A satellite propulsion system has both a chemical monopropellant thruster providing high thrust for rapid maneuvering and an electrospray thruster providing high specific impulse. Both thrusters operate off of a single ionic liquid propellant delivered from a common fuel tank, with a series of electrically actuated valves controlling the distribution of propellant.
申请公布号
WO2010036291(A2)
申请公布日期
2010.04.01
申请号
WO2009US03732
申请日期
2009.06.22
申请人
AEROJET-GENERAL CORPORATION;DE GRYS, KRISTI, H.;WILSON, ALFRED, C.