A Virtual Testing Approach For Honeycomb Sandwich Panel Joints In Aircraft Interior

Virtual test methods can contribute to reducing the great effort for physical tests in the development of lightweight products. The present work describes an approach for virtual testing of sandwich panel joints based on the Building Block Approach and the Finite Elements Method. Building on a multitude of physical tests on sandwich materials and joints, adequate sub-models are developed, validated and synthesized to top-level models. The developed approach is eventually applied for the development of a novel sandwich panel joint.

This book, framed in the processes of engineering analysis and design, presents concepts in mechanics of materials for students in two-year or four-year programs in engineering technology, architecture, and building construction; as well as for students in vocational schools and technical institutes. Using the principles and laws of mechanics, physics, and the fundamentals of engineering, Mechanics of Materials: An Introduction for Engineering Technology will help aspiring and practicing engineers and engineering technicians from across disciplines—mechanical, civil, chemical, and electrical—apply concepts of engineering mechanics for analysis and design of materials, structures, and machine components. The book is ideal for those seeking a rigorous, algebra/trigonometry-based text on the mechanics of materials.

This book provides a self-contained course in aircraft structures which contains not only the fundamentals of elasticity and aircraft structural analysis but also the associated topics of airworthiness and aeroelasticity.

Polymer composites are increasingly used in aerospace applications due to properties such as strength and durability compared to weight. Edited by two leading authorities in the field, this book summarises key recent research on design, manufacture and performance of composite components for aerospace structures. Part one reviews the design and manufacture of different types of composite component. Part two discusses aspects of performance such as stiffness, strength, fatigue, impact and blast behaviour, response to temperature and humidity as well as non-destructive testing and monitoring techniques.

Fatigue of the pressurized fuselages of transport aircraft is a significant problem all builders and users of aircraft have to cope with for reasons associated with assuring a sufficient lifetime and safety, and formulating adequate inspection procedures. 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 lap joints, sometimes leading to circumstances that threaten safety in critical ways. The problem of fatigue of lap joints has been considerably enlarged by the goal of extending aircraft lifetimes. Fatigue of riveted lap joints between aluminium alloy sheets, typical of the pressurized aircraft fuselage, is the major topic of the present book. The richly illustrated and well-structured chapters treat subjects such as: structural design solutions and loading conditions for fuselage skin joints; relevance of laboratory test results for simple lap joint specimens to riveted joints in a real structure; effect of various production and design related variables on the riveted joint fatigue behaviour; analytical and experimental results on load transmission in mechanically fastened lap joints; theoretical and experimental analysis of secondary bending and its implications for riveted joint fatigue performance; nucleation and shape development of fatigue cracks in riveted longitudinal lap joints; overview of experimental investigations into the multi-site damage for full scale fuselage panels and riveted lap joint specimens; fatigue crack growth and fatigue life prediction methodology for riveted lap joints; residual strength predictions for riveted lap joints in a fuselage structure. The major issues of each chapter are recapitulated in the last section.

Introduction to Aircraft Structural Analysis is an essential resource for learning aircraft structural analysis. Based on the author's best-selling book Aircraft Structures for Engineering Students, this brief text introduces the reader to the basics of structural analysis as applied to aircraft structures. Coverage of elasticity, energy methods and virtual work sets the stage for discussions of airworthiness/airframe loads and stress analysis of aircraft components. Numerous worked examples, illustrations, and sample problems show how to apply the concepts to realistic situations. The book covers the core concepts in about 200 fewer pages by removing some optional topics like structural vibrations and aero elasticity. It consists of 23 chapters covering a variety of topics from basic elasticity to torsion of solid sections; energy methods; matrix methods; bending of thin plates; structural components of aircraft; airworthiness; airframe loads; bending of open, closed, and thin walled beams; combined open and closed section beams; wing spars and box beams; and fuselage frames and wing ribs. This book will appeal to undergraduate and postgraduate students of aerospace and aeronautical engineering, as well as professional development and training courses. Based on the author's best-selling text Aircraft Structures for Engineering Students, this Intro version covers the core concepts in about 200 fewer pages by removing some optional topics like structural vibrations and aeroelasticity Systematic step by step procedures in the worked examples Self-contained, with complete derivations for key equations

The Fourth Conference on Fibrous Composites in Structural Design was a successor to the First-to-Third Conferences on Fibrous Composites in Flight Vehicle Design sponsored by the Air Force (First and Second Conferences, September 1973 and May 1974) and by NASA (Third Conference, November 1975) which were aimed at focusing national attention on flight vehicle applications of a new class of fiber reinforced materials, the advanced com posites, which afforded weight savings and other advantages which had not been previously available. The Fourth Conference, held at San Diego, California, 14-17 November 1978, was the fi rst of these conferences to be jointly sponsored by the Army, Navy and Ai r Force together with NASA, as well as being the first to give attention to non-aerospace applications of fiber reinforced composites. While the design technology for aerospace applications has reached a state of relative maturity, other areas of application such as mi litary bridging, flywheel energy storage systems, ship and surface vessel components and ground vehicle components are in an early stage of development, and it was an important objective to pinpoint where careful attention to structural design was needed in such applications to achfeve maximum structural performance payoff together with a high level of reliability and attractive economics.