Experimental study of repair efficiency for single-sided composite patches bonded to aircraft structural panels.

Fatigue response of cracked aluminum panels repaired with a single-sided composite patch is examined. Fatigue tests were carried out under various temperature and humidity conditions. From the experimental results of fatigue tests, the repair efficiency for single-sided composite patches bonded to cracked aluminum panels is evaluated using the range of stress intensity at crack tip. The effect of temperature on the repair efficiency can be found by comparing the results of crack growth at 353 K, 300 K and 223 K. Likewise, the effect of humidity on their repair efficiency can be found by comparing the results of crack growth at 90%, 50% and 25% relative humidity. Other factors that reduce the repair efficiency are also discussed. [ABSTRACT FROM AUTHOR]