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The use of topology optimisation in the conceptual design of next generation lattice composite aircraft fuselage structures

Published online by Cambridge University Press:  27 January 2016

S. Niemann ,
B. Kolesnikov ,
H. Lohse-Busch ,
C. Hühne ,
O. M. Querin ,
V. V. Toropov  and
D. Liu
S. Niemann*
Affiliation:
DLR, Braunschweig, Germany
B. Kolesnikov*
Affiliation:
DLR, Braunschweig, Germany
H. Lohse-Busch*
Affiliation:
DLR, Braunschweig, Germany
C. Hühne*
Affiliation:
DLR, Braunschweig, Germany
O. M. Querin*
Affiliation:
University of Leeds, Leeds, UK
V. V. Toropov*
Affiliation:
University of Leeds, Leeds, UK
D. Liu*
Affiliation:
University of Leeds, Leeds, UK
*
[email protected]
[email protected]
[email protected]
[email protected]
[email protected]
[email protected]
[email protected]
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Abstract

Conventional commercial aircraft fuselages use all-aluminium semi-monocoque structures where the skin carries the external loads, the internal fuselage pressurisation and is strengthen using frames and stringers. Environmental and economic issues force aircraft designers to minimise weight and costs to keep air transport competitive and safe. But as metal designs have reached a high degree of perfection, extraordinary weight and cost savings are unlikely in the future. Carbon composite materials combined with lattice structures and the use of topology optimisation have the potential to offer such weight reductions. The EU FP7 project Advanced Lattice Structures for Composite Airframes (ALaSCA) was started to investigate this. This article present some of this research which has now led to the development of a new airframe concept which consists of: a load carrying inner skin; transverse frames; CFRP-metal hybrid stiffeners helically arranged in a grid configuration; insulating foam and an additional aerodynamic outer skin.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1197 , November 2013 , pp. 1139 - 1154
Copyright
Copyright © Royal Aeronautical Society 2013 

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