Residual stresses are present after elevated temperature cure of adhesively bonded patches to cracked aircraft structures. These residual stress will affect the performance and the durability of the repair. Strain and temperature measurements were made on a real aircraft fuselage section during and after repair at three locations. Thermal buckling of the skin was observed and therefore a pre-curing at a lower temperature was employed. Also at a lower temperature a significant outward bending of the skin was observed which influences the residual stresses. The measured temperature field corresponded well with the theoretical model of Rose. (Copyright (c) 1995, by Delft University of Technology, Faculty of Aerospace Engineering, Delft, The Netherlands.)
Residual Thermal Stresses around Bonded Fibre Metal Laminate Repair Patches on an Aircraft Fuselage
1995
25 pages
Report
No indication
English
Residual Thermal Stresses Around Bonded Fibre Metal Laminate Repair Patches on an Aircraft Fuselage
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