In　this　article,　active　flutter　and　aerothermal　postbuckling　control　of　the　nonlinear　composite　laminated　panel　with　large　deformation　in　supersonic　airflow　using　the　piezoelectric　material　are　investigated.　The　distributed　piezoelectric　actuator　and　sensor　pairs　are　bonded　on　the　top　and　bottom　surfaces　of　the　laminated　panel.　The　von　Karman　strain-displacement　relation　is　used　in　the　structural　modeling.　Unsteady　aerodynamic　pressure　is　evaluated　by　the　supersonic　piston　theory.　Hamilton＇s　principle　and　the　assumed　mode　method　are　applied　to　formulate　the　equation　of　motion　of　the　structural　system.　A　discrete　linear-quadratic-Gaussian　controller　is　designed　in　this　study　to　conduct　the　active　flutter　and　postbuckling　control.　The　proportional　feedback　control　method　is　also　applied　in　designing　the　controller.　Time　domain　responses　of　the　structural　system　are　computed　using　the　Runge-Kutta　method.　The　control　effects　of　the　two　control　methods　are　compared.　The　influences　of　the　placements　of　the　piezoelectric　actuator　and　sensor　pairs　on　the　control　effects　are　also　investigated.　This　study　is　helpful　for　the　active　aeroelastic　design　of　the　nonlinear　structural　system.