1. A built-in diagnostic technique has been developed to monitor hidden fatigue crack growth in aircraft structures.
2. The technique uses diagnostics signals generated from nearby piezoelectric actuators built into the structures to detect crack growth.
3. The proposed diagnostic technique was applied to riveted fuselage joints and a cracked metallic plate repaired with a bonded composite patch, and predictions were correlated quite well with measurements from other methods.
The article is generally reliable and trustworthy, as it provides evidence for its claims in the form of correlations between predictions made using the proposed diagnostic technique and measurements from other methods such as eddy current tests and ultrasonic scans. However, there are some potential biases that should be noted. For example, the article does not explore any counterarguments or present both sides of the argument equally; instead, it focuses solely on promoting the proposed diagnostic technique without considering any potential drawbacks or risks associated with it. Additionally, there is no mention of any limitations or uncertainties associated with the results presented in the article, which could lead readers to overestimate its accuracy and reliability. Finally, there is no discussion of how this technique could be improved upon or adapted for use in different contexts.