Using　Reddy＇s　high-order　shear　theory　for　laminated　plates　and　Hamilton＇s　principle,　a　nonlinear　partial　differential　equation　for　the　dynamics　of　a　deploying　cantilevered　piezoelectric　laminated　composite　plate,　under　the　combined　action　of　aerodynamic　load　and　piezoelectric　excitation,　is　introduced.　Two-degree　of　freedom　(DOF)　nonlinear　dynamic　models　for　the　time-varying　coefficients　describing　the　transverse　vibration　of　the　deploying　laminate　under　the　combined　actions　of　a　first-order　aerodynamic　force　and　piezoelectric　excitation　were　obtained　by　selecting　a　suitable　time-dependent　modal　function　satisfying　the　displacement　boundary　conditions　and　applying　second-order　discretization　using　the　Galerkin　method.　Using　a　numerical　method,　the　time　history　curves　of　the　deploying　laminate　were　obtained,　and　its　nonlinear　dynamic　characteristics,　including　extension　speed　and　different　piezoelectric　excitations,　were　studied.　The　results　suggest　that　the　piezoelectric　excitation　has　a　clear　effect　on　the　change　of　the　nonlinear　dynamic　characteristics　of　such　piezoelectric　laminated　composite　plates.　The　nonlinear　vibration　of　the　deploying　cantilevered　laminate　can　be　effectively　suppressed　by　choosing　a　suitable　voltage　and　polarity.