Integrated design method for inverted double-module mandibular inward rotation air inlet channel/cone-like forebody

The invention discloses an integrated design method for an inverted double-module mandibular inward turning air inlet channel/cone-like forebody, and relates to an air-breathing hypersonic aircraft. The method comprises the following steps: 1) designing conical precursor configuration; 2) designing a reference flow field; 3) determining the installation position and the installation angle of the inward rotation air inlet channel ; 4) determining the capture area and the inlet three-dimensional shape of the inward turning air inlet; and 5) generating an inward turning air inlet channel molded surface of a double-module integrated structure. The inverted integrated layout effectively reduces the bending degree of the S-bend isolation section of the air inlet channel, and reduces the flow loss in the S-bend isolation section. Incident outer cone shock waves of the cone front body hit the lip position of the inward turning air inlet channel, it is guaranteed that an air inlet channel lip cover does not overflow,