is the lack of definitive methodology to generate high fidelity data of in-flight thermal conditions of fast-jet subsystems and provide evidence towards effective future thermal management technologies. It is shown that, through the development of a new methodology, the knowledge gap can be reduced and as an output of this approach the unknown system behaviour can be defined. A multidisciplinary approach to the replication, analysis and optimisation of a fast-jet TMS is detailed. The development of a new Ground Test Facility (GTF) allows previously unidentified system thermal behaviour to be evaluated at component, subsystem and system level. The development of new data to characterise current thermal performance of a fast jet TMS allows recommendations of several new technologies to be implemented through a component led integrative system optimisation. This approach is to consider the TMS as a single system to achieve a single goal of component thermal management. Three technologies are implemented to optimise avionic conditions through the minimisation of bleed air consumption, improve avionic reliability through increased avionic component isothermalisation and increase growth capacity through improved avionic heat exchanger fin utilisation. These component level technologies improved system level performance. A reduction in TMS bleed air consumption from 1225kg to 510kg was found to complete a typical flight profile. A peak predicted aircraft specific fuel consumption saving of 1.23% is seen at a cruise flight condition because of this approach to avionic thermal management.

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