In the design of the previous generation rocket power system, real-time adjustment and control of the rocket engine thrust was not required during flight, and the engine timing adjustment during ignition was also completed by the actuator drive control and electrical system. With the development of intelligent liquid launch vehicles, the requirements for real-time thrust adjustment, real-time utilization of propellant, engine fault diagnosis, and health monitoring during the flight of variable thrust liquid engines are becoming increasingly high. The requirements for telemetry and control of power systems are gradually increasing, and the requirements for integrated and intelligent control of liquid rocket engines are also increasing. At the same time, in the integrated design of the next generation of intelligent rockets, the requirements for integrated control of various subsystems are gradually increasing. In response to the current demand for integrated electronic control of variable thrust liquid rocket engines, and in combination with domestic and international development trends, research is conducted on the integrated technology of power and propulsion control for the next generation of launch vehicles, and relevant plans are proposed to provide relevant reference for researchers of related propulsion control technologies.