E. W. Thrall, Jr (McDonnell Douglas Corporation, Douglas Aircraft Company, 3855 Lakewood Boulevard, Long Beach, California 90846, USA)
2. Fatigue Testing of Structural Adhesives . :. . . 55
R. B. Krieger, Jr (American Cyanamid Company, Blooming-dale Aerospace Products, Havre de Grace, Maryland 21078, USA)
3. Contribution oj Corrosion to Adhesive Bond Failure in Aluminium •Alloys...........71
A. Mahoon (Aircraft Group, British Aerospace, Weybridge, Surrey KT13 OSP, UK)
4. Strength of CFRP Lap Joints......87
R. D. Adams (Department of Mechanical Engineering, University of Bristol, Bristol BS8 1TR, UK)
5. The Environmental Fracture of Adhesive Joints . . .103
B. W. Cherry and K. W. Thomson (Department of Materials Engineering, Monash University, Clayton, Victoria 3168, Australia)
6- A Critique of Acoustic Methods of Adhesive Bond Strength
Determination.........113
G. J. Curtis (Acoustics Section, Materials Physics Division, Atomic Energy Research Establishment, Harwell, Didcot, Oxon OX11 ORA, UK)
7. Practical Experience in Nondestructive Testing of Adhesive Bonded Joints in Aircraft . . . . . . .149
A. R. Bond (NDT Services, British Airways, Heathrow, ' Hounslow, Middlesex, UK)
8. Ultrasonic Spectroscopy and the Detection of Hydrothermal Degradation in Adhesive Bonds . . . . . .159
E. A. Lloyd and D. S. Wadhwani (Department of Physics, The City University, St John Street, London EC1V 4PB, UK)
9. The Influence of the Interface Reaction on Rubber-to-brass Adhesion and Adhesion Retention......175
G. Haemers (N. V. Bekaert S.A., B-8550 Zwevegem, Belgium)
10. Novel "Paniculate-type Adhesives.....199
P. J. Corish, T. H. Osmant and D. I. Clarke (Research Centre, Dunlop Ltd, Kingsbury Road, Birmingham B24 9QT,
UK)
11. Surface Pretreatment of Polytetrafluoroethene . . . 215
R. H. Dahm, D. J. Barker, D. M. Brewis (School of Chemistry, Leicester Polytechnic, P.O. Box 143, Leicester LEI 9BH, UK) and L. R. J. Hoy (Plastics Division, ICI Ltd, Welwyn Garden City, Herts. AL7 1HD, UK)
Index .......... .233
Chapter 1
The Primary Adhesively Bonded Structure Technology (PABST) Program
E. W. THRALL, JR. McDonnell Douglas Corporation, California, USA
INTRODUCTION
The purpose of this paper is to present a general summary of the Primary Adhesively Bonded Structure Technology (PABST) program. This program is a US Air Force-funded study sponsored by the Air Force Flight Dynamics Laboratory (AFFDL) under joint management and technical direction of AFFDL and the Air Force Materials Laboratory, Wright-Patterson Air Force Base, Ohio. The work described herein was performed by the Douglas Aircraft Company starting in February 1975.
This is a multidiscipline program, the primary objective of which is to achieve significant improvement in cost, weight, integrity and durability of primary fuselage structure applicable to the Advanced Medium STOL Transport (AMST) (Fig. 1) and other wide-body transports through (1) the development and validation—ultimately by full-scale test—of adhesively bonded structure technology, and (2) the prompt and complete transfer of the knowledge and data obtained to the aerospace community. It is hoped that the presentation of this paper will help to accomplish the latter goal.
There are essentially no primary aircraft structures of US design in commercial service today which rely on an adhesive to carry or transfer 100 % of the local structural loads. Many so-called secondary structures are joined with adhesives (honeycomb sandwich and doublers), but in many cases rivets are also installed through the metal-to-metal joints. It is well known that this combination joint has superior fatigue strength (life) when compared with rivets alone. In Europe, several primary structures have
een joined by using an adhesively bonded joint; for example, the Fokker r-27 and F-28 (1955), the de Havilland Comet (1949) and Hawker-Siddeley
"dent П1В, all using Redux (a Ciba-Geigy registered trademark for a
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