CONTROL SYSTEM OF ELECTRICAL ROCKET ENGINE Russian patent published in 2015 - IPC F03H1/00 

FIELD: electricity.

SUBSTANCE: radio-frequency energy generation device includes microcontroller (8), power amplifier (3) and electrical power source (6) of the power amplifier. Microcontroller (8) is provided with an analogue-to-digital converter of input control signals, a digital-to-analogue converter of output signals and a clock generator of a signal with retuned frequency. Outputs of power amplifier (3) are connected through a communication line to energy input device (1) that is made in the form of an inductor. Device (1) is installed on the outer side of walls of gas-discharge chamber (2). Current (4) and voltage (5) sensors are connected to the communication line with energy input device (1). Outputs of sensors are connected to inputs of phase detector (7) and to signal inputs of microcontroller (8). Output of phase detector (7) is connected to a signal input of microcontroller (8). Electrical power supply to neutraliser (11) of spatial charge of an ion flux and a thermionic cathode that is a part of it is performed by means of sources (13) and (14). A positive pole of voltage source (19) and a negative pole of voltage source (17) are separately connected through current sensors (25) and (26) to a common output of the engine electrical power supply system. Consumption of working gas supplied to the gas-discharge chamber and to the chamber of the neutraliser is controlled by means of two independently controlled regulators. Electrical power supply to gas flow regulators is performed by means of controlled current sources.

EFFECT: improving efficiency of an engine; enlarging the thrust control range at a high specific pulse and improving thrust stability due to automatic maintenance of design values of currents and voltages in power circuits of assemblies and unites of the engine during its continuous operation.

7 cl, 2 dwg