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  • 1.
    Amadori, Kristian
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Development of a subscale flight testing platform for a generic future fighter2010Konferensbidrag (Refereegranskat)
    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.

    Ladda ner fulltext (pdf)
    ICAS2010_477
  • 2.
    Amadori, Kristian
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    A Framework for Aerodynamic and Structural Optimization in Conceptual Design2007Ingår i: 25th AIAA Applied Aerodynamics Conference, 25-28 June, Miami, FL, USA, AIAA , 2007, s. 4061-Konferensbidrag (Övrigt vetenskapligt)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Aircraft Conceptual Design Optimization2008Ingår i: International Congress of the Aeronautical Sciences ICAS,2008, Stockholm, Sweden: ICAS , 2008Konferensbidrag (Refereegranskat)
    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.  

    Ladda ner fulltext (pdf)
    fulltext
  • 4.
    Amadori, Kristian
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Use of Panel Code Modeling in a Framework for Aircraft Concept Optimization2006Ingår i: 11th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 6-8 September, Portsmouth, Virginia, USA, 2006, s. 7084-Konferensbidrag (Övrigt vetenskapligt)
    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.

    Ladda ner fulltext (pdf)
    fulltext
  • 5.
    Johansson, Björn
    et al.
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Distributed aircraft analysis using web service technology2003Ingår i: SAE Technical Paper, 2003, s. 2003-01-3007-Konferensbidrag (Refereegranskat)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Distributed aircraft analysis using web service technology2004Ingår i: The World Aviation Congress,2003, Montreal, Canada: World Aviation Congress , 2004Konferensbidrag (Refereegranskat)
  • 7.
    Johansson, Björn
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Distributed aircraft analysis using web service technology2003Ingår i: SAE Transactions Journal of Aerospace, ISSN 0096-736X, Vol. 112, nr 1, s. 445-453Artikel i tidskrift (Refereegranskat)
    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
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Aircraft project 2007 - Linköpings University RAVEN Biz Jet Medivac2007Ingår i: European Workshop on Aircraft Design Education,2007, 2007Konferensbidrag (Övrigt vetenskapligt)
    Abstract [sv]

      

  • 9.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Bizjet demonstrator, En dynamisk skalad jetmodell2007Ingår i: FLYGTEKNIK 2007,2007, 2007Konferensbidrag (Övrigt vetenskapligt)
  • 10.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Jet Version of a Research UAV Design Study2005Rapport (Övrigt vetenskapligt)
  • 11.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Model based aircraft design: high angle of attack aerodynamics and weight estimation methods2005Doktorsavhandling, sammanläggning (Övrigt vetenskapligt)
    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.

    Delarbeten
    1. Distributed aircraft analysis using web service technology
    Öppna denna publikation i ny flik eller fönster >>Distributed aircraft analysis using web service technology
    2003 (Engelska)Ingår i: SAE Transactions Journal of Aerospace, ISSN 0096-736X, Vol. 112, nr 1, s. 445-453Artikel i tidskrift (Refereegranskat) 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.

    Ort, förlag, år, upplaga, sidor
    New York: , 2003
    Nyckelord
    aircraft analysis, web service technology
    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-23789 (URN)3306 (Lokalt ID)3306 (Arkivnummer)3306 (OAI)
    Tillgänglig från: 2009-10-07 Skapad: 2009-10-07 Senast uppdaterad: 2012-12-12
    2. Implications of scale effect for the prediction of high angle of attack aerodynamics
    Öppna denna publikation i ny flik eller fönster >>Implications of scale effect for the prediction of high angle of attack aerodynamics
    2005 (Engelska)Ingår i: Progress in Aerospace Sciences, ISSN 0376-0421, E-ISSN 1873-1724, ISSN 0376-0421, Vol. 41, nr 3-4, s. 301-322Artikel i tidskrift (Refereegranskat) 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.

    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-29478 (URN)10.1016/j.paerosci.2005.05.001 (DOI)14832 (Lokalt ID)14832 (Arkivnummer)14832 (OAI)
    Tillgänglig från: 2009-10-09 Skapad: 2009-10-09 Senast uppdaterad: 2017-12-13
    3. Wing weight estimation using an automated CAD-model
    Öppna denna publikation i ny flik eller fönster >>Wing weight estimation using an automated CAD-model
    (Engelska)Manuskript (preprint) (Övrigt vetenskapligt)
    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.

    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-86271 (URN)
    Tillgänglig från: 2012-12-12 Skapad: 2012-12-12 Senast uppdaterad: 2012-12-12
    4. Unsteady aerodynamic modelling: a simple state-space approach
    Öppna denna publikation i ny flik eller fönster >>Unsteady aerodynamic modelling: a simple state-space approach
    2005 (Engelska)Ingår i: Proc. of 43rd AIAA Annual Meeting and Exhibits, Reno, Nevada: AIAAA , 2005Konferensbidrag, Publicerat paper (Refereegranskat)
    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.

    Ort, förlag, år, upplaga, sidor
    Reno, Nevada: AIAAA, 2005
    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-31408 (URN)10.2514/6.2005-855 (DOI)17179 (Lokalt ID)17179 (Arkivnummer)17179 (OAI)
    Konferens
    43rd AIAA Annual Meeting and Exhibits, Reno, Nevada, USA, 2005
    Anmärkning

    Proceedings on CD

    Tillgänglig från: 2009-10-09 Skapad: 2009-10-09 Senast uppdaterad: 2012-12-12
    5. Influences of unsteady aerodynamic in conceptual design
    Öppna denna publikation i ny flik eller fönster >>Influences of unsteady aerodynamic in conceptual design
    (Engelska)Manuskript (preprint) (Övrigt vetenskapligt)
    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.

    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-86277 (URN)
    Tillgänglig från: 2012-12-12 Skapad: 2012-12-12 Senast uppdaterad: 2012-12-12
  • 12.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Modelling of unsteady aerodynamics for aircraft design2003Licentiatavhandling, sammanläggning (Övrigt vetenskapligt)
    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.

    Delarbeten
    1. Lift Coefficient Predictions for Delta Wing Under Pitching Motions
    Öppna denna publikation i ny flik eller fönster >>Lift Coefficient Predictions for Delta Wing Under Pitching Motions
    2002 (Engelska)Ingår i: 32nd AIAA Fluid Dynamics Conference Proceedings (2002), USA: AIAA , 2002, s. AIAA-2002-2969-Konferensbidrag, Publicerat paper (Refereegranskat)
    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.

    Ort, förlag, år, upplaga, sidor
    USA: AIAA, 2002
    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-40982 (URN)10.2514/6.2002-2969 (DOI)54814 (Lokalt ID)54814 (Arkivnummer)54814 (OAI)
    Konferens
    32nd AIAA Fluid Dynamics Conference. 24 June 2002 - 26 June 2002. St. Louis, Missouri.
    Tillgänglig från: 2009-10-10 Skapad: 2009-10-10 Senast uppdaterad: 2013-12-12
    2. Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings
    Öppna denna publikation i ny flik eller fönster >>Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings
    2002 (Engelska)Ingår i: Proceedings 23rd International Congress of Aeronautical Sciences (ICAS), Toronto: ICAS , 2002Konferensbidrag, Publicerat paper (Refereegranskat)
    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.

    Ort, förlag, år, upplaga, sidor
    Toronto: ICAS, 2002
    Nyckelord
    delta wings, unsteady, modeling, preliminary design, aerodynamic coefficient
    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-40989 (URN)54823 (Lokalt ID)0-9533991-3-3 (ISBN)54823 (Arkivnummer)54823 (OAI)
    Konferens
    23nd Congress of International Council of the Aeronautical Sciences, Toronto, Canda, 2002 (ICAS 2002)
    Tillgänglig från: 2009-10-10 Skapad: 2009-10-10 Senast uppdaterad: 2013-12-12
    3. Aircraft manoeuvers simulation, steady and unsteady aerodynamic
    Öppna denna publikation i ny flik eller fönster >>Aircraft manoeuvers simulation, steady and unsteady aerodynamic
    2003 (Engelska)Ingår i: SAE Technical Paper, Montreal, Canada: World Aviation Congress , 2003, s. 2003-01-3034-Konferensbidrag, Publicerat paper (Refereegranskat)
    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.

    Ort, förlag, år, upplaga, sidor
    Montreal, Canada: World Aviation Congress, 2003
    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-36426 (URN)10.4271/2003-01-3034 (DOI)31303 (Lokalt ID)31303 (Arkivnummer)31303 (OAI)
    Konferens
    World Aviation Congress, Montreal, Canada. 9-11 September 2003
    Tillgänglig från: 2009-10-10 Skapad: 2009-10-10 Senast uppdaterad: 2013-12-12
    4. Distributed aircraft analysis using web service technology
    Öppna denna publikation i ny flik eller fönster >>Distributed aircraft analysis using web service technology
    2003 (Engelska)Ingår i: SAE Technical Paper, 2003, s. 2003-01-3007-Konferensbidrag, Publicerat paper (Refereegranskat)
    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.

    Nationell ämneskategori
    Teknik och teknologier
    Identifikatorer
    urn:nbn:se:liu:diva-102504 (URN)10.4271/2003-01-3007 (DOI)
    Konferens
    World Aviation Congress. Montreal, Canada. 9-11 September, 2003
    Tillgänglig från: 2013-12-12 Skapad: 2013-12-12 Senast uppdaterad: 2013-12-12
  • 13.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Sub-Scale Flight Testing - Project Course2005Rapport (Övrigt vetenskapligt)
  • 14.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Andersson, Lars
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Sethson, Magnus
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Design process for micro air vehicles2003Ingår i: Bristol International UAV systems conference,2003, Bristol, UK: UAV , 2003Konferensbidrag (Refereegranskat)
    Abstract [en]

      

  • 15.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Aircraft design education at Linköpings University2007Ingår i: Proceedings of the Institution of Mechanical Engineers. Part G, Journal of Aerospace Engineering, ISSN 0954-4100, E-ISSN 2041-3025, ISSN 0954-4100, Vol. 221, nr 2, s. 217-224Artikel i tidskrift (Refereegranskat)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    MANTA - From conceptual design to flight test2005Ingår i: European Workshop on Aircraft Design Education,2005, 2005Konferensbidrag (Övrigt vetenskapligt)
  • 17.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Subscale flight testing used in conceptual design2012Ingår i: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 84, nr 3, s. 192-199Artikel i tidskrift (Refereegranskat)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Eguerev Rib. Da Silv, Sergio
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Krus, Petter
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Use of CAD Tools for Weight Estimation in Aircraft Conceptual Design2004Ingår i: 24th International Congress of the Aeronautical Sciences,2004, 2004Konferensbidrag (Övrigt vetenskapligt)
  • 19.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Aircraft manoeuvers simulation, steady and unsteady aerodynamic2003Ingår i: SAE Technical Paper, Montreal, Canada: World Aviation Congress , 2003, s. 2003-01-3034-Konferensbidrag (Refereegranskat)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    An empirical model for delta wing vortex breakdown location in sideslip condition2003Ingår i: Atmospheric flight mechanics,2003, Austin, USA: AIAA , 2003Konferensbidrag (Refereegranskat)
    Abstract [en]

      

  • 21.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    An Empirical Model for Delta Wing Vortex Breakdown Location in Sideslip Condition2003Ingår i: AIAA Atmospheric Flight Mechanics Conference and Exhibit,2003, USA: AIAA , 2003Konferensbidrag (Refereegranskat)
  • 22.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Direct Simulation Based Optimization for Aircraft Design Including Systems2006Ingår i: AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference,2006, Portsmouth, USA: AIAA/ISSMO , 2006Konferensbidrag (Övrigt vetenskapligt)
  • 23.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Direct Simulation-Based Optimization for Aircraft Conceptual Design2007Ingår i: AIAA ATIO Conf,2007, USA: AIAA , 2007Konferensbidrag (Refereegranskat)
  • 24.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Influences of unsteady aerodynamic in conceptual designManuskript (preprint) (Övrigt vetenskapligt)
    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.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Lift Coefficient Predictions for Delta Wing Under Pitching Motions2002Ingår i: 32nd AIAA Fluid Dynamics Conference Proceedings (2002), USA: AIAA , 2002, s. AIAA-2002-2969-Konferensbidrag (Refereegranskat)
    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.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Modeling of Unsteady Aerodynamic Charactersitics of Delta Wings2002Ingår i: Proceedings 23rd International Congress of Aeronautical Sciences (ICAS), Toronto: ICAS , 2002Konferensbidrag (Refereegranskat)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Modelling of High Angle of Attack Aerodynamic2007Ingår i: AIAA Applied Aerodynamics Conference,2007, USA: AIAA , 2007Konferensbidrag (Refereegranskat)
  • 28.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Modelling of High Angle of Attack Aerodynamic, a State-Space Approach2006Ingår i: AIAA Applied Aerodynamics Conference,2006, USA: AIAA , 2006Konferensbidrag (Refereegranskat)
  • 29.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Sideslip effect on a series of delta wings, flow visualization results2003Ingår i: International Conference on Advanced Engineering Design,2003, Prague, Czech republic: Advanced Engineering Design , 2003Konferensbidrag (Refereegranskat)
    Abstract [en]

        

  • 30.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling. Linköpings universitet, Tekniska högskolan.
    Unsteady aerodynamic modelling: a simple state-space approach2005Ingår i: Proc. of 43rd AIAA Annual Meeting and Exhibits, Reno, Nevada: AIAAA , 2005Konferensbidrag (Refereegranskat)
    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.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Design and Flight Testing of an ECO-Sport Aircraft2010Konferensbidrag (Övrigt vetenskapligt)
    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.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Lundström, David
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Amadori, Kristian
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion.
    Berry, Patrick
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik.
    Design of a Very Light Jet and a Dynamically Scaled Demonstrator2008Ingår i: AIAA Aerospace Sciences Meeting and Exhibit,2008, USA: AIAA , 2008Konferensbidrag (Refereegranskat)
    Abstract [en]

      

  • 33.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Morphing Wing Design, from Study to Flight Test2009Konferensbidrag (Refereegranskat)
    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.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Sobron, Alejandro
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Annes da Silva, Roberto Gil
    Instituto Tecnológico de Aeronáutica, São José dos Campos, Brazil.
    Catalano, Fernando
    USP, San Carlos, Brazil.
    Greco, Paulo
    USP, San Carlos, Brazil.
    Aerodynamic database of a subscale demonstrator2017Ingår i: 35th AIAA Applied Aerodynamics Conference, Reston, VA, USA, 2017, artikel-id 2017-4075Konferensbidrag (Refereegranskat)
    Abstract [en]

    This paper reports the current status of a joint Swedish-Brazilian research project aiming at exploring sub scale flight testing. A 13% scale fighter aircraft is used as a test bench for developing methods and procedures for data acquisition. This paper will present an aerodynamic database as a partial result of the collaborative project.

  • 35.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Lundström, David
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Berry, Patrick
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Design and Flight Testing of a Solar Powered Aircraft, a Student Challenge2013Konferensbidrag (Övrigt vetenskapligt)
    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

  • 36.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Munro, Cameron
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Water tunnel investigation of chined fore body characteristics at high angles of attack2003Ingår i: Applied Aerodynamic Conference,2003, Orlando, USA: AIAA , 2003Konferensbidrag (Refereegranskat)
    Abstract [en]

        

  • 37.
    Jouannet, Christopher
    et al.
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Silva, Sergio E. R.
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Wing weight estimation using an automated CAD-modelManuskript (preprint) (Övrigt vetenskapligt)
    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.

  • 38.
    Knöös Franzén, Ludvig
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Schön, Sofia
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Papageorgiou, Athanasios
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Filosofiska fakulteten.
    Ölvander, Johan
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    A System of Systems Approach for Search and Rescue Missions2020Konferensbidrag (Refereegranskat)
    Abstract [en]

    System-of-Systems Engineering (SoSE) has become a constantly growing field within product development for complex systems. Systems are becoming more and more connected with other systems and the operational environment in general. This takes the development process to new levels of complexity where high degrees of uncertainties are expected due to ever occurring changes in the operational environment, and other external factors such as politics, economy, and technology. This creates a need of being able to understand the influence of changes early in the development process and to facilitate the systems? perseverance. The focus of the development shifts from fulfilling specific requirements, to being able to meet needs and deliver capabilities over time. Additionally, modeling and simulation for complex systems and System-of-Systems (SoS) becomes a valued alternative to the economically prohibited and almost impossible prototype testing. In consideration of this problem, the presented work introduces a method for both modeling and simulation of a SoS. The method uses ontology with description logic reasoning to derive and narrow down a SoS design space which is further analyzed using Agent Based Simulation (ABS). A Search and Rescue (SAR) scenario is used as a case study to test the method. Measures of Effectiveness (MoE), based on the time it takes to find a rescue subject and the cost of doing so, are used to evaluate the SoS performances. The presented method is envisioned to be used early in the development of complex systems and SoS to increase the overall understanding of them.

  • 39.
    Knöös Franzén, Ludvig
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Filosofiska fakulteten.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten. Overall Design and System Integration, Saab Aeronautics, Linköping, Sweden.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    An Ontological Approach to System of Systems Engineering in Product Development2019Ingår i: Linköping Electronic Conference Proceedings 162 (2019) / [ed] Dr. Ingo Staack and Prof. Petter Krus, Linköping: Linköping University Electronic Press, 2019, Vol. 162:4, s. 35-44Konferensbidrag (Refereegranskat)
    Abstract [en]

    This paper presents an approach to system-of-systems engineering for product development with the use of ontology. A proposed method for building as well as using ontology to generate and explore system-of-systems design spaces based on identified system-of-system needs is presented. The method is largely built to cover the first levels of related work, where a process for system of systems in the context of product development is introduced. Within this work, it is shown that scenarios for a system-of-systems can be used to identify needs and subsequently the system-of-systems capabilities that fulfils them. The allocation of capabilities to possible constituent systems is used to show the available design space. The proposed method of this paper therefore addresses these initial challenges and provides a framework for approaching the system-of-systems design space creation using ontology. A case study is used to test the method on a fictitious search and rescue scenario based on available resources and information from the Swedish Maritime Administration. The case study shows that a representation of a system-of-systems scenario can be created in an ontology using the method. The ontology provides a representation of the involved entities from the fictitious scenario and their existing relationships. Defined ontology classes containing conditions are used to represent the identified needs for the system-of-systems. The invocation of a description logic reasoner is subsequently used to classify and create an inferred ontology where the available system-of-systems solutions are represented as sub-classes and individuals of the defined classes representing the needs. Finally, several classes representing different possible system-of-systems needs are used to explore the available design space and to identify the most persistent solutions of the case study.

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  • 40.
    Knöös Franzén, Ludvig
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Filosofiska fakulteten.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten. Overall Design and Survivability, Saab Aeronautics, Linköping, Sweden.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten. Overall Design and Survivability, Saab Aeronautics, Linköping, Sweden.
    A Breakdown of System of Systems Needs Using Architecture Frameworks, Ontologies and Description Logic Reasoning2021Ingår i: Aerospace, E-ISSN 2226-4310, Vol. 8, nr 4Artikel i tidskrift (Refereegranskat)
    Abstract [en]

    Aerospace systems are connected with the operational environment and other systems in general. The focus in aerospace product development is consequently shifting from a singular system perspective to a System-of-Systems (SoS) perspective. This increasing complexity gives rise to new levels of uncertainty that must be understood and managed to produce aerospace solutions for an ever-changing future. This paper presents an approach to using architecture frameworks, and ontologies with description logic reasoning capabilities, to break down SoS needs into required capabilities and functions. The intention of this approach is to provide a consistent way of obtaining the functions to be realized in order to meet the overarching capabilities and needs of an SoS. The breakdown with an architecture framework results in an initial design space representation of functions to be performed. The captured knowledge is then represented in an ontology with description logic reasoning capabilities, which provides a more flexible way to expand and process the initial design space representation obtained from the architecture framework. The proposed approach is ultimately tested in a search and rescue case study, partly based on the operations of the Swedish Maritime Administration. The results show that it is possible to break down SoS needs in a consistent way and that ontology with description logic reasoning can be used to process the captured knowledge to both expand and reduce an available design space representation.

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  • 41.
    Krus, Petter
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluid och mekanisk systemteknik. Linköpings universitet, Tekniska högskolan.
    Whole Mission Simulation for Aircraft Preliminary Design2010Ingår i: 48th AIAA Aerospace Sciences Meeting, AIAA , 2010Konferensbidrag (Övrigt vetenskapligt)
    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.

  • 42.
    Melin, Tomas
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Wing profile performance variations influenced by manufacturing tolerances2013Konferensbidrag (Övrigt vetenskapligt)
    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.

  • 43.
    Munjulury, Raghu Chaitanya
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Staack, Ingo
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Abdalla, Alvaro Martins
    The University of São Paulo (USP), Brazil.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Knowledge-based design for future combat aircraft concepts2014Konferensbidrag (Refereegranskat)
    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.

  • 44.
    Munro, Cameron
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Correlation of flow visualization and force and moment measurements in a water tunnel2003Ingår i: The World Aviation Congress,2003, Montreal, Canada: World Aviation Congress , 2003Konferensbidrag (Refereegranskat)
    Abstract [en]

       

  • 45.
    Munro, Cameron
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Flow visualisation and force and moment correlations in a water tunnel2003Ingår i: Triennial International Symposium on Fluid Control,2003, 2003Konferensbidrag (Övrigt vetenskapligt)
    Abstract [en]

      

  • 46.
    Munro, Cameron
    et al.
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Statistical Study of Unmanned Air Vehicles for the Platform Designer2003Ingår i: 3rd International Conference on Advanced Engineering Design,2003, 2003Konferensbidrag (Refereegranskat)
  • 47.
    Munro, Cameron
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Krus, Petter
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Maskinkonstruktion.
    Statistical survey of unmanned air vehicles for the platform designer2004Ingår i: International Conference on Advanced Engineering Design,2003, Prague, Czech republic: Advanced Engineering Design , 2004Konferensbidrag (Refereegranskat)
    Abstract [en]

      

  • 48.
    Munro, Cameron
    et al.
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för konstruktions- och produktionsteknik. Linköpings universitet, Tekniska högskolan.
    Implications of scale effect for the prediction of high angle of attack aerodynamics2005Ingår i: Progress in Aerospace Sciences, ISSN 0376-0421, E-ISSN 1873-1724, ISSN 0376-0421, Vol. 41, nr 3-4, s. 301-322Artikel i tidskrift (Refereegranskat)
    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.

  • 49.
    Papageorgiou, Athanasios
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Amadori, Kristian
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    Ölvander, Johan
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska fakulteten.
    Multidisciplinary Optimization of Unmanned Aircraft in a System of Systems Context2018Ingår i: 31st Congress of The International Council of the Aeronautical Sciences (ICAS), September 9-14 2018, Belo Horizonte, Brazil., 2018Konferensbidrag (Övrigt vetenskapligt)
    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.

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  • 50.
    Rösth, Marcus
    et al.
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Jouannet, Christopher
    Linköpings universitet, Tekniska högskolan. Linköpings universitet, Institutionen för konstruktions- och produktionsteknik, Fluid och mekanisk systemteknik.
    Static calculation on hydraulic power steering, special regards on catch up effect2005Rapport (Övrigt vetenskapligt)
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