The　stability　and　vibration　of　the　telescopic　wing　are　studied　by　the　theoretical,　numerical　and　experimental　methods　when　the　wing　is　in　the　deployment　and　retraction.　The　telescopic　wing　is　simplified　to　a　telescopic　cantilevered　laminated　composite　rectangular　plate　subjected　to　the　first-order　aerodynamic　force　and　in-plane　excitation.　The　time-varying　dynamic　characteristics　of　the　telescopic　cantilevered　laminated　composite　rectangular　plate　are　investigated　by　using　the　analytical,　numerical　and　experimental　methods.　The　approximate　analytical　solution　of　the　nonlinear　time-varying　system　is　obtained　by　using　the　improved　averaging　method.　Compared　with　numerical　simulations,　the　approximate　analytical　results　demonstrate　a　good　agreement.　The　stability　of　the　telescopic　cantilever　plate　during　the　deploying　process　is　studied　by　using　the　eigenvalue　method,　which　demonstrates　the　effect　of　the　velocity,　acceleration　and　thickness　on　the　stability　of　the　deployment.　The　experimental　results　are　consistent　with　the　theoretical　results　and　provide　the　theoretical　basis　and　technical　support　for　the　axial　moving　wing.