This Master's Thesis describes methods of software certification and development of airborne systems, focusing on software testing and verification during project's life cycle. Thesis includes also designed software verification plan for concrete application according to RTCA/DO-178B. Another part of thesis illustrates the exemplary realization of tests according to designed verification plan. At the close we describe the options of applying the designed verification plan and evaluation of its results.

Le développement de tests pour les systèmes d’avioniques met en jeu une multiplicité de langages de test propriétaires, sans aucun standard émergent.Les fournisseurs de solutions de test doivent tenir compte des habitudes des différents clients, tandis que les échanges de tests entre les avionneurs et leurs équipementiers / systémiers sont entravés. Nous proposons une approche dirigée par les modèles pour s’attaquer à ces problèmes: des modèles de test sont développés et maintenus à la place du code, avec des transformations modèle-vers-code vers des langages de test cibles. Cette thèse présente trois contributions dans ce sens. La première consiste en l’analyse de quatre langages de test propriétaires actuellement déployés. Elle nous a permis d’identifier les concepts spécifiques au domaine, les meilleures pratiques,ainsi que les pièges à éviter. La deuxième contribution est la définition d’un méta-modèle en EMF Ecore, qui intègre tous les concepts identifiés et leurs relations. Le méta-modèle est la base pour construire des éditeurs de modèles de test et des motifs de génération de code. Notre troisième contribution est un d´démonstrateur de la façon dont ces technologies sont utilisées pour l’élaboration des tests. Il comprend des éditeurs personnalisables graphiques et textuels pour des modèles de test, ainsi que des transformations basées-motifs vers un langage du test exécutable sur une plateforme de test réelle. / The development of tests for avionics systems involves a multiplicity of in-house test languages, with no standard emerging. Test solution providers have to accommodate the habits of different clients, while the exchange of tests between aircraft manufacturers and their equipment/system providers is hindered. We propose a model-driven approach to tackle these problems: test models would be developed and maintained in place of code, with model-to-code transformations towards target test languages. This thesis presents three contributions in this direction. The first one consists in the analysis of four proprietary test languages currently deployed. It allowed us to identify the domain-specific concepts, best practices, as well as pitfalls to avoid. The second contribution is the definition of a meta-model in EMF Ecore that integrates all identified concepts and their relations. The meta-model is the basis for building test model editors and code generation templates. Our third contribution is a demonstrator of how these technologies are used for test development. It includes customizable graphical and textual editors for test models, together with template-based transformations towards a test language executable on top of a real test platform.

In the aviation industry, safety and robustness are the number one priorities, which is why they use well-tested systems such as hydraulic actuators. However, drawbacks such as high weight and maintenance have pushed the industry toward newer, electrical, actuators that are more efficient and lighter. Electrical actuators, on the other hand, have some reliability issues. In particular, short circuits in the stator windings of Permanent-Magnet SynchronousMotors (PMSMs), referred to as Inter-Turn Short Faults (ITSFs), are the dominating faults, and is the focus of this thesis. ITSFs are usually challenging to detect and often do not become noticeable until the fault has propagated, and the motor is on the verge of being destroyed. This thesis investigates the possibility of detecting ITSFs in a PMSM, at an early stage when only one turn is shorted. The method is limited to finding the faults using ML algorithms. Both an experiential PMSM and a simulated model of the experimental PMSM, with the ability to induce an ITSF, were used to collect the data. Several Machine Learning (ML) models were developed, and then trained and tested with the collected data. The results show that four of the tested ML models, being: Random Forest, Gaussian SVM, KNN, and the CNN, all achieve an accuracy exceeding 95%, and that the fault can be found at an early stage in a PMSM with three coils connected in parallel in each phase. The results also show that the ML models are able to identify the ITSF when the simulated data is downsampled to the same frequency as the experimental data. We conclude that the ML models, provided in this study, can be used to detect an ITSF in a simulated PMSM, at an early stage when only one turn is shorted, and that there is great potential for them to detect ITSFs in a physical motor as well.

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<p dir="ltr">The absence or limited availability of operational statistics at general aviation airports restricts airport managers and operators from assessing comprehensive operational data. The traditional manual compilation of operational statistics is labor-intensive and lacks the depth and accuracy to depict a holistic picture of a general aviation airport’s operations. This research developed a reliable and efficient approach to address the problem by providing a comprehensive and versatile flight status identification framework. </p><p dir="ltr">Leveraging the BlueSky flight simulation module, the research can generate a synthetic flight database to emulate real-world general aviation aircraft’s flight scenarios. Two neural network architectures, namely, an RNN-GAN network and a refined Seq2Seq network, were explored to examine their capability to reconstruct flight trajectories. The Seq2Seq network, which demonstrated better performance, was further employed to estimate the simulated aircraft’s different metrics, such as internal mechanical metrics and flight phase. Additionally, this research undertook an array of diverse tailored evaluation techniques to assess the efficacy of flight status predictions and conducted comparative analyses between various configurations. </p><p dir="ltr">Furthermore, the research concluded by discussing the future development of the framework, emphasizing its potential for generalization across various flight data applications and scenarios. The enhanced methodology for collecting operational statistics and the analysis tool will enable airport managers and regulators to better receive a comprehensive view of the airport’s operations, facilitating airport planning and development.</p>

In today’s world, the applications of Unmanned Aerial Vehicle (UAV) systems are leaping by extending their scope from military applications on to commercial and medical sectors as well. Owing to this commercialization, the need to append external hardware with UAV systems becomes inevitable. This external hardware could aid in enabling wireless data transfer between the UAV system and remote Wireless Sensor Networks (WSN) using low powered architecture like Thread, BLE (Bluetooth Low Energy). The data is being transmitted from the flight controller to the ground control station using a MAVlink (Micro Air Vehicle Link) protocol. But this radio transmission method is not secure, which may lead to data leakage problems. The ideal aim of this research is to address the issues of integrating different hardware with the flight controller of the UAV system using a light-weight protocol called UAVCAN (Unmanned Aerial Vehicle Controller Area Network). This would result in reduced wiring and would harness the problem of integrating multiple systems to UAV. At the same time, data security is addressed by deploying an encryption chip into the UAV system to encrypt the data transfer using ECC (Elliptic curve cryptography) and transmitting it to cloud platforms instead of radio transmission.

Dans un contexte industriel aéronautique où les problématiques de sécurité constituent un facteur différentiateur clé, l’objectif de cette thèse est de répondre à la problématique ambitieuse de la réduction des accidents de type opérationnel. Les travaux de recherche s’inscrivent dans le domaine des systèmes d’alarmes pour l’évitement de collision qui ne font pas une analyse approfondie des solutions d’évitement par rapport à la situation de danger. En effet, les situations d’urgence en vol ne bénéficient pas à ce jour d’une représentation et d’un guide des solutions associées formels. Bien que certains systèmes d’assistance existent et qu’une partie de la connaissance associée aux situations d’urgence ait pu être identifiée, la génération dynamique d’une séquence de manœuvres sous fortes contraintes de temps et dans un environnement non connu à l’avance représente une voie d’exploration nouvelle. Afin de répondre à cette question et de rendre objective la notion de danger, les travaux de recherche présentés dans cette thèse mettent en confrontation la capacité d’évolution d’un aéronef dans son environnement immédiat avec une enveloppe physique devenant contraignante. Afin de mesurer ce danger, les travaux de recherche ont conduit à construire un module de trajectoires capable d’explorer l’espace en 3D. Cela a permis de tirer des enseignements en terme de flexibilité des manœuvres d’évitement possibles à l’approche du sol. De plus l’elicitation des connaissances des pilotes et des experts d’Airbus Helicopters (ancien Eurocopter) mis en situation d’urgence dans le cas d’accidents reconstitués en simulation a conduit à un ensemble de paramètres pour l’utilisation de la méthode multicritère PROMETHEE II dans le processus de prise de décision relatif au choix de la meilleure trajectoire d’évitement et par conséquent à la génération d’alarmes anti-collision. / In the aeronautics industrial context, the issues related to the safety constitute a highly differentiating factor. This PhD thesis addresses the challenge of operational type accident reduction. The research works are positioned and considered within the context of existing alerting equipments for collision avoidance, who don’t report a thorough analysis of the avoidance manoeuvres with respect to a possible threat. Indeed, in-flight emergency situations are various and do not all have a formal representation of escape procedures to fall back on. Much of operational accident scenarios are related to human mistakes. Even if systems providing assistance already exist, the dynamic generation of a sequence of manoeuvres under high constraints in an unknown environment remain a news research axis, and a key development perspective. In order to address this problematic and make the notion of danger objective, the research works presented in this thesis confront the capabilities of evolution of an aircraft in its immediate environment with possible physical constraints. For that purpose, the study has conducted to generate a module for trajectory generation in the 3D space frame, capable of partitioning and exploring the space ahead and around the aircraft. This has allowed to draw conclusions in terms of flexibility of escape manoeuvres on approach to the terrain. Besides, the elicitation of the Airbus Helicopters (former Eurocopter) experts knowledge put in emergency situations, for reconstituted accident scenarios in simulation, have permitted to derive a certain number of criteria and rules for parametrising the multicriteria method PROMETHEE II in the process for the relative decision-making of the best avoidance trajectory solution. This has given clues for the generation of new alerting rules to prevent the collisions.

Dans une aviation où la sécurité des vols est au cœur des préoccupations des constructeurs, le contrôle de santé des structures est l'un des nouveaux pôles majeurs de recherche et développement engagé par la communauté aéronautique depuis ces dix dernières années. Un système SHM (structural Heath monitoring) intégré aux structures avioniques (tels que le sont déjà les systèmes de monitoring des moteurs) permettrait de : - rendre l’aviation plus sûre et éviterait certains des accidents aériens ; - réduire les coûts de maintenance ; - alléger, à terme, le poids total car cela permettrait de d’éviter les sur-renforcements structuraux actuels. Le travail développé durant cette thèse, dans le cadre d'un projet industriel, concerne le développement de solutions exploitant l'utilisation de nœuds piezoélectriques au sein de microsystèmes reconfigurables dédiés à la détection de défauts dans des éléments de structure d'avion. L'exploitation de données issues de la génération/capture d'ondes de Lamb ainsi que des techniques se basant sur l'étude de l'impédance électromécanique du capteur ont été développées et étudiées sur différents types de défauts identifiés tels que cracks, corrosion, délaminages etc... La méthode proposée repose sur la comparaison et l'évolution dans le temps de signatures de réseaux de capteurs utilisant l’effet piezoélectrique et placés sur des éléments choisis de structures avions. L'interface capteur-matériau a été spécialement étudiée afin de garantir le couplage le plus efficace possible. Les techniques de « monitoring » ainsi développées ont été testées sur des structures aéronautiques métalliques et des structures en matériaux composites simples/sandwichs extraites d’avions Airbus et ATR. Différentes solutions d’intégration de ces capteurs et nœuds ont été passées en revue et une démarche a été proposée, allant de l’architecture des effecteurs au conditionnement et à la transmission des signaux et informations d’intéret. Une nouvelle vision de l’électronique de détection de défauts, permettant de développer une instrumentation « universelle » de capteurs à travers une combinaison de circuits numériques/analogiques reconfigurables à entrées/sorties versatiles, a été implémentée et testée avec succès / Structural health monitoring (SHM) is certainly one of the key technologies required to provide the safety and the reliability of future aviation. Based on non-destructive testing, current on the ground periodical structural integrity inspections showed their limit as evidenced by the Columbia tragedy. For the time being, structural health monitoring technology has reached a good technology readiness level (TRL). However, the integration of these solutions into future aerospace vehicle will require advanced and innovative system architecture. Further, improved SHM techniques and alleged assessment algorithm will be necessary to ensure an embedded integration, as well as to fully exploit their sensing capability. For now, most of high critical embedded systems are based on federate architectures, where each calculator is dedicated to a specific function and to a unique kind of sensor. By consequence, the integration on the field of conventional SHM solutions is highly difficult due to the scale and the weight of the global electronics systems. Based on a fully reconfigurable micro-system, I propose in this thesis, a novel SHM approach that combines into a unique System on Chip: • Sensors instrumentation and interfacing using reconfigurable analog circuits• Signal management and conditioning using reconfigurable digital electronics • Heath diagnostic assessment algorithms using an embedded CPUBased on elastic guided waves and electromechanical impedance analysis, the presented solution is capable through piezoelectric sensors to detect different kinds of abnormal events such as impacts. Moreover, using advanced wavelet transform and signature comparison algorithms, the system is also capable to detect mechanical damages such as corrosion, cracks or delaminations ; no matter if the probed structure is in simple composite, honeycomb composite or metallic alloy. The feasibility was proven using multiples specimens directly extracted from Airbus and ATR airplanes. To cover large areas, the system is fully scalable and accepts a hardware upgrade through multiple communication ports and protocols. Moreover, the versatility of inputs/outputs interface allows the exploitation of multiple sensors in order to locate and triangulate flaws