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  • 1.
    Amadori, Kristian
    et al.
    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 Mechanical Engineering Systems. 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.
    Development of a subscale flight testing platform for a generic future fighter2010Conference paper (Refereed)
    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.
    Amadori, Kristian
    et al.
    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 Mechanical Engineering Systems . Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Machine Design . Linköping University, The Institute of Technology.
    A Framework for Aerodynamic and Structural Optimization in Conceptual Design2007In: 25th AIAA Applied Aerodynamics Conference, 25-28 June, Miami, FL, USA, AIAA , 2007, p. 4061-Conference 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.

  • 3.
    Amadori, Kristian
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design.
    Aircraft Conceptual Design Optimization2008In: International Congress of the Aeronautical Sciences ICAS,2008, Stockholm, Sweden: ICAS , 2008Conference paper (Refereed)
    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 new aircraft. By linking together various modules via a userfriendly spreadsheet interface, the framework allows multidisciplinary analysis and optimizations to be carried out. The geometrical model created with a high-end CAD system, contains all the available information on the product and thus it plays a central role in the framework. In this work great attention has been paid to techniques that allow creating robust yet highly flexible CAD models. Two different case studies are presented. The first one is a hypothetic wing-box design that is studied with respect to aerodynamic efficiency and loads, and to structural analysis. In this study two approaches were compared. In one case the wing-box design was optimized with a fixed number of structural elements, where only dimensions and position were allowed to change. Then the same wing-box was analyzed allowing also the number of structural elements to vary. Thus only the parts that are required are left and a more efficient design can be obtained. In the second case study a mission simulation is performed on a UAV-type aircraft. Required data for the simulation are gathered from the CAD model and from aerodynamic analysis carried out with PANAIR, a high order panel code. The obtained data are then used as inputs parameters for flight simulation in order to determined hydraulic systems characteristics.  

  • 4.
    Amadori, Kristian
    et al.
    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 Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, The Institute of Technology.
    Use of Panel Code Modeling in a Framework for Aircraft Concept Optimization2006In: 11th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 6-8 September, Portsmouth, Virginia, USA, 2006, p. 7084-Conference 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.

  • 5.
    Johansson, Björn
    et al.
    Linköping University, Department of Mechanical Engineering. 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.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Distributed aircraft analysis using web service technology2003In: SAE Technical Paper, 2003, p. 2003-01-3007-Conference paper (Refereed)
    Abstract [en]

    The design modern aircraft requires integration of multidisciplinary models for analysis in early design phase to increase the chances of a successful project. In this paper, a framework for distributed aircraft analysis in the conceptual design including several domains is presented. The framework is based on so-called W eb service standards, allowing integration of distributed models for system simulation and optimization using standardized interfaces. The analysis is controlled by a so-called sequencer which manages the interaction between simulation modules and an XML-based design data repository. This repository includes all design data and an executable process description defining the sequence for execution of the modules.

    In the paper, the framework with underlying concepts is described. The approach is further illustrated using the design of an Unmanned Aerial Vehicle as an example. This includes the definition of the simulation modules, the process model and definition and execution of an optimization problem.

  • 6.
    Johansson, Björn
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Distributed aircraft analysis using web service technology2004In: The World Aviation Congress,2003, Montreal, Canada: World Aviation Congress , 2004Conference paper (Refereed)
  • 7.
    Johansson, Björn
    et al.
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Jouannet, Christopher
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Distributed aircraft analysis using web service technology2003In: SAE Transactions Journal of Aerospace, ISSN 0096-736X, Vol. 112, no 1, p. 445-453Article in journal (Refereed)
    Abstract [en]

    The design of modern aircraft requires the integration of multidisciplinary mouels for analysis in the early design phase to increase the chances of a successful project. In this paper, a framework for distributed aircraft analysis in the conceptual design including several domains is presented. The framework is based on so-called Web Service Standards, allowing integration of distributed models for system simulation and optimization using standardized interfaces. The analysis is controlled by a so-called sequencer which manages the interaction between simulation modules and an XML-based design data repository. This repository includes all design data and an executable process description defining the sequence for execution of the modules. In the paper, the framework with its underlying concepts is described. The approach is further illustrated using thedesign of an Unmanned Aerial Vehicle as an example. This includes the definition of the stimulation modules, the process model, and definition and execution of an optimization problem.

  • 8.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Aircraft project 2007 - Linköpings University RAVEN Biz Jet Medivac2007In: European Workshop on Aircraft Design Education,2007, 2007Conference paper (Other academic)
    Abstract [sv]

      

  • 9.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Bizjet demonstrator, En dynamisk skalad jetmodell2007In: FLYGTEKNIK 2007,2007, 2007Conference paper (Other academic)
  • 10.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Jet Version of a Research UAV Design Study2005Report (Other academic)
  • 11.
    Jouannet, Christopher
    Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Model based aircraft design: high angle of attack aerodynamics and weight estimation methods2005Doctoral thesis, comprehensive summary (Other academic)
    Abstract [en]

    This thesis addresses modelling of high angle of attack aerodynamic characteristics and weight estimation for highly maneuverable aircraft during conceptual design. In order to allow configuration selection with sufficient confidence, especially with unconventional configurations, high angle of attack aerodynamic prediction and weight estimations methods need to be improved. In this thesis, a state-space variable approach is proposed for modelling high angle of attack aerodynamics including large angular rates. A new weight estimation based on a parametrical CAD model is also proposed.

    The aerodynamic model is intended for use in both conceptual design and in later design phases. In conceptual design, the parameters are defined from geometrical data. Good results have been obtained with slender delta wings and on in various full configurations. When test data or CFD data arc available, the parameters are obtained from identification. Various results are presented with high accuracy iu the model. The developed model has been implemented in flight simulation, and in a sizing example, where two different aerodynamic models were used in order to show the influences of large angular rates on the geometrical layout. The presented weight estimation method is based on parametrical CAD models, and the weight is extracted from the structure layout. This allows any type of a ircraft configuration to be investigated, without the use of empirical or statistical approaches. Comparison with known aircraft has shown good agreement.

    This thesis introduces a new aerodynamic model that includes large angular rates at any angle of attack, and a new weight prediction method. Both have shown good agreement with compared data and indicate that the models are suitable for conceptual design and that further studies should be conducted in order to extend the possibilities demonstrated here.

    List of papers
    1. Distributed aircraft analysis using web service technology
    Open this publication in new window or tab >>Distributed aircraft analysis using web service technology
    2003 (English)In: SAE Transactions Journal of Aerospace, ISSN 0096-736X, Vol. 112, no 1, p. 445-453Article in journal (Refereed) Published
    Abstract [en]

    The design of modern aircraft requires the integration of multidisciplinary mouels for analysis in the early design phase to increase the chances of a successful project. In this paper, a framework for distributed aircraft analysis in the conceptual design including several domains is presented. The framework is based on so-called Web Service Standards, allowing integration of distributed models for system simulation and optimization using standardized interfaces. The analysis is controlled by a so-called sequencer which manages the interaction between simulation modules and an XML-based design data repository. This repository includes all design data and an executable process description defining the sequence for execution of the modules. In the paper, the framework with its underlying concepts is described. The approach is further illustrated using thedesign of an Unmanned Aerial Vehicle as an example. This includes the definition of the stimulation modules, the process model, and definition and execution of an optimization problem.

    Place, publisher, year, edition, pages
    New York: , 2003
    Keywords
    aircraft analysis, web service technology
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-23789 (URN)3306 (Local ID)3306 (Archive number)3306 (OAI)
    Available from: 2009-10-07 Created: 2009-10-07 Last updated: 2012-12-12
    2. Implications of scale effect for the prediction of high angle of attack aerodynamics
    Open this publication in new window or tab >>Implications of scale effect for the prediction of high angle of attack aerodynamics
    2005 (English)In: Progress in Aerospace Sciences, ISSN 0376-0421, E-ISSN 1873-1724, ISSN 0376-0421, Vol. 41, no 3-4, p. 301-322Article in journal (Refereed) Published
    Abstract [en]

    Scale effect is of significance in all experimental aerodynamics testing. At high angles of attack such issues as Reynolds and Mach number scaling are further complicated by the presence of complex, unsteady separated flow structures. The understanding and quantification of such flow effects remains a substantial challenge to the combat aircraft designer. The challenge, especially during conceptual and preliminary design stages, is to obtain sufficiently accurate information to make relevant design decisions, addressing potential weaknesses before proceeding to detail design. The focus in the present review is on the application of the water tunnel in such cases. The combination of qualitative and quantitative data obtainable from the water tunnel provides a useful complement to other tools during the early design stages. The effect of Reynolds number in particular is however critical; and appreciation of its effects are critical to the effective use of such a tool. It is shown however that for certain configurations such effects can be small in comparison to other experimental effects.

    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-29478 (URN)10.1016/j.paerosci.2005.05.001 (DOI)14832 (Local ID)14832 (Archive number)14832 (OAI)
    Available from: 2009-10-09 Created: 2009-10-09 Last updated: 2017-12-13
    3. Wing weight estimation using an automated CAD-model
    Open this publication in new window or tab >>Wing weight estimation using an automated CAD-model
    (English)Manuscript (preprint) (Other academic)
    Abstract [en]

    Advantages and possibilities offered by modern CAD tools in conceptual design are discussed. In order to illustrate these possibilities, a Computer Integrated (CI) method to estimate weight in conceptual design is presented. The CI method is based on geometry and simple load analysis; the weight is determined from a 3D computer model. The CI method is a compromise between empirical methods and time-consuming methods based on finite element analysis. The CI method allows investigation of unconventional and conventional configuration, and possibility of creating different structure layouts. The method has been applied on commercial aircraft for validation. The presented results have been compared with, other available methods in conceptual design. In addition to weight estimation, modern CAD programs offer integration and data exchange with other domains such as computational fluid dynamics, system simulation and production analysis and planning.

    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-86271 (URN)
    Available from: 2012-12-12 Created: 2012-12-12 Last updated: 2012-12-12
    4. Unsteady aerodynamic modelling: a simple state-space approach
    Open this publication in new window or tab >>Unsteady aerodynamic modelling: a simple state-space approach
    2005 (English)In: Proc. of 43rd AIAA Annual Meeting and Exhibits, Reno, Nevada: AIAAA , 2005Conference paper, Published paper (Refereed)
    Abstract [en]

    A simple mathematical prediction model for high angles of attack aerodynamics, including dynamic effect over delta wings, and an extension to full configuration is presented. The model presented is intended for application in conceptual design and is extended to parameters identifications in preliminary design with validation against experimental data. The aerodynamic model is based on leading edge suction analogy. In order to extend it to high angles of attack and dynamic motions, internal state variables are used to describe the different flow conditions, or state, over the wing/aircraft. In conceptual design the parameters used are determined from geometrical considerations and analogies with delta wings. To extend the mathematical mode to later design phases and augment the accuracy, the parameters are determined from wind tunnel data, in static case the present model has been extended to sideslip. The results obtained shows high accuracy in both static and dynamic cases.

    Place, publisher, year, edition, pages
    Reno, Nevada: AIAAA, 2005
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-31408 (URN)10.2514/6.2005-855 (DOI)17179 (Local ID)17179 (Archive number)17179 (OAI)
    Conference
    43rd AIAA Annual Meeting and Exhibits, Reno, Nevada, USA, 2005
    Note

    Proceedings on CD

    Available from: 2009-10-09 Created: 2009-10-09 Last updated: 2012-12-12
    5. Influences of unsteady aerodynamic in conceptual design
    Open this publication in new window or tab >>Influences of unsteady aerodynamic in conceptual design
    (English)Manuscript (preprint) (Other academic)
    Abstract [en]

    Integration of unsteady and high-angles aerodyuamics is often done late in aircraft design. An attempt to integrate these aspects in conceptual and preliminary design is presented here. A simple aerodynamic model has been developed and used in conceptual design to study the influences of dynamic effects on platform geometry during high angular rate manoeuvres. In order to include these effects in conceptual design, flight simulation has been coupled with classic sizing and turn rate performance is included in the requirements for conceptual sizing. In one case, the sizing and simulation are performed with static aerodynamics, in the other case dynamic effects are included . The impact of large augular rate and its significance for open loop simulation is presented in the form of a pitch up manoeuver.

    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-86277 (URN)
    Available from: 2012-12-12 Created: 2012-12-12 Last updated: 2012-12-12
  • 12.
    Jouannet, Christopher
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Modelling of unsteady aerodynamics for aircraft design2003Licentiate thesis, comprehensive summary (Other academic)
    Abstract [en]

    This thesis present a simple mathematical prediction model for high angles of attack aerodynamics, including dynamic effects over delta wings, and an extension to full configuration. The model presented is intended for application in conceptual design and is extended to parameters identifications in preliminary design with validation against experimental data.

    The aerodynamic model is based on leading edge suction analogy. In order to extend it to high angles of attack and dynamic motions, internal state variables are used to describe the different flow conditions, or state, over the wing/aircraft.

    In conceptual design the parameters used are determined from geometrical considerations and analogies with delta wings. For slender delta wings, the parameters are determined from flow visualisation, determining the three transition states used here; potential, vortex and fully separated. Results from conceptual design have shown good agreement with published data and demonstrates the usefulness of integration of dynamic effects in aerodynamic predictions. To extend the mathematical model to later design phases and augment the accuracy, the parameters were determined from wind tunnel data. The results obtained then showed high accuracy in both static and dynamic cases.

    The results obtained both in conceptual design and from parameters identifications are suitable for flight simulation and stability analyses, and will allow the aircraft designer to increase his knowledge of the behaviour at high angles of attack and large pitch motions. The present model allows to keep the same mathematical structure through the entire design, the parameters being refined when new data is available from wind tunnel tests or CDF or flight tests.

    The present model will be included in a distributed aircraft analyse to simulate the whole aircraft including systems and sub-systems.

    List of papers
    1. Lift Coefficient Predictions for Delta Wing Under Pitching Motions
    Open this publication in new window or tab >>Lift Coefficient Predictions for Delta Wing Under Pitching Motions
    2002 (English)In: 32nd AIAA Fluid Dynamics Conference Proceedings (2002), USA: AIAA , 2002, p. AIAA-2002-2969-Conference paper, Published paper (Refereed)
    Abstract [en]

    An analytic prediction method is presented to estimate the lift coefficient of delta wings under pitching motions. The method is based on the leading edge suction analogy, with regards to the dynamic effect resulting in the unsteady behaviour. The goal of the method is to provide suitable lift equation for use in simulation in preliminary design.

    Place, publisher, year, edition, pages
    USA: AIAA, 2002
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-40982 (URN)10.2514/6.2002-2969 (DOI)54814 (Local ID)54814 (Archive number)54814 (OAI)
    Conference
    32nd AIAA Fluid Dynamics Conference. 24 June 2002 - 26 June 2002. St. Louis, Missouri.
    Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
    2. Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings
    Open this publication in new window or tab >>Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings
    2002 (English)In: Proceedings 23rd International Congress of Aeronautical Sciences (ICAS), Toronto: ICAS , 2002Conference paper, Published paper (Refereed)
    Abstract [en]

    An analytic prediction model is presented to estimate aerodynamic coefficient of delta wing undergoing dynamic motions. The model is based on the introduction of a state space variable describing the vortex breakdown. This model will be suitable for modeling of flight dynamics in the preliminary design phase.

    Place, publisher, year, edition, pages
    Toronto: ICAS, 2002
    Keywords
    delta wings, unsteady, modeling, preliminary design, aerodynamic coefficient
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-40989 (URN)54823 (Local ID)0-9533991-3-3 (ISBN)54823 (Archive number)54823 (OAI)
    Conference
    23nd Congress of International Council of the Aeronautical Sciences, Toronto, Canda, 2002 (ICAS 2002)
    Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
    3. Aircraft manoeuvers simulation, steady and unsteady aerodynamic
    Open this publication in new window or tab >>Aircraft manoeuvers simulation, steady and unsteady aerodynamic
    2003 (English)In: SAE Technical Paper, Montreal, Canada: World Aviation Congress , 2003, p. 2003-01-3034-Conference paper, Published paper (Refereed)
    Abstract [en]

    The current work present a simple model to integrate non-linear aerodynamic in conceptual design phase, before wind tunnel testing. A presentation of a simple pitch up maneuver based on three different aerodynamic models is simulated. The simulation indicates different behaviors depending on the aerodynamic model, and shows the importance of including unsteady aerodynamic.

    Place, publisher, year, edition, pages
    Montreal, Canada: World Aviation Congress, 2003
    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-36426 (URN)10.4271/2003-01-3034 (DOI)31303 (Local ID)31303 (Archive number)31303 (OAI)
    Conference
    World Aviation Congress, Montreal, Canada. 9-11 September 2003
    Available from: 2009-10-10 Created: 2009-10-10 Last updated: 2013-12-12
    4. Distributed aircraft analysis using web service technology
    Open this publication in new window or tab >>Distributed aircraft analysis using web service technology
    2003 (English)In: SAE Technical Paper, 2003, p. 2003-01-3007-Conference paper, Published paper (Refereed)
    Abstract [en]

    The design modern aircraft requires integration of multidisciplinary models for analysis in early design phase to increase the chances of a successful project. In this paper, a framework for distributed aircraft analysis in the conceptual design including several domains is presented. The framework is based on so-called W eb service standards, allowing integration of distributed models for system simulation and optimization using standardized interfaces. The analysis is controlled by a so-called sequencer which manages the interaction between simulation modules and an XML-based design data repository. This repository includes all design data and an executable process description defining the sequence for execution of the modules.

    In the paper, the framework with underlying concepts is described. The approach is further illustrated using the design of an Unmanned Aerial Vehicle as an example. This includes the definition of the simulation modules, the process model and definition and execution of an optimization problem.

    National Category
    Engineering and Technology
    Identifiers
    urn:nbn:se:liu:diva-102504 (URN)10.4271/2003-01-3007 (DOI)
    Conference
    World Aviation Congress. Montreal, Canada. 9-11 September, 2003
    Available from: 2013-12-12 Created: 2013-12-12 Last updated: 2013-12-12
  • 13.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Sub-Scale Flight Testing - Project Course2005Report (Other academic)
  • 14.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Andersson, Lars
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Sethson, Magnus
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Design process for micro air vehicles2003In: Bristol International UAV systems conference,2003, Bristol, UK: UAV , 2003Conference paper (Refereed)
    Abstract [en]

      

  • 15.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems.
    Berry, Patrick
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design.
    Aircraft design education at Linköpings University2007In: 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, no 2, p. 217-224Article in journal (Refereed)
    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.

  • 16.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Berry, Patrick
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    MANTA - From conceptual design to flight test2005In: European Workshop on Aircraft Design Education,2005, 2005Conference paper (Other academic)
  • 17.
    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.

  • 18.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Eguerev Rib. Da Silv, Sergio
    Linköping University, Department of Mechanical Engineering.
    Krus, Petter
    Linköping University, Department of Mechanical Engineering.
    Use of CAD Tools for Weight Estimation in Aircraft Conceptual Design2004In: 24th International Congress of the Aeronautical Sciences,2004, 2004Conference paper (Other academic)
  • 19.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Mechanical Engineering, Machine Design. Linköping University, The Institute of Technology.
    Aircraft manoeuvers simulation, steady and unsteady aerodynamic2003In: SAE Technical Paper, Montreal, Canada: World Aviation Congress , 2003, p. 2003-01-3034-Conference paper (Refereed)
    Abstract [en]

    The current work present a simple model to integrate non-linear aerodynamic in conceptual design phase, before wind tunnel testing. A presentation of a simple pitch up maneuver based on three different aerodynamic models is simulated. The simulation indicates different behaviors depending on the aerodynamic model, and shows the importance of including unsteady aerodynamic.

  • 20.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    An empirical model for delta wing vortex breakdown location in sideslip condition2003In: Atmospheric flight mechanics,2003, Austin, USA: AIAA , 2003Conference paper (Refereed)
    Abstract [en]

      

  • 21.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    An Empirical Model for Delta Wing Vortex Breakdown Location in Sideslip Condition2003In: AIAA Atmospheric Flight Mechanics Conference and Exhibit,2003, USA: AIAA , 2003Conference paper (Refereed)
  • 22.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Direct Simulation Based Optimization for Aircraft Design Including Systems2006In: AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference,2006, Portsmouth, USA: AIAA/ISSMO , 2006Conference paper (Other academic)
  • 23.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    Direct Simulation-Based Optimization for Aircraft Conceptual Design2007In: AIAA ATIO Conf,2007, USA: AIAA , 2007Conference paper (Refereed)
  • 24.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Influences of unsteady aerodynamic in conceptual designManuscript (preprint) (Other academic)
    Abstract [en]

    Integration of unsteady and high-angles aerodyuamics is often done late in aircraft design. An attempt to integrate these aspects in conceptual and preliminary design is presented here. A simple aerodynamic model has been developed and used in conceptual design to study the influences of dynamic effects on platform geometry during high angular rate manoeuvres. In order to include these effects in conceptual design, flight simulation has been coupled with classic sizing and turn rate performance is included in the requirements for conceptual sizing. In one case, the sizing and simulation are performed with static aerodynamics, in the other case dynamic effects are included . The impact of large augular rate and its significance for open loop simulation is presented in the form of a pitch up manoeuver.

  • 25.
    Jouannet, Christopher
    et al.
    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, Machine Design. Linköping University, The Institute of Technology.
    Lift Coefficient Predictions for Delta Wing Under Pitching Motions2002In: 32nd AIAA Fluid Dynamics Conference Proceedings (2002), USA: AIAA , 2002, p. AIAA-2002-2969-Conference paper (Refereed)
    Abstract [en]

    An analytic prediction method is presented to estimate the lift coefficient of delta wings under pitching motions. The method is based on the leading edge suction analogy, with regards to the dynamic effect resulting in the unsteady behaviour. The goal of the method is to provide suitable lift equation for use in simulation in preliminary design.

  • 26.
    Jouannet, Christopher
    et al.
    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, Machine Design. Linköping University, The Institute of Technology.
    Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings2002In: Proceedings 23rd International Congress of Aeronautical Sciences (ICAS), Toronto: ICAS , 2002Conference paper (Refereed)
    Abstract [en]

    An analytic prediction model is presented to estimate aerodynamic coefficient of delta wing undergoing dynamic motions. The model is based on the introduction of a state space variable describing the vortex breakdown. This model will be suitable for modeling of flight dynamics in the preliminary design phase.

  • 27.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    Modelling of High Angle of Attack Aerodynamic2007In: AIAA Applied Aerodynamics Conference,2007, USA: AIAA , 2007Conference paper (Refereed)
  • 28.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems .
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Management and Engineering, Machine Design .
    Modelling of High Angle of Attack Aerodynamic, a State-Space Approach2006In: AIAA Applied Aerodynamics Conference,2006, USA: AIAA , 2006Conference paper (Refereed)
  • 29.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Sideslip effect on a series of delta wings, flow visualization results2003In: International Conference on Advanced Engineering Design,2003, Prague, Czech republic: Advanced Engineering Design , 2003Conference paper (Refereed)
    Abstract [en]

        

  • 30.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering. Linköping University, The Institute of Technology.
    Unsteady aerodynamic modelling: a simple state-space approach2005In: Proc. of 43rd AIAA Annual Meeting and Exhibits, Reno, Nevada: AIAAA , 2005Conference paper (Refereed)
    Abstract [en]

    A simple mathematical prediction model for high angles of attack aerodynamics, including dynamic effect over delta wings, and an extension to full configuration is presented. The model presented is intended for application in conceptual design and is extended to parameters identifications in preliminary design with validation against experimental data. The aerodynamic model is based on leading edge suction analogy. In order to extend it to high angles of attack and dynamic motions, internal state variables are used to describe the different flow conditions, or state, over the wing/aircraft. In conceptual design the parameters used are determined from geometrical considerations and analogies with delta wings. To extend the mathematical mode to later design phases and augment the accuracy, the parameters are determined from wind tunnel data, in static case the present model has been extended to sideslip. The results obtained shows high accuracy in both static and dynamic cases.

  • 31.
    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.

  • 32.
    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]

      

  • 33.
    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.

  • 34.
    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

  • 35.
    Jouannet, Christopher
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Munro, Cameron
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering.
    Water tunnel investigation of chined fore body characteristics at high angles of attack2003In: Applied Aerodynamic Conference,2003, Orlando, USA: AIAA , 2003Conference paper (Refereed)
    Abstract [en]

        

  • 36.
    Jouannet, Christopher
    et al.
    Linköping University, Department of Mechanical Engineering. Linköping University, The Institute of Technology.
    Silva, Sergio E. R.
    Linköping University, Department of Mechanical Engineering. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Mechanical Engineering. Linköping University, The Institute of Technology.
    Wing weight estimation using an automated CAD-modelManuscript (preprint) (Other academic)
    Abstract [en]

    Advantages and possibilities offered by modern CAD tools in conceptual design are discussed. In order to illustrate these possibilities, a Computer Integrated (CI) method to estimate weight in conceptual design is presented. The CI method is based on geometry and simple load analysis; the weight is determined from a 3D computer model. The CI method is a compromise between empirical methods and time-consuming methods based on finite element analysis. The CI method allows investigation of unconventional and conventional configuration, and possibility of creating different structure layouts. The method has been applied on commercial aircraft for validation. The presented results have been compared with, other available methods in conceptual design. In addition to weight estimation, modern CAD programs offer integration and data exchange with other domains such as computational fluid dynamics, system simulation and production analysis and planning.

  • 37.
    Krus, Petter
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Jouannet, Christopher
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Whole Mission Simulation for Aircraft Preliminary Design2010In: 48th AIAA Aerospace Sciences Meeting, AIAA , 2010Conference paper (Other academic)
    Abstract [en]

    Developments in computational hardware and simulation software have come to a point where it is possible to use whole mission simulation in the preliminary design. This paper address some key issues needed to realize this. These are, system simulation using distributed solvers for robust large scale simulation, time scale compression to deal with the widely different time scales involved, e.g. the transient behaviour of control surface actuators, to the tracking of fuel consumption. The application is a flight simulation model with subsystems such as control surface actuators. In this way it is possible to do real time simulation (RTS) and faster than real time simulation (FRTS) of rather complex systems. Using such models it is possible to do design analysis, e.g sensitivity analysis and trade of analysis, as well as design optimisation, In this paper this is demonstrated on a flight simulation model with subsystems, such as control surface actuators.

  • 38.
    Melin, Tomas
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. 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.
    Wing profile performance variations influenced by manufacturing tolerances2013Conference paper (Other academic)
    Abstract [en]

    The sensitivity of wing profile performance metrics as a function of manufacturing tolerances and operational environment influence was studied using a numerical simulation. By employing a Monte-Carlo approach of varying the geometrical properties of a set of wing profiles, the sensitivity and statistical response was found, which in turn gives an indication towards both the most critical geometrical features and to which airfoil is the most robust with respect to constructions errors and operational fouling.

  • 39.
    Munjulury, Raghu Chaitanya
    et al.
    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.
    Abdalla, Alvaro Martins
    The University of São Paulo (USP), Brazil.
    Melin, Tomas
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. 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.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Knowledge-based design for future combat aircraft concepts2014Conference paper (Refereed)
    Abstract [en]

    A new fighter aircraft will most likely be acollaborative project. In this study conceptualknowledge-based design is demonstrated, usingmodels of comparable fidelity for sizing, geometrydesign, aerodynamic analysis and system simulationfor aircraft conceptual design. A newgeneration fighter is likely to involve advancedcontrol concept where an assessment of feasibilitythrough simulation is needed already atthe conceptual stage. This co-design leads to adeeper understanding of the trade-offs involved.In this paper a study for a future combat aircraftis made. Conceptual knowledge-based design isdemonstrated by optimizing for a design mission,including a super-cruise segment.

  • 40.
    Munro, Cameron
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Correlation of flow visualization and force and moment measurements in a water tunnel2003In: The World Aviation Congress,2003, Montreal, Canada: World Aviation Congress , 2003Conference paper (Refereed)
    Abstract [en]

       

  • 41.
    Munro, Cameron
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Flow visualisation and force and moment correlations in a water tunnel2003In: Triennial International Symposium on Fluid Control,2003, 2003Conference paper (Other academic)
    Abstract [en]

      

  • 42.
    Munro, Cameron
    et al.
    Linköping University, Department of Mechanical Engineering.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Statistical Study of Unmanned Air Vehicles for the Platform Designer2003In: 3rd International Conference on Advanced Engineering Design,2003, 2003Conference paper (Refereed)
  • 43.
    Munro, Cameron
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Krus, Petter
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Machine Design.
    Statistical survey of unmanned air vehicles for the platform designer2004In: International Conference on Advanced Engineering Design,2003, Prague, Czech republic: Advanced Engineering Design , 2004Conference paper (Refereed)
    Abstract [en]

      

  • 44.
    Munro, Cameron
    et al.
    Linköping University, Department of Mechanical Engineering. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Mechanical Engineering. Linköping University, The Institute of Technology.
    Jouannet, Christopher
    Linköping University, Department of Mechanical Engineering. Linköping University, The Institute of Technology.
    Implications of scale effect for the prediction of high angle of attack aerodynamics2005In: Progress in Aerospace Sciences, ISSN 0376-0421, E-ISSN 1873-1724, ISSN 0376-0421, Vol. 41, no 3-4, p. 301-322Article in journal (Refereed)
    Abstract [en]

    Scale effect is of significance in all experimental aerodynamics testing. At high angles of attack such issues as Reynolds and Mach number scaling are further complicated by the presence of complex, unsteady separated flow structures. The understanding and quantification of such flow effects remains a substantial challenge to the combat aircraft designer. The challenge, especially during conceptual and preliminary design stages, is to obtain sufficiently accurate information to make relevant design decisions, addressing potential weaknesses before proceeding to detail design. The focus in the present review is on the application of the water tunnel in such cases. The combination of qualitative and quantitative data obtainable from the water tunnel provides a useful complement to other tools during the early design stages. The effect of Reynolds number in particular is however critical; and appreciation of its effects are critical to the effective use of such a tool. It is shown however that for certain configurations such effects can be small in comparison to other experimental effects.

  • 45.
    Papageorgiou, Athanasios
    et al.
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, Faculty of Science & Engineering.
    Amadori, Kristian
    Linköping University, Department of Management and Engineering, Machine Design. 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.
    Ölvander, Johan
    Linköping University, Department of Management and Engineering, Machine Design. Linköping University, Faculty of Science & Engineering.
    Multidisciplinary Optimization of Unmanned Aircraft in a System of Systems Context2018Conference paper (Other academic)
    Abstract [en]

    This paper explores the use of Multidisciplinary Design Optimization (MDO) in the development of Unmanned Aerial Vehicles (UAVs) when the requirements include a collaboration in a System of Systems (SoS) environment. In this work, the framework considers models that can capture the mission, stealth, and surveillance performance of each aircraft, while at the same time, a dedicated simulation module assesses the total cooperation effect on a given operational scenario. The resulting mixed continuous and integer variable problem is decomposed with a multi-level architecture, and in particular, it is treated as a fleet allocation problem that includes a nested optimization routine for sizing a “yet-to-be-designed” aircraft. Overall, the models and the framework are evaluated through a series of optimization runs, and the obtained Pareto front is compared with the results from a traditional aircraft mission planning method in order to illustrate the benefits of this SoS approach in the design of UAVs.

  • 46.
    Rösth, Marcus
    et al.
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Jouannet, Christopher
    Linköping University, The Institute of Technology. Linköping University, Department of Mechanical Engineering, Fluid and Mechanical Engineering Systems.
    Static calculation on hydraulic power steering, special regards on catch up effect2005Report (Other academic)
  • 47.
    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.

  • 48.
    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.

  • 49.
    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.

  • 50.
    Venkata, Raghu. C. M.
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Tarkian, Mehdi
    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.
    Model Based Aircraft Control System Design And Simulation2010In: 27th Congress of the International Council of the Aeronautical Sciences 2010 (ICAS 2010), Proceedings of a meeting held 19-24 September 2010, Nice, France. / [ed] Professor I Grant, Optimage Ltd. on behalf of the International Council of the Aeronautical Sciences (ICAS) , 2010, p. 3338-3347Conference paper (Refereed)
    Abstract [en]

    Development of modern aircrafts has become more and more expensive and time consuming. In order to minimize the development cost, an improvement of the conceptual design phase is needed. The desired goal of the project is to enhance the functionality of an in house produced framework conducted at theDepartment of Machine Design, Link¨ping University, consisting of parametric aircraft models used for conceptual design. The former part of the work consists of the construction of geometric aircraft control surfaces such as flaps, aileron, rudder and elevator parametrically in CATIA V5. The next part of the work involves designing and simulating an Inverse dynamic model in Dymola software. An Excel interface has been developed between CATIA and Dymola. Parameters can be varied in the interface as per user specification; these values are sent to CATIA or Dymola and vice versa. The constructed concept model of control surfaces has been tested for different aircraft shapes and layout. An interface is developed between CATIA, Dymola and Tornado. An optimization case is performed to visualize the automation capability of choosing an actuator from a database for the proposed framework, and enhance the early design phases for aircraft conceptual design.

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