Shaker frequency response measurements of a composite aircraft wing: raw time records, acquisition program and analysis script

This dataset contains the raw time-series records, data acquisition program, and analysis script used for shaker-based frequency response function measurements on a composite unmanned aerial vehicle wing with a spanwise length of 749.3 mm. The wing was clamped at its root and excited by an electrodynamic shaker through a stinger and an in-line force transducer. A Schroeder-phase multisine covering 5–800 Hz with a frequency resolution of 0.1 Hz was used as the excitation signal. Two measurement points were defined 60 cm from the root: one near the trailing edge and the other near the leading edge. Four measurements were carried out, forming a nominal two-by-two input-output layout. Each raw measurement file contains a self-describing header followed by five tab-separated columns: time, analog output command, force, duplicate force channel, and acceleration. The sampling rate was 10 kHz, and each measurement consisted of 10 successive periods with a total duration of 100 s. The force transducer sensitivity was 22.18 mV/N, and the accelerometer sensitivity was 103.0 mV/g. Data acquisition was performed using an ADLINK PCI-9222 card, with the analog output and input streams started from a common trigger. The MATLAB script estimates the accelerance frequency response functions using the H1 estimator and reproduces the modal frequencies reported in the associated article, “Design and Modal Analysis of an Aircraft Wing in SolidWorks and ANSYS with Experimental Verification.” README.txt provides further information about the measurement configurations, file structure, signal-processing steps, and the observability of the identified structural modes.