Patent ID: 7703273
Filing Date: 2010-04-27
Classification: B64G,F02K,F03H

Abstract:
1. A dual-mode spacecraft thruster comprising: a thruster body containing a solid propellant, and having a combustion region adjacent to said solid propellant and a nozzle region adjacent to said combustion region, wherein the propellant ignites to produce a thrust only with the application of electrical power to the solid propellant; a source of electrical power in electrical communication with said solid propellant through a primary electrode, said primary electrode being disposed within the combustion region of the thruster body; a secondary electrode disposed within the nozzle region in electrical communication with said electrical power source; and a control system for controlling the application of the electrical power, wherein the control system is adapted to switch the thruster between a high-thrust mode wherein only the primary electrode is operated to combust the solid propellant, and a high-exhaust-velocity mode wherein first the primary electrode is triggered to atomize the propellant and then the secondary electrode is triggered to ionize and accelerate the atomized propellant.