For my case, there are no PSD input base excitation provided and I do not have access to an accelerometer. I've tried using the max deformation from each node of total deformation in Modal Analysis to determine the PSD Displacement (m2/Hz) for Random Analysis. I used the formula (deformation x deformation) / frequency. My goal is to determine the amount of vibration exerted on the wing of the model. Does the Response PSD obtained valid? Do you have any suggestion?
Below are how I've done my analysis on the aircraft model wing geometry.
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