In this paper, effects of thermal residual stresses on the fatigue strength and crack front shape of the single-side repaired panels using composite patches were investigated. Upon cooling the fully cured, patched structure to the ambient temperature, thermal stress will inevitably develop in both the plate and the reinforcement, due to cooling a locally stiffened structure, especially when the reinforcing patch has a lower coefficient of thermal expansion than the plate being repaired. Thermal stresses may also arise when the patch structure experiences thermal cycling in service. Therefore, thermal residual stresses represent a major concern to the repair efficiency of a repair. This is because the resulting thermal residual stresses highly affect the stress-intensity for repaired cracks. These stresses lead to an increase of the stress-intensity factor, which provoke the reduction of the fatigue life of repaired aeronautical structures. To attenuate the effects of the thermal residual stresses on the repair performance the curing temperature and the adhesive properties must be optimised. As a perspective, the authors will analyse experimentally the effect of the thermal residual stresses on the fatigue life of the repaired structures.
Numerical analysis of the effect of thermal residual stresses on the performances of bonded composite repairs in aircraft structures
Composites, Part B: Engineering ; 42 , 3 ; 511-516
2011
6 Seiten, 9 Bilder, 1 Tabelle, 24 Quellen
Aufsatz (Zeitschrift)
Englisch
Adhäsion , Ausbesserung (Reparatur) , Aushärten , Dauerschwingfestigkeit , Ermüdungslebensdauer , Finite-Elemente-Methode , Klebstoff , Kühlen , Luftfahrttechnik , Luftfahrzeug , numerisches Verfahren , Reparatursatz , Restspannung (mechanisch) , Riss , Spannungsintensitätsfaktor , Temperaturwechselbeanspruchung , thermischer Ausdehnungskoeffizient , Verbundwerkstoff , Verstärkung (Festigkeit) , Wärmespannung
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