The invention discloses a variable-cycle air
turbine combined engine of a
rocket. The variable-cycle air
turbine combined engine of the
rocket comprises an
axial compressor, a shaft, a main
combustion chamber, an air duct, a
turbine, an
afterburner and an exhaust
nozzle, wherein the
axial compressor is arranged on the side, with an air inlet, of the main
combustion chamber, the turbine is arranged on the side, with an air outlet, of the main
combustion chamber, the
axial compressor is connected with the turbine through the shaft, the air duct is arranged on the outer side of the main
combustion chamber, and is used for communicating the axial compressor with the
afterburner, the
afterburner is arranged on the exhaust side of the turbine, and the exhaust
nozzle is communicated with the afterburner. The variable-cycle air turbine combined engine of the
rocket further comprises a
fuel gas generator and a second turbine, wherein the
fuel gas generator is arranged between the air duct and the main
combustion chamber, the second turbine is arranged at the blade
tip position of the turbine, and is connected with the axial compressor through the shaft, and an outlet of the
fuel gas generator exactly faces the second turbine. The variable-cycle air turbine combined engine of the rocket provides a power
system solution scheme for a
spacecraft, wherein according to the power
system solution scheme, the
spacecraft can carry out the long-time economical
cruise, and can carry out high-speed maneuver in a short time in a high comprehensive performance mode, and the problem that an existing
aviation turbine engine can not carry out self-starting can be solved.