validation articles  
WP2 Airliner Fuselage Overview

Building upon the knowledge gained within the TANGO Composite Fuselage platform for current fuselage areas, the purpose of this platform is to make the next logical step forward towards the application of a full composite fuselage to a large civil airliner.

The objective of this work is to mature full composite fuselage architecture by consideration of key fuselage challenges and complex design features. This covers:

Large cut-outs in curved panels

Load introduction longitudinal and circumferential

Damage capabilities impact, large damage, post-buckling, crash

Systems integration

The overall objective for the application of composite material to airliner fuselage is the same as for airliner wing to offer improved aircraft performance, by proving the application of composites to these structural items, realizing the weight reduction potential and by demonstrating lower manufacturing recurring costs through the use of low-cost technologies. Maintenance costs should also be reduced by using composite materials.

To improve on the weight advantage of a full composite fuselage against the reference state-of-the-art metallic fuselage

Target 20% weight saving compared to metallic

To improve on the recurring costs of the manufacture of a full composite fuselage against the reference metallic baseline

Target ZERO increasing in recurring cost compared to metallic

By concept studies and curved panel tests to identify the most appropriate configuration for large door cut-outs, and the integration of longitudinal and circumferential load inputs into a composite fuselage.

By studies, coupon and curved panel testing to develop and validate methods to consideration of tyre debris and multi bay damage scenarios

By studies, coupon and curved panel testing to develop and validate methods for post buckling analysis, to facilitate component weight saving

By coupon testing to provide dynamic material characterisation for crash analysis and by fuselage energy absorption estimation

By evaluation of weight and system concept consequences due to a composite fuselage

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