The　stability　analysis　and　active　control　of　a　nonlinear　composite　laminated　plate　in　subsonic　airflow　are　studied.　The　equation　of　motion　of　a　plate　with　a　piezoelectric　patch　in　subsonic　air　flow　is　established　by　using　the　Hamilton＇s　principle　with　the　assumed　mode　method.　The　perturbation　aerodynamic　pressure　is　derived　from　linear　potential　flow　theory.　For　the　linear　system,　the　eigenfrequencies　of　the　system　are　calculated　for　different　flow　velocities,　and　the　critical　instability　flow　velocity　and　the　flutter　flow　velocity　are　obtained.　For　the　nonlinear　system,　the　bifurcation　of　the　transverse　displacement　with　respect　to　the　flow　velocity　is　analyzed　by　solving　the　equations　of　equilibrium　of　the　nonlinear　dynamic　system.　The　effects　of　the　ply　angles　on　the　critical　instability　flow　velocities　of　the　plate　are　analyzed.　According　to　the　mechanism　for　the　instability　of　the　plate　in　subsonic　flow,　the　displacement　feedback　control　strategy　is　adopted　to　stabilize　the　system.　The　influences　of　the　control　gain　on　the　critical　instability　velocity　of　the　plate　are　analyzed.　From　the　analysis　and　numerical　simulations,　it　can　be　concluded　that　with　the　ply　angle　increasing　from　to　,　the　critical　instability　flow　velocity　of　the　plate　has　a　maximum　at　a　finite　critical　angle.　When　the　flow　velocity　exceeds　the　critical　instability　flow　velocity,　the　stable　point　of　the　nonlinear　system　deviates　from　the　zero　point　of　the　system.　It　also　can　be　concluded　that　the　displacement　feedback　control　can　effectively　improve　the　aerodynamic　properties　of　the　plate　by　providing　the　active　stiffness　for　the　unstable　system.　With　displacement　feedback　control　gain　increasing,　the　critical　instability　flow　velocity　increases.