Owing　to　the　excellent　mechanical　properties,　polymethyl　methacrylate　(PMMA)/carbon　nanotube　(CNT)　composite　has　been　increasingly　adopted　in　the　aerospace　field,　which　is　usually　subjected　to　various　temperature　conditions　and　supersonic　aerodynamic　loads.　Using　a　molecular　dynamics　(MD)-based　multiscale　simulation,　the　nonlinear　forced　vibration　of　PMMA/CNT　composite　plate　is　investigated　under　coupled　temperature　and　aerodynamic　load　conditions.　The　longitudinal,　transverse　and　shear　moduli　of　PMMA/single-walled　CNT　(SWCNT)　nanocomposite　obtained　from　MD　simulation　at　different　temperature　and　pressure　levels　are　substituted　into　the　extended　rule　of　mixtures　to　establish　the　constitutive　equations　of　PMMA/CNT　composite　plate.　Meanwhile,　Poisson＇s　ratio　and　thermal　expansion　coefficient　of　nanocomposite　are　used　in　the　constitutive　equations.　Based　on　the　third-order　shear　deformation　theory,　von　Karman　nonlinear　strain-displacement　relation　and　Hamilton＇s　principle,　the　partial　differential　equation　of　composite　plate　is　derived,　which　is　reduced　into　a　set　of　coupled　ordinary　differential　equations　by　applying　Galerkin　method　and　is　solved　using　the　fourth-order　Runge-Kutta　method.　The　bifurcation　diagrams,　phase　portraits,　time　histories　and　Poincare　maps　of　composite　plate　are　obtained　under　the　complex　loads　including　transverse　harmonic　excitation　and　aerodynamic　pressure,　which　are　applied　to　analyze　the　dynamic　characteristics　of　system.　This　study　reveals　the　nonlinear　dynamic　characteristics　of　PMMA/CNT　composite　plate,　which　contributes　to　the　prediction　of　long-term　performance　of　composite　materials　in　aerospace　field.