The　stability　analysis　and　active　control　of　a　composite　laminated　open　cylindrical　shell　in　subsonic　airflow　are　conducted　using　piezoelectric　material.　The　equation　of　motion　of　the　shell　with　piezoelectric　patch　is　derived　from　Hamilton＇s　principle　and　transformed　into　the　ordinary　differential　equations　using　Galerkin＇s　method.　The　linear　potential　flow　theory　is　applied　to　derive　the　aerodynamic　pressure.　The　displacement　and　acceleration　feedback　control　strategies　are　used　to　obtain　the　active　stiffness　and　mass　by　applying　an　appropriate　external　control　voltage　to　activate　the　piezoelectric　patch.　The　natural　frequencies　of　the　system　are　calculated,　from　which　the　flow　velocity　for　the　open　cylindrical　shell　under　instability　can　be　obtained.　The　effects　of　the　ply　angles　of　the　shell　and　the　feedback　control　gains　on　the　stability　properties　of　the　structural　system　are　discussed.　From　the　results,　it　can　be　seen　that　when　the　flow　velocity　becomes　sufficiently　high,　the　open　cylindrical　shell　exhibits　instability　of　the　divergence　type　and　the　instability　velocity　decreases　with　the　increase　in　the　ply　angle.　The　stability　of　the　system　can　be　improved　by　the　displacement　feedback　control　strategy.　With　the　increase　in　the　displacement　feedback　control　gain,　the　instability　velocity　of　the　system　increases.　For　the　acceleration　feedback　control　strategy,　the　instability　velocity　of　the　system　remains　unchanged,　which　illustrates　that　the　active　mass　induced　by　the　acceleration　feedback　has　no　effect　on　the　instability　velocity　of　the　composite　laminated　open　cylindrical　shell.