This is the statement of work for my Advanced Technology Demonstration Aircraft project, to inspire interest in aerospace engineering for the RAeS and AIAA.

1. ADVANCED TECHNOLOGY DEMONSTRATION AIRCRAFT
G. A. Wardle MSc. MSc. Senior Member AIAA.
RAeS Structures and Materials Group. Page i
Paper “Health” Warning
This paper has been created, for the sole purpose of private study and is not the work of a company or
government organisation it entirely the work of the author using resources in the public domain. This
paper will be submitted for peer - review by the American Institute of Aeronautics and Astronautics,
Design Engineering Technical Committee, and the RAeS Structures and Material Group for pre
submission assessment. Readers must be aware that the work contained may not be necessarily 100%
correct, and caution should be exercised if this project or the data it contains is being used for future
work. If in doubt, please refer to the RAeS Structures and Material Group.
All of the views and material contained within this document are the sole research of the author and
are not meant to directly imply the intentions of the Boeing Company, Airbus Group, GKN
Aerospace, or any contractor thereof, or any third party at this date. Although the USAF and NASA
have awarded contracts for studies into stitched composite aircraft structures this work is not the
product of their results or any part of their body of research and should not be considered as such.
This document contains no material whatsoever generated or conceived by myself or others during my
employment with BAE SYSTEMS (PLC), or that is governed by ITAR restrictions. This work is
solely my own creation and is based on my own academic studies and literature research and the
distribution of all information contained within this document is unlimited public release and has been
approved. This document and any part thereof cannot be reproduced by any means for distribution
without written permission form and the author.
None of the data contained within this paper is to be used in any format or for any other research
project without consultation with AIAA DETC the RAeS S and M Group or the author.
Acknowledgements
Mr Philip Stocking, Professor J. P. Fielding, and Professor Howard Smith, all at Cranfield University
for whose advice I am eternally grateful, Professor Nick Bennett University of Portsmouth for private
help with background material on Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) and
finally acknowledgement to the following: - Steven A. Brandt: John J. Bertin: Randall J. Stiles: and
Ray. Whitford: of the UASFA for producing the AeroDYNAMIC V2.08 (Jet Designer) analysis Multi
Discipline Optimisation software, and the AeroDYNAMIC V3 design resource CD which were major
aids in producing this paper.

2. ADVANCED TECHNOLOGY DEMONSTRATION AIRCRAFT
G. A. Wardle MSc. MSc. Senior Member AIAA.
RAeS Structures and Materials Group. Page ii
Abstract.
The objective of this paper is to produce and assess a conceptual design study for a future large
transport aircraft using the supercritical SC (2)-0412 wing, produced using advanced composite
manufacturing processes namely the PRSEUS process and compare this to reference composite
airframe based on both Airbus A350XWB and Boeing 787 composite airframe technology. This is to
assess the possible benefits of using PRSEUS on a conventional wing and tube aircraft configuration
in a pressurised environment i.e. fuselage and wing fuel tanks, as a prelude to its adoption for
advanced concept wing / tube and BWB aircraft. This project will also study the automated assembly
of the wing structure using kinematic simulation tools. The result will be to establish the advantages
and limitations of readily available structural design, process simulation, kinematic and structural
analysis toolsets, namely Catia V5.R20 and NASTRAN / PATRAN 2000, the source for configuration
and loading being AeroDYNAMIC V2.08 and JET Designer 3 in developing an innovative
manufacturing and assembly concept in a virtual environment.
PRSEUS or Pultruded Rod Stitched Efficient Unitized Structure is one of many, possible architectures
which are classed under the more generic category of Stitched Resin Infusion (S/RI). The major
benefits of stitched composites are as follows: - damage arresting: enable thickness gradients: build
one-piece larger structures-combined frame, skin and stringer: more efficient load paths hence lighter
structure: reduces fasteners, and facilitates bolted repair of damage: externally bagged structure-soft
tooling-no inter-modeline tooling: and resin infusion with oven curing at one atmosphere so does not
require an autoclave.
Currently stitched resin infused composite structures include all eight moderately loaded landing gear
door structures on the Boeing C-17 military transport circa 2007: the lightly loaded LAIRCM system
fairing also on the C-17 circa 2003 , and NASA test wing box of the 1990’s, and flat panel test articles
to support the NASA BWB program. Therefore there is a need assess this technology in a highly
loaded more complex structure to fully assess the benefits and limitations of this technology.
This conceptual design study is only a starting point to much more ambitious funded research, and is a
conventional twin engine 250-300 seat class point to point aircraft design. The study consists of two
phases, the first of which was overall airframe configuration design and parametric analysis using both
classical analysis and the Jet306 / AeroDYNAMIC V2.08 analysis tool set, and the second was major
structural airframe component layout of the airframe initial structure with systems integration using
hand calculations with Catia V5 FEA modelling for structural sizing. This final design study for both
versions of the airframe reference and new build contained herein consists of parametric analysis,
initial optimisation and structural layout and constitutes a feasibility study proposal to determine the
benefits. Recommended further work on the proposed design includes CFD aerodynamic analysis, and
more rigorous FEA analysis using more accurately defined aero and structural loads.