Sandwich　structures　with　lattice　core　are　novel　composite　structures,　but　the　aeroelastic　behaviors　of　them　have　not　been　fully　studied.　This　paper　is　devoted　to　investigate　the　flutter　and　buckling　properties　of　sandwich　panels　with　triangular　lattice　core　in　supersonic　airflow,　and　the　active　flutter　and　buckling　control　are　also　carried　out,　which　can　provide　theoretical　basis　for　the　use　of　sandwich　structures　in　the　design　of　aircrafts.　The　unsteady　aerodynamic　pressure　is　evaluated　by　the　supersonic　piston　theory　in　which　the　yawed　flow　angle　is　taken　into　account.　Hamilton＇s　principle　with　the　assumed　mode　method　is　applied　to　formulate　the　equation　of　motion　of　the　structural　system.　The　active　controller　is　designed　by　the　displacement　feedback　method.　Aeroelastic　characteristics　of　the　sandwich　panels　are　studied,　and　the　influences　of　the　aerodynamic　pressure　on　the　frequency　and　mode　shape　of　the　panel　are　analyzed.　The　effects　of　yawed　flow　angle　on　the　flutter　properties　of　the　sandwich　panel　are　also　analyzed.　When　considering　the　external　in-plane　load,　the　buckling　behaviors　of　the　sandwich　panel　are　investigated.　Moreover,　the　flutter　and　buckling　properties　between　the　sandwich　and　equivalent　isotropic　panels　are　compared　to　show　the　superior　aeroelastic　properties　of　the　sandwich　panels.　The　effects　of　piezoelectric　patch　placements　on　the　active　flutter　control　are　analyzed.　The　optimal　locations　of　piezoelectric　actuator　and　sensor　pairs　are　obtained　by　the　genetic　algorithm.　The　present　study　verifies　that　the　sandwich　structures　have　different　aeroelastic　and　flutter　suppression　properties,　which　is　useful　in　the　research　of　lightweight　sandwich　materials.　(C)　2016　Elsevier　Ltd.　All　rights　reserved.