Described herein is a power processing unit (PPU) for use with a Hall Effect Thruster (HET) and a Propellant Management Assembly (PMA) of a spacecraft. The PPU comprises an anode and ignitor supply subsystem that provides anode and ignitor signals to an anode and an ignitor circuit of the HET. The PPU also comprises a valve control subsystem that provides valve control signal(s) to valve(s) of the PMA. The anode and ignitor supply subsystem and the valve control subsystem are each coupled to a low voltage (LV) bus of an electrical power subsystem of the spacecraft. The anode and ignitor supply subsystem includes a step-up DC-DC converter having a transformer that steps-up a voltage of the LV bus to a higher voltage used to produce the anode and ignitor signals. The valve control subsystem is devoid of a transformer. An Electric Propulsion System (EPS) includes the PPU, HET and PMA.
POWER PROCESSING UNIT (PPU) AND ELECTRIC PROPULSION SYSTEM (EPS) FOR SPACECRAFT
LEISTUNGSVERARBEITUNGSEINHEIT UND ELEKTRISCHES ANTRIEBSSYSTEM FÜR RAUMFAHRZEUGE
UNITÉ DE CONDITIONNEMENT D'ÉNERGIE (PPU) ET SYSTÈME DE PROPULSION ÉLECTRIQUE (EPS) POUR ENGIN SPATIAL
2025-03-12
Patent
Electronic Resource
English
Power processing unit (PPU) and electric propulsion system (EPS) for spacecraft
European Patent Office | 2023
|POWER PROCESSING UNIT (PPU) AND ELECTRIC PROPULSION SYSTEM (EPS) FOR SPACECRAFT
European Patent Office | 2023
|