BACKSTEPPING-B ASED APPROACH FOR CONTROLLING SPACECRAFT MICROPUMP FOR PROPULSION SYSTEM

摘要

The purpose of this article is to design a robust controller for the new design of hydrazine micropump, by studying the real prototype device using a high-performance oscilloscope. In other words, we have designed a relatively accurate mathematical model of the micropump by using the data extracted from the oscilloscope, and then, we have calculated and tested a robust controller by using the backstepping technique. Simulation results are shown to be satisfactory regarding the desired criteria. This micropump consists of an electromagnetic actuator with a variable reluctance and which moves a piston forward and backward (stroke 0 to a few millimeters). The main advantage in using these new devices lies in the increase of the maneuverability capacity of the satellite, with respect to the existing satellites systems, allowing the overall system to operate even if the gas reservoir pressure level is low, thus bringing great advantages (reduced costs, better maneuverability).