Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures

    Research output: Contribution to conferencePaper

    Published

    Standard

    Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures. / Harley, C.; Quinn, D.; Robinson, T.; Nolan, D.

    2018. Paper presented at RAS 6th Aircraft Structural Design Conference, Bristol, United Kingdom.

    Research output: Contribution to conferencePaper

    Harvard

    Harley, C, Quinn, D, Robinson, T & Nolan, D 2018, 'Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures' Paper presented at RAS 6th Aircraft Structural Design Conference, Bristol, United Kingdom, 09/10/2018 - 11/10/2018, .

    APA

    Harley, C., Quinn, D., Robinson, T., & Nolan, D. (2018). Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures. Paper presented at RAS 6th Aircraft Structural Design Conference, Bristol, United Kingdom.

    Vancouver

    Harley C, Quinn D, Robinson T, Nolan D. Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures. 2018. Paper presented at RAS 6th Aircraft Structural Design Conference, Bristol, United Kingdom.

    Author

    Harley, C. ; Quinn, D. ; Robinson, T. ; Nolan, D. / Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures. Paper presented at RAS 6th Aircraft Structural Design Conference, Bristol, United Kingdom.10 p.

    Bibtex

    @conference{f611c75269294d1a8659dc0afd743379,
    title = "Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures",
    abstract = "This paper proposes to use laminate damage modelling capabilities, together with global aircraft level modelling methods, to create a multi-fidelity simulation framework. The framework will enable the early evaluation of composite wing panel damage response and residual strength within its representative in-service structural environment. The framework is developed on the principles of Simulation Intent, utilising the concepts of cellular modelling to efficiently define and construct analysis models for key structural features, and equivalencing to intelligently and automatically map the different representation of the features in the aircraft GFEM and the higher fidelity local stiffened panel design domain model. Example output demonstrates the capability of the modelling framework to evaluate skin laminate residual strength within the global wing structure, and inform the structural design process with more representative laminate maximum allowable stress data.",
    author = "C. Harley and D. Quinn and T. Robinson and D. Nolan",
    year = "2018",
    language = "English",
    note = "RAS 6th Aircraft Structural Design Conference, ASDC ; Conference date: 09-10-2018 Through 11-10-2018",
    url = "https://www.aerosociety.com/events-calendar/6th-aircraft-structural-design-conference/",

    }

    RIS

    TY - CONF

    T1 - Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures

    AU - Harley, C.

    AU - Quinn, D.

    AU - Robinson, T.

    AU - Nolan, D.

    PY - 2018

    Y1 - 2018

    N2 - This paper proposes to use laminate damage modelling capabilities, together with global aircraft level modelling methods, to create a multi-fidelity simulation framework. The framework will enable the early evaluation of composite wing panel damage response and residual strength within its representative in-service structural environment. The framework is developed on the principles of Simulation Intent, utilising the concepts of cellular modelling to efficiently define and construct analysis models for key structural features, and equivalencing to intelligently and automatically map the different representation of the features in the aircraft GFEM and the higher fidelity local stiffened panel design domain model. Example output demonstrates the capability of the modelling framework to evaluate skin laminate residual strength within the global wing structure, and inform the structural design process with more representative laminate maximum allowable stress data.

    AB - This paper proposes to use laminate damage modelling capabilities, together with global aircraft level modelling methods, to create a multi-fidelity simulation framework. The framework will enable the early evaluation of composite wing panel damage response and residual strength within its representative in-service structural environment. The framework is developed on the principles of Simulation Intent, utilising the concepts of cellular modelling to efficiently define and construct analysis models for key structural features, and equivalencing to intelligently and automatically map the different representation of the features in the aircraft GFEM and the higher fidelity local stiffened panel design domain model. Example output demonstrates the capability of the modelling framework to evaluate skin laminate residual strength within the global wing structure, and inform the structural design process with more representative laminate maximum allowable stress data.

    M3 - Paper

    ER -

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