A motor and fuel-powered hybrid system for a rocket thruster, comprising: a casing including a first chamber , a second chamber , and a third chamber that are connected in sequence, the first chamber including an air inlet and a first space communicating with each other, the second chamber including a second space communicating with the first space , and the third chamber including a third space communicating with the second space ; an electric motor disposed in the first chamber , and including a central processing system , and a compressor that is power connected to the central processing system ; a fluid fuel injector disposed on the casing , controllingly connected to the central processing system , and including an injection head extending into the second chamber , and the injection head being arranged toward the third chamber to spray fluid fuel; and an igniter disposed in the third chamber and controllingly connected to the central processing system , and being used for igniting fluid fuel; there are a first phase, a second phase and a third phase; wherein in the first phase, the central processing system drives the compressor to operate and the compressor provides kinetic energy; wherein in the second phase, the central processing system controls the compressor to gradually reduce load; wherein in the third phase, the central processing system drives the fluid fuel injector to inject fluid fuel toward the third chamber to provide kinetic energy, the motor and fuel-powered hybrid system for a rocket thruster being characterized in that the rocket enters the second phase when raised to a certain height, and in each of the first, second and third phases, the fluid fuel injector is controlled to inject fluid fuel, wherein the amounts of fluid fuel that the fluid fuel injector is controlled to inject by the central processing system are the same in the first, second and third phases. a casing including a first chamber , a second chamber , and a third chamber that are connected in sequence, the first chamber including an air inlet and a first space communicating with each other, the second chamber including a second space communicating with the first space , and the third chamber including a third space communicating with the second space ; an electric motor disposed in the first chamber , and including a central processing system , and a compressor that is power connected to the central processing system ; a fluid fuel injector disposed on the casing , controllingly connected to the central processing system , and including an injection head extending into the second chamber , and the injection head being arranged toward the third chamber to spray fluid fuel; and an igniter disposed in the third chamber and controllingly connected to the central processing system , and being used for igniting fluid fuel; there are a first phase, a second phase and a third phase; wherein in the first phase, the central processing system drives the compressor to operate and the compressor provides kinetic energy; wherein in the second phase, the central processing system controls the compressor to gradually reduce load; wherein in the third phase, the central processing system drives the fluid fuel injector to inject fluid fuel toward the third chamber to provide kinetic energy, the motor and fuel-powered hybrid system for a rocket thruster being characterized in that the rocket enters the second phase when raised to a certain height, and in each of the first, second and third phases, the fluid fuel injector is controlled to inject fluid fuel, wherein the amounts of fluid fuel that the fluid fuel injector is controlled to inject by the central processing system are the same in the first, second and third phases. <EOS>