Prediction and control method for separation process of hypersonic aircraft under action of two-phase flow field

The invention discloses a prediction and control method for a separation process of a hypersonic aircraft under the action of a two-phase flow field. The prediction method is realized by the followingsteps: discretizing the flow field of a hypersonic aircraft by adopting an overlapping grid method, carrying out equivalent correction on kinetic energy and momentum of the fluid through thrust reverser rocket inner fluid equivalent to air, establishing an N-S equation of the flow field after equivalence, carrying out flow field CFD calculation according to the established N-S equation of the equivalent flow field to obtain the aerodynamic force and moment borne of the separated bodies in the separation process and solving separation motion under different working conditions by utilizing theobtained aerodynamic force and moment borne of the separated body to obtain centroid motion and attitude motion parameters of the separated body, wherein the separated body comprises a front body anda rear body. 两相流场作用下高超声速飞行器