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  • 1.
    Amadori, Kristian
    et al.
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Design Automation Framework for Micro Air Vehicles2009Conference paper (Other academic)
    Abstract [en]

    At Linköping University work has been done to automate the design process of Micro or Mini Air Vehicles. A design optimization framework that links together a CAD system for airframe design and panel code for aerodynamic design has been developed. This paper describes the experience made so far, and demonstrates a case study on fully automated design where a 3D printer is used for manufacturing.

  • 2.
    Amadori, Kristian
    et al.
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Automated Design and Fabrication of Micro Air Vehicles2011In: Journal of Aerospace Engineering, ISSN 0893-1321, E-ISSN 1943-5525, Vol. 226, no 10, p. 1271-1282Article in journal (Refereed)
    Abstract [en]

    A methodology for an automated design and fabrication of micro-air vehicles (MAVs) is presented. A design optimization framework has been developed that interfaces several software systems to generate MAVs to optimally fulfil specific mission requirements. By means of amulti-objective genetic algorithm, families of MAVs are tailored with respect to objectives such as weight and endurance. The framework takes into consideration the airframe and aerodynamic design as well as the selection and positioning of internal components. The selection of propulsion system components is made from a database of off-the-shelf components. In combination with a three-dimensional printer, physical prototypes can be quickly manufactured. A validation of the framework results from flight tests of a real MAV is also presented.

  • 3.
    Amadori, Kristian
    et al.
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Evaluation of Automatically Designed Micro Air Vehicles and Flight Testing2010Conference paper (Refereed)
    Abstract [en]

    The presented work is centered on the evaluation of Micro or Mini Air Vehicles (MAV) that have been automatically designed and manufactured. An in-house developed design framework uses several coupled computer software’s to generate the geometric design in CAD, a well as list of off the shelf components for the propulsion system, and computer code for autonomous flight ready to upload in the intended autopilot. The paper describes the experiences made so far regarding automation of the design process and of manufacturing. Furthermore, it presents results from evaluation and analysis of the optimization algorithm and flight testing, and from continuing work with the framework to achieve deeper understanding of the process and to fine-tune the design automation performance. The flight data is correlated to the predicted performances to validate the models and design process.

  • 4.
    Conte, Gianpaolo
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Hempel, Maria
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Rudol, Piotr
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Lundström, David
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems.
    Duranti, Simone
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group .
    Wzorek, Mariusz
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Doherty, Patrick
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    High Accuracy Ground Target Geo-Location Using Autonomous Micro Aerial Vehicle Platforms2008In: Proceedings of the AIAA Guidance, Navigation, and Control Conference (GNC), AIAA , 2008Conference paper (Refereed)
    Abstract [en]

    This paper presents a method for high accuracy ground target localization using a Micro Aerial Vehicle (MAV) equipped with a video camera sensor. The proposed method is based on a satellite or aerial image registration technique. The target geo-location is calculated by registering the ground target image taken from an on-board video camera with a geo- referenced satellite image. This method does not require accurate knowledge of the aircraft position and attitude, therefore it is especially suitable for MAV platforms which do not have the capability to carry accurate sensors due to their limited payload weight and power resources.  The paper presents results of a ground target geo-location experiment based on an image registration technique. The platform used is a MAV prototype which won the 3rd US-European Micro Aerial Vehicle Competition (MAV07). In the experiment a ground object was localized with an accuracy of 2.3 meters from a ight altitude of 70 meters.

  • 5.
    Duranti, Simone
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group .
    Conte, Gianpaolo
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Lundström, David
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group .
    Rudol, Piotr
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Wzorek, Mariusz
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    Doherty, Patrick
    Linköping University, The Institute of Technology. Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab.
    LinkMAV, a prototype rotary wing micro aerial vehicle.2007In: 17th IFAC Symposium on Automatic Control in Aerospace,2007, Oxford: Elsevier , 2007Conference paper (Refereed)
  • 6.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Berry, Patrick
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Melin, Tomas
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Subscale flight testing used in conceptual design2012In: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 84, no 3, p. 192-199Article in journal (Refereed)
    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.

  • 7.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Berry, Patrick
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Design and Flight Testing of an ECO-Sport Aircraft2010Conference paper (Other academic)
    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.

  • 8.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Lundström, David
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Amadori, Kristian
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    Berry, Patrick
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Design of a Very Light Jet and a Dynamically Scaled Demonstrator2008In: AIAA Aerospace Sciences Meeting and Exhibit,2008, USA: AIAA , 2008Conference paper (Refereed)
    Abstract [en]

      

  • 9.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Berry, Patrick
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Morphing Wing Design, from Study to Flight Test2009Conference paper (Refereed)
    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.

  • 10.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Melin, Tomas
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Berry, Patrick
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Design and Flight Testing of a Solar Powered Aircraft, a Student Challenge2013Conference paper (Other academic)
    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

  • 11.
    Kleiner, Alexander
    et al.
    University of Freiburg.
    Dornhege, Christian
    University of Freiburg.
    Kümmerle, Rainer
    University of Freiburg.
    Ruhnke, Michael
    University of Freiburg.
    Steder, Bastian
    University of Freiburg.
    Nebel, Bernhard
    University of Freiburg.
    Doherty, Patrick
    Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab. Linköping University, The Institute of Technology.
    Wzorek, Mariusz
    Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab. Linköping University, The Institute of Technology.
    Rudol, Piotr
    Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab. Linköping University, The Institute of Technology.
    Conte, Gianpaolo
    Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab. Linköping University, The Institute of Technology.
    Duranti, Simone
    Linköping University, Department of Computer and Information Science, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group . Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Computer and Information Science, KPLAB - Knowledge Processing Lab. Linköping University, The Institute of Technology.
    RoboCupRescue - Robot League Team RescueRobots Freiburg (Germany)2006In: RoboCup 2006 (CDROM Proceedings), Team Description Paper, Rescue Robot League, 2006Conference paper (Refereed)
    Abstract [en]

    This paper describes the approach of the RescueRobots Freiburg team, which is a team of students from the University of Freiburg that originates from the former CS Freiburg team (RoboCupSoccer) and the ResQ Freiburg team (RoboCupRescue Simulation). Furthermore we introduce linkMAV, a micro aerial vehicle platform. Our approach covers RFID-based SLAM and exploration, autonomous detection of relevant 3D structures, visual odometry, and autonomous victim identification. Furthermore, we introduce a custom made 3D Laser Range Finder (LRF) and a novel mechanism for the active distribution of RFID tags.

  • 12.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Aircraft Design Automation and Subscale Testing: With Special Reference to Micro Air Vehicles2012Doctoral thesis, comprehensive summary (Other academic)
    Abstract [en]

    This dissertation concerns how design automation as well as rapid prototyping and testing of subscale prototypes can support aircraft design. A framework for design automation has been developed and is applied specifically to Micro Air Vehicles (MAV). MAVs are an interesting area for design automation as they are an application where the entire design, from requirements to manufacturing, can indeed be automated. From a complexity point of view it can be considered to be similar to conceptual design of manned aircraft.

    The created design optimization framework interfaces several software systems to generate MAVs to optimally fulfil specific mission requirements. The goal has been to find a method for MAV design and optimization from a holistic viewpoint, i.e. not a method for optimizing single subsystems, such as motor or propeller, but a method that embraces all disciplines of MAV design. Key drivers have been the use of off-the-shelf components wherever possible and to optimize the geometric shape not just from an aerodynamic perspective, but also to consider internal component placement and stability criteria. The optimization technique chosen is a multi-objective genetic algorithm. Finally, a novel method for direct digital manufacturing of MAVs is proposed.

    The utility of the framework has been demonstrated with several case studies on MAV design. The propulsion system is identified as most influential on MAV performance and thus is where it is most important to have accurate models. For this reason the models used in the framework are experimentally validated. The influence of atmospheric winds and turbulence on MAV performance is also experimentally investigated

    The subscale testing efforts are aimed at reducing cost and increasing the usability of flight testing with subscale vehicles. Data acquisition system design is described and low-cost testing methods are presented, such as car top testing or in-flight flow visualization. Two subscale flight projects are also presented.

    List of papers
    1. 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, p. 140-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
    2. Automated Design and Fabrication of Micro Air Vehicles
    Open this publication in new window or tab >>Automated Design and Fabrication of Micro Air Vehicles
    2011 (English)In: Journal of Aerospace Engineering, ISSN 0893-1321, E-ISSN 1943-5525, Vol. 226, no 10, p. 1271-1282Article in journal (Refereed) Published
    Abstract [en]

    A methodology for an automated design and fabrication of micro-air vehicles (MAVs) is presented. A design optimization framework has been developed that interfaces several software systems to generate MAVs to optimally fulfil specific mission requirements. By means of amulti-objective genetic algorithm, families of MAVs are tailored with respect to objectives such as weight and endurance. The framework takes into consideration the airframe and aerodynamic design as well as the selection and positioning of internal components. The selection of propulsion system components is made from a database of off-the-shelf components. In combination with a three-dimensional printer, physical prototypes can be quickly manufactured. A validation of the framework results from flight tests of a real MAV is also presented.

    Place, publisher, year, edition, pages
    SAGE Journals online, 2011
    Keywords
    Micro Air Vehicle; multidisciplinary optimization; multi-objective optimization; genetic algorithm; CAD automation; design automation
    National Category
    Mechanical Engineering
    Identifiers
    urn:nbn:se:liu:diva-73107 (URN)10.1177/0954410011419612 (DOI)000312145300006 ()
    Available from: 2011-12-16 Created: 2011-12-16 Last updated: 2017-12-08Bibliographically approved
    3. Validation of Models for Small Scale Electric Propulsion Systems
    Open this publication in new window or tab >>Validation of Models for Small Scale Electric Propulsion Systems
    2010 (English)Conference paper, Published paper (Other academic)
    Abstract [en]

    At Linköping University work has been carried out towards having an automated designand manufacturing process of Micro Air Vehicles (MAV). A dedicated design optimizationframework has been developed. Initial experience has shown that choosing the rightpropulsion system has a major relevance on the overall performance of the aircraft. Thusthe correctness and fidelity of the models used to describe each component of the propulsionsystem are matters of great importance. With this knowledge an effort has been made tovalidate the propulsion system’s models. Using a specifically designed test rig a number ofdifferent motors and motor controllers have been tested. The motor model has shown goodcorrelation with test data, although manufacturer’s specifications have proven less reliable.Motor controller characteristics has shown to be complex and difficult to model.

    Place, publisher, year, edition, pages
    American Institute of Aeronautics and Astronautics, 2010
    Keywords
    Design automation, multidisciplinary optimization, MAV, model validation
    National Category
    Vehicle Engineering
    Identifiers
    urn:nbn:se:liu:diva-62586 (URN)10.2514/6.2010-483 (DOI)978-1-61738-422-6 (ISBN)
    Conference
    48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, Jan. 4-7, 2010
    Available from: 2010-11-30 Created: 2010-11-30 Last updated: 2016-05-11Bibliographically approved
    4. Testing of Atmospheric Turbulence Effects on the Performance of Micro Air Vehicles
    Open this publication in new window or tab >>Testing of Atmospheric Turbulence Effects on the Performance of Micro Air Vehicles
    2012 (English)In: INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES, ISSN 1756-8293, Vol. 4, no 2, p. 133-149Article in journal (Refereed) Published
    Abstract [en]

    Micro Air Vehicles (MAV) are generally operated at low altitudes and within the earth boundary layer. This is a very dynamic environment with varying wind intensity and turbulence levels far greater than those experienced by traditional manned aircraft cruising at higher altitudes. Yet aerodynamic research on MAVs is often based on the assumption of steady aerodynamics. Little effort has been made to experimentally determine the validity of this assumption. In this paper, the effect of turbulence on the performance of a MAV is studied using flight testing in different wind conditions. Flight testing technique, data logging equipment and data reduction are explained. Additionally, a low cost technique for propeller performance measurement is presented. Results show that the flow around a MAV flying in windy conditions qualifies as highly unsteady, although the impact on its performance is surprisingly small for the kind of turbulence levels at which MAVs can be expected to operate. Accelerometer data from the flights reveals that if steady aerodynamic theory is assumed, increasing turbulence should have resulted in a measurable drag increase, thus indicating that the tested MAV to some extent passively manages to benefit from the turbulence.

    Place, publisher, year, edition, pages
    Multi-Science Publishing, 2012
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-81837 (URN)10.1260/1756-8293.4.2.133 (DOI)000307637400003 ()
    Available from: 2012-09-25 Created: 2012-09-24 Last updated: 2012-10-17
    5. RAVEN - A Subscale Radio Controlled Business Jet Demonstrator
    Open this publication in new window or tab >>RAVEN - A Subscale Radio Controlled Business Jet Demonstrator
    2008 (English)In: proceedings from the ICAS 2008, CD-ROM, Anchorage: International Council of the Aeronautical Sciences, (ICAS) , 2008Conference paper, Published paper (Refereed)
    Abstract [en]

    A dynamically scaled model of a Business-Jet has been build and is undergoing testing at Linköping University. The goal of the project was to understand the difficutlties of dynamic scaling and how to extract useful data from subscale flight testing. This paper presents the experience made during the projects up to the time of writing, and includes details from manufacturing, ground testing equipment such as car top testing, in flight data acquisition system design and preparation for the fligt testing.

    Place, publisher, year, edition, pages
    Anchorage: International Council of the Aeronautical Sciences, (ICAS), 2008
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-43959 (URN)75233 (Local ID)0-9533991-9-2 (ISBN)75233 (Archive number)75233 (OAI)
    Conference
    26th Congress of the International Council of the Aeronautical Sciences, 14-19 September 2008, Anchorage, Alaska, USA
    Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2012-10-17Bibliographically approved
    6. Subscale flight testing used in conceptual design
    Open this publication in new window or tab >>Subscale flight testing used in conceptual design
    Show others...
    2012 (English)In: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 84, no 3, p. 192-199Article in journal (Refereed) Published
    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.

    Place, publisher, year, edition, pages
    EMERALD GROUP PUBLISHING LIMITED, 2012
    Keywords
    Aircraft; Design; Aerodynamics; Subscale flight testing; Conceptual design; Prototype; Demonstrator
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-79714 (URN)10.1108/00022661211222058 (DOI)000305871700008 ()
    Available from: 2012-08-13 Created: 2012-08-13 Last updated: 2012-10-17Bibliographically approved
  • 13.
    Lundström, David
    et al.
    Linköping University, Department of Computer and Information Science, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group . Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    RAVEN - A Subscale Radio Controlled Business Jet Demonstrator2008In: proceedings from the ICAS 2008, CD-ROM, Anchorage: International Council of the Aeronautical Sciences, (ICAS) , 2008Conference paper (Refereed)
    Abstract [en]

    A dynamically scaled model of a Business-Jet has been build and is undergoing testing at Linköping University. The goal of the project was to understand the difficutlties of dynamic scaling and how to extract useful data from subscale flight testing. This paper presents the experience made during the projects up to the time of writing, and includes details from manufacturing, ground testing equipment such as car top testing, in flight data acquisition system design and preparation for the fligt testing.

  • 14.
    Lundström, David
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Automation of Design and Prototyping of Micro Aerial Vehicle2009Conference paper (Refereed)
    Abstract [en]

    The presented work is centered on the automation of the design process of Micro or MiniAerial Vehicles (MAV). A design optimization framework that links together a CAD systemfor airframe design and a panel code for aerodynamic evaluations has been developed. Thispaper is based on research and results previously published by the research team. Itdescribes the experiences made so far, and demonstrates with a case study, how fullyautomated design is indeed possible. The user is required to enter the initial requirementsinto the system that will then optimize the MAV design. Both the geometry and thepropulsion system are taken into account. Finally, a 3D printer is used for manufacturing ofthe aircraft. The optimization comprises both discrete and continuous variables. Validationof common propulsion system models is also presented.

  • 15.
    Lundström, David
    et al.
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Distributed Framework for Micro Aerial Vehicle Design Automation2008In: Proceedings from the 46th AIAA Aerospace Sciences Meeting and Exhibit, 7 - 10 January, Reno, NV, USA, AIAA , 2008, p. 140-Conference 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.

     

  • 16.
    Lundström, David
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Validation of Models for Small Scale Electric Propulsion Systems2010Conference paper (Other academic)
    Abstract [en]

    At Linköping University work has been carried out towards having an automated designand manufacturing process of Micro Air Vehicles (MAV). A dedicated design optimizationframework has been developed. Initial experience has shown that choosing the rightpropulsion system has a major relevance on the overall performance of the aircraft. Thusthe correctness and fidelity of the models used to describe each component of the propulsionsystem are matters of great importance. With this knowledge an effort has been made tovalidate the propulsion system’s models. Using a specifically designed test rig a number ofdifferent motors and motor controllers have been tested. The motor model has shown goodcorrelation with test data, although manufacturer’s specifications have proven less reliable.Motor controller characteristics has shown to be complex and difficult to model.

  • 17.
    Lundström, David
    et al.
    Linköping University, Department of Computer and Information Science, AUTTEK - Autonomous Unmanned Aerial Vehicle Research Group . Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Micro Aerial Vehicle Design Optimization using Mixed Discrete and Continuous Variables2006In: A collection of technical papers : 11th AIAAA/ISSMO Multidisciplinary Analysis and Optimization Conferences, Reston, Virginia, USA: American Institute of Aeronautics and Astronautics, 2006, p. 1277-1290Conference paper (Refereed)
    Abstract [en]

     Micro or mini aerial vehicles are characterized by the fact that they are likely to be build in relatively low numbers 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 design optimization with both discrete and continuous variables. This involves both selections of components for the propulsion system, as well as geometrical parameters for the airframe.

  • 18.
    Lundström, David
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Testing of Atmospheric Turbulence Effects on the Performance of Micro Air Vehicles2012In: INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES, ISSN 1756-8293, Vol. 4, no 2, p. 133-149Article in journal (Refereed)
    Abstract [en]

    Micro Air Vehicles (MAV) are generally operated at low altitudes and within the earth boundary layer. This is a very dynamic environment with varying wind intensity and turbulence levels far greater than those experienced by traditional manned aircraft cruising at higher altitudes. Yet aerodynamic research on MAVs is often based on the assumption of steady aerodynamics. Little effort has been made to experimentally determine the validity of this assumption. In this paper, the effect of turbulence on the performance of a MAV is studied using flight testing in different wind conditions. Flight testing technique, data logging equipment and data reduction are explained. Additionally, a low cost technique for propeller performance measurement is presented. Results show that the flow around a MAV flying in windy conditions qualifies as highly unsteady, although the impact on its performance is surprisingly small for the kind of turbulence levels at which MAVs can be expected to operate. Accelerometer data from the flights reveals that if steady aerodynamic theory is assumed, increasing turbulence should have resulted in a measurable drag increase, thus indicating that the tested MAV to some extent passively manages to benefit from the turbulence.

  • 19.
    Sobron, Alejandro
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Jouannet, Christopher
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Sandoval Goez, Luiz Carlos
    Instituto Tecnológico de Aeronáutica, Brasil.
    Flight test design for remotely-piloted aircraft in confined airspace2017In: 6th CEAS Air and Space Conference, Aerospace Europe, 16-20 October, 2017, Bucharest, Romania. / [ed] The Council of European Aerospace Societies, Brussels, 2017Conference paper (Refereed)
    Abstract [en]

    Thispaper presents various techniques and procedures that aim to simplify flighttesting of fixed-wing, remotely-piloted aircraft with the purposes ofperformance evaluation and system identification. These methods have beenspecifically developed for flight within visual line-of-sight, a type ofoperation that limits the available airspace severely but offers major costadvantages considering the current regulations for unmanned flight in mostWestern countries.

  • 20.
    Sobron, Alejandro
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Larsson, Roger
    Linköping University, Department of Electrical Engineering, Automatic Control. Linköping University, Faculty of Science & Engineering.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Jouannet, Christopher
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Methods for efficient flight testing and modelling of remotely piloted aircraft within visual line-of-sight2018In: Proceedings of the 31st Congress of The International Council of the Aeronautical Sciences (ICAS), September 9-14 2018, Belo Horizonte, Brazil. / [ed] The International Council of the Aeronautical Sciences, Bohn, 2018Conference paper (Refereed)
    Abstract [en]

    Remotely piloted scaled models not only serve as convenient low-risk flying test-beds but also can provide useful data and increase confidence in an eventual full-scale design. Nevertheless, performing advanced flight tests in a safe and cost-effective manner is often a challenge for organizations with limited resources. A typical scenario is testing within visual line-of-sight at very low altitude, a type of operation that offers major cost advantages at the expense of a reduced available airspace. This paper describes some of the authors' work towards efficient performance evaluation and system identification of fixed-wing, remotely piloted aircraft under these challenging conditions. Results show that certain techniques, manoeuvre automation, and platform-optimised multisine input signals can improve the flight test efficiency and the modelling process. It is also probable that some of the benefits observed here could be extrapolated to flight testing beyond visual line-of-sight or even to full-scale flight testing.

  • 21.
    Staack, Ingo
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Chaitanya Manjula, Raghu
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Berry, Patrick
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Melin, Tomas
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Jouannet, Christopher
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Parametric Aircraft Conceptual Design Space2012In: Prceedings of the 28th International Congress of the Aeronautical Sciences, 2012Conference paper (Other academic)
    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.

  • 22.
    Staack, Ingo
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems . Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems . Linköping University, The Institute of Technology.
    Subscale Flight Testing at Linköping University2010In: 27th International Congress of the Aeronautical Sciences, Stockholm: ICAS , 2010Conference paper (Other academic)
    Abstract [en]

    At Linkoping University aeronautical research is focusing on design methodologies in early stages of aircraft design. Rapid design and evaluation of prototypes is considered an important branch of this work. In this paper flight test activities at the university are described, the design of a light weight affordable data acquisition system is explained and some flight test results including flow visualization are presented.

1 - 22 of 22
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