Math model of digital relay electromechanical system for controlling thrust vector of liquid-propellant rocket engine

The article contains development results of the mathematical dynamics model of a digital relay electromechanical thrust vector control system of a liquid-propellant rocket engine of a manned transportation spacecraft. The development of a mathematical system model is based on mathematical models of a magneto electric engine (an electric engine with permanent magnetic field) and a two-drive electromechanical steering actuator, as well as mathematical models of electromechanical drives and systems. The article deals with decomposition of a digital relay electromechanical system into constituent functional elements. The parameters of the constituent functional system elements are computed. The nonlinear mathematical dynamics model of the digital relay electromechanical system is aggregated. The evaluation results of the developed mathematical dynamics model of such a digital relay electromechanical system are provided for its operation with one running magneto electric engine of the steering actuator and with the second magnetoelectric engine in a «cold» reserve, and for its operation with both running engines.