The invention provides a supersonic air film cooling structure which can adaptively inject plasmas into a shock wave action zone corresponding to the shock wave strength according to occurrence and the strength of shock waves when shock waves happen to high-temperature components in a hypersonic vehicle to achieve the effect of suppressing damage of shock waves. A plasma actuation adaptive shock-wave-resisting supersonic air film cooling device comprises a supersonic air film cooling flow channel, a spray nozzle, a protected wall surface, a pressure monitoring pipeline, a pressure switch group, a power supply, dielectric, an electrode A, an electrode B and a connecting circuit. Rising fluid pressure caused by shock waves is guided to combined pressure switches through the pressure monitoring pipeline. Different corresponding circuits in the combined pressure switches are connected according to different shock wave strengths, so that the power supply is switched on and outputs corresponding voltage values. Plasmas are generated between the electrode A and the electrode B to weaken damage of shock waves to supersonic air film cooling.