Design and Analysis of KIIT Nanosatellite’s Micro-Pulsed Plasma Thruster

Abstract

AbstractMechanical and electrical designs for a micro-pulsed plasma thruster have been presented here, which is to be accommodated in the KIIT University’s Nanosatellite for technological demonstration in space. Design-related calculations based on dimensional limitations, power constraints, and optimal thruster performance have been done and laid out. Mechanical design includes accurate computer-aided design (CAD) and physical calculations of thruster casing, miniature spark plug, and electrodes. The electrical design includes the printed circuit board (PCB) design and circuit-related calculations. The thruster being considered here uses a flared electrode and casing in order to achieve optimal thruster performance. Thrusters are well known for their issues of erosion which hamper the thruster lifetime, therefore, the correct choice of materials for electrode, casing, and spark plug has been considered after a wide survey in order to limit the erosion as much as possible. Analysis of both the mechanical and electrical system has been done using SOLIDWORKS and PROTEUS software, respectively, for critical validation. A space grade micro-pulsed plasma thruster weighing only 130 g capable of surviving loads of a polar satellite launch vehicle (PSLV) by Indian Space Research Organization (ISRO) and providing a specific impulse of 600 s has been concluded.