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  • 1.
    Amadori, Kristian
    et al.
    Linköping University, Department of Management and Engineering, Machine Design. 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.
    Staack, Ingo
    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.
    Multidisciplinary Optimization of Wing Structure Using Parametric Models2013Conference paper (Other academic)
    Abstract [en]

    Aircraft design is an inherently multidisciplinary activity that requires integrating different models and tools to reach a well-balanced and optimized product. At Linköping University a design framework is being developed to support the initial design space exploration and the conceptual design phase. Main characteristics of the framework are its flexible database in XML format, together with close integration of automated CAD and other tools, which allows the developed geometry to be directly used in the subsequent preliminary design phase. In particular, the aim of the proposed work is to test the framework by designing, optimizing and studying a transport aircraft wing with respect to aerodynamic, geometry, structural and accessability constraints. The project will provide an initial assessment of the capability of the framework, both in terms of processing speed and accuracy of the results.

  • 2.
    Axin, Mikael
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Braun, Robert
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Dell'Amico, Alessandro
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Eriksson, Björn
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Nordin, Peter
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Pettersson, Karl
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems. Linköping University, The Institute of Technology.
    Next Generation Simulation Software using Transmission Line Elements2010In: Fluid Power and Motion Control / [ed] Dr D N Johnston and Professor A R Plummer, Centre for Power Transmission and Motion Control , 2010, p. 265-276Conference paper (Refereed)
    Abstract [en]

    A suitable method for simulating large complex dynamic systems is represented by distributed modelling using transmission line elements. The method is applicable to all physical systems, such as mechanical, electrical and pneumatics, but is particularly well suited to simulate systems where wave propagation is an important issue, for instance hydraulic systems. By using this method, components can be numerically isolated from each other, which provide highly robust numerical properties. It also enables the use of multi-core architecture since a system model can be composed by distributed simulations of subsystems on different processor cores.

    Technologies based on transmission lines has successfully been implemented in the HOPSAN simulation package, develop at Linköping University. Currently, the next generation of HOPSAN is developed using an object-oriented approach. The work is focused on compatibility, execution speed and real-time simulation in order to facilitate hardware-in-the-loop applications. This paper presents the work progress and some possible features in the new version of the HOPSAN simulation package.

  • 3.
    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.

  • 4.
    Munjulury, Raghu Chaitanya
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Martins Abdalla, Alvaro
    USP, São Carlos, Brazil.
    Staack, Ingo
    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.
    Knowledge-based future combat aircraft optimization2016In: 30th Congress of the International Council of the AeronauticalSciences (ICAS 2016), Bonn: International Council of Aeronautical Sciences (ICAS) , 2016, Vol. 1, p. 273-280Conference paper (Refereed)
    Abstract [en]

    Future combat aircraft inherently conceal all the components internally essentially for stealth reasons. The geometry is optimized for subsonic and supersonic flight area distribution and the components and payload to be fitted inside the aircraft. The basic requirements to accomplish are fuel consumption, mission profile, and military performance. Analytical methods comprise of a quick aerodynamic and structural optimization. The result obtained is then compared with multi-fidelity aero-structural analysis

  • 5.
    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.

  • 6.
    Munjulury, Raghu Chaitanya
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Berry, Patrick
    Saab Aeronautics, Linköping.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    A knowledge-based integrated aircraft conceptual design framework2016In: CEAS Aeronautical Journal, ISSN 1869-5582, 1869-5590, Vol. 7, no 1, p. 95-105Article in journal (Refereed)
    Abstract [en]

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

  • 7.
    Munjulury, Raghu
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Arts and Sciences.
    Sabate Lopez, Adrian
    Linköping University, Department of Management and Engineering. 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.
    Knowledge-based aircraft fuel system integration2018In: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 90, no 7, p. 1128-1135Article in journal (Refereed)
    Abstract [en]

    Purpose This paper aims to present a knowledge-based fuel system, implementation and application, oriented towards its use in aircraft conceptual design. Design/methodology/approach Methodology and software tools oriented to knowledge-based engineering applications (MOKA) is used as a foundation for the implementation and integration of fuel systems. Findings Including fuel systems earlier in the design process creates an opportunity to optimize it and obtain better solutions by allocating suitable locations in an aircraft, thereby reflecting on the centre of gravity of the aircraft. Research limitations/implications All geometries are symbolic, representing a space allocation inside the aircraft for the fuel system. A realistic representation of the real components could be realized in detail design. Practical implications Fuel weight is a significant part of take-off weight and decisive in aircraft sizing and range estimations. The three-dimensional geometry provides a better estimation of the volume that is available to allocate the necessary entities. It also provides fast measures for weight and balance, fuel capacity, relative tank positions and a first estimation of piping length. Originality/value Fuel systems appear early in the design process, as they are involved in several first estimations. By using a knowledge-based engineering approach, several alternatives can be visualized and estimated in the conceptual design process. Furthermore, using the weights and centre of gravity at different angles of pitch and roll of each fuel tank, the aircraft could be optimized for handling qualities by using automatically generated system simulation models.

  • 8.
    Munjulury, Venkata 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.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Integrated Aircraft Design Network2013In: CEAS 2013 The International Conference of the European Aerospace Societies: 4:th CEAS conference, 2013 / [ed] Tomas Melin, Petter Krus, Emil Vinterhav, Knut Övrebo, Linköping, 2013, p. 263-269Conference paper (Refereed)
    Abstract [en]

    This paper describes the XML basedmultidisciplinary tool integration in aconceptual aircraft design framework,developed by the Division of Fluid andMechatronic Systems (FluMeS), LinköpingUniversity. Based on a parametric datadefinition in XML, this approach allows for afull 3D CAD integration. The one-databaseapproach, also conducted by many researchorganizations, enables the flexible and efficientintegration of the different multidisciplinaryprocesses during the whole conceptual designphase. This central database approach with adetailed explanation of the developed geometrydescription and the data processing, focusing onthe CAD integration is presented. Applicationexamples of the framework are presentedshowing the data build up and data handling.

  • 9.
    Scholz, Dieter
    et al.
    Hamburg University of Applied Sciences, Germany.
    Seresinhe, Ravinka
    Cranfield University, UK.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Lawson, Craig
    Cranfield University, UK.
    Fuel Consumption Due to Shaft Power Off-takes from The Engine2013In: Proceedings of the 4th International Workshop on Aircraft System Technologies / [ed] Frank Thielecke, Aachen: Shaker Verlag, 2013, p. 169-179Conference paper (Other academic)
    Abstract [en]

    This paper looks at fuel consumption due to shaft power off-takes from the engine and the related increase in the aircraft’s fuel consumption. It presents a review and comparison of published and unpublished data on this kind of consumption. The paper presents results from the TURBOMATCH engine simulation model, calibrated to real world engine data. A generic equation is derived for the calculation of fuel consumption due to shaft power extraction. Main result is the shaft power factor kP found to be in the order of 0.002 N/W for a typical cruise flight. This yields an amazingly high efficiency for power generation by shaft power extraction from a turbo fan engine of more than 70 %.

  • 10.
    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.
    Staack, Ingo
    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.
    Design and Testing of a Low-Cost Flight Control and Data Acquisition System for Unstable Subscale Aircraft2016In: Proceedings of the 30th Congress of The International Council of the Aeronautical Sciences (ICAS), September 25-30, Daejeon, South Korea., Bonn: The International Council of the Aeronautical Sciences , 2016Conference paper (Refereed)
    Abstract [en]

    Current research on subscale flight testing methodologies at Linköping University is performed by using various platforms, some of them with advanced configurations. These have been previously flown in open-loop under direct commands from the pilot. However, the interest in flying some of these platforms with relaxed stability and the investigation of multi-surface control allocation techniques motivated the implementation of a simple low-cost flight control system based on commercial-off-the-shelf components. The work described in this paper evaluates the simplest available solutions that provide control augmentation for small, longitudinally unstable, free-flying models. This work also tries to define a reliable, fail-safe system architecture that can be implemented in more advanced platforms. Moreover, data acquisition and analysis are evaluated with the aim of applying system identification techniques.

  • 11.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Science & Engineering.
    Aircraft Systems Conceptual Design: An object-oriented approach from <element> to <aircraft>2016Doctoral thesis, monograph (Other academic)
    Abstract [en]

    Aircraft Conceptual Design (ACD) is facing new challenges on the way to enhanced fidelity level required of the nowadays complex system design. Namely the integration of models and simulations of different fidelity levels to enhance the analysis capability while maintaining a streamlined, transparent, and low cost working process is required.

    In this thesis, the use of object-oriented Knowledge-Based Engineering (KBE) methods to enable an early integration of simulation models within the ACD phase are presented. Careful investigations of modelling and simulation approaches of multi-domain systems are carried out before, and their use in the ACD phase is examined regarding the efficiency between spend effort and result in accuracy. Enabling the named topics, a central, parametric information model approach is presented. By the extended use of XML, XSD and XSLT, domain-specific models can be translated from this dataset, supporting a direct CAD and automated simulations integration.

    Modelling systems as graph networks is a simple approach for unified modelling within the conceptual design stage. Based on this theory, the similarity of different modelling approaches like Dependency Structure Matrix (DSM), MDDSM, or Channel-Agency Networks is shown. Using object-oriented programming, all these and more aspects such as e.g. Fault Tree Analysis (FTA) can be globally handled as one graph set.

    Based on the outcomes of the theoretical part, the development of a ACD framework is described. Backed by a central XML-based namespace, this framework integrates a complete CAD environment to ensure an appropriate environment for the geometric domain modelling. Furthermore, the use of KBE for automated simulation model integration is exemplified by a whole aircraft simulation including the hydraulic aircraft flight control system (FCS).

  • 12.
    Staack, Ingo
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, Faculty of Arts and Sciences.
    Establishment of the Swedish Aeronautical Research Center (SARC)2019In: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 91, no 6, p. 857-864Article in journal (Refereed)
    Abstract [en]

    Purpose This paper aims to present the newly founded Swedish Aeronautical Research Center (SARC), based on the triple helix theory, to foster the seamless Swedish aerospace research interplay between academia, research organizations and industry. Design/methodology/approach The paper is a technical paper, mainly relating and explaining sources and concepts for research planning and organization. Used concepts are the triple helix approach (for socioeconomic effects), the role of academia and industry interplay for education and the technology readiness level (TRL) concept for strategic research planning. Focusing on the establishment of a graduate school, lessons learned from previous national research schools are also presented. Findings The paper gives an overview of and explains the interplay between politics, social welfare and industrial Ramp;D needs, with the academic viewpoint of aeronautical research and education. Shortcomings in both the use of TRL for research program planning and the Swedish competence cluster system are identified and remedies suggested. The main findings are suggestions for future actions to be conducted by SARC in the fields of research and education. Originality/value So far, no publication about the newly founded SARC has been made yet. It is unique in the way that it makes substantial use of national technical documents so that this information becomes available for non-Swedish speakers. Additionally, the perhaps-unique system of industrial competence clusters is presented.

  • 13.
    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.

  • 14.
    Staack, Ingo
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Chaitanya Munjulury, Raghu
    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.
    Abdalla, Alvaro Martins
    The University of São Paulo (USP), Brazil.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    CONCEPTUAL AIRCRAFT DESIGN MODEL MANAGEMENTDEMONSTRATED ON A 4TH GENERATION FIGHTER2014Conference paper (Refereed)
    Abstract [en]

    Model management during conceptual aircraftdesign is an important issue. This paper showsthe basic ideas and capabilities of the conceptualaircraft design framework developed atLinköping University with focus on efficient lowfidelity geometry definition. As an example, theanalysis of an F-16 fighter is presented.

  • 15.
    Staack, Ingo
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Ellström, Hans
    Saab Aeronautics.
    Bergman, Mats
    Saab Aeronautics.
    Sarwe, Pål
    Saab Aeronautics.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    More  electrical environmental control system simulation2012In: Proceedings of the 28th  International Congress of the Aeronautical Sciences, Brisbane: ICAS , 2012Conference paper (Other academic)
    Abstract [en]

    This paper describes the development of a scalable simulation model of a bleed-less, fully electric Environmental Control System (ECS). The focus during development of the model was on fast execution speed and system architecture in order to enable optimization algorithms for system efficiency optimization to be constructed. Classical sensitivity and robustness analysis were used during model development. ECS architecture functionality and reliability has been proven for different flight mission working conditions as well as different failure modes. For this purpose, an analysis tool related to the simulation model and active simulation model control was developed.

  • 16.
    Staack, Ingo
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Krus, Petter
    Linköping University, Department of Management and Engineering, Fluid and Mechatronic Systems. Linköping University, The Institute of Technology.
    Integration of On-Board Power Systems Simulation in Conceptual Aircraft Design2013In: Proceedings of the 4th CEAS Conference in Linköping / [ed] Tomas Melin, Petter Krus,Emil Vinterhav, Knut Övrebö, Linköping, Sweden: Linköping University Electronic Press, 2013, p. 709-718Conference paper (Other academic)
    Abstract [en]

    This paper describes the methodology of generating simulation models out of basic information, available during conceptual design phase. The implementation of an aircraft system is shown as an example using the simulation software HOPSAN.

    Because of the limited direct project-related data available at the conceptual stage, the traditional method of creating physical simulation models by the bottom up approach with the help of (standard) component libraries is not applicable. Instead, the respective systems’ architecture as well as their composition has to be descriptively predefined in a flexible, wide-range applicable manner, known as the knowledge base (KB) approach. These system technology driven design declarations – combined with project related data – result in roughly pre-tuned system simulation models, which may help when conducting more detailed investigations of the project such as performance analysis.

    This (system architecture) knowledge-based approach is shown on the whole aircraft system level down to the detailed implementation of the control surface actuator systems of the primary flight control system.

  • 17.
    Staack, Ingo
    et al.
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems . Linköping University, The Institute of Technology.
    Lundström, David
    Linköping University, Department of Management and Engineering, Fluid and Mechanical Engineering Systems . Linköping University, The Institute of Technology.
    Subscale Flight Testing at Linköping University2010In: 27th International Congress of the Aeronautical Sciences, Stockholm: ICAS , 2010Conference paper (Other academic)
    Abstract [en]

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

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