The invention discloses a hypersonic aircraft aero-propulsive integrated layout method based on combined power. According to the hypersonic aircraft aero-propulsive integrated layout method, a hypersonic air inlet channel of a dual-mode ramjet passage and a tailpipe nozzle are integrally designed with the front body and the rear body of an aircraft respectively; the dual-mode ramjet passage is taken as a basis; a turbine engine passage, a rocket ejector ramjet passage and the dual-mode ramjet passage are parallelly arranged, so that the three passages can coordinate with one another to work according to the own working conditions under the flight Mach number; the dual-mode ramjet passage and the rocket ejector ramjet passage are parallelly connected in an up-down manner; the turbine engine passage is parallelly connected with the dual-mode ramjet passage and the rocket ejector ramjet passage in a left-right manner; and a dual-engine mode under the left-right side-by-side layout is designed. By adoption of the hypersonic aircraft aero-propulsive integrated layout method disclosed by the invention, the middle-altitude and low-altitude working performance advantages of a turbine engine can be remained; through a rocket ejector ramjet, relatively high residual thrust can be provided in a transonic and supersonic climbing acceleration process of the aircraft; and the climbing acceleration of the aircraft to a cruising altitude within a short time can be achieved.