By Baker A.A.
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Additional resources for Advances In The Bonded Composite Repair Of Metallic Aircraft Structure
Furthermore it is known that the residual thermal stresses due to the bonding process may be significant. Typically the bonding process results in curing at a temperature of approximately 80-120 " C . In the case of a boron/epoxy repair to an aluminium plate there is a large difference in the coefficients of thermal expansion. As a result the residual stress intensity for a repair involving boron/ Chapter 19. Bonded repair of acoustic fatigue cracking 561 epoxy is comparable to the stress intensity for the out-of-plane vibration.
Fig. 9. Frequency versus crack length for un-repaired and repaired cases Chapter 19. 1 Hz 54 1 Fig. 10. Mode shapes for the repaired panel containing a short crack (2a=50mm). short and long cracks for the un-repaired and repaired panel. 10. 10 indicate that the crack tip behaviour is dominated by the mode I stress intensity factor KI. 3 Hz Fig. 11. Mode shapes for the repaired panel containing a long crack (2a= 196mm). 8). These mode shapes indicate that the unsupported crack tip behaviour will now have significant contributions from mode I11 stress intensity factor, The modal analysis indicates that all the mode I, I1 and I11 stress intensity factors will be significant.
Comparison of Dyad 606 and 609 over the entire temperature range. 9. Thermal environment for F/A-18 Results of a thermal profile of the F/A-18 have been obtained from . These flight tests were performed to establish the thermal profile at the edges of the flight envelope in order to provide design information for bonded repairs.