CONCEPT STUDY OF A SOLID PROPELLANT MAGNETOPLASMADYNAMIC MICROTHRUSTER

摘要

An Ablative Magnetoplasmadynamic (AMPD) thruster is being developed as a low cost-mass-power simple, safe and highly efficient propulsion option for nano/microsatellites orbit and/or attitude control. The purpose of this work is to perform a review of the concept study phase as to date. Different nano/microsatellites mission scenarios in LEO were investigated in order to establish most probable performance requirements. On the basis of a simplified onedimensional model of the thruster and its magnetogasdynamic flow, a system optimization was performed for minimum mass design while complying with operational requirements and power constraints. For 1000 Ns total impulse, a obtained 100 μN, 5W input power baseline thruster configuration was obtained, using Teflon~(TM)as the solid propellant. The technological characterization of the thruster was performed at a preliminary level and its feasibility was assessed on the basis of national technological resources. Near term planning concerning a technology demonstrator (breadboard class) at thruster subsystem and system level is subsequently described. Special attention was paid to the low cost implementation of the AMPD stationary thrust measurement, leading to a test stand concept based on a platform free to translate along one horizontal axis by means of two parallel, low-stiffness, flexural supports.