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SUMMARY:Some aspects to strength analysis of aircraft structures with resp
 ects to fatigue and fracture mechanics
DTSTART;VALUE=DATE-TIME:20110330T160000Z
DTEND;VALUE=DATE-TIME:20110330T170000Z
DTSTAMP;VALUE=DATE-TIME:20261009T225534Z
UID:indico-event-122@indico.ipb.ac.rs
DESCRIPTION:Abstract:The fatigue life of structural components is generall
 y divided into crack initiation and crack growth. Where plastic strain pre
 dominates\, at short lives\, crack growth accounts for the major part of c
 yclic to failure. At long lives\, elastic strain is dominant\, as are the 
 cycles occupied by crack initiation. Even in the case of nominal elastic l
 oading\, some zones have stress concentrations leading to plastic fatigue.
  In summary\, fatigue analysis may be thought of as a process of initiatin
 g and then growing a crack\, which finally causes the structure to break i
 nto two or more pieces. The mathematical models used to simulate the initi
 ation and propagation processes are quite different. The initiation phase 
 is usually modelled using strain-life and cyclic stress-strain curves whil
 e the propagation phase uses crack growth rate versus stress intensity cur
 ves.Attention in this consideration is focused on developing computation m
 ethods of damaged structural components with respect fatigue and fracture 
 mechanics. Considered computation methods are based on combining singular 
 finite elements to determine stress intensity factors for cracked structur
 al components with corresponding crack growth lows that include effect of 
 load spectra on number of cycles or blocks up to failure. Crack growth ana
 lyses are considered using two aproaches: conventional and strain energy d
 ensity (SED) approach.For the lifetime evaluation of structural elements u
 ntil the occurrence of initial damage in the low-cycle fatigue domain the 
 relations for which the magnitudes of low-cycle material behaviour propert
 ies have to be obtained experimentally are being used. For the crack propa
 gation analysis and evaluation of residual lifetime of structures two appr
 oaches can be used. First approach is based on conventional crack propagat
 ion laws such as Paris` crack propagation law\, for which it is necessary 
 to experimentally obtain dynamic properties of the material. The second ap
 proach for crack propagation analysis is based on the use of Strain Energy
  Density Method. This approach uses the low-cycle properties of the materi
 al\, which are also being used for the lifetime evaluation until the occur
 rence of initial damage. Therefore experimentally obtained dynamic propert
 ies of the material such as Paris` constants are not required when this ap
 proch is concerned.To demonstrate efficient computation procedure in fatig
 ue life estimation here numerical examples are included. Attention in this
  work is focused on design of aircraft wing-fuselage joints. Computation p
 rocedure to strength analize with respects fatigue and fracture mechanic i
 s applied to cracked aircraft structural components. Computation results a
 re compared with correspond experiments.\n\nhttps://events.saifa.rs/event/
 122/
LOCATION:Mathematical Institute 301 F
URL:https://events.saifa.rs/event/122/
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