Features wear nodes mechanization wing aircraft operating under dynamic loads

Dynamic Response of Single Piles Under Lateral Loads and Earthquakes

Simultaneous Ultrasonic Monitoring of Crack Growth and Dynamic Loads during a Full Scale Fatigue Test of an Aircraft Wing

An in situ ultrasonic angle beam method has been developed to detect and size fatigue cracks emanating from fastener holes. The method employs transducers mounted in a pitch-catch configuration on each side of the hole, and the modulation of received signals with load is used to detect and size small fatigue cracks. The focus of this paper is the monitoring of a series of critical fastener hole...

Dynamic Analysis of Single Piles Under Vertical Loads

Dynamic Response of Single Piles Under Lateral Loads and Earthquakes

Obliique-Wing Aircraft

The application of the eigensystem synthesis technique to place the closed-loop eigenvalues and shape the closed-loop eigenvectors has not been practical for active flutter suppression, primarily because of the availability of only one control surface (aileron) for flutter suppression. The oblique-wing aircraft, because of its configuration, provides two independent surfaces (left and right ail...