Performance of pulsed plasma thruster at low discharge energy

Document Type

Article

Publication Date

4-1-2024

Abstract

As the size of satellites scales down, low-power and compact propulsion systems such as the pulsed plasma thruster (PPT) are needed for stabilizing these miniature satellites in orbit. Most PPT systems are operated at 2 J or more of discharge energy. In this work, the performance of a PPT with a side-fed, tongue-flared electrode configuration operated within a lower discharge energy range of 0.5-2.5 J has been investigated. Ablation and charring of the polytetrafluoroethylene propellant surface were analyzed through field-effect scanning electron microscopy imaging and energy-dispersive X-ray spectroscopy. When the discharge energy fell below 2 J, inconsistencies occurred in the specific impulse and the thrust efficiency due to the measurement of the low mass bit. At energy 2 J, the performance parameters are compared with other PPT systems of similar configuration and discussed in depth.

Keywords

pulsed plasma thruster, low discharge energy, performance parameters

Publication Title

Plasma Science & Technology

Divisions

PHYSICS

Funders

Ministry of Energy, Science, Technology, Environment and Climate Change (MESTECC), Malaysia (04-02-12-SF0339)

Volume

26

Issue

4

Publisher

IOP Publishing

Publisher Location

TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND

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