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Whether the aero engine can obtain the steady state performance, at the same time ensure the stability of the working process, to a large extent, depends on the control law of the engine. The aerodynamic performance optimization control can effectively excavate the potential of the engine. Component characteristics method was adopted for static modeling of the engine, and conducts simulation of steady state under three different control laws for a twin rotor turbojet engine, gets change trend of different engine performance parameters, then detailed analysis was carried on. The results show that under control law of keep low pressure rotor speed unchanged, with the increase of compressor inlet total temperature, the speed of the high pressure rotor is increased, the temperature of turbine inlet is increased and the thrust of the engine is increased; Under control law of keep the temperature of turbine inlet unchanged, with the increase of compressor inlet total temperature, low pressure compressor load becomes heavier, the low pressure rotor speed is decreased, the high pressure rotor speed is also decreased, but the drop is very small, and the fuel flow rate increases; Under control law of keep high pressure rotor speed unchanged, with the increase of the total temperature of compressor inlet, the fuel flow rate increases, the low pressure rotor speed decreases, engine thrust is influenced by multiple factors, so the thrust value change trend is more complicated.