High　speed　rotating　blades　are　crucial　components　of　modern　large　aircraft　engines.　The　rotating　blades　under　working　condition　frequently　suffer　from　the　aerodynamic,　elastic　and　inertia　loads,　which　may　lead　to　large　amplitude　nonlinear　oscillations.　This　paper　investigates　nonlinear　dynamic　responses　of　the　blade　with　varying　rotating　speed　in　supersonic　airflow.　The　blade　is　simplified　as　a　pre-twist　and　presetting　cantilever　composite　plate.　Warping　effect　of　the　rectangular　cross-section　of　the　plate　is　considered.　Based　on　the　first-order　shear　deformation　theory　and　von-Karman　nonlinear　geometric　relationship,　nonlinear　partial　differential　dynamic　equations　of　motion　for　the　plate　are　derived　by　using　Hamilton＇s　principle.　Galerkin　approach　is　applied　to　discretize　the　partial　differential　governing　equations　of　motion　to　ordinary　differential　equations.　Asymptotic　perturbation　method　is　exploited　to　derive　four-degree-of-freedom　averaged　equation　for　the　case　of　1　:　3　internal　resonance-1/2　sub-harmonic　resonance.　Based　on　the　averaged　equation,　numerical　simulation　is　used　to　analyze　the　influence　of　the　perturbation　rotating　speed　on　nonlinear　dynamic　responses　of　the　blade.　Bifurcation　diagram,　phase　portraits,　waveforms　and　power　spectrum　prove　that　periodic　motion　and　chaotic　motion　exist　in　nonlinear　vibration　of　the　rotating　cantilever　composite　plate.