This invention discloses a dual-component thrust
attitude control engine, comprising a mounting plate, a swirling mixer, an igniter, and a
combustion chamber
nozzle. The mounting plate contains two isolated gas chambers, each with an intake
pipe connected to its inlet and an on / off controllable
solenoid valve at its outlet. The two inlets of the swirling mixture are connected to the outlets of the two gas chambers, and the outlet of the swirling mixer is connected to the inlet of the
combustion chamber
nozzle. The swirling mixer is used to swirl and mix the gas input into it before outputting it. The igniter is used to ignite the
mixed gas input into the
combustion chamber
nozzle. The
combustion chamber nozzle is used to supply the combusted
mixed gas for combustion output. This configuration solves the problem that existing technologies cannot simultaneously achieve compact structure, high mixing efficiency, and excellent thermal management performance.