Hostname: page-component-586b7cd67f-gb8f7 Total loading time: 0 Render date: 2024-11-27T21:57:29.512Z Has data issue: false hasContentIssue false
  • English
  • Français

Blended wing body structural concept development

Published online by Cambridge University Press:  03 February 2016

A. Velicki  and
P. Thrash
A. Velicki
Affiliation:
The Boeing Company, Huntington Beach, California, USA
P. Thrash
Affiliation:
The Boeing Company, Huntington Beach, California, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

A lightweight robust airframe design is one of the key technological advancements necessary for the successful launch of a blended wing body aircraft. The non-circular pressure cabin dictates that substantial improvements beyond current state-of-the-art aluminium and composite structures is needed, and that improvements of this magnitude will require radically new airframe design and manufacturing practices. Such an approach is described in this paper. It is a highly integrated structural concept that is tailored and optimised to fully exploit the orthotropic nature and unique processing advantages inherent in dry carbon fibres, while also employing stitching to enable a unique damage-arrest design approach.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1158 , August 2010 , pp. 513 - 519
Copyright
Copyright © Royal Aeronautical Society 2010 

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. Liebeck, R.H., Design of the blended wing-body subsonic transport, August 2002, 2002 Wright Brothers Lecture, AIAA Paper 2002-0002.Google Scholar
2. Velicki, A., NASA TCAT Phase I Study (Novel Blended Wing Body Structural Concepts), July 2004, Contract NNL04AA36C CLIN 0001.Google Scholar
3. Hoffman, K., Air vehicle technology integration program (AVTIP), Delivery Order 0059: Multi-role Bomber Structural Analysis, AFRL-VA-WP-TR-2006-3067, May 2006, Final Report for 14 December 2004-08 May 2006, AFRL-VA-WP-TR-2006-3067.Google Scholar
4. Velicki, A. and Thrash, P.J., Advanced structural concept development using stitched composites, 2008, 49th AIAA/ASME/ASCE/SHS/ASC Structures, Structural Dynamics, and Materials Conference, 7-10 April 2008, Schaumburg, IL, AIAA Paper 2008-2329.Google Scholar
5. Velicki, A., Thrash, P.J., Burgess, R.A. and Standish, C., US Patent Application for a Molding Process and Apparatus for Producing Unified Composite Structures, The Boeing Company, Huntington Beach, CA, Patent No 6,896,841 B2, granted 24 May 2005.Google Scholar
6. Renton, J. W., Olcott, D., Roeseler, B., Batzer, R., Baron, B. and Velicki, A., Future of flight vehicle structures (2002-2023), AIAA J, 2004, 41, (51), pp 995–998.Google Scholar
7. Karal, M., AST composite wing study — executive summary, March 2001, NASA/CR-2001-210650, Prepared for NASA, Langley Research Center under Contract NAS1-20546.Google Scholar