Aeroelastic　characteristics　of　supersonic　panels　with　different　boundary　conditions　are　analyzed.　The　classical　thin　plate　theory　is　used　in　the　structural　modeling.　The　unsteady　aerodynamic　pressure　is　evaluated　using　the　supersonic　piston　theory.　To　formulate　the　governing　equation　of　motion　for　the　aeroelastic　structural　system,　Hamilton’s　principle　is　carried　out.　The　assumed　mode　method　(AMM)　and　the　finite　element　method　are　used　to　obtain　the　discrete　equation　of　motion.　Frequency-domain　method　is　conducted　to　analyze　the　aeroelastic　performances　of　the　panel　with　different　boundary　conditions.　The　special　flutter　properties　of　panels　with　elastically　restrained　boundary　condition　are　also　investigated.　The　accuracy　of　the　AMM　in　the　flutter　analysis　of　panels　with　different　constraints　is　researched.　Aeroelastic　characteristics　of　the　panels　with　different　boundary　conditions　are　also　investigated.　©　2013,　Springer-Verlag　Berlin　Heidelberg.