Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/3207912/figures/3207912.fig.0014a.svgz" name="3207912.fig.0014a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Displacement of a wing tip</td></tr><tr class="fig-image" id="b"><td><object data="https://static.hindawi.com/articles/ijae/volume-2019/3207912/figures/3207912.fig.0014b.svgz" name="3207912.fig.0014b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Relative deviation between FEM and ROM</td></tr></table>

<div>Displacement of a wing tip under validation loads.</div>

International Journal of Aerospace Engineering

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Figure 14

Figure 14: Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM 