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Life extension of impact damaged honeycomb sandwich panels

Published online by Cambridge University Press:  04 July 2016

R. R. Aitken ,
D. P. W. Horrigan  and
G. Moltschaniwskyj
R. R. Aitken
Affiliation:
Composites Research Centre, Department of Mechanical Engineering, The University of Auckland, Auckland, New Zealand
D. P. W. Horrigan
Affiliation:
Composites Research Centre, Department of Mechanical Engineering, The University of Auckland, Auckland, New Zealand
G. Moltschaniwskyj
Affiliation:
Composites Research Centre, Department of Mechanical Engineering, The University of Auckland, Auckland, New Zealand
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Abstract

The assessment of damage due to impacts in composite sandwich panels and the component life reductions associated with such damage is becoming increasingly important within the aerospace industry. This study analyses minimum gauge, non-metallic honeycomb wing panels subject to impact damage. In all instances the damage is caused by ‘soft body’ impactors travelling at elevated velocities to simulate bird strike and other soft debris. The damage formed during these impacts is shown to be large in plan area but shallow and primarily causes crushing of the core in a thin layer. Loading of the panels after impact has been performed to determine the reduction in load carrying capacity and associated failure mechanisms. Damage due to soft body impact is shown to be very different to the classical rigid body impact upon which current repair schemes are based. As a result in many applications the use of current repair schemes may be inappropriate. The viability of new repair techniques is discussed with particular attention to the prevention of failure mechanisms due to loading after impact.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1041 , November 2000 , pp. 509 - 516
Copyright
Copyright © Royal Aeronautical Society 2000 

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