Tesis sobre el tema "Multidisciplinary Design Optimisation"
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Yin, Xuefei. "Application of multidisciplinary design optimisation to engine calibration optimisation". Thesis, University of Bradford, 2012. http://hdl.handle.net/10454/5630.
Texto completoSmith, David D. "Multidisciplinary design optimisation of morphing nonplanar wing systems". Thesis, University of Bristol, 2014. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.681343.
Texto completoDababneh, Odeh. "Multidisciplinary design optimisation for aircraft wing mass estimation". Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/10172.
Texto completoPant, Sanjay. "Multidisciplinary and multiobjective design optimisation of coronary stents". Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/349008/.
Texto completoKianifar, Mohammed R. "Application of multidisciplinary design optimisation frameworks for engine mapping and calibration". Thesis, University of Bradford, 2014. http://hdl.handle.net/10454/14843.
Texto completoKingsley, Thomas Charles. "Multidisciplinary design and optimisation of liquid containers for sloshing and impact". Diss., Pretoria : [s.n.], 2005. http://upetd.up.ac.za/thesis/available/etd-01242006-100142.
Texto completoOllar, Jonathan. "A multidisciplinary design optimisation framework for structural problems with disparate variable dependence". Thesis, Queen Mary, University of London, 2017. http://qmro.qmul.ac.uk/xmlui/handle/123456789/24715.
Texto completoWhellens, Matthew W. "Multidisciplinary optimisation of aero-engines using genetic algorithms and preliminary design tools". Thesis, Cranfield University, 2003. http://dspace.lib.cranfield.ac.uk/handle/1826/10510.
Texto completoThauvin, Jérôme. "Exploring the design space for a hybrid-electric regional aircraft with multidisciplinary design optimisation methods". Phd thesis, Toulouse, INPT, 2018. http://oatao.univ-toulouse.fr/23607/1/Thauvin_jerome.pdf.
Texto completoLapuh, Rok. "Mesh Morphing Technique used with Open-Source CFD Toolbox in Multidisciplinary Design Optimisation". Thesis, Uppsala universitet, Institutionen för informationsteknologi, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-348873.
Texto completoGonzalez, Luis F. "Robust evolutionary methods for multi-objective and multdisciplinary design optimisation in aeronautics". Phd thesis, School of Aerospace, Mechanical and Mechatronic Engineering, 2005. http://hdl.handle.net/2123/6296.
Texto completoBalesdent, Mathieu. "Optimisation multidisciplinaire de lanceurs". Phd thesis, Ecole centrale de Nantes, 2011. http://tel.archives-ouvertes.fr/tel-00659362.
Texto completoDamp, Lloyd Hollis. "Multi-Objective and Multidisciplinary Design Optimisation of Unmanned Aerial Vehicle Systems using Hierarchical Asynchronous Parallel Multi-Objective Evolutionary Algorithms". Thesis, The University of Sydney, 2007. http://hdl.handle.net/2123/1858.
Texto completoDamp, Lloyd Hollis. "Multi-Objective and Multidisciplinary Design Optimisation of Unmanned Aerial Vehicle Systems using Hierarchical Asynchronous Parallel Multi-Objective Evolutionary Algorithms". University of Sydney, 2007. http://hdl.handle.net/2123/1858.
Texto completoThe overall objective of this research was to realise the practical application of Hierarchical Asynchronous Parallel Evolutionary Algorithms for Multi-objective and Multidisciplinary Design Optimisation (MDO) of UAV Systems using high fidelity analysis tools. The research looked at the assumed aerodynamics and structures of two production UAV wings and attempted to optimise these wings in isolation to the rest of the vehicle. The project was sponsored by the Asian Office of the Air Force Office of Scientific Research under contract number AOARD-044078. The two vehicles wings which were optimised were based upon assumptions made on the Northrop Grumman Global Hawk (GH), a High Altitude Long Endurance (HALE) vehicle, and the General Atomics Altair (Altair), Medium Altitude Long Endurance (MALE) vehicle. The optimisations for both vehicles were performed at cruise altitude with MTOW minus 5% fuel and a 2.5g load case. The GH was assumed to use NASA LRN 1015 aerofoil at the root, crank and tip locations with five spars and ten ribs. The Altair was assumed to use the NACA4415 aerofoil at all three locations with two internal spars and ten ribs. Both models used a parabolic variation of spar, rib and wing skin thickness as a function of span, and in the case of the wing skin thickness, also chord. The work was carried out by integrating the current University of Sydney designed Evolutionary Optimiser (HAPMOEA) with Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) tools. The variable values computed by HAPMOEA were subjected to structural and aerodynamic analysis. The aerodynamic analysis computed the pressure loads using a Boeing developed Morino class panel method code named PANAIR. These aerodynamic results were coupled to a FEA code, MSC.Nastran® and the strain and displacement of the wings computed. The fitness of each wing was computed from the outputs of each program. In total, 48 design variables were defined to describe both the structural and aerodynamic properties of the wings subject to several constraints. These variables allowed for the alteration of the three aerofoil sections describing the root, crank and tip sections. They also described the internal structure of the wings allowing for variable flexibility within the wing box structure. These design variables were manipulated by the optimiser such that two fitness functions were minimised. The fitness functions were the overall mass of the simulated wing box structure and the inverse of the lift to drag ratio. Furthermore, six penalty functions were added to further penalise genetically inferior wings and force the optimiser to not pass on their genetic material. The results indicate that given the initial assumptions made on all the aerodynamic and structural properties of the HALE and MALE wings, a reduction in mass and drag is possible through the use of the HAPMOEA code. The code was terminated after 300 evaluations of each hierarchical level due to plateau effects. These evolutionary optimisation results could be further refined through a gradient based optimiser if required. Even though a reduced number of evaluations were performed, weight and drag reductions of between 10 and 20 percent were easy to achieve and indicate that the wings of both vehicles can be optimised.
Baudoui, Vincent. "Optimisation robuste multiobjectifs par modèles de substitution". Phd thesis, Toulouse, ISAE, 2012. http://tel.archives-ouvertes.fr/tel-00742023.
Texto completoBrevault, Loïc. "Contributions à l'optimisation multidisciplinaire sous incertitude, application à la conception de lanceurs". Thesis, Saint-Etienne, EMSE, 2015. http://www.theses.fr/2015EMSE0792/document.
Texto completoLaunch 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
Achard, Timothée. "Techniques de calcul de gradient aéro-structure haute-fidélité pour l'optimisation de voilures flexibles". Thesis, Paris, CNAM, 2017. http://www.theses.fr/2017CNAM1140/document.
Texto completoTo improve the structural design of flexible wings, gradient based Multidisciplinary Design Optimization (MDO) techniques are effective and widely used. However, gradients calculation is not trivial and can be costly when high-fidelity models are considered. Our objective is to study different suitable approaches to compute gradients of aeroelastic loads with respect to structural design parameters.To this end, two high-fidelity aero-structure gradient computation techniques for strongly coupled aeroelastic systems are proposed. The most intrusive technique includes the well-established direct and adjoint formulations that require substantial implementation effort. In contrast, we propose an alternative uncoupled non-intrusive approach easier to implement and yet capable of providing accurate gradients approximations. Both techniques have been implemented in the Onera elsA CFD software.Accuracy, efficiency and applicability of these methods are demonstrated on the civil transport aircraft Common Research Model (CRM) test-case. More specifically, an inverse design problem is set up with the objective of matching an in-flight target twist law distribution. These two methods prove to be comparable in terms of accuracy and cost. Thus they offer additional operational flexibility depending on the level of integration sought in the MDO process
Moussouni, Fouzia. "Méthodologie et algorithmes adaptés à l’optimisation multi-niveaux et multi-objectif de systèmes complexes". Thesis, Ecole centrale de Lille, 2009. http://www.theses.fr/2009ECLI0016/document.
Texto completoThe design of an electrical system is a very complex task which needs experts from various fields of competence. In a competitive environment, where technological advance is a key factor, industry seeks to reduce study time and to make solutions reliable by way of a rigorous methodology providing a systemic solution.Then, it is necessary to build models and to develop optimization methods which are suitable with these concerns. Indeed, the optimization of sub-systems without taking into account the interaction does not allow to achieve an optimal system. More complex the system is more the work is difficult and the development time is important because it is difficult for the designer to understand and deal with the system in its complexity. Therefore, it is necessary to integrate the design components in a systemic and holistic approach to take into account, in the same time, the characteristics of a component and its relationship with the system it belongs to.Analytical Target Cascading is a multi-level optimization method for handling complex systems. This hierarchical approach consists on the breaking-down of a complex system into sub-systems, and component where their optimal design is ensured by way of classical optimization algorithms. The optimal solution of the system must be composed of the component's solutions. Then a coordination strategy is needed to ensure consistency of all sub-systems. First, the studied and proposed optimization algorithms are tested and compared on the optimization of electrical components. The second part focuses on the multi-level optimization of complex systems. The optimization of railway traction system is taken as a test case
Mcharek, Mehdi. "Gestion des connaissances pour la conception collaborative et l’optimisation multi-physique de systèmes mécatroniques". Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLC098/document.
Texto completoMechatronic products are complex and multidisciplinary in nature. The requirements to design them are often contradictory and must be validated by the various disciplinary engineering (DE) teams. To address this complexity and reduce design time, disciplinary engineers need to collaborate dynamically, resolve interdisciplinary conflicts, and reuse knowledge from previous projects. In addition, they need to work seamlessly with the Systems Engineering (SE) team to have direct access to requirements and the Multidisciplinary Design Optimization (MDO) team for global validation. We propose to use Knowledge Management techniques to structure the knowledge generated during collaboration activities and harmonize the overall design cycle. Our primary contribution is a unification approach, elaborating how SE, DE, and MDO complement each-other and can be used in synergy for an integrated and continuous design cycle. Our methodology centralizes the product knowledge necessary for collaboration. It ensures traceability of the exchange between disciplinary engineers using graph theory. This formalized process knowledge facilitates MDO problem definition
Tremolet, Arnault. "Modèles et méthodes numériques les études conceptuelles d'aéronefs à voilure tournante". Phd thesis, Aix-Marseille Université, 2013. http://tel.archives-ouvertes.fr/tel-00952559.
Texto completoAmmar, Karim. "Conception multi-physique et multi-objectif des cœurs de RNR-Na hétérogènes : développement d’une méthode d’optimisation sous incertitudes". Thesis, Paris 11, 2014. http://www.theses.fr/2014PA112390/document.
Texto completoSince Phenix shutting down in 2010, CEA does not have Sodium Fast Reactor (SFR) in operating condition. According to global energetic challenge and fast reactor abilities, CEA launched a program of industrial demonstrator called ASTRID (Advanced Sodium Technological Reactor for Industrial Demonstration), a reactor with electric power capacity equal to 600MW. Objective of the prototype is, in first to be a response to environmental constraints, in second demonstrates the industrial viability of:• SFR reactor. The goal is to have a safety level at least equal to 3rd generation reactors. ASTRID design integrates Fukushima feedback;• Waste reprocessing (with minor actinide transmutation) and it linked industry.Installation safety is the priority. In all cases, no radionuclide should be released into environment. To achieve this objective, it is imperative to predict the impact of uncertainty sources on reactor behaviour. In this context, this thesis aims to develop new optimization methods for SFR cores. The goal is to improve the robustness and reliability of reactors in response to existing uncertainties. We will use ASTRID core as reference to estimate interest of new methods and tools developed.The impact of multi-Physics uncertainties in the calculation of the core performance and the use of optimization methods introduce new problems:• How to optimize “complex” cores (i.e. associated with design spaces of high dimensions with more than 20 variable parameters), taking into account the uncertainties?• What is uncertainties behaviour for optimization core compare to reference core?• Taking into account uncertainties, optimization core are they still competitive? Optimizations improvements are higher than uncertainty margins?The thesis helps to develop and implement methods necessary to take into account uncertainties in the new generation of simulation tools. Statistical methods to ensure consistency of complex multi-Physics simulation results are also detailed.By providing first images of innovative SFR core, this thesis presents methods and tools to reduce the uncertainties on some performance while optimizing them. These gains are achieved through the use of multi-Objective optimization algorithms. These methods provide all possible compromise between the different optimization criteria, such as the balance between economic performance and safety
Tonnelier, Gilles. "Contribution à la conception et à l'optimisation multi-physique de batterie mécaniques pour les applications mobiles". Thesis, Besançon, 2011. http://www.theses.fr/2011BESA2048.
Texto completoTo improve its tram offer, ALSTOM Transport has decided to develop a mechanical batterythat provides energy of a vehicle between two stations. But even if the flywheels are essentiallydevelopped since the 1950s for mobile applications, none of them is designed to ensure 100%of energy for mobile applications. The battery must be light, weigh as little as possible, besafe and respect the specifications.Following a bibliographic data analysis, we undertook to develop a method of pre-sizingmechanical battery by taking into account interactions between different major organs, whereaspreviously, methods were concentrated on developing mechanical batteries part by part.For this, we developed an integrated design tool that takes into account the energy (energyand power), mechanic (strength of materials, rotor dynamics), electromagnetic (electric motor)and geometric (template integration, creation of volumes). We also develop a method forselecting the right materials for flywheels, from which we have compiled a list of relevantmaterials.We have shown that the integrated design is more efficient in terms of integration andbalance between the mechanical and electromagnetic.We also showed that composite materialsare not necessarily the best design choices and materials such as high performance steels areexcellent candidates according to the study area of interest (the threshold being the criticalrotational speed 30000 rpm). We have shown that it is possible to achieve stable areas ofoperation, although it will probably be inevitable to pass critical speeds at startup. The designmethod we developed ensures that the only modes excited are the dynamic modes of bearings,which can be treaten quite easily. It can also represent the system configuration, make a staticstress analysis, study the dynamic phenomena of a mechanical battery, and finally, this methodallows an overall system optimization by the Kohonen method.The results are significant because the systematic method we developed can be applied toevery cases. It helps to know what materials to choose, the configuration you want, presentsgraphically the results of behavioral systems studied and brings a knowledge of the systemunder development. This allows us to anticipate potential changes in design. It is therefore atool for understanding and making during the design process.The scientific path that we have taken is the one advocated by Professor Giancarlo Genta,Italian specialist in the field, at the end of his own studies. This evolutionary approach hasled to increased knowledge of batteries and better mechanical design.Keywords
Gonzalez, Gallego Oscar. "Dimensionnement et contrôlabilité de configurations avion innovantes". Toulouse 3, 2013. http://www.theses.fr/2013TOU30340.
Texto completoThe current aircraft design process focuses on Performance optimization (minimize the airframe drag, reduce noise levels, maximize Range, reduce pollutant emissions, etc. ) and treats all other disciplines sequentially and as design constraints. Among the constraint disciplines, Stability & Control is the most important one, although not always recognized as such. Indeed, in addition to being responsible for equipping the airframe with stabilizers and controls that ensure the proper handling of the vehicle, Stability & Control is strongly tied to Performance, safety, and aircraft certification aspects. In the earliest aircraft design stage (Conceptual Design phase), the Stability & Control discipline is only partially considered and consists of little more than statistical relationships (volume coefficients) and static analyses (Scissors Plot). It is not until later in the aircraft development process (Detailed Design phase and flight tests), that the Stability & Control discipline plays a dominant role and where the airplane design choices made at the conceptual level are validated or not. Although this traditional design procedure proved to be "successful" when sizing the stabilizers and controls of typical airplanes (wing + tubular fuselage + rear empennage), it fails when the aircraft layout under study deviates from the conventional one. Furthermore, the wide discrepancy between the rather sophisticated manner in which the Stability & Control discipline is considered in the Detailed Design phase, compared to the relatively simple approach used during the Conceptual Design level, results in "sub-optimal" airplane designs with stability and/or deficiencies that not only are expensive to fix, but can also be detrimental to the vehicle performance characteristics and jeopardize its safety. This research work introduces a generic, alternative, and fast aircraft conceptual design methodology capable of sizing and optimizing any aircraft configuration by giving further importance to the Stability & Control discipline. In this methodology, the sequential character of the current conceptual design process is replaced with a simultaneous and integrated Multi-Disciplinary Optimization (MDO) approach in which the discipline of Stability & Control, in particular, is considered at the same level as Performance. The proposed design procedure aims at deriving the airplane outer shape satisfying, among others, a set of generic (i. E. Independent of the aircraft configuration) stability and control requirements, while possessing the best operational performance throughout a typical mission profile. Compared to the traditional aircraft design methodology, the derived optimization problem is much more constrained from the Stability & Control perspective and considers not only static requirements, but also dynamic and maneuver criteria. The methodology resembles an "inverse" (or "reverse engineering") design process since the desired stability and control features of the airplane are imposed in advance as constraints of the optimization problem. The conceptual designer therefore seeks to determine the aircraft shape having specific handling characteristics. Integrating the Stability & Control discipline at conceptual level requires a modular and integrated tool, capable of performing MDO, that is not yet available within the civilian aviation industry. To counter this, a "simple" tool was created for partially mimicking the environment required. The methodology is illustrated with two different aircraft configurations of similar size. Although the work presented herein represents only a small fraction of the whole research challenge, the methodology is demonstrated to be viable and it is shown that further performance benefits can be extracted if the stability and control constraints are taken into account from the early design stages. This approach also enables to compare different aircraft configurations from a physical and rational basis and not on subjective and disparate opinions, as is currently the case
Kianifar, Mohammed R., I. Felician Campean y D. Richardson. "Evaluation of camshaft control strategies for a GCI engine using a multidisciplinary optimisation framework". 2014. http://hdl.handle.net/10454/10715.
Texto completoThis paper presents a calibration optimization study for a Gasoline Direct Injection engine based on a multidisciplinary design optimization (MDO) framework. The paper presents the experimental framework used for the GDI engine mapping, followed by an analysis of the calibration optimization problem. The merits of the MDO approach to calibration optimization are discussed in comparison with a conventional two-stage approach based on local trade-off optimization analysis, focused on a representative emissions drive cycle (NEDC) and limited part load engine operation. The benefits from using the MDO optimisation framework are further illustrated with a study of relative effectiveness of different camshaft timing control strategies (twin independent Versus fixed timing, exhaust only, inlet only and fixed overlap / dual equal) for the reference GDI engine based on the part load test data. The main conclusion is that the MDO structure offers an effective framework for the GDI steady state calibration optimization analysis.
Kianifar, Mohammed R. y I. Felician Campean. "Application of analytical target cascading for engine calibration optimization problem". 2014. http://hdl.handle.net/10454/10916.
Texto completoThis paper presents the development of an Analytical Target Cascading (ATC) Multidisciplinary Design Optimization (MDO) framework for a steady-state engine calibration optimization problem. The implementation novelty of this research is the use of the ATC framework to formulate the complex multi-objective engine calibration problem, delivering a considerable enhancement compared to the conventional 2-stage calibration optimization approach [1]. A case study of a steady-state calibration optimization of a Gasoline Direct Injection (GDI) engine was used for the calibration problem analysis as ATC. The case study results provided useful insight on the efficiency of the ATC approach in delivering superior calibration solutions, in terms of “global” system level objectives (e.g. improved fuel economy and reduced particulate emissions), while meeting “local” subsystem level requirements (such as combustion stability and exhaust gas temperature constraints). The ATC structure facilitated the articulation of engineering preference for smooth calibration maps via the ATC linking variables, with the potential to deliver important time saving for the overall calibration development process.