Aerothermoelastic　analysis　for　composite　laminated　panels　in　supersonic　flow　is　carried　out.　The　flutter　and　thermal　buckling　control　for　the　panels　are　also　investigated.　In　the　modeling　for　the　equation　of　motion,　the　influences　of　in-plane　thermal　load　on　the　transverse　bending　deflection　are　taken　into　account,　and　the　unsteady　aerodynamic　pressure　in　supersonic　flow　is　evaluated　by　the　linear　piston　theory.　The　governing　equation　of　the　structural　system　is　developed　applying　the　Hamilton＇s　principle.　In　order　to　study　the　influences　of　aerodynamic　pressure　on　the　vibration　mode　shape　of　the　panel,　both　the　assumed　mode　method　(AMM)　and　the　finite　element　method　(FEM)　are　used　to　derive　the　equation　of　motion.　The　proportional　feedback　control　method　and　the　linear　quadratic　regulator　(LQR)　are　used　to　design　the　controller.　The　aeroelastic　stability　of　the　structural　system　is　analyzed　using　the　frequency-domain　method.　The　effects　of　ply　angle　of　the　laminated　panel　on　the　critical　flutter　aerodynamic　pressure　and　the　critical　buckling　temperature　change　are　researched.　The　flutter　and　thermal　buckling　control　effects　using　the　proportional　feedback　control　and　the　LQR　are　compared.　An　effective　method　which　can　suppress　the　flutter　and　thermal　buckling　simultaneously　is　proposed.　(c)　2013　Elsevier　Ltd.　All　rights　reserved.