Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures

C. Harley; D. Quinn; T. Robinson; D. Nolan

Simulation Intent for Multi-Fidelity Analysis of Composite Aircraft Structures

C. Harley, D. Quinn, T. Robinson, D. Nolan

School of Mechanical and Aerospace Engineering

Research output: Contribution to conference › Paper

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.

Original language	English
Number of pages	10
Publication status	Published - 2018
Event	RAS 6th Aircraft Structural Design Conference - Bristol, United Kingdom Duration: 09 Oct 2018 → 11 Oct 2018 https://www.aerosociety.com/events-calendar/6th-aircraft-structural-design-conference/

Conference

Conference	RAS 6th Aircraft Structural Design Conference
Abbreviated title	ASDC
Country	United Kingdom
City	Bristol
Period	09/10/2018 → 11/10/2018
Internet address	https://www.aerosociety.com/events-calendar/6th-aircraft-structural-design-conference/

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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.

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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",

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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 -