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

By Baker A.A.

ISBN-10: 0080426956

ISBN-13: 9780080426952

ISBN-10: 0080427022

ISBN-13: 9780080427027

ISBN-10: 0080436897

ISBN-13: 9780080436890

ISBN-10: 0080437109

ISBN-13: 9780080437101

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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.

Fig. 14. 15, (KrI),s has been substantially reduced. Note that when the right hand crack tip grows out from under the repair, the value for (KII)rmsfor the right hand outer crack tip exceeds the value for the right hand inner crack tip. 11. Also it would be expected that the right hand inner and outer values would converge approaching the right hand boundary. 17. 16. The values of (KIII)rmsincrease significantly with crack length for both left and right hand crack tips, and the 544 Advances in the bonded composite repair of metallic aircraft structure -m-f 55- e- 4- -i 31 I v 2 -A- KII left outer KII left inner KII right outer .

Acoustic fatigue crack growth data In this study, it has been necessary to show that standard crack growth laws can be applied to structures subject to high frequency out-of-plane bending excitation. K. ) and a standard crack growth law. 32, is equivalent to 2014-T6. 0 x assumed to be equal to AK,,,. The crack growth law is usually determined from testing at a frequency of typically 4-10 Hz. Also Eq. 11) is only valid for a range of 6-50 MPa m1’2. 33. The experimental data corresponds to a sinusoidal data at 175Hz and shows surprisingly good agreement.

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

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