Based　on　the　structures　of　unmanned　aerial　vehicle　(UAV)　wings,　nonlinear　dynamic　analysis　of　macrofiber　composite　(MFC)　laminated　shells　is　presented　in　this　paper.　The　effects　of　piezoelectric　properties　and　aerodynamic　forces　on　the　dynamic　stability　of　the　MFC　laminated　shell　are　studied.　Firstly,　under　the　flow　condition　of　ideal　incompressible　fluid,　the　thin　airfoil　theory　is　employed　to　calculate　the　effects　of　the　mean　camber　line　to　obtain　the　circulation　distribution　of　the　wings　in　subsonic　air　flow.　The　steady　aerodynamic　lift　on　UAV　wings　is　derived　by　using　the　Kutta-Joukowski　lift　theory.　Then,　considering　the　geometric　nonlinearity　and　piezoelectric　properties　of　the　MFC　material,　the　nonlinear　dynamic　model　of　the　MFC　laminated　shell　is　established　with　Hamilton＇s　principles　and　the　Galerkin　method.　Next,　the　effects　of　electric　field,　external　excitation　force,　and　nonlinear　parameters　on　the　stability　of　the　system　are　studied　under　1　:　1　internal　resonance　and　the　effects　of　material　parameters　on　the　natural　frequency　of　the　structure　are　also　analyzed.　Furthermore,　the　in　fluence　of　the　aerodynamic　forces　and　electric　field　on　the　nonlinear　dynamic　responses　of　MFC　laminated　shells　is　discussed　by　numerical　simulation.　The　results　indicate　that　the　electric　field　and　external　excitation　have　great　in　fluence　on　the　structural　dynamic　responses.