Riveted Lap Joints in Aircraft Fuselage

Transcription

1 Riveted Lap Joints in Aircraft Fuselage

2 SOLID MECHANICS AND ITS APPLICATIONS Volume 189 Series Editors: G.M.L. GLADWELL Department of Civil Engineering University of Waterloo Waterloo, Ontario, Canada N2L 3GI Aims and Scope of the Series The fundamental questions arising in mechanics are: Why?, How?, and How much? The aim of this series is to provide lucid accounts written by authoritative researchers giving vision and insight in answering these questions on the subject of mechanics as it relates to solids. The scope of the series covers the entire spectrum of solid mechanics. Thus it includes the foundation of mechanics; variational formulations; computational mechanics; statics, kinematics and dynamics of rigid and elastic bodies: vibrations of solids and structures; dynamical systems and chaos; the theories of elasticity, plasticity and viscoelasticity; composite materials; rods, beams, shells and membranes; structural control and stability; soils, rocks and geomechanics; fracture; tribology; experimental mechanics; biomechanics and machine design. The median level of presentation is the first year graduate student. Some texts are monographs defining the current state of the field; others are accessible to final year undergraduates; but essentially the emphasis is on readability and clarity. For further volumes:

3 Andrzej Skorupa Małgorzata Skorupa Riveted Lap Joints in Aircraft Fuselage Design, Analysis and Properties 123

4 Andrzej Skorupa Faculty of Mechanical Engineering and Robotics AGH University of Science and Technology Al. Mickiewicza Kraków Poland Małgorzata Skorupa Faculty of Mechanical Engineering and Robotics AGH University of Science and Technology Al. Mickiewicza Kraków Poland ISSN ISBN ISBN (ebook) DOI / Springer Dordrecht Heidelberg New York London Library of Congress Control Number: Springer Science+Business Media Dordrecht 2012 This work is subject to copyright. All rights are reserved by the Publisher, whether the whole or part of the material is concerned, specifically the rights of translation, reprinting, reuse of illustrations, recitation, broadcasting, reproduction on microfilms or in any other physical way, and transmission or information storage and retrieval, electronic adaptation, computer software, or by similar or dissimilar methodology now known or hereafter developed. Exempted from this legal reservation are brief excerpts in connection with reviews or scholarly analysis or material supplied specifically for the purpose of being entered and executed on a computer system, for exclusive use by the purchaser of the work. Duplication of this publication or parts thereof is permitted only under the provisions of the Copyright Law of the Publisher s location, in its current version, and permission for use must always be obtained from Springer. Permissions for use may be obtained through RightsLink at the Copyright Clearance Center. Violations are liable to prosecution under the respective Copyright Law. The use of general descriptive names, registered names, trademarks, service marks, etc. in this publication does not imply, even in the absence of a specific statement, that such names are exempt from the relevant protective laws and regulations and therefore free for general use. While the advice and information in this book are believed to be true and accurate at the date of publication, neither the authors nor the editors nor the publisher can accept any legal responsibility for any errors or omissions that may be made. The publisher makes no warranty, express or implied, with respect to the material contained herein. Printed on acid-free paper Springer is part of Springer Science+Business Media (

5 Preface Fatigue of the pressurized fuselages of transport aircraft is a significant problem for all builders and users of hundreds of thousands of aircraft, servicing millions of air travellers and cargoes. Primary facets of this issue are: How to assure a sufficient lifetime for each and every component of each and every aircraft. How to determine adequate safety features compatible with differing structures. How to formulate and enforce inspection procedures commensurate with the demands of individual aircraft. These aspects are all addressed in various formal protocols for creating and maintaining airworthiness, including damage tolerance considerations. In most transport aircraft, fatigue occurs in joints, and more especially in lap joints between sheets of aluminium alloys, sometimes leading to circumstances that threaten safety in critical ways. This fact was recognized as early as the 1950s. Since then, fatigue of lap joints has become a fundamental design question and an increasingly detailed inspection problem for the aircraft operator. The aircraft industry and the airlines are both interested in the use of thin sheet material in order to achieve weight reduction. Moreover, the economics of aircraft production, the increasing sophistication of inspection procedures and the need for lengthened lifetimes of aircraft already in service must all be considered. The problem of fatigue of lap joints has been considerably enlarged by the goal of extending aircraft lifetimes which may already exceed, e.g., 20 years. Fatigue of riveted lap joints between aluminium alloy sheets, typical of the pressurized aircraft fuselage, is the major topic of this book. Bonded lap joints are not included. These joints appear to have attractive fatigue properties. However, no major breakthrough has occurred due to questions associated with production techniques, quality assurance and inspections. One newcomer to the industry is using weldable aluminium alloys in integral structures with stiffeners, which offer a means of replacing lap joints by butt joints. Long time service experience with these structures is not yet available and this type of connection is also outside the present survey. Fatigue response of a riveted connection depends on the integrated effect of a large number of variables related to joint design and production and applied loading conditions. In view of that dependency, numerous research programs on v

6 vi Preface fatigue of riveted lap joints have been carried out and reported in the literature, as discussed in this book. The book consists of ten chapters. Chapter 1 gives basic information on structural design solutions for fuselage skin joints and loading conditions. Although the stress distribution in a fuselage lap joint is of a complex character, a great majority of experimental studies reported in the literature were carried out in laboratory conditions on simple small lap joint specimens under uniaxial tension. The relevance of such results to riveted joints in a real structure is considered in Chap. 2. The fatigue behaviour of riveted lap joints shows a considerable dependency on factors associated with the production process. In Chap. 3, the following production variables are taken into account: sheet material, rivet type and material as well as the manufacturing process, including riveting techniques, rivet hole imperfections, surface treatment of the sheets and the squeeze force. The latter is a major factor that influences the fatigue behaviour of riveted joints. In Chap. 4, the dependence of joint fatigue performance on various design parameters is addressed. Specifically, the effects of the number of rivet rows, rivet row spacing, rivet pitch in a row, rivet pattern and sheet thickness are accounted for. An analytical solution and experimental results on load transmission in lap joints with mechanical fasteners are considered in Chap. 5. Special attention is paid to the experimental and theoretical determination of fastener flexibility and to friction between the faying sheets in view of their importance for load transfer. Eccentricities occurring in the overlap region of a joint induce a so-called secondary bending. Estimates of secondary bending by means of simple analytical models, FE computations and measurements are presented in Chap. 6. Also, implications of secondary bending for joint fatigue performance are considered. The nucleation and shape development of fatigue cracks in longitudinal lap joints is covered in Chap. 7. Issues given special attention are the influence of the squeeze force on the mode of failure and the significance of fretting for fatigue crack initiation. A characteristic and very dangerous form of fatigue damage in longitudinal riveted lap joints is the so-called multi-site damage (MSD). In Chap. 8, passenger aircraft catastrophic accidents due to MSD are described first. Next, an overview of experimental investigations into MSD performed on full scale fuselage panels and riveted lap joint specimens is offered. Chapter 9 is devoted to fatigue crack growth and fatigue life prediction methodology for riveted lap joints, including the MSD problem. Models and codes most commonly used for that purpose are outlined and stress intensity factor solutions appropriate for cracks at rivet holes are presented. A particular consideration is given to the equivalent initial flaw size concept due to its significance for the prediction quality. Residual strength predictions for riveted lap joints in a fuselage structure are addressed in Chap. 10. Failure criteria and crack growth directional criteria are thoroughly considered. Various computational approaches to estimate residual strength of panels with riveted connections are presented and reported comparisons between predictions and experimental results are reviewed. Structural risk analysis methodology applicable to riveted joints with MSD is overviewed. The major issues of each chapter are recapitulated in the last section. The material presented in the book is richly illustrated.

7 Acknowledgements Though the authors of the book appear to be the only contributors to its contents, in reality it is an achievement made possible due to the help and efforts of other persons whom we would like to thank. First of all we want to express our deepest thanks to Prof. Jaap Schijve from the Delft University of Technology, our friend and collaborator for many years, for his encouragement, enduring help and interest in this work. Without his suggestions and support, in particular providing us with a number of literature sources to which it was difficult to gain access, we would have never been able to prepare this book. We want to express our appreciation to Johannes Homan, M.Sc., from Fatec Engineering for his useful comments and information on some selected problems. Our co-workers Dr. Tomasz Machniewicz and Adam Korbel, M.Sc., from the AGH University of Science and Technology in Kraków were always available for discussion. They also deserve our particular thanks for their great help in preparing the figures in a printable form. We gratefully acknowledge the thorough work done by Mr. Edwin Beschler, an English language copy editor provided by Springer to improve the text of the book. With respect to publishing the book by Springer, we appreciate the nice and effective cooperation with Ms. Nathalie Jacobs and Ms. Anneke Pot as well as Ms. Arulmurugan Pavitra responsible for the typesetting of the book. An incentive to write this book was the authors participation in projects concerning fatigue of riveted joints in aircraft structures. Financial support from the associated governmental research funds within the years is acknowledged. vii

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9 Contents Nomenclature... xiii Units and Conversion Factors... xv 1 Riveted Lap Joints in a Pressurized Aircraft Fuselage Constructional Solutions of the Fuselage Skin Structure Loading Conditions for a Longitudinal Lap Splice Joint Bonded and Riveted-Bonded Lap Joints Fatigue Damage of Longitudinal Lap Splice Joints Summary of This Chapter Differences Between the Fatigue Behaviour of Longitudinal Lap Joints in a Pressurized Fuselage and Laboratory Lap Joint Specimens Stress Distribution and Specimen Geometry Effect of the Load Frequency and Environmental Conditions Summary of This Chapter Production Variables Influencing the Fatigue Behaviour of Riveted Lap Joints Sheet Material Fastener Type and Material Manufacturing Process Riveting Method Imperfections of Rivet Holes Cold Working of Rivet Holes Surface Treatment of the Sheets Squeeze Force Summary of This Chapter Design Parameters Influencing the Fatigue Behaviour of Riveted Lap Joints Number of Rivet Rows ix

10 x Contents 4.2 Rivet Row Spacing RivetPitchinRow Distance of the Rivet from the Sheet Edge Rivet Pattern Sheet Thickness Size Effect Summary of This Chapter Load Transfer in Lap Joints with Mechanical Fasteners Simple Computation of Axial Forces in the Sheets Fastener Flexibility Analytical Solution Experimental Determination Measurement Results on Load Transmission Frictional Forces Summary of This Chapter Secondary Bending for Mechanically Fastened Joints with Eccentricities The Phenomenon of Secondary Bending Analytical Investigations Models Exemplary Applications to Lap Joints Finite Element Modelling Measurements of Secondary Bending Methodology Comparisons Between Measured and Computed Results Parametric Studies In Situ Measurement Results Fatigue Behaviour of Joints Exhibiting Secondary Bending Effect of Secondary Bending on Fatigue Life Effect of Faying Surface Conditions Summary of This Chapter Crack Initiation Location and Crack Shape Development in Riveted Lap Joints Experimental Trends Crack Initiation Site Static Loading Fatigue Loading The Role of Fretting The Phenomenon of Fretting Cracking in the Presence of Fretting Fatigue Crack Shape Development Summary of This Chapter

11 Contents xi 8 Multiple-Site Damage in Riveted Lap Joints Experimental Observations Examples of Aircraft Catastrophic Failure Due to MSD Experimental Investigations of MSD Multiple-Site Damage Versus Single-Site Damage Influence of the Riveting Force on MSD MSD Under Biaxial Loading MSD Tests on Fuselage Panels Effect of Fuselage Design on MSD Effect of Bending, Overloads and Underloads on MSD Fatigue Behaviour of Lap Joints Repaired by Riveting Approach to MSD in Aging and New Aircraft Summary of This Chapter Predictions of Fatigue Crack Growth and Fatigue Life for Riveted Lap Joints Introduction Crack Growth Prediction Models Stress Intensity Factor Solutions Equivalent Initial Flaw Size Predictions of MSD Crack Growth Fatigue Life Predictions Summary of This Chapter Residual Strength Predictions for Riveted Lap Joints in Fuselage Structures Introduction Crack Link-Up and Failure Criteria Plastic Zone Link-Up (PZL) Criterion Elastic-Plastic Fracture Mechanics Failure Criteria Crack Growth Directional Criteria Computational Issues Comparisons Between Predicted and Measured Residual Strength of Fuselage Lap Joints for Self-Similar Crack Growth Flat Panels Curved Panels Comparisons Between Observed and Predicted Effect of Tear Straps on Crack Path Structural Risk Analysis Summary of This Chapter References Index

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13 Nomenclature Symbols a c D D o d dc/dn d e E E f e F cl F sq F u f H H o h he K K b M N f P p R R TR r S depth of part through crack crack length rivet driven head diameter rivet shank diameter rivet hole diameter fatigue crack growth rate expanded hole diameter sheet material elastic modulus fastener material elastic modulus load path eccentricity clamping force squeeze force shear strength rivet flexibility, or load frequency rivet driven head height initial rivet height (protruding) countersink depth hole expansion stress intensity factor bending factor bending moment fatigue life applied tensile load rivet row spacing, or pressure stress ratio, or fuselage radius load transfer ratio rivet hole radius applied or nominal stress xiii

14 xiv Nomenclature S b S LO S sq S u S y s T BP T BR T FR T TR t w ı c b LINK-UP r nominal bending stress lift-off stress squeeze pressure ultimate tensile strength yield stress rivetpitchinrow bypass load bearing load friction force transfer load sheet thickness bending deflection, or specimen width rivet deflection friction coefficient Poisson s ratio critical CTOA local bending stress applied stress at which crack link-up occurs residual radial stress, or residual strength residual tangential stress Subscripts a m max (min) op amplitude mean maximum (minimum) level of S or K in fatigue cycle crack opening level of S or K in fatigue cycle Abbreviations CA CGR CTOA CW EIFS EPFM FE LEFM MSD POF PSC constant amplitude fatigue crack growth rate crack tip opening angle cold working equivalent initial flaw size elastic plastic fracture mechanics finite element linear elastic fracture mechanics multiple-site damage probability of failure plane strain core

15 Nomenclature xv PZL SB SIF SSD SY TTCI VA plastic zone link-up secondary bending stress intensity factor single-site damage strip yield time to crack initiation variable amplitude Units and Conversion Factors 1ftD m 1in.D 25.4 mm 1ksiD MPa 1psiD kpa 1lbD kg 1ksi p ind MPa p m

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