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On Aircraft Conceptual Design: A Framework for Knowledge Based Engineering and Design Optimization
Linköping University, Department of Management and Engineering, Machine Design . Linköping University, The Institute of Technology.
2008 (English)Licentiate thesis, comprehensive summary (Other academic)
Abstract [en]

This thesis presents a design framework where analytical tools are linked together and operated from an efficient system level interface. The application field is aircraft conceptual design. Particular attention has been paid to CAD system integration and design optimization.

Aircraft design is an inherently multidisciplinary process. The goal is to search for the design that, in the best of possible ways, fulfills the requirements. It is therefore desirable to be able to effectively investigate and analyze solutions from a variety of points of view, weighting together the results and gathering a general figure of merit. At the same time, increasing competition on a global market forces to shorten the design process and to reduce costs. Thus a system that allows a tight and efficient integration of different disciplines and improving data flow and storage plays a key role.

Integrating a CAD system to the framework is of central relevance. The geometrical model includes most of the information; specific data, required to carry out particular analysis, can be extracted from it. This is possible adopting parametric associative models that are controlled from a spreadsheet user interface. Strategies for building CAD models with a very high degree of flexibility are presented. Not only the external shape can be changed, but also the internal structure can be completely modified. Structural elements can be added or removed, and their position and shaping changed.

In this work the design of an Unmanned Aerial Vehicle is used as test case for comparing three different optimization algorithms. The presented framework is also used for automatically design Micro Aerial Vehicles, starting from a short list of requirements and ending with a physical prototype produced by a rapid prototyping machine.

Place, publisher, year, edition, pages
Institutionen för ekonomisk och industriell utveckling , 2008. , 38 p.
Series
Linköping Studies in Science and Technology. Thesis, ISSN 0280-7971 ; 1366
National Category
Information Science
Identifiers
URN: urn:nbn:se:liu:diva-11873ISBN: 978-91-7393-880-8 (print)OAI: oai:DiVA.org:liu-11873DiVA: diva2:18279
Presentation
2008-05-23, A33, Hus A, Campus Valla, Linköpings universitet, Linköping, 10:15 (English)
Opponent
Supervisors
Available from: 2008-05-21 Created: 2008-05-21 Last updated: 2009-04-23Bibliographically approved
List of papers
1. Use of Panel Code Modeling in a Framework for Aircraft Concept Optimization
Open this publication in new window or tab >>Use of Panel Code Modeling in a Framework for Aircraft Concept Optimization
2006 (English)In: 11th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 6-8 September, Portsmouth, Virginia, USA, 2006, 7084- p.Conference paper, Published paper (Other academic)
Abstract [en]

 

 

In this study the use of a high-order panel code within a framework for aircraft concept design is discussed. The framework is intended to be a multidisciplinary optimization tool to be adopted from the very beginning of the conceptual design phase in order to define and refine the aircraft design, with respect to its aerodynamic, stability and control, structure and basic aircraft systems. The presented work is aimed at developing a module for aerodynamic analysis of concepts as a basis for a direct search optimization of the concept layout. The design criterion, used in the example presented here, is to minimize the maximum take-off weight required to fulfil the mission. Classic and simple equations are used together with the data generated by the panel code solver to calculate the aircraft’s performances. Weights are calculated by means of statistical group weight equations, but the weight could also be calculated from a CAD-model. The design of an Unmanned Combat Air Vehicle is used as test case for three different optimization algorithms: one gradient method based (Fmincon), one non-gradient based (Complex) and one Genetic Algorithm (GA). Comparison of results and performances shows that the Genetic Algorithm is best fitted for the specific problem, having the by far best hit rate, even if it is at a cost of longer computing time. The Complex algorithm requires less iterations and is also able to find the optimum solution, but with a worse hit rate, while Fmincon can not reach to a global optimum. The suggested optimized configuration for the aircraft is very similar to the Boeing X-45C and Northrop Grumman X-47B.

National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-13306 (URN)
Available from: 2011-11-10 Created: 2008-05-21 Last updated: 2011-12-16Bibliographically approved
2. A Framework for Aerodynamic and Structural Optimization in Conceptual Design
Open this publication in new window or tab >>A Framework for Aerodynamic and Structural Optimization in Conceptual Design
2007 (English)In: 25th AIAA Applied Aerodynamics Conference, 25-28 June, Miami, FL, USA, AIAA , 2007, 4061- p.Conference paper, Published paper (Other academic)
Abstract [en]

Aircraft design is an inherently multidisciplinary activity that requires different models and tools for various aspects of the design. At Linköping University a novel design framework is being developed to support the initial conceptual design phase of a new aircraft. In this work main attention has been paid to wing design, with respect to aerodynamic efficiency and loads, and to structural analysis. By linking together various modules via a user-friendly interface based on a spreadsheet, the framework allows multidisciplinary analysis and optimizations to be carried out. This paper will present the framework, give an overview of its development status and give an indication on the future work.

Place, publisher, year, edition, pages
AIAA, 2007
Keyword
Aircraft design, multi domain optimization
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-13307 (URN)
Available from: 2008-05-21 Created: 2008-05-21 Last updated: 2009-04-22
3. Distributed Framework for Micro Aerial Vehicle Design Automation
Open this publication in new window or tab >>Distributed Framework for Micro Aerial Vehicle Design Automation
2008 (English)In: Proceedings from the 46th AIAA Aerospace Sciences Meeting and Exhibit, 7 - 10 January, Reno, NV, USA, AIAA , 2008, 140- p.Conference paper, Published paper (Other academic)
Abstract [en]

Micro or mini aerial vehicles are characterized by being simple and inexpensive to build, and due to their small size very important to optimize. They are also likely to be built in relatively small series and be tailored for the sensors and equipment available at the time of deployment. Therefore "design and build on demand" is very attractive, where a modular concept with a more or less automated design process is desirable. In this paper design automation of a Micro or Mini Aerial Vehicle (MAV) is demonstrated using a distributed design optimization framework that involves selections of components from a database of propulsion system equipment and geometrical shape optimization. The framework links together a CAD system, responsible for the aircraft shape generation, with a panel code for aerodynamic evaluations.

 

Place, publisher, year, edition, pages
AIAA, 2008
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-13308 (URN)978-1-62410-128-1 (ISBN)
Conference
46th AIAA Aerospace Sciences Meeting and Exhibit, 7 - 10 January, Reno, NV, USA
Available from: 2008-05-21 Created: 2008-05-21 Last updated: 2012-10-17Bibliographically approved

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Amadori, Kristian

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