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  • 1.
    Amadori, Kristian
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Development of a subscale flight testing platform for a generic future fighter2010Konferansepaper (Fagfellevurdert)
    Abstract [en]

    One branch of the current research in aircraft design at Linköping University is focused on fast concept evaluation in early design stages. This covers multidisciplinary optimization using tools of different level of complexity and low-cost subscale flight testing. In some cases a flight test will provide more answers than several computations ever could. In order to achieve this goal a methodology is required to allow fast creation of subscale flying concepts and to obtain as much reliable information as possible from the tests. The methodology is currently being developed. One important part of it is the scaling methodology and the imposed requirements on manufacturing. The present paper presents the latest subscale demonstrator from Linköping University that has been built as part of the study initiated by the Swedish Material Board on a Generic Future Fighter aircraft.

  • 2.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Aircraft Conceptual Design Methods2010 (oppl. 1)Bok (Annet vitenskapelig)
    Abstract [en]

    Aircraft Conceptual Design Synthesis means design by fitness-for-purpose. Design engineers can jump off from the point of given parameters and requirements - required performance, payloads and other factors. This is the first book for the aeronautical designer devoted to guiding the reader through this highly effective conceptual design synthesis process. This forms the procedure for the initial stage of the aircraft design process - the interpretation of a requirement into the preliminary layout. A logical design sequence is developed utilizing original modules to represent propulsion, lift, drag, mass, and performance. Aircraft Conceptual Design Synthesis includes a disk of spreadsheets that provides core data. Unlike existing approaches, the design synthesis method can be applied to novel aircraft concepts.CONTENTS INCLUDE* The design process* Aircraft configuration* Flight regime and powerplant considerations* Fuselage layout* Configuration of the wing* Basic lift, drag and mass representations* Performance estimation* Parametric analysis and optimisation* Analysis of concept design  "This is an important landmark book and in my view will become a standard by which others will be compared" - Dr E C P Ransom, Kingston University, UK

  • 3.
    Berry, Patrick
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Aircraft conceptual design methods2005Licentiatavhandling, med artikler (Annet vitenskapelig)
    Abstract [en]

    Generally aircraft conceptual design is defined as the starting point for concept sketcing and evaluation, but before that work can start an even earlier stage has to be covered.

    This is the stage where different scenarios are being worked through in which the aircraft as a platform is supposed to work. The scenarios will differ between civil and military use of course. but will have to fit well inside both customers and manufacturers strategic plans for the future.

    In planning for the future it's vital to think and plan in broader terms, i.e. not only creating single products but rather create families of aircraft. This way of thinking and planning is usual amongst civil manufacturers. Creating a family based product line means better economics, better market coverage and of course lesser risk taking if and when the market changes. On the military side this way of thinking and planning is still quite unusual, mainly because customers are governments which usually only ask for single products.

    The manufacturer from his point of view must think differently, he needs to spread his risk taking, especially as orders from the govemment are becoming scarcer. Therefore a modular product line would be of economic interest and would probably interest more customers.

    The basic idea behind Saab Gripen (three roles merged into one single platform), or the US Joint Strike Fighter (JSF) idea of a modular aircraft, could be seen as the start of some kind of new family planning, but family planning on the military side could reach further than that. Probably military manufacturers can learn a lot from their civil counterparts.

    Conceptual design might be a one man job in the early stages, but will very soon develop into team work. This development is only natural since the conceptual designer can't be expected to have detailed knowledge or experience which will cover every item. Conceptual design introduces a holistic viewpoint into the aircraft design process and it's vital to keep this viewpoint as long as possible. This becomes even more important over time, since the more detailed the project gets, the overall goal tends to drown into details.

    Conceptual design phase offers the only occasion when design changes still can be made quite easily. Design freeze is not only a simple freeze of aircraft layout and geometry, it also sets the fmal prize tag on the aircraft. So in a way it is what you did (and what you forgot to do) in the conceptual design phase which fmally decides the faith of the end product. Hence conceptual design needs all the time it takes to be able to develop successful future products.

    Generally there are two sides to conceptual design: either you develop a brand new design or make changes to an already existing one. Either way has its own needs and can't be run in the same manner, since different tools are needed in both cases. A new design needs a good conceptual design program, while in the latter case only minor parts of it might be used. A new design starts off fresh; everything is possible and nothing is sacred, but changing on an existing design means working with hands tied, you do not change things that easily.

    Aircraft Conceptual Design takes long time to learn. It requires more than just being able to run a conceptual design program. Previous experience in a number of different aircraft design disciplines is a must; so is the ability to be able to humbly listen to experienced people's knowledge and advice.

    This paper describes methods for aircraft conceptual design at two basic levels. At the top level there's a method described for conceptual design of civil jet transport aircraft.

    On the second level different methods for conceptual design of core aircraft systems such as landing gear, environmental control and hydraulic are presented.

    Delarbeid
    1. The Sunriser - A Design Study in Solar Powered Flight
    Åpne denne publikasjonen i ny fane eller vindu >>The Sunriser - A Design Study in Solar Powered Flight
    2000 (engelsk)Inngår i: SAE Technical Paper 2000-01-5507, 2000Konferansepaper, Publicerat paper (Annet vitenskapelig)
    Abstract [en]

    The design task for last year students in Aircraft Design at Linköping University was to design a manned solar-powered aircraft. The mission was to survey the U.S./Mexican borderline in search for possible intruders. The Sunriser began as a sole paper project, but quite soon we felt a need to prove that solar-powered flight really was feasible. Thus the decision was made to design and build a solar powered demonstrator of our own design.

    The demonstrator aircraft, a radio controlled model aircraft named "the Sunrazor," was designed, built and flown with good result.

    This paper deals with the basic theory of sun-powered flight and describes the basic thoughts and design considerations which finally led to the configurations chosen.

    HSV kategori
    Identifikatorer
    urn:nbn:se:liu:diva-35265 (URN)10.4271/2000-01-5507 (DOI)26023 (Lokal ID)26023 (Arkivnummer)26023 (OAI)
    Konferanse
    2000 World aviation Congress, San Diego, California, October, 2000
    Tilgjengelig fra: 2009-10-10 Laget: 2009-10-10 Sist oppdatert: 2013-11-07
    2. Landing Gear Design in the Conceptual Design Phase
    Åpne denne publikasjonen i ny fane eller vindu >>Landing Gear Design in the Conceptual Design Phase
    1999 (engelsk)Inngår i: SAE Technical Paper 1999-01-5523, 1999Konferansepaper, Publicerat paper (Annet vitenskapelig)
    Abstract [en]

    A well-designed landing gear and a proper integration is of utmost importance for the success of any aircraft design. This should never be neglected but often is, especially in the conceptual design stage. This paper reflects the author''s own experience in landing gear design of the Saab Gripen aircraft as well as experience gained on aircraft conceptual designs of later dates. The aim of the paper is to underline the importance of spending more time on landing gear design and integration in conceptual design. The paper reflects the importance of proper interaction between landing gear design and other disciplines and above all underlines the fact that landing gear design should be treated as an equally important design parameter, just as any other, in the final choice of aircraft configuration.

    HSV kategori
    Identifikatorer
    urn:nbn:se:liu:diva-100442 (URN)10.4271/1999-01-5523 (DOI)
    Konferanse
    1999 World aviation Congress, San Fransisco, California, October, 1999
    Tilgjengelig fra: 2013-11-07 Laget: 2013-11-07 Sist oppdatert: 2013-11-07
    3. Sizing the Landing Gear in the Conceptual Design Phase
    Åpne denne publikasjonen i ny fane eller vindu >>Sizing the Landing Gear in the Conceptual Design Phase
    2000 (engelsk)Inngår i: SAE Technical Paper 2000-01-5601, 2000Konferansepaper, Publicerat paper (Annet vitenskapelig)
    Abstract [en]

       

    A tool has been developed in order to design or evaluate a proposed landing gear layout and to determine its size and weight. The methodology has been developed primarily for landing gears of the telescopic suspension type.

    HSV kategori
    Identifikatorer
    urn:nbn:se:liu:diva-35273 (URN)10.4271/2000-01-5601 (DOI)26049 (Lokal ID)26049 (Arkivnummer)26049 (OAI)
    Konferanse
    2000 World aviation Congress, San Diego, California, October, 2000
    Tilgjengelig fra: 2009-10-10 Laget: 2009-10-10 Sist oppdatert: 2013-11-07
    4. Conceptual Design of a New Generation JAS 39 Gripen Aircraft
    Åpne denne publikasjonen i ny fane eller vindu >>Conceptual Design of a New Generation JAS 39 Gripen Aircraft
    2006 (engelsk)Konferansepaper, Publicerat paper (Fagfellevurdert)
    Abstract [en]

    This paper describes the conceptual phase of a modification proposal for Saab Gripen, which aims to create the best possible basis for future aircraft development. One of the main tasks in this respect is to investigate different means to extend range. This paper describes the technical outcome from the concept generation, concept selection, and concept refinement at system and airframe level. The chosen concept involves relocation and redesign of the main landing gear. The original main landing gear bay is converted into fuel tanks. The relocation of the main gear enables a new ventral twin store carriage with supersonic jettison capability to be introduced. The concept proposal yields the following improvements:

    · Increased range due to increased fuel capability

    · Increased maximum allowed takeoff weight due to beefe d-up main gear

    · Increased weapon flexibility and capability due to introduction of two new ventral store

    · Introducing supersonic jettison capability

    The paper also includes a description of how the work is related to the overall design process in general and the conceptual phase in particular, as described in design methodology literature.

    HSV kategori
    Identifikatorer
    urn:nbn:se:liu:diva-12980 (URN)10.2514/6.2006-31 (DOI)
    Konferanse
    44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, USA
    Tilgjengelig fra: 2008-04-01 Laget: 2008-04-01 Sist oppdatert: 2013-11-07
  • 4.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Aircraft Desígn at LiU2004Inngår i: EWADE 2004,2004, 2004Konferansepaper (Annet vitenskapelig)
  • 5.
    Berry, Patrick
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Landing Gear Design in the Conceptual Design Phase1999Inngår i: SAE Technical Paper 1999-01-5523, 1999Konferansepaper (Annet vitenskapelig)
    Abstract [en]

    A well-designed landing gear and a proper integration is of utmost importance for the success of any aircraft design. This should never be neglected but often is, especially in the conceptual design stage. This paper reflects the author''s own experience in landing gear design of the Saab Gripen aircraft as well as experience gained on aircraft conceptual designs of later dates. The aim of the paper is to underline the importance of spending more time on landing gear design and integration in conceptual design. The paper reflects the importance of proper interaction between landing gear design and other disciplines and above all underlines the fact that landing gear design should be treated as an equally important design parameter, just as any other, in the final choice of aircraft configuration.

  • 6.
    Berry, Patrick
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Sizing the Landing Gear in the Conceptual Design Phase2000Inngår i: SAE Technical Paper 2000-01-5601, 2000Konferansepaper (Annet vitenskapelig)
    Abstract [en]

       

    A tool has been developed in order to design or evaluate a proposed landing gear layout and to determine its size and weight. The methodology has been developed primarily for landing gears of the telescopic suspension type.

  • 7.
    Berry, Patrick
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    The Sunriser - A Design Study in Solar Powered Flight2000Inngår i: SAE Technical Paper 2000-01-5507, 2000Konferansepaper (Annet vitenskapelig)
    Abstract [en]

    The design task for last year students in Aircraft Design at Linköping University was to design a manned solar-powered aircraft. The mission was to survey the U.S./Mexican borderline in search for possible intruders. The Sunriser began as a sole paper project, but quite soon we felt a need to prove that solar-powered flight really was feasible. Thus the decision was made to design and build a solar powered demonstrator of our own design.

    The demonstrator aircraft, a radio controlled model aircraft named "the Sunrazor," was designed, built and flown with good result.

    This paper deals with the basic theory of sun-powered flight and describes the basic thoughts and design considerations which finally led to the configurations chosen.

  • 8.
    Berry, Patrick
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Ahmad, Shakeel
    Linköpings universitet, Institutionen för systemteknik, Elektroniksystem. Linköpings universitet, Tekniska högskolan.
    Sport Aviation of the Future. Possible Concepts for Future Sport Aircraft using Differrent Environmental Friendly Propulsion Concepts 2010Inngår i: ICAS 2010, 2010, s. 10-Konferansepaper (Annet vitenskapelig)
  • 9.
    Gavel, Hampus
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Axelsson, Arne
    Saab Aerostructures, Linköping, Sweden.
    Conceptual Design of a New Generation JAS 39 Gripen Aircraft2006Konferansepaper (Fagfellevurdert)
    Abstract [en]

    This paper describes the conceptual phase of a modification proposal for Saab Gripen, which aims to create the best possible basis for future aircraft development. One of the main tasks in this respect is to investigate different means to extend range. This paper describes the technical outcome from the concept generation, concept selection, and concept refinement at system and airframe level. The chosen concept involves relocation and redesign of the main landing gear. The original main landing gear bay is converted into fuel tanks. The relocation of the main gear enables a new ventral twin store carriage with supersonic jettison capability to be introduced. The concept proposal yields the following improvements:

    · Increased range due to increased fuel capability

    · Increased maximum allowed takeoff weight due to beefe d-up main gear

    · Increased weapon flexibility and capability due to introduction of two new ventral store

    · Introducing supersonic jettison capability

    The paper also includes a description of how the work is related to the overall design process in general and the conceptual phase in particular, as described in design methodology literature.

  • 10.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Aircraft design education at Linköpings University2007Inngår i: Proceedings of the Institution of Mechanical Engineers. Part G, Journal of Aerospace Engineering, ISSN 0954-4100, E-ISSN 2041-3025, ISSN 0954-4100, Vol. 221, nr 2, s. 217-224Artikkel i tidsskrift (Fagfellevurdert)
    Abstract [sv]

    Aircraft design is a complex multi-disciplinary task and teaching can easily tend to be too theoretical, not providing the students the tools they need to successfully participate in industrial projects. The approach chosen at Linköping University is intended to create the right balance between theory and practice, and to place the student in the centre of the problem, in order to achieve an overall perspective of the aircraft design process. This article presents in brief layout of the courses, and in more detail, the aircraft design project course given in the last year of the aeronautical masters program, where flying hardware is designed and build, in response to a design challenge. © IMechE 2007.

  • 11.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    MANTA - From conceptual design to flight test2005Inngår i: European Workshop on Aircraft Design Education,2005, 2005Konferansepaper (Annet vitenskapelig)
  • 12.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Subscale flight testing used in conceptual design2012Inngår i: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 84, nr 3, s. 192-199Artikkel i tidsskrift (Fagfellevurdert)
    Abstract [en]

    Purpose - The purpose of this paper is to present the latest subscale demonstrator aircraft developed at Linkoping University. It has been built as part of a study initiated by the Swedish Material Board (FMV) on a Generic Future Fighter aircraft. The paper will cover different aspects of the performed work: from paper study realised by SAAB to the first flight of the scaled demonstrator. The intention of the paper is to describe what has been realised and explain how the work is may be used to fit within aircraft conceptual design. Design/methodology/approach - The approach has been to address the challenges proposed by the customer of the demonstrator, how to design, manufacture and operate a scaled demonstrator of an aircraft study in conceptual design within five months. Similar research projects have been reviewed in order to perform the current work. Findings - The results obtained so far have led to new questions. In particular, the project indicated that more research is needed within the area of subscale flight testing for usage in aircraft conceptual design, since a scaled demonstrator is likely to answer some questions but will probably open up new ones. Research limitations/implications - The current research is just in its infancy and does not bring any final conclusion but does, however, offer several guidelines for future works. Since the aircraft study was an early phase concept study, not much data are available for validation or comparison. Therefore, the paper is not presenting new methods or general conclusions. Practical implications - Results from a conceptual aircraft study and a realisation of a scaled prototype are presented, which show that scaled flight testing may be used with some restriction in conceptual design. Originality/value - The value of this paper is to show that universities can be involved in prototype development and can work in close collaboration with industries to address issues and solutions within aircraft conceptual design.

  • 13.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Design and Flight Testing of an ECO-Sport Aircraft2010Konferansepaper (Annet vitenskapelig)
    Abstract [en]

    The presented work is centered on different concept studies for “greener” sport aircraft. The goal is to show the possibility to manufacture a sport aircraft based on different environmental friendly propulsion systems. A first theoretical part consists of creating a sizing program for studying different concepts. Then the gathered knowledge will result in the realization of two flying down-scaled demonstrators. This study was realized during a student project over a 5 month period.

  • 14.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Lundström, David
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Amadori, Kristian
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Design of a Very Light Jet and a Dynamically Scaled Demonstrator2008Inngår i: AIAA Aerospace Sciences Meeting and Exhibit,2008, USA: AIAA , 2008Konferansepaper (Fagfellevurdert)
    Abstract [en]

      

  • 15.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Morphing Wing Design, from Study to Flight Test2009Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Mission adaptive wing have been implement in the past, this article present an approach were wingarea reduction of at least 40% has to be achieved. The project goal is to evaluate different concept bythe uses of flying demonstrators. This was realized during a student project over a five month period.

  • 16.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Design and Flight Testing of a Solar Powered Aircraft, a Student Challenge2013Konferansepaper (Annet vitenskapelig)
    Abstract [en]

    The presented work considers designing, building and flight testing a solar poweraircraft as a student project. The goal is to allow student to participate in an aircraft projectfrom design to flight test in order to acquire aircraft design knowledge from theoretical andpractical means. A first theoretical part consists of creating a sizing program for studyingdifferent concepts. Then the gathered knowledge will result in the realization of a flyingdemonstrator. This was realized during a student project over a 5 month period

  • 17.
    Munjulury, Raghu Chaitanya
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Knowledge-based Integrated Wing Automation and Optimization for Conceptual Design2015Inngår i: 16th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference16th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, American Institute of Aeronautics a, 2015Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Contemporary aircraft design and development incurs high costs and consumes a lot of time for research and implementation. To minimize the development cost, an improvement of the conceptual design phase is desirable. A framework to support the initial design space exploration and conceptual design phase is presently being developed at Linköping University. In the aircraft design, the geometry carries a critical, discriminating role since it stores a significant part of the information and the data needed for most investigations. Methodology for design automation of a wing with a detailed description such that the geometry is effectively propagated for further analysis is presented in this paper. Initial weight estimation of the wing is performed by combining the weight penalty method with a sophisticated CAD model. This wing model is used for airfoil shape optimization and later for structural optimization. A methodology for automatic meshing of the geometry for CFD and FEM when the surfaces increase or decrease during the design automation is proposed. The framework combining automation capability with shape and structural optimization will enhance the early design phases of aircraft conceptual design.

  • 18.
    Munjulury, Raghu Chaitanya
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Berry, Patrick
    Saab Aeronautics, Linköping.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    A knowledge-based integrated aircraft conceptual design framework2016Inngår i: CEAS Aeronautical Journal, ISSN 1869-5582, 1869-5590, Vol. 7, nr 1, s. 95-105Artikkel i tidsskrift (Fagfellevurdert)
    Abstract [en]

    "The conceptual design is the early stage of aircraft design process where results are needed fast, both analytically and visually so that the design can be analyzed and eventually improved in the initial phases. Although there is no necessity for a CAD model from the very beginning of the design process, it can be an added advantage to have the model to get the impression and appearance. Furthermore, this means that a seamless transition into preliminary design is achieved since the CAD model can guardedly be made more detailed. For this purpose, knowledge-based aircraft conceptual design applications Tango (Matlab) and RAPID (CATIA) are being developed at Linköping University. Based on a parametric data definition in XML, this approach allows for a full 3D CAD integration. The one-database approach, also explored by many research organizations, enables the flexible and efficient integration of the different multidisciplinary processes during the whole conceptual design phase. This paper describes the knowledge-based design automated methodology of RAPID, data processing between RAPID and Tango and its application in the courses ‘‘Aircraft conceptual design’’ and ‘‘Aircraft project course’’ at Linköping University. A multifaceted user interface is developed to assist the whole design process."

  • 19.
    Munjulury, Venkata Raghu Chaitanya
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    RAPID – Robust Aircraft Parametric Interactive Design: A Knowledge Based Aircraft Conceptual Design Tool2013Inngår i: Proceedings of the 4th CEAS Conference in Linköping 2013: 4:th CEAS conference, 2013 / [ed] Tomas Melin, Petter Krus, Emil Vinterhav and Knut Övrebo, Linköping, 2013, s. 255-262Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Conceptual design is the early stage of theaircraft design process where results areneeded faster both analytically and visually sothat the design can be modified or changed atthe earliest stages. Although there is nonecessity for a CAD model from the verybeginning of the design process it can be anadded advantage to have the model, to get theimpression and appearance.Tango and RAPID are knowledge basedaircraft conceptual design applications beingdeveloped in Matlab and CATIA respectively.The user can work in parallel with bothprograms and exchange the data between themvia XML. This paper describes the knowledgebased design automated methodology of RAPIDand its application in the courses “Aircraftconceptual design” and “Aircraft projectcourse” at Linköping University. A multifaceteduser interface is developed to assist in the wholedesign processes.

  • 20.
    Munro, Cameron
    et al.
    IKP .
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Integration of Subscale Flight Testing in Design Education2000Inngår i: International Congress or Aeronautical Sciences,2000, 2000Konferansepaper (Annet vitenskapelig)
  • 21.
    Parés Prat, Andreu
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Borhani Coca, Dario
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Munjulury, Raghu Chaitanya
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Analytical weight estimation of unconventional landing gear designs2015Inngår i: Proceedings of the Institution of MechanicalEngineers, Part G: : Journal of Aerospace Engineering, 2015, , s. 10Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Landing gear weight calculations can be carried out using statistical or analytical methods. Statistical methods were used in the past and offered quick group weights, however, they are not capable of computing with accuracy the weight of unconventional landing gears which have special geometries and performances. In this work, landing gear weight is computed using analytical methods. The procedure established by Kraus and Wille is acquired as a baseline so as to create a program able to deal with landing gear weight calculations. This software has been designed to be as much flexible as possible, giving the user the freedom to modify many options and parameters.

  • 22.
    Staack, Ingo
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Chaitanya Manjula, Raghu
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Parametric Aircraft Conceptual Design Space2012Inngår i: Prceedings of the 28th International Congress of the Aeronautical Sciences, 2012Konferansepaper (Annet vitenskapelig)
    Abstract [en]

    This paper presents the development of a design framework for the initial conceptual design phase. The focus in this project is on a flexible database in XML format, together with close integration of automated CAD, and other tools, which allows the developed geometry to be used directly in the subsequent preliminary design phase. The database and the geometry are also described and an overview is given of included tools like aerodynamic analysis and weight estimation.

  • 23.
    Tarkian, Mehdi
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Ölvander, Johan
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Exploring Parametric CAD-models in Aircraft Conceptual Design2008Inngår i: 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2008, Reston, VA, USA: American Institute of Aeronautics and Astronautics, 2008Konferansepaper (Annet vitenskapelig)
    Abstract [en]

    The ever fast growing information technology is enabling the re-definition of early stages of aircraft design which have been restricted mostly by statistical and empirical approaches because of lengthy and costly simulation times. This paper will describe a methodology based on parametric and generic CAD modeling methods which will save time when performing repetitive tasks automatically. Furthermore, it enables greater comprehension by giving a holistic view of the aircraft systems because of the proposed multidisciplinary and modular framework. The framework involves a centralized easy to use interface which is coupled to a series of analyses tools. The proposed methods have been applied in student projects of the course -Aircraft Conceptual Design- from Linköping University where it has shown great promises.

1 - 23 of 23
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