Advances In The Bonded Composite Repair Of Metallic Aircraft by Baker A.A.

Advances In The Bonded Composite Repair Of Metallic Aircraft by Baker A.A.

By Baker A.A.

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3. Residual thermal stresses Thermal stresses arise due to the different coefficients of thermal expansion of the materials involved and may be significant at the extremes of the operating temperatures. 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.

The resonant frequency increases by 5%, 10% and 13% for vibration modes 1, 2 and 3, respectively, when the patch width increased from 80 to 126mm. A. 20. 6 Frequencies for original uncracked un-repaired plate. Mode Resonant frequency (Hz) 1 218 314 506 2 3 ooz EOP 80E E61 ase3 ,08/0'Z ase3 LIP 61E ,9ZI/O'Z 19P ZPP E IPE SEE Z 91Z 802 1 (ZH)K ~ u a n b q$ueuosa~ apon *9ZI/O'I ase3 ,08/0'1 ase3 Chapter 19. 6~10~ h C 1 . 0x10-6 1E-12 8 . 0 1E-1 5 100 1000 10000 Frequency ( H r ) Fig. 21. O mm thick damping layer with [0/90] boron/epoxy constraining layer and an 80 mm wide by 77 mm long boron/epoxy reinforcement.

Clearly crack closure will occur at an increasing distance away from the crack tip, however the complexity in introducing such constraints is not included in this preliminary study. 4. 1. Modal shapes and frequencies As previously mentioned, one of the main concerns regarding a particular repair is the change of frequency of the plate to the excitation frequencies. 6. 7. The reinforcing patch length ( L ) is 77mm. In all cases the addition of the highly-damped patch configuration resulted in a reduction of frequency.

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