This　paper　investigates　the　aeroelastic　properties　of　the　cylindrical　cabin　with　reinforcement　plate　(CCRP)　in　a　thermal　aerodynamic　environment,　where　the　plate　and　cylindrical　cabin　are　coupled　at　any　position　along　the　busbar.　The　theoretical　model　is　constructed　using　the　first-order　shear　deformation　theory　(FSDT)　and　the　Jacobi　differential　quadrature　method　(JDQM).　The　unsteady　aerodynamic　pressure　is　established　using　supersonic　piston　theory.　Hamilton＇s　principle　and　two-dimensional　Jacobi　polynomials　are　applied　to　obtain　the　motion　equation　of　the　coupled　model.　The　center　point　virtual　spring　method　(CPVSM)　is　used　to　set　up　the　coupled　boundary　to　overcome　the　three-structure　coupling.　The　accuracy　and　efficiency　of　the　proposed　method　are　demonstrated　by　comparing　the　modes,　steady-state　responses　and　flutter　with　the　finite　element　method　(FEM).　Based　on　the　environmental　conditions,　the　effects　of　temperature　on　the　dimensionless　critical　aerodynamic　pressure　of　the　coupled　model　and　the　cylindrical　cabin　are　studied.　The　influences　of　length-to-radius　ratio,　coupling　positions,　plate-to-cabin　thickness　ratio　and　ply　angles　on　the　aeroelasticity　properties　of　the　coupled　model　are　researched　to　determine　the　optimal　geometry　of　the　coupled　model　in　supersonic　airflow.　In　addition,　the　forced　vibration　responses　of　this　coupled　model　are　analyzed　under　different　dimensionless　aerodynamic　pressures.