Specialists at the Research Institute of Electromechanics have developed a corrective propulsion unit for a spacecraft with real-time thrust measurement. The solution is intended to improve the accuracy of orbit correction and monitor the operation of an electric propulsion engine directly during flight.
The unit is built on the basis of ablative pulsed plasma engines with two working channels. Each channel has a built-in current sensor, a quadratic converter, and a low-pass filter.
These elements form a signal from which the onboard microcomputer calculates the actual thrust force taking calibration data into account. The information is transmitted via telemetry to the ground complex.
The main difference is the direct measurement of discharge parameters instead of indirect estimation based on trajectory changes. This reduces errors, speeds up decision-making, and increases the reliability of orbital maneuvers.
The system also includes an energy storage unit, discharge initiation modules, and power management. The technology is designed for small spacecraft, where mass, power consumption, and service life are critical.
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