Development of a micro-thruster system for an advanced nano-satellite

• Main Author: Lee, Ming Kai.
• Other Authors: Low Kay Soon
• Format: Final Year Project
• Language: English
• Published: 2012
• Subjects: DRNTU::Engineering::Electrical and electronic engineering::Nanoelectronics; DRNTU::Engineering::Electrical and electronic engineering::Satellite telecommunication
• Online Access: http://hdl.handle.net/10356/49668
• Institution: Nanyang Technological University

Pulsed Plasma Thrusters (PPTs) are becoming increasingly popular due to the growth in nano-satellite applications. PPTs help greatly in expanding the capabilities of satellites to include possibilities such as precision pointing, station keeping, orbital insertion and attitude control. Chemical propulsive devices are generally too large and cannot produce the small impulse bits needed. PPTs are simple, low-mass and high Isp propulsion systems that utilizes solid Teflon Fuel allowing for a self-contained, and stable propulsion system. In this project, a thruster system based on PPT was designed and built that aimed to extend the lifetime of a nano-satellite from 3-6 months to a year. A detailing analysis coupled with PPT modelling and simulation of results was carried out to determine and understand the requirements of a thruster system for nano-satellite station-keeping missions. The prototype is about the size of 1U (i.e 10cm x 10cm x 10xm), with a discharge voltage of 1.5kV and power requirements of 1 to 2W only. Various designs were also experimented with the PPT prototype and the thrust values could range from 1 μNs to an excess of 150 μNs.