Design, analysis and properties solid mechanics and its applications skorupa, andrzej, skorupa, malgorzata on. A semiempirical fatigue life prediction model under development by the present authors for riveted lap joints used in aircraft structures is outlined. The specimens are representative of the lonitudinag l lap joints of a commercial aircraft in which multiplesite damage msd was found in service. This simple model does not require detailed contact analysis. The joint consists of two sheets with dimensions of 125. Stress analysis and fatigue estimation of centre fuselage. Simple energy dissipation model of riveted lap joint in. In this study, we made a simple energy dissipation model for riveted lap joint by replacing the joint part with a material that draws a hysteresis loop. For the cj aft fuselage, the framing process needed to be redesigned to allow for 70% 80% automation of fastener installation. Design, analysis and properties solid mechanics and its applications. The aluminium alloys are used in the splice joints. Fuselages of naval aircraft have much in common from the standpoint of construction and design. Corrosion pillowing in aircraft fuselage lap joints. Design, analysis and properties solid mechanics and its applications 2012 by andrzej skorupa, malgorzata skorupa isbn.
As an example, a manoeuvre case which produces high vertical bending moment on the rear fuselage. Highlights effect of design and production factors on riveted lap joint fatigue response studied experimentally. Uniaxial and biaxial tests on riveted fuselage lap joint specimens october 1998 final report this document is available to the u. To determine the effect of rivet hole interference on the fatigue behaviour of a riveted joint, a series of. This structure consists of a skin to which have been riveted longitudinal stiffeners along. Fatigue strength reduction factors at rivet holes for. Proceedings of the 8th joint nasafaadod conference on aging aircraft, january 31 february 3, 2005, palm springs, ca evolution of multiplesite damage in the riveted lap joint of a fuselage panel abubaker ahmed faadrexel fellowship student faa william j. Us20150097076a1 aircraft wingtofuselage joint with. Skorupa and others published fatigue strength reduction factors at rivet holes for aircraft fuselage lap joints find, read and. Experimental studies of the fatigue and durability of panels forming a longitudinal lap joint of the fuselage skin are considered. The first genav aircraft to do so was jim bedes bd1 known to the rest of us a american aviation yankee. Rivets are highly used in aircraft fuselage manufacturing and repairing processes.
The procedure was developed to eliminate the risk of widespread fatigue damage wfd in the upper rivet row of a fuselage lap joint. In singleengine aircraft, it will usually contain an engine, as well, although in some amphibious aircraft the single engine is mounted on a pylon attached to the fuselage, which in turn is used as a floating hull. There is a big range of bolt and riveted joint applications, both in aircraft and jet engine structures. However, examination of fatigue test results on a fullscale fuselage test article 1 indicate that the riveted holes in the lap joint are in a neatfit condition and interference is not needed to predict the fatigue crack growth rates.
Riveted lap joints in aircraft fuselage andrzej skorupa. Hughes technical center atlantic city international airport, nj 08405, usa. A series of fatigue tests on aluminium alloy sheet coupons with an open hole and filled hole subjected to remote tension, pin loading and outofplane bending have been carried out. A series of fatigue tests on aluminium alloy sheet coupons with an open hole and filled hole subjected to remote tension, pin loading. This investigation was conducted to propose an estimation method for energy dissipation in riveted lap joints. References are provided to literature that explores these suggestions in more detail.
Both of the lee and aerodrome designs have been successful with a riveted tube construction i am told. There is no comparable book with such a comprehensive and explanatory description of fatigue of riveted lap joint. An experimental investigation on crack initiation and. Among the solutions are the interior layout and cross section definition, initial geometric and weight. Only those load cases critical for that particular section of the fuselage are recovered and processed. C a comparative investigation on the fatigue strength at fluctuating tension of several types of riveted lap joints, a series of bolted and some series of glued lap joints of 24 st alclad. Riveted lap joints in aircraft fuselage design, analysis.
Pdf download riveted lap joints in aircraft fuselage. Use features like bookmarks, note taking and highlighting while reading riveted lap joints in aircraft fuselage. A test and evaluation program has been conducted by fostermiller, inc. Figure 191 shows an aluminum aircraft fuselage skin subassembly. The decoupled joint can be an active suspension system. Static and buckling analysis of center fuselage structure. Applicability of empirical formulae for the fatigue notch. After the aloha 737200 accident, in which a 12ft x 8ft section of the upper fuselage tore away in flight, all 737s with over 50,000 cycles must have their lap joints reinforced with external doublers. The design of bolted and riveted joints are usually calculated based on the loads across the joint and how they are applied. Stress analysis and fatigue estimation of centre fuselage of an aircraft. The designer of an aircraft chooses the solutions best adapted to the materials used a continuous joint with wood and composites, a single bolt or heavy thick fittings with steel. In the ordinary lapjoint, the plates overlap each other and are held together by one or more rows of rivets.
We will examine the fuselage construction in more detail later, and will brie. Growth of multiple cracks and their linkup in a fuselage. The fuselage can be made from a wide range of materials which can be riveted, bolted, screwed, welded or bonded together. Growth of multiple cracks and their linkup in a fuselage lap joint ripudaman singh, jai h. Dotfaaar042 office of aviation research washington, d. Although different joining techniques exist, the skin panels are typically fastened together with rivets. Laboratory nlr has carried out fatigue tests on riveted lap joint specimens. This project deals with the stress analysis of adhesively bonded riveted lap joints. For thick sheets hole expansion and load transfer are behind the squeeze force impact.
Design, analysis and properties solid mechanics and its applications book 189 kindle edition by skorupa, andrzej, skorupa, malgorzata. An aircraft includes a fuselage, a wing, and a decoupled joint interconnecting the fuselage and the wing. Proceedings of the 8th joint nasafaadod conference on aging aircraft, january 31 february 3, 2005, palm springs, ca evolution of multiplesite damage in the riveted lap joint of a fuselage panel abubaker ahmed faadrexel fellowship student. This tired old aircraft is a 737200 and the patching is clearly visable. Fatigue crack location and fatigue life for riveted lap. Lap joints aircraftengineering aircraft passionates. A method of adapting an aircraft to attenuate forces between a main wing and a fuselage thereof includes providing a plurality of sensors upon the aircraft, configured for sensing motion andor mechanical stress of the main.
Effects of variables related to design and production of riveted lap joints representative of longitudinal sheet connections for a pressurized transport aircraft fuselage were experimentally investigated. This paper presents, as an example, the solutions of the structures design of a fuselage for a 30 seats commercial aircraft. Us20140054418a1 us973,341 us20973341a us2014054418a1 us 20140054418 a1 us20140054418 a1 us 20140054418a1 us 20973341 a us20973341 a us 20973341a us 2014054418 a1 us2014054418 a1 us 2014054418a1 authority us united states prior art keywords former door frame metal laminate frame construction fibre metal. Dotfaaar9833 uniaxial and biaxial tests on riveted. Download it once and read it on your kindle device, pc, phones or tablets. Does anybody knows how to calculate rivet dia for lap. Aircraft rivets download this royalty free stock photo in seconds. Correction factors for calculating strain intensities, panel durability until crack formation, the duration of the process of fatigue crack growth until damage to panels, and criteria of their residual strength are given. Everyday low prices and free delivery on eligible orders. Numerical analysis of riveted lap joint used in aircraft structures the paper presents the results of fem analysis of two rivet lap joints loaded with tension. The fuselage is the body of the aircraft, the main structure to which all other units attach. The fuselage of an aircraft consists of sheet panels, stringers, and stiffeners held together by riveted lap joints.
Legacy processes for the manufacture of riveted aircraft structures typically involve locating rivets by means of pilot holes in the substructure. Two different rivet configurations, dimpled and countersunk riveted joints, were investigated. Whenever fatigue of lap joints must be considered for designing a fuselage or analysing fatigue in lap joints of existing aircraft, this book should be consulted. Fatigue test results to be utilized in a fatigue life prediction model for aircraft fuselage riveted lap joints are presented.
Riveted lap joints in a pressurized aircraft fuselage. Dotfaaar042 bulging factor solutions for cracks in. Fmi to evaluate the terminating action repair of the upper rivet row of a commercial aircraft fuselage lap splice. While steel was used for a few aircraft in germany in the 1930s, the metal of choice was, and still is, aluminum. Bonded joints are what made the skin of all aa1abc and aa5ab and ag5b as well as ag7 cougars so clean that they fly a lot faster than their contemporary riveted competitors on. Read riveted lap joints in aircraft fuselage design analysis and properties solid mechanics ebooks online. Basically there are two kinds of riveted joints, the lapjoint and the buttjoint. This filtering of load cases is performed from the integrated loads envelope of the aircraft structure. Application of rivets with the compensator is beneficial only for joints from thicker sheets. The fatigue life of the composite material is also determined. For thin sheets the joint fatigue behaviour is also affected by riveting imperfections. The following sections will cover only structural and machinemember riveted joints. By replacing these alloys by composite material kevlar 49 the fatigue life of the fuselage can be increased.
Full text of a practical engineering approach to predicting fatigue crack growth in riveted lap joints see other formats nasatm2000210106 a practical engineering approach to predicting fatigue crack growth in riveted lap joints c. The specimens from an aircraft al alloy d16 alclad sheets of three different thicknesses 1. Main components of an aircraft are, fuselage, wing empennage or tail, power plant, landing gear or under carriage. Jaap schijve, international journal of fatigue, vol. Department of transportation federal aviation administration. In contrast to existing models, it will account for the influence of the rivet squeeze force on the fatigue life of riveted joints. The problem of fatigue of lap joints has been considerably enlarged by the goal of extending aircraft lifetimes. Introduction forms main body of aircraft to which wings, tail plane, engines and gears are attached in modern aircraft forms a tube structure housing flight deck, pax cabin, hold and equipment also acts as a pressure hull in pressurized aircraft 2. Numerous rivets are required to join the skin completely. It provides space for the crew, passengers, cargo, most of the accessories, and other equipment. Fatigue of riveted lap joints between aluminium alloy sheets, typical of the pressurized aircraft fuselage, is the major topic. Langley research center, hampton, virginia may 2000 the nasa sti program office.
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