DC Field | Value | Language |
---|---|---|
dc.contributor.advisor | Della Vecchia, Pierluigi | - |
dc.contributor.author | Mandorino, Massimo | - |
dc.date.accessioned | 2025-07-08T07:30:28Z | - |
dc.date.available | 2025-07-08T07:30:28Z | - |
dc.date.issued | 2024 | - |
dc.identifier.uri | https://hdl.handle.net/20.500.12738/17830 | - |
dc.description.abstract | The aviation industry is currently encountering unprecedented challenges, including the critical need to achieve climate neutrality and meet the growing demand for improved performance. The Flightpath 2050 initiative, led by the Advisory Council for Aeronautical Research in Europe, sets out ambitious objectives for reducing emissions and cutting costs in air travel. In this rapidly evolving landscape, aircraft manufacturers must transition to innovative aeronautical concepts. In pursuit of the ambition to minimize the environmental impact of the aviation industry, the EU Commission, in collaboration with industry partners, launched the Clean Sky 2 program. This program explores innovative concepts aimed at improving aircraft fuel efficiency and reducing air and noise emissions in comparison to current state-of-the-art solutions. Within the scope of this program, which emphasizes the exploration of advanced engines and aircraft configurations, the development of the Advanced Rear End demonstrator is currently in progress. This prototype combines a comprehensive array of interconnected aircraft rear-end and empennage components, taking advantage of the introduction of innovative configurations and technologies. Researchers have indeed recognized the potential benefits of these components in reducing weight and improving production rates for next-generation medium-sized passenger aircraft. The introduction of these novel and disruptive technologies significantly increases the complexity of aeronautical systems, requiring a larger number of designers and generating vast amounts of data and information. Several disciplines and aspects beyond conventional design must be considered to address the complexity of such a system. This factor can lead to a situation in which any change can have significant implications for the entire process. Early aircraft design encounters challenges in exploring a high-dimensional design space, assessing innovative concepts, and handling continuous variations in requirements. In response to these challenges, there is a growing interest in Model-Based Systems Engineering, which is considered a crucial step in addressing the complexity and challenges in early aircraft development. It offers benefits such as enhanced consistency, transparency, and collaboration across diverse disciplines. In addition, the aerospace industry has widely recognized the potential of Multidisciplinary Design and Optimization, which offers a novel approach to addressing challenges such as disruptive configuration design by seamlessly integrating and optimizing multiple disciplines or subsystems. The efficiency and effectiveness of aircraft conceptual design can be improved by using a synergistic approach that involves the seamless integration of Model-Based Systems Engineering and Multidisciplinary Design Analysis and Optimization methods. Their integration offers a synergistic solution for efficiently addressing the complexity of conceptual design, combining the benefits of both methodologies. Based on these observations, the work described in this thesis addresses the following research question: How can model-based systems engineering methodologies be effectively utilized to develop multidisciplinary analysis and optimization workflows for designing an innovative rear-end for large passenger commercial jet aircraft? To facilitate the development of new solutions, such as innovative rear-end fuselage and tailplane configurations, including a forward-swept tailplane equipped with leading-edge extension and integrated into a bottle-neck-shaped fuselage, aircraft designers should have access to a specialized environment. The development of these complex systems involves multidisciplinary processes, imposing requirements on system components, technologies, and interactions. The interconnected data encompasses diverse aspects of product development. A dedicated environment should facilitate easy and prompt execution of optimizations and trade-off studies across all necessary disciplines, even at conceptual and preliminary design stages. Furthermore, the system must gather all relevant information that impacts the final solution within a model-based framework and automatically generate a structure based on this data. This approach would offer aircraft designers the ability to trace all data that influences the steps in the system development process from the early design stages. Furthermore, it would provide a flexible framework capable of adapting to specific requirements and illustrating the impact of each individual model component. However, the existing literature lacks evidence of studies utilizing the integrated application of MBSE and MDAO methodologies for designing unconventional aircraft configurations. Specifically, there is an absence of this kind of analysis focusing on forward-swept horizontal tailplanes. Furthermore, the assessment of this innovative technology in aeronautics fails to encompass various disciplines, such as aerodynamics, structure, and ice formation, as well as considerations related to aeronautical design, regulation, and certification. The primary goal of this thesis is to develop a framework with these features to support the design of advanced rear-end configurations. The proposed methodology facilitates the development of the rear-end of a large passenger commercial jet aircraft, incorporating features such as a negative-sweep horizontal tail, a leading-edge extension, and a bottleneck-shaped fuselage. The proposed solutions are obtained through a Multidisciplinary Design and Optimization approach which is emerged from analyses conducted using Model-Based Systems Engineering technologies. This analysis outlines all stakeholder needs and translates them into requirements that serve as the foundation for modeling the system under examination. Multiple workflows are subsequently created to develop the system, leading to a solution designed to meet all identified requirements. The entire process is capable of encompassing various aspects that extend beyond design considerations, integrating disciplines at a high level of fidelity, such as aeroelasticity and in-flight ice formation. The framework’s adaptability to the selected requirements and its flexibility in addressing various types of optimization problems are demonstrated through the generation of four different optimization problems. Optimizations are conducted with reference to geometric macro-parameters, taking into account multiple flight conditions. The proposed framework efficiently employs modeling techniques to enhance agility in defining complex systems, integrating various automated processes to streamline development. Key benefits include improved coherence among data, enhanced traceability through a model-based approach, and comprehensive stakeholder needs addressing. Time and efficiency in development are optimized through a shift to model-based approaches, with seamless integration of Systems Engineering activities. Significant time savings are achieved in problem formulation and resolution, aided by surrogate models and advanced optimization algorithms. The results suggest innovative tailplane configurations that offer improved aerodynamics, reduced weight, and flexible characteristics. The study reveals a 4% reduction in tail area and a mass decrease of up to 16%, while maintaining comparable drag capabilities. Additionally, there is noted enhancement in lift and aeroelastic performance. The utilization of a forward-swept tailplane with a leading-edge extension device shows potential for reducing horizontal empennage dimensions. Multi-objective optimization results provide designers with various optimal solutions tailored to specific requirements. Evaluation at the aircraft level suggests a potential 2% reduction in block fuel compared to the Airbus A320-neo, with a design range of 3200 nautical miles and 180 passengers. These configurations take into account stability constraints and critical ice accretion conditions. The developed framework enabled the illustration of the impact of specific requirements on the final solutions. Furthermore, the impact of the optimized tail arrangement at the aircraft level is illustrated. From an industrial standpoint, this study illustrates how an automated framework can expedite complex multidisciplinary optimization processes, accelerating formulation, integration, and execution phases. This improvement has the potential to reduce time to market and costs associated with developing a new aircraft configuration. | en |
dc.language.iso | en | en_US |
dc.subject.ddc | 620: Ingenieurwissenschaften | en_US |
dc.title | Model-based systems engineering for multidisciplinary optimization of advanced aircraft rear-end | en |
dc.type | Thesis | en_US |
dcterms.dateAccepted | 2024-03-25 | - |
dc.description.version | AlternativeReviewed | en_US |
thesis.grantor.place | Neapel | en_US |
thesis.grantor.universityOrInstitution | Università degli Studi di Napoli Federico II | en_US |
tuhh.contributor.referee | Scholz, Dieter | - |
tuhh.contributor.referee | Blasi, Luciano | - |
tuhh.contributor.referee | De Marco, Agostino | - |
tuhh.contributor.referee | Grassi, Michele | - |
tuhh.oai.show | true | en_US |
tuhh.publication.institute | Forschungsgruppe Flugzeugentwurf und -systeme (AERO) | en_US |
tuhh.publication.institute | Department Fahrzeugtechnik und Flugzeugbau | en_US |
tuhh.publication.institute | Fakultät Technik und Informatik | en_US |
tuhh.publication.institute | Università degli Studi di Napoli Federico II | en_US |
tuhh.type.opus | Dissertation | - |
dc.type.casrai | Dissertation | - |
dc.type.dini | doctoralThesis | - |
dc.type.driver | doctoralThesis | - |
dc.type.status | info:eu-repo/semantics/publishedVersion | en_US |
dc.type.thesis | doctoralThesis | en_US |
dcterms.DCMIType | Text | - |
local.comment.external | Further Supervisor: Nicolosi, Fabrizio | en_US |
item.creatorGND | Mandorino, Massimo | - |
item.grantfulltext | none | - |
item.openairetype | Thesis | - |
item.advisorGND | Della Vecchia, Pierluigi | - |
item.fulltext | No Fulltext | - |
item.languageiso639-1 | en | - |
item.cerifentitytype | Publications | - |
item.creatorOrcid | Mandorino, Massimo | - |
item.openairecristype | http://purl.org/coar/resource_type/c_46ec | - |
Appears in Collections: | Publications without full text |
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