A Structural Design Concept for a Multi-Shell Blended Wing Body with Laminar Flow Control

Majeed Bishara, Peter Horst, Hinesh Madhusoodanan, Martin Brod, Benedikt Daum and Raimund Rolfes
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Majeed Bishara: Aeronautics Research Center Niedersachsen (NFL), TU Braunschweig, Hermann-Blenk-Straße 42, 38108 Braunschweig, Germany
Peter Horst: Institute of Aircraft Design and Lightweight Structures, TU Braunschweig, Hermann-Blenk-Straße 35, 38108 Braunschweig, Germany
Hinesh Madhusoodanan: Institute of Structural Analysis, Leibniz University of Hannover, Appelstraße 9A, 30167 Hannover, Germany
Martin Brod: Institute of Structural Analysis, Leibniz University of Hannover, Appelstraße 9A, 30167 Hannover, Germany
Benedikt Daum: Institute of Structural Analysis, Leibniz University of Hannover, Appelstraße 9A, 30167 Hannover, Germany
Raimund Rolfes: Institute of Structural Analysis, Leibniz University of Hannover, Appelstraße 9A, 30167 Hannover, Germany

Energies, 2018, vol. 11, issue 2, 1-21

Abstract: Static and fatigue analyses are presented for a new blended wing body (BWB) fuselage concept considering laminar flow control (LFC) by boundary layer suction in order to reduce the aerodynamic drag. BWB aircraft design concepts profit from a structurally beneficial distribution of lift and weight and allow a better utilization of interior space over conventional layouts. A structurally efficient design concept for the pressurized BWB cabin is a vaulted layout that is, however, aerodynamically disadvantageous. A suitable remedy is a multi-shell design concept with a separate outer skin. The synergetic combination of such a multi-shell BWB fuselage with a LFC via perforation of the outer skin to attain a drag reduction appears promising. In this work, two relevant structural design aspects are considered. First, a numerical model for a ribbed double-shell design of a fuselage segment is analyzed. Second, fatigue aspects of the perforation in the outer skin are investigated. A design making use of controlled fiber orientation is proposed for the perforated skin. The fatigue behavior is compared to perforation methods with conventional fiber topologies and to configurations without perforations.

Keywords: blended wing body; multi-bubble fuselage; structural analysis; controlled fiber placement; fiber-reinforced plastics; fatigue; degradation; damage model (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2018
References: View references in EconPapers View complete reference list from CitEc
Citations: View citations in EconPapers (1)

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