Icing　and　stalling　on　the　surfaces　of　aircraft　wings　endanger　flight　safety.　The　object　of　this　research　is　a　nanosecond　pulsed　dielectric-barrier-discharge　plasma　actuation　unit　with　a　distributed　layout,　and　the　aerodynamic　performance　of　aircraft　wing　surfaces　under　icing　and　stalling　conditions　is　improved　by　changing　the　plasma　actuation　electrical　parameters.　Actuated　under　low　voltage　and　frequency,　the　unit　acts　as　a　sensor　to　judge　icing　according　to　the　change　in　electrical　parameters.　Actuated　under　high　voltage　and　frequency,　the　discharge　is　severe　and　generates　a　large　amount　of　heat,　giving　rise　to　an　anti-icing　unit;　anti-icing　is　carried　out　through　distributed-layout　plasma　actuation,　forming　modulated　ice　with　evenly　spaced　distribution,　which　acts　as　a　vortex　generator　and　lessens　the　deterioration　of　aircraft　aerodynamic　performance　under　icing　conditions.　Actuating　under　high　voltage　and　low　frequency　enables　flow　control,　delays　stalling,　and　increases　lift.　The　different　plasma-actuation　functions　are　realized　by　connecting　multiple　units,　which　offers　improved　aircraft　survivability　in　complex　weather　conditions.　©　2022　Author(s).