Fibre Metal Laminates: An Introduction

508 Pages·2001·21.572 MB·English

by  A. Vlot (auth.), Ad Vlot, Jan Willem Gunnink (eds.)

Fibre Metal Laminates
Cover design: Willemien Veldhoven and Frans Oostrum
Acknowledgement of support and disclaimer:
This material is based upon work supported by the European Office of Aerospace
Research and Development, Air Force Office of Scientific Research, Air Force
Research Laboratory, under Contract No. F61775-01-WF003.
Any opinions, findings and conclusions or recommendations expressed in this
material are those of the author(s) and do not necessarily reflect the views of the
European Office of Aerospace Research and Development, Air Force Office of
Scientific Research, Air Force Research Laboratory.
Fibre Metal Laminates
An Introduction
Edited by
ADVLOT
Delft University of Technology,
Faculty (~t'Aerospace Engineering Delft,
The Netherlands
and
JAN WILLEM GUNNINK
Fibre Metal Laminates Centre of Competence,
Deift, The Netherlands
SSpprriinnggeerr -SScciieennccee++BBuussiinneessss MMeeddiiaa,, BB.,VV.,
A CLP. Catalogue record for this book is available from the Library of Congress.
ISBN 978-1-4020-0391-2 ISBN 978-94-010-0995-9 (eBook)
DOI 10.1007/978-94-010-0995-9
Printed on acid-free paper
All Rights Reserved
© 2001 Springer Science+Business Media Dordrecht
Originally published by Kluwer Academic Publishers in 2001
Softcover reprint of the hardcover 1st edition 2001
No part of the material protected by this copyright notice may be reproduced or
utilized in any form or by any means, electronic or mechanical,
including photocopying, recording or by any information storage and
retrieval system, without written permission from the copyright owner.
Table of Contents
Preface ......................................................................... vii
A Material Properties ................................................... 1
Historical overview ........................................................................................... 3
2 Glare features ........................ , ..... , ............................ , ...................................... 23
3 Next Generation Fibre Metal Laminates ......................................................... 39
4 Long-term behaviour ...................................................................................... 53
5 Material design allowables and qualification .................................................. 69
6 New aluminium alloys for Glare ..................................................................... 79
BMethods ................................................................ 99
7 Stress-strain curve ......................................................................................... 101
8 Shear yield strength ........................................................................................ III
9 Blunt notch strength ....................................................................................... 117
10 Stability ......................................................................................................... 133
11 Fatigue .......................................................................................................... 155
12 Fatigue of riveted joints ................................................................................ 173
13 Residual strength ........................................................................................... 197
14 Damage tolerance aspects ............................................................................. 219
C Design Aspects .................................................... 235
15 Fuselage barrel design and design for manufacturing ................................... 237
16 Cut-outs; door surrounding ........................................................................... 255
17 Detailed design concepts ............................................................................... 267
18 Numerical modelling: delamination buckling ............................................... 281
19 Glare - from invention to innovation ............................................................ 299
20 Secondary applications ................................................................................. 309
v
D Production .......................................................... 325
21 Machineability .............................................................................................. 327
22 Formability .................................................................................................... 337
23 Curved panels ................................................................................................ 355
24 Quality control .............................................................................................. 369
E Safety, Maintenance and Inspection ...................... 381
25 Inspection and maintenance .......................................................................... 383
26 Bum-through and lightning strike ................................................................. 399
27 Impact properties .......................................................................................... 409
28 Corrosion ...................................................................................................... 427
29 Riveted repairs .............................................................................................. 441
30 Bonded repair patches ................................................................................... 451
31 Bonded repairs for C-5A fuselage crown cracking ....................................... 477
32 Eddy current inspection ................................................................................ 499
33 Glare as part of Sustainable and Environmentally Sound Engineering ........ 513
Authors and Affiliations ............................................... 525
Sponsors ................................................................... 527
vi
Preface
This is the first monograph on Fibre Metal Laminates, a material that has been
developed over the last decades at Delft University of Technology, faculty of
Aerospace Engineering in the Netherlands. This book was compiled for an
international conference at 24-26 September 2001 on the occasion of the formal
retirement of Professor Boud Vogelesang. He was the 'founding father' and the
driving force during all the years of research. His enthusiasm, team spirit and
perseverance were vital for the continuity and the success of the development.
This is one of the three books that were published for the conference. This book
covers the technical afternoon sessions. Only a fraction of the chapters in this book
were presented at the conference. The other chapters were added to provide a
complete picture of the various material properties. The book mainly focuses on
Glare, the Fibre Metal Laminate with glass fibres. A second book with the title
Around Glare - the context of a new aircraft material, covers the broader subject of
the morning sessions on the context of material development in the aviation industry,
and also includes the farewell lecture of Boud Vogelesang. The third book, Glare -
history o/the development o/a new aircraft material, provides the inside story of the
development activities in Delft. All three books are published by Kluwer academic
publishers b.v .. Arno Schouwenburg of Kluwer did a great job in transforming our
electronic data into real material!
I also want to thank the sponsors of the conference. Their names are included at the
end of the book. Without their help it would have been impossible to realise this
event.
The scientific board helped to assure the quality of the papers. The board members
were:
Profdr. Peter Beaumont, Cambridge University, United Kingdom
Profdr. Alan Baker, DSTO and RMI, Melbourne, Australia
Profdr.ir. Andre de Boer, University of Twente, the Netherlands
Dr. Bob Bucci, ALCOA, USA
Dr. Jim Greer, Lt.Col. USAF, Center of Aircraft Structural Life Extension, US Air
Force Academy, USA
Dr. Peter Poole, DERA, United Kingdom
Thank you all very much for your time and assistance!
vii
The layout and corrections of the papers were taken care of by a team of students,
see Figure 0.1, who did excellent work. The members of this team were:
Ronald van der Meijs
Dort Daandels
Lex Dop
Geoff Morris
It was ajoy to work with you!
The cover design is based on a painting by Willemien Veldhoven. Together with
Frans Oostrum she did a great job in creating an artistic cover for this technical
book.
Prof.dr.ir. Ad Vlot
Delft, June 200 I
Figure 0.1 Stress distribution around LRSMLGT020 in Glarebook HQ, June 26,2001.
viii
A. Material Properties
99
235
•
325
•
3 1
1
1
Historical overview
A. Vlot
Abstract - In this chapter a brief overview of the history of Fibre Metal
Laminates Arall and Glare is given as background information for the other, technical
chapters of this book. This is a summary of a more complete description that can be
found in Vlot [I].
...
.. .... ---
-------
~ ~.-------
1.1 Arall
1.1.1 The development of Arall
The origins of our story can be traced back to the devastated Fokker facilities of
1945. The Fokker engineers that had to start from scratch grasped the opportunity to
introduce new technologies. One of those engineers was Rob Schliekelmann, who
graduated at Delft University. He did some practical training at the English aircraft
manufacturer De Havilland. This was the first company to bond metal parts together.
Schliekelmann took the metal bonding technology to Fokker where he optimised the
pretreatment of the aluminium layers and the production process of bonded
structures, for example by introducing autoclaves. As no expensive milling
equipment was available, metal bonding was applied to create a built-up, laminated
structure for the Fokker F -27 tailored to its local strength.
Later it was discovered that the bonded, laminated structure also appeared to have
good fatigue properties. The team of Schijve at the National Aerospace Laboratory
NLR carried out different types of fatigue tests on F-27 centre wings. A major
finding was the favourable resistance to fatigue crack growth of laminated sheet
metal reinforcements around a large wing joint. The crack growth was extremely
slow because cracks started to grow in a single layer. The other intact layers
effectively bridged the crack and in this way considerably slowed down crack
growth.
3
A. Vlot et al. (eds.), Fibre Metal Laminates
© Springer Science+Business Media Dordrecht 2001