Automatic control of electric propulsion power consumption,based on a signal proportional to overall spacecraft power balance,on electrically propelled spacec

摘要

A control loop is implement on an electrically propelled spacecraft that automatically changes the power utilisation of the electric propulsion system based on a signal proportional to the overall spacecraft power balance, derived from one or more spacecraft power bus(es). This can be implemented as an additional domain 5 in the spacecraft main error amplifier signal. Also described is a software implementation using tuneable hysteresis levels to allow for changeable, safe operational margins. The increased power utilisation of the electric propulsion system is used to affect any operating characteristic of the electric propulsion system(s). Increased power utilisation of the electric propulsion system benefits the mission by increasing thrust and/or specific impulse. Increased thrust results in reduced thrusting times for a given velocity increment. This implies faster transfer times for orbit raising and interplanetary missions. Increased specific impulse implies reduced propellant use, useful to increase range, lifetime, or reduce launch mass.