La conception de lanceurs est un problème d’optimisation multidisciplinaire dont l’objectif est de trouverl’architecture du lanceur qui garantit une performance optimale tout en assurant un niveau de fiabilité requis.En vue de l’obtention de la solution optimale, les phases d’avant-projet sont cruciales pour le processus deconception et se caractérisent par la présence d’incertitudes dues aux phénomènes physiques impliqués etaux méconnaissances existantes sur les modèles employés. Cette thèse s’intéresse aux méthodes d’analyse et d’optimisation multidisciplinaire en présence d’incertitudes afin d’améliorer le processus de conception de lanceurs. Trois sujets complémentaires sont abordés. Tout d’abord, deux nouvelles formulations du problème de conception ont été proposées afin d’améliorer la prise en compte des interactions disciplinaires. Ensuite, deux nouvelles méthodes d’analyse de fiabilité, permettant de tenir compte d’incertitudes de natures variées, ont été proposées, impliquant des techniques d’échantillonnage préférentiel et des modèles de substitution. Enfin, une nouvelle technique de gestion des contraintes pour l’algorithme d’optimisation ”Covariance Matrix Adaptation - Evolutionary Strategy” a été développée, visant à assurer la faisabilité de la solution optimale. Les approches développées ont été comparées aux techniques proposées dans la littérature sur des cas tests d’analyse et de conception de lanceurs. Les résultats montrent que les approches proposées permettent d’améliorer l’efficacité du processus d’optimisation et la fiabilité de la solution obtenue. / Launch vehicle design is a Multidisciplinary Design Optimization problem whose objective is to find the launch vehicle architecture providing the optimal performance while ensuring the required reliability. In order to obtain an optimal solution, the early design phases are essential for the design process and are characterized by the presence of uncertainty due to the involved physical phenomena and the lack of knowledge on the used models. This thesis is focused on methodologies for multidisciplinary analysis and optimization under uncertainty for launch vehicle design. Three complementary topics are tackled. First, two new formulations have been developed in order to ensure adequate interdisciplinary coupling handling. Then, two new reliability techniques have been proposed in order to take into account the various natures of uncertainty, involving surrogate models and efficient sampling methods. Eventually, a new approach of constraint handling for optimization algorithm ”Covariance Matrix Adaptation - Evolutionary Strategy” has been developed to ensure the feasibility of the optimal solution. All the proposed methods have been compared to existing techniques in literature on analysis and design test cases of launch vehicles. The results illustrate that the proposed approaches allow the improvement of the efficiency of the design process and of the reliability of the found solution.

Un système de lancement aéroporté est constitué d'un porteur de type avion larguant un lanceur à une certaine altitude. De tels systèmes sont l'objet d'un intérêt croissant, notamment pour la mise à poste de petits satellites. Les travaux présentés dans cette thèse s'intègrent dans le programme Perseus du CNES qui a déjà donné lieu à la construction d'un modèle réduit appelé EOLE. Il s'agit d'étudier la phase de largage, particulièrement sensible.Les contraintes de similitude pouvant permettre l'étude du largage taille réelle avec EOLE sont d'abord identifiées. Les possibilités d'extrapolation directe et déterministe des mesures réalisées avec EOLE étant limitées par le non respect d'une contrainte de masse, il est choisi d'étudier le largage avec une approche probabiliste en développant un nouveau modèle multi-corps. Une grande variété d'incertitudes est prise en compte, concernant par exemple aussi bien les interactions aérodynamiques que le mécanisme de séparation. Un nouveau critère de performance générique,basé sur des géométries élémentaires, est développé pour évaluer la fiabilité du largage.L'analyse de sensibilité du largage aux facteurs d'incertitude est ensuite réalisée. Compte tenu du nombre élevé de paramètres en jeu et du temps de simulation, il est d'abord recherché une simplification du modèle. La méthode de Morris est utilisée pour identifier des facteurs d'incertitude peu influents pouvant être fixés à une certaine valeur. Cette étape est fréquente, mais il est montré qu'il existe un risque important de fixer des facteurs dont l'influence a en fait été sous-estimée. Une adaptation de la méthode de Morris améliorant l'échantillonnage des facteurs, le calcul de leurs influences et le traitement statistique des résultats permet de réduire considérablement ce risque.Une fois l'impact des différentes incertitudes estimé, il a été possible d'optimiser les conditions de largage afin de réduire la probabilité qu'un problème intervienne. / In an air launch to orbit, a space rocket is launched from a carrier aircraft. Air launchto orbit appears as particularly interesting for small satellites. This Ph.D. thesis is part of the program Pegasus of the French space agency CNES and it follows the development of a small scale demonstrator called EOLE. It focuses on the very sensitive separation phase.The similitude constraints which have to be respected to study the large scale system with EOLEare first identified. A problem of mass limits the possibilities to directly extrapolate at a larger scale, in a deterministic approach, data obtained with EOLE. It is decided to study the separation in a probabilistic approach by developing a new multi-body model. A great variety of uncertainties are taken into account, from the aerodynamic interactions to the atmospheric turbulences, the separation mechanism, and the launch trajectories. A new performance criterion is developed to quantify the safety of the separation phase. It is based on elementary geometries and it could beused in other contexts.A sensitivity analysis is applied to estimate the influence of the uncertainties on the performance criterion. Given the large number of factors of uncertainty and the non-negligible simulation time,the model is first simplified. The Morris method is applied to identify the factors with a low influence which can be fixed to a given value. It is a frequent step, but it is shown that there isa high risk to fix the wrong factors. Any further study would then be altered. The risk to fix the wrong factors is significantly reduced by improving the factors sampling, the calculation of their influence, and the statistical treatment of the results. This new method is used to estimate the influence of the uncertainties at the separation and the safety is improved by optimizing launch trajectories.

The main objective of this thesis is to introduce the reader to the problematics of air-launch and to a custom design solution applying this concept. The specifics of this method of bringing a payload into orbit are described and explained. Overview of projects which use aircraft to launch spacecraft is included. Determination of primary parameters of a launch vehicle designed to carry a payload of a specified mass is conducted. The required flight performance has been estimated, a computational model has been developed in software MATLAB, and a multidisciplinary optimization of the design parameters has been performed using a genetic algorithm optimization method. Parameters of the designed air-launched rocket are compared with those of a ground-launched rocket. According to the specific criteria, the Airbus A310-300 aircraft was selected as the most suitable transport aircraft to be used for launching the designed launch vehicle. The last part of the thesis is devoted to the proposal of necessary modifications and estimation of the flight performance.

The diploma thesis deals with a new product launch in Czech market. First, the appropriate market segment, competitive products and environment of launching company is analyzed. Based on the analysis and the knowledge gained from the literature, the diploma thesis proposes a solution in form of a marketing mix, which is suitable for the new product.

Tato diplomová práce je zaměřena na vývoj marketingové strategie pro zavedení produktů na vysoce konkurečním trhu zdravotnických prostředků. Konkrétně se zaměřuje na zavedení ablačního katetru a mapovacího zařízení pro léčbu srdečních chorob, které vyrábí americká společnost St. Jude Medical. Práce popisuje zavedení na trh, aby bylo možné najít kritické body a optimalizovat celý tento proces.

Master’s thesis deals with aerodynamic heating of launch vehicle during ascent phase by using CFD simulation. Ascent trajectory and payload fairing geometry is design using data of existing small launch vehicles. Critical flight regimes are identified using 2D calculations, and in these regimes analysis is performed by axially symmetric simulations. Simulation results are compared to values obtained from theoretical and semi-empirical calculations.

Purpose: The purpose of the thesis is to study a process within Systembolaget AB that affects a selected part of the assortment model. The assortment is defined as TSE, which stands for tillfälligt sortiment exklusivt, that can be described as temporary assortment exclusively. According to Systembolaget the process currently lacks clarity with associated deviations in launch plans of TSE items to stores. The purpose is to improve visibility to counteract deviations in the process. Method: The report's data collection consists of semi-structured interview studies, literature studies and document review. Analysis of data has been accomplished by a fishbone diagram. Theory: The theoretical framework is made up of the kano model, Porter's five forces and ISO 9000. Results: The TSE process is necessary for Systembolaget's attractiveness as an alcohol monopoly. The range contributes to a width of offers for the customer and satisfies customers who demand more alcoholic drinks than what is available in the fixed range. TSE is mostly a stated need that has one-dimensional attributes that increase customer satisfaction and fulfillment rates. The fishbone diagram has excavated underlying root causes and identified method and measurement as the most serious in affecting quality deficiencies. Systembolaget's power structures in the microenvironment are significantly dependent on the suppliers' ability to act. Currently, the TSE process lacks a quality and management system, with the consequence that a vision, business concept and definition of quality are missing. Likewise, there is no measurement system for measuring the performance of the process in the form of deviations from launch plans. There are still challenges with the lack of internal software systems that impair the transparency of the process. Conclusion: The report suggests that the organization examines the suitability of implementing a quality and management system, measurement system, system support and vision and business idea. / Syfte: Rapportens syfte är att studera en process inom Systembolaget AB som berör en utvald del inom sortimentsmodellen. Sortimentet betecknas TSE som står för tillfälligt sortiment exklusivt. Processen i dagsläget brister i överskådlighet med tillhörande avvikelser i lanseringsplaner av TSE-artiklar till butiker. Syftet är att förbättra överskådligheten i TSE-processen för att motverka avvikelser lanseringsplanerna.   Metod: Rapportens datainsamling består av semistrukturerade intervjustudier, litteraturstudier och dokumentgranskning. Dataanalysen har gjorts med hjälp av fiskbensdiagram. Teori: Det teoretiska ramverket är uppbyggt av kanomodellen, Porter´s five forces och ISO 9000. Resultat: TSE-processen är nödvändig för Systembolagets attraktivitet som alkoholmonopol, då sortimentet bidrar till en bredd i erbjudande för kunden och tillfredsställer kunder som efterfrågar fler alkoholdrycker än det som finns i fasta sortimentet. TSE är till största del ett uttalat behov som har endimensionella attribut som höjer kundtillfredsställelsen och uppfyllelsegraden. Fiksbensdiagrammet har urholkat bakomliggande rotorsaker och identifierat metod och mätning som störst allvarlighet i påverkan av kvalitetsbrister. Systembolagets maktstrukturer i mikromiljön är signifikant beroende av leverantörernas handlingskraft. I dagsläget saknar TSE-processen ett kvalitets- och ledningssystem med efterföljd att vision, verksamhetsidé och definition av kvalitet saknas. Likaså saknas mätsystem för mätning av processens prestanda i form av avvikelser av lanseringsplaner. Fortsättningsvis finns utmaningar med avsaknad av interna stödsystem som försämrar överskådligheten av processen. Slutsats: Rapporten föreslår att organisationen undersöker lämplighet av att implementera ett kvalitets- och ledningssystem, mätsystem, systemstöd och vision samt verksamhetsidé.

In the present thesis, the objective was to find the maximum amount of payload mass that can be put into a 500 km polar orbit by a 1400 kg air-launched multi-stage rocket launched from a fighter jet platform. To fulfill the objective an algorithm incorporating several modules was developed. The modules performed calculations based on theoretical models and literature values to arrive at optimal design variables. From the design the maximum payload mass was able to be derived and it was concluded that a three-stage launch vehicle was able to deliver a 22.0 kg payload to the desired orbit. / I den här avhandlingen var syftet att hitta den maximala mängden nyttolastmassa som kan transporteras av en 1400 kg flerstegsraket uppskjuten från luften till en 500 km polär bana. För att uppfylla målet utvecklades en algoritm med flera moduler. Modulerna utförde beräkningar baserade på teoretiska modeller och litteraturvärden för att komma fram till optimala designvariabler. Från konstruktionen kunde den maximala nyttolastmassan härledas och det konstaterades att en trestegsraket kunde leverera en nyttolast på 22.0 kg till den önskade omloppsbanan.

In the present thesis, the objective was to find the maximum amount of payload mass that can be put into a 500 km polar orbit by a 1400 kg air-launched multi-stage rocket launched from a fighter jet platform. To fulfill the objective an algorithm incorporating several modules was developed. The modules performed calculations based on theoretical models and literature values to arrive at optimal design variables. From the design the maximum payload mass was able to be derived and it was concluded that a three-stage launch vehicle was able to deliver a 22.0 kg payload to the desired orbit. / I den här avhandlingen var syftet att hitta den maximala mängden nyttolastmassa som kan transporteras av en 1400 kg flerstegsraket uppskjuten från luften till en 500 km polär bana. För att uppfylla målet utvecklades en algoritm med flera moduler. Modulerna utförde beräkningar baserade på teoretiska modeller och litteraturvärden för att komma fram till optimala designvariabler. Från konstruktionen kunde den maximala nyttolastmassan härledas och det konstaterades att en trestegsraket kunde leverera en nyttolast på 22.0 kg till den önskade omloppsbanan.

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