The invention relates to an injector used for a double-component attitude control thruster and belongs to the technical field of spacecraft propulsion. The injector is used for the double-component attitude control thruster used for a spacecraft, wherein the thruster is high in performance and long in service life, and the injector is especially suitable for being used for the spacecraft attitude control double-component thruster. A connection mouth, a connection plate, an intermediate connection pipe and an inner nozzle in the injector form a combustion gas path propellant channel, and flow control and atomization on combustion gas path propellant are achieved through control over the structure of spiral channels; the connection mouth, the connection plate, the connection pipe, the inner nozzle and an outer nozzle form an oxygen path propellant channel, and flow control and atomization on oxygen path propellant are achieved through control over the structure of spiral channels.