The　optimal　active　flutter　control　of　supersonic　composite　laminated　panels　is　studied　using　the　distributed　piezoelectric　actuators/sensors　pairs.　The　supersonic　piston　theory　is　used　to　calculate　the　unsteady　aerodynamic　pressure,　and　Hamilton＇s　principle　with　the　assumed　mode　method　is　employed　to　develop　the　equation　of　motion　of　the　structural　system.　The　controllers　are　designed　by　the　proportional　feedback　control　method　and　the　linear　quadratic　Gauss　(LQG)　algorithm.　The　optimal　locations　of　the　actuator/sensor　pairs　are　determined　by　the　genetic　algorithm　(GA).　The　aeroelastic　properties　of　the　structural　system　are　mainly　analyzed　using　the　frequency-domain　method.　The　time-domain　responses　of　the　structure　are　also　computed　using　the　Runge-Kutta　method.　The　influences　of　ply　angle　on　the　flutter　bound　of　the　laminated　panel　with　different　length-width　ratios　are　analyzed.　The　optimal　design　for　the　locations　for　different　numbers　of　piezoelectric　patches　used　in　the　proportional　feedback　control　is　carried　out　through　the　GA.　Meanwhile,　the　control　effects　using　different　numbers　of　actuator/sensor　pairs　are　investigated.　The　flutter　suppression　by　the　LQG　algorithm　is　also　carried　out.　The　control　effects　using　the　two　different　controllers　are　compared.　Numerical　simulations　show　that　the　optimal　locations　obtained　by　the　GA　can　increase　the　critical　flutter　aerodynamic　pressure　significantly,　and　the　LQG　algorithm　is　more　effective　in　flutter　suppression　for　supersonic　structures　than　the　proportional　feedback　controller.