High Input Voltage, Power Processing Unit Performance Demonstration

TL;DR: Aerojet Rocketdyne's Advanced Electric Propulsion System (AEPS) program is completing development and qualification of a 13kW flight EP system to support NASA exploration as mentioned in this paper.

TL;DR: The Advanced Electric Propulsion System (AEPS) program is developing and qualifying a 13.3kW Hall thruster system to be demonstrated on the Power and Propulsion Element (PPE), which is intended to be the first element of a Lunar Outpost Platform - Gateway (LOP-G) as discussed by the authors.

TL;DR: In this paper, the authors have shown that the harness impedance between the power supply and the thruster is the main contributor towards generating voltage ripple at the thrusters and that increasing the size of the discharge filter capacitor, as previously implemented during thruster tests, does not reduce the voltage oscillations.

TL;DR: In this article, the authors describe the parameterized assessment of power and propulsion technologies for a piloted solar electric vehicle to a near-Earth asteroid, based on a "reasonable vehicle configuration" bounded by an assumed launch date.

TL;DR: In this paper, the integrated design of power and propulsion systems that utilize the capabilities of existing PPUs in an unregulated power architecture is considered for small near-Earth Objects (NEOs) exploration.

TL;DR: In this paper, NASA GRC successfully designed, built and tested four different power processor concepts for high power Hall thrusters, each of which satisfies unique goals including the evaluation of a novel silicon carbide semiconductor technology, validation of innovative circuits to overcome the problems with high input voltage converter design, development of a direct-drive unit to demonstrate potential benefits, or simply identification of lessonslearned from the development of PPU using a conventional design approach.