In　this　study,　the　nonlinear　aeroelastic　properties　of　graphene　platelet-reinforced　composite　(GPLRC)　lattice　sandwich　plates　under　general　boundary　conditions　in　supersonic　airflow　is　investigated　for　the　first　time　by　considering　temperature-dependent　properties.　Face　sheets　are　reinforced　with　graphene　platelets　(GPLs)　uniformly　or　linearly　distributed　in　the　thickness　direction.　Similarly,　the　lattice　core　trusses　are　reinforced　with　GPLs.　The　Halpin-Tsai　model　is　used　to　calculate　the　effective　elastic　modulus　of　GPLRCs;　Poisson＇s　ratio,　mass　density,　and　thermal　expansion　coefficient　are　determined　by　the　rule　of　mixture.　The　face　sheets　and　lattice　core　layer　are　modeled　separately　using　the　Kirchhoff　plate　and　first-order　shear　deformation　theories.　The　nonlinear　strain-displacement　relationship　is　derived　by　the　von　Karman　large　deformation　theory.　The　aerodynamic　load　on　the　structure　is　expressed　by　the　piston　theory.　The　motion　equations　of　are　calculated　using　the　Lagrange　equation.　Fourier　series　combined　with　auxiliary　functions　is　used　to　describe　the　displacement　components　of　sandwich　plates.　The　Newmark　direct　integration　combined　with　the　Newton-Raphson　iteration　technique　is　employed　to　solve　the　nonlinear　aeroelastic　response.　Finally,　the　influences　of　boundary　condition,　thermal　load,　GPL　distribution　pattern,　and　weight　fraction,　on　the　nonlinear　aeroelastic　properties　of　lattice　sandwich　plates　are　analyzed　in　detail.