The design and implementation for a kind of wide-range variable thrust liquid propellant rocket engine control system is presented. Accelerated circuit of electromagnetic valve is designed based on switching between high and low voltage, and embed operation system μCOS - II is transplanted to 80C196KC. Regulation of thrust in wider range is implemented by variable parameter proportion and dead zone compensation. The semi-physical test demonstrates that the system can satisfy the control target, with the regulating time less than 60ms and stable state error no greater than 5%.