Structural Configuration Systems Analysis for Advanced Aircraft Fuselage Concepts

Structural configuration analysis of an advanced aircraft fuselage concept is investigated. This concept is characterized by a double-bubble section fuselage with rear mounted engines. Based on lessons learned from structural systems analysis of unconventional aircraft, high-fidelity finite-element...

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Bibliographic Details
Published inNASA Center for AeroSpace Information (CASI). Conference Proceedings
Main Authors Mukhopadhyay, Vivek, Welstead, Jason R, Quinlan, Jesse R, Guynn, Mark D
Format Conference Proceeding
LanguageEnglish
Published Hampton NASA/Langley Research Center 13.06.2016
Subjects
Aircraft
Aircraft components
Airframes
Aluminum
Bubbles
Commercial aircraft
Configurations
Finite element method
Fuel consumption
Fuselages
Mathematical models
Stress analysis
Structural analysis
Structural weight
Systems analysis
Weight reduction
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Summary:Structural configuration analysis of an advanced aircraft fuselage concept is investigated. This concept is characterized by a double-bubble section fuselage with rear mounted engines. Based on lessons learned from structural systems analysis of unconventional aircraft, high-fidelity finite-element models (FEM) are developed for evaluating structural performance of three double-bubble section configurations. Structural sizing and stress analysis are applied for design improvement and weight reduction. Among the three double-bubble configurations, the double-D cross-section fuselage design was found to have a relatively lower structural weight. The structural FEM weights of these three double-bubble fuselage section concepts are also compared with several cylindrical fuselage models. Since these fuselage concepts are different in size, shape and material, the fuselage structural FEM weights are normalized by the corresponding passenger floor area for a relative comparison. This structural systems analysis indicates that an advanced composite double-D section fuselage may have a relative structural weight ratio advantage over a conventional aluminum fuselage. Ten commercial and conceptual aircraft fuselage structural weight estimates, which are empirically derived from the corresponding maximum takeoff gross weight, are also presented and compared with the FEM- based estimates for possible correlation. A conceptual full vehicle FEM model with a double-D fuselage is also developed for preliminary structural analysis and weight estimation.