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
Divisions
PHYSICS
Funders
Ministry of Energy, Science, Technology, Environment and Climate Change (MESTECC), Malaysia (04-02-12-SF0339)
Publication Title
Plasma Science & Technology
Volume
26
Issue
4
Publisher
IOP Publishing
Publisher Location
TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND