Hostname: page-component-78c5997874-4rdpn Total loading time: 0 Render date: 2024-11-05T06:16:34.944Z Has data issue: false hasContentIssue false

Damage arrest design approach using stitched composites

Published online by Cambridge University Press:  27 January 2016

A. Velicki*
Affiliation:
The Boeing Company, Huntington Beach, California, USA
P. Thrash*
Affiliation:
The Boeing Company, Huntington Beach, California, USA

Abstract

Although the deployment of carbon fibre structural components has enjoyed wide success on smaller aircraft, their acceptance on larger transport airframes is less sanguine – especially in the case of primary structure applications where the increasing out of plane loads found on the larger airframes have exposed the weak interlaminar properties of the layered material system. This has led to an overreliance on mechanical attachments to suppress these through thickness failures, which ultimately degrades structural performance and increases manufacturing costs. Until these resin dominated failure modes can be dealt with more effectively, without adversely affecting the in plane properties of the laminate, the true weight-savings potential afforded by carbon fibre material systems will be difficult to attain. This paper describes how researchers at NASA-LaRC and The Boeing Company are working to develop a next generation stitched composite design solution that addresses the fundamental challenges in achieving improved structural performance and reduced fabrication costs for large carbon fibre airframe structures.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 2011 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Velicki, A. and Thrash, P.J. Advanced Structural Concept Development Using Stitched Composites, 49th AIAA/ASME/ASCE/SHS/ASC Structures, Structural Dynamics, and Materials Conference, 7-10 April 2008, Schaumburg, IL, USA, AIAA Paper 2008-2329.Google Scholar
2. FAR Part 25 Airworthiness Standards: Transport Category Airplanes.Google Scholar
3. Air Vehicle Technology Integration Program (AVTIP), Multi-role Bomber Structural Analysis, AFRL-VA-WP-TR-2006-3067, Krishna Hoffman, May 2006, Final Report for 14 December 2004 – 08 May 2006, distribution request referred to AFRL/VASA, Wright-Patterson AFB, OH, USA, 45433-7542.Google Scholar
4. Air Vehicle Technology Integration Program (AVTIP), Multi-role Transport Structural Analysis, AFRL-VA-WP-TR-2008-3063, Kim Linton, September 2007, Final Report, contract from September 2005 through February 2008, distribution request referred to AFRL/VASA, Wright-Patterson AFB, OH, USA, 45433-7542.Google Scholar
5. Jegley, D.C., Velicki, A. and Hansen, D. Structural Efficiency of Stitched Rod-stiffened Composite Panels With Stiffener Crippling, 49th AIAA/ASME/ASCE/SHS/ASC Structures, Structural Dynamics, and Materials Conference, 7-10 April 2008, Schaumburg, IL, USA.Google Scholar
6. Velicki, A. and Thrash, P.J. Damage Arresting Composites for Shaped Vehicles, NASA Contract NNL07AA48C, Phase I Final Report for October 2007 through September 2008, released as NASA/CR-2009-215932, September 2009.Google Scholar