2026-09-20T08:33:17Z https://www.ideals.illinois.edu/oai-pmh

oai:www.ideals.illinois.edu:2142/117846 2023-07-11 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Rovey, Joshua L 2022-12 application/pdf en text Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2023-04-12 without embargo terms The student, Jacob Eisen, accepted the attached license on 2022-12-08 at 10:11. The student, Jacob Eisen, submitted this Thesis for approval on 2022-12-08 at 10:28. This Thesis was approved for publication on 2022-12-08 at 14:12. DSpace SAF Submission Ingestion Package generated from Vireo submission #18776 on 2023-04-12 at 07:39:34 Electrospray power processing unit for a monopropellant-electrospray multimode thruster Eisen, Jacob 2022-12-08 Electrospray Converter Ppu Multimode Propulsion Power Electronics High-voltage Multimode space propulsion combines two or more propulsive methods into a single system with a shared propellant, the goal of which is to offer spacecraft improved maneuver flexibility and efficiency. A power processing unit (PPU) is described and developed here to meet the high-voltage low-power needs of the electrospray mode of a monopropellant-electrospray multimode thruster. The PPU is resilient to the variable-load nature of electrospray thrusters, producing a consistent output voltage regardless of the thruster’s current draw. The PPU consists of a two-phase interleaved boost converter, transformer, and Cockcroft-Walton voltage multiplier. By designing a transformer magnetizing inductance of at least 1 mH and using a 10 MΩ bleed resistor at the PPU output, discontinuous conduction mode is avoided during the thruster startup period before Taylor cone formation. This allows the desired thruster voltage of 3.25 kV to be maintained both during and after thruster startup. A 20 MΩ current-limiting resistor placed just before the thruster prevents PPU component damage during thruster shorts. The presence of this resistor also maintains the voltage multiplier output voltage even if the thruster voltage itself cannot be sustained without overcurrent, allowing nominal electrospraying to resume if the thruster recovers from the short. The PPU is integrated with a real multimode thruster for a ground-based test to prove its suitability for the application, marking the first time a purpose-built electrospray PPU has been successfully applied to a monopropellant-electrospray multimode thruster. Thesis eng https://hdl.handle.net/2142/117846 Copyright 2022 Jacob Eisen M.S. Thesis Aerospace Engineering University of Illinois at Urbana-Champaign Aerospace Engineering