LMI Optimal Control for a Flexible Aircraft

The feasibility of linear matrix inequalities (LMI) method for state feedback
$\boldsymbol{H}_{\infty}$
control in aircraft gust alleviation is studied. Taking “1-cos” gust as input disturbance, three examples are used to verify its feasibility, which are a two-dimensional aeroelastic wing model, a rigid aircraft and a flexible aircraft. The results show that the H control law designed based on the LMI method can achieve the purpose of alleviating the gust load.