This　paper　theoretically　and　experimentally　investigates　the　dynamic　snap-through　phenomena　and　the　nonlinear　vibrations　of　the　bi-stable　asymmetric　laminated　composite　square　panel　under　the　foundation　excitation.　We　propose　a　new　method　to　describe　the　dynamic　snap-through　phenomena　of　the　bi-stable　asymmetric　laminated　composite　square　panel　by　using　the　time-varying　principle　curvatures.　The　boundary　conditions　of　the　bi-stable　asymmetric　laminated　composite　square　panel　are　clamped　at　the　center　of　the　panel　and　free　at　four　edges.　The　mode　shapes　are　obtained　by　employing　Rayleigh-Ritz　method　and　Lagrangian　multipliers　method.　According　to　the　double　curvature　type　of　von-Karman　nonlinear　strain-displacement　relations,　the　third-order　shear　deformation　theory　and　Hamilton　principle,　the　nonlinear　partial　differential　governing　equations　of　motion　are　derived　for　the　bi-stable　asymmetric　laminated　composite　square　panel.　The　nonlinear　ordinary　differential　governing　equation　of　motion　is　obtained　by　using　Galerkin　method.　Numerical　simulations　are　used　to　study　the　nonlinear　vibrations　and　the　dynamic　snap-through　phenomena　of　the　bi-stable　asymmetric　laminated　composite　square　panel　including　the　effect　of　the　structural　damping　by　using　the　4-order　Runge-Kutta　method.　Analyzing　the　phase　portrait　and　time　history　of　the　principle　curvature,　the　dynamic　snap-through　phenomena　of　the　bi-stable　asymmetric　laminated　composite　square　panel　are　observed　through　changing　the　amplitude　of　the　foundation　excitation.　The　vibration　experiments　are　also　finished　to　find　the　dynamic　snap-through　phenomena　and　the　nonlinear　vibrations　of　the　bi-stable　asymmetric　laminated　composite　square　panel.　It　is　known　that　the　theoretical　and　the　experimental　results　are　the　qualitative　agreement　and　the　experimental　results　provide　a　reference　for　the　application　of　the　bi-stable　asymmetric　laminated　composite　square　panel　in　the　aeronautic　and　mechanical　engineering　fields.