Aero-thermal-elastic　characteristics　of　hypersonic　nonlinear　laminated　panels　considering　the　shock　wave　(SW)　as　well　as　the　aerodynamic　heating　are　studied　in　this　paper.　The　linear　and　third　order　piston　theories　are　used　to　evaluate　the　aerodynamic　pressure.　Hamilton＇s　principle　is　employed　to　establish　the　aeroelastic　model　of　the　laminated　panel.　In　the　aerothermal　model,　the　heat　flux　in　the　aerodynamic　heating　is　computed　using　the　reference　temperature　method,　and　the　finite　element　method　(FEM)　is　applied　to　solve　the　transient　heat　transfer　in　the　panel.　After　solving　the　aeroelastic　and　aerothermal　models　separately,　the　solutions　are　substituted　into　each　other.　Then　performing　the　procedure　of　iteration,　the　coupling　effects　among　the　structure,　fluid　and　thermal　are　realized.　Time　domain　responses　of　the　laminated　panel　are　obtained.　The　influences　of　the　shock　wave　on　the　aeroleastic　characteristics　of　the　panel　are　also　investigated.　From　the　numerical　simulation,　it　can　be　observed　that　the　aeroelastic　stability　is　weakened　with　the　increase　of　the　temperature　change.　It　is　also　noted　that　in　the　calculation　of　the　airflow　parameters　for　the　aerothermoelastic　analysis　in　the　hypersonic　flow,　the　influences　of　the　shock　wave　should　be　taken　into　account.　(C)　2013　Elsevier　Ltd.　All　rights　reserved.