By Antonio Culla, Walter D Ambrogio (auth.), Tom Proulx (eds.)
Advanced Aerospace purposes, quantity 1. court cases of the twenty ninth IMAC, A convention and Exposition on Structural Dynamics, 2011, the 1st quantity of six from the convention, brings jointly 32 contributions to this crucial zone of study and engineering. the gathering offers early findings and case reviews on primary and utilized points of Structural Dynamics, together with papers on Aeroelasticity, floor trying out, Dynamic trying out of Aerospace buildings, and Random Vibration.
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Extra resources for Advanced Aerospace Applications, Volume 1: Proceedings of the 29th IMAC, A Conference on Structural Dynamics, 2011
0 SPACECRAFT DESCRIPTION The CASSIOPE spacecraft in the stowed launch configuration is shown Figure 1. 4 m in height. The interface to the launch vehicle consists of six discrete mounts which mate with nonexplosive actuators on the launch vehicle. The spacecraft core structure consists of a hexagonal vertical frame constructed of aluminum honeycomb sandwich panels and machined corner posts. There are three horizontal aluminum honeycomb sandwich panels: the ePOP payload panel, the internal Mid-Deck panel, and the CX payload panel.
It may therefore be possible to use such a feature to distinguish damage from boundary condition changes. Figure 8 Relative ultrasonic vibration amplitude changes introduced by boundary condition changes and damage. The results for both the S0 loading function and the A0 loading function are included. Figure 9 Relative changes in the A0/S0 vibration amplitude ratios for different test conditions. The A0/S0 ratios were calculated by dividing the vibration amplitudes obtained under the A0 loading function by the corresponding amplitudes obtained under the S0 loading function.
Surface out-of-plane displacements at a far field location were used for the comparisons. As demonstrated, excellent agreements were obtained. Notice that the amplitudes of the signals were not normalized. Such a comparison therefore validates our time delay annular array guided wave excitation model. 28 Figure 3 Comparison between FEM result and analytical prediction for out-of-plane displacements excited by a 4 element time delay annular array. Excellent agreements were obtained. This validates our analytical model.
Advanced Aerospace Applications, Volume 1: Proceedings of the 29th IMAC, A Conference on Structural Dynamics, 2011 by Antonio Culla, Walter D Ambrogio (auth.), Tom Proulx (eds.)