Encyclopedia Astronautica
Electric


Category of engines.

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Associated Engines
  • 11B97 Korolev nuclear electric/xenon rocket engine. 450 mN. Engine for Interorbital Tug for launch by Energia. Developed 1978-1986. Isp=3000s. Powered by nuclear reactor providing 50-150 kWt for 3 to 5 years operation. More...
  • Aerojet 50kW Redmond electric/xenon rocket engine. Effort 2001-2003 developed a 50 kW Hall thruster in parallel to NASA's in-house development of the NASA-457M thruster. More...
  • ATS 5 cm EOS electric/cesium rocket engine. 0.089 mN. Flown in 1968-1969. Isp=6700s. Thruster for the ATS-4 and ATS-5 tests; consisted of two contact ionization engines using cesium propellant. More...
  • ATS 8 cm EOS electric/cesium rocket engine. 4.5 mN. Flown in 1974. Isp=6700s.Thruster for the ATS-6 test; consisted of two electron bombardment engines using cesium propellant. The thruster anode diameter was 8 cm, and a cesiated tungsten neutralizer was used. More...
  • BPT-600k Redmond electric/xenon rocket engine. 0.030 kN. In Development, 2005-2006. Isp=1800s. Began as 1995 contract for 600kWe Hall thruster electric propulsion system designed for future interplanetary manned spacecraft. More...
  • BPT-4000 Redmond electric/xenon rocket engine. 270 mN. In Production. Hall effect thruster. Nominal power input 4500 W at 350 V. Isp=1950s. More...
  • BPT-2000 Redmond electric/xenon rocket engine. 120 mN. In Production. Hall effect thruster. Nominal power input 2200 W at 350 V. Isp=1765s. More...
  • D-100-II TsNIIMASH electric/xenon rocket engine. 65 mN. Development. Isp=1600s. Hall effect thruster with anode layer, designed for satellite orbital raising. Taken to engineering model stage. More...
  • D-20 TsNIIMASH electric/xenon rocket engine. 1.5 mN. Development. Isp=1400s. Hall effect thruster with anode layer, designed for satellite station-keeping and attitude control. Taken to engineering model stage. More...
  • D50 Yuzhnoye electric/xenon rocket engine. 48 mN. Development. Isp=1700s. Hall engine electric jet propulsion system intended for use by spacecraft for inter-orbital transfer, orbit correction, and stabilization. More...
  • End Hall Thruster UM-NASA electric/lh2 rocket engine. 1 kW arcjet, ran on H2, N2, or a mixture, at about 12A, 1 kW, peak around 600s Isp, (20-30% efficiency). Isp=600s. More...
  • ESEX Arcjet Redmond electric/ammonia rocket engine. 2 N. In Production. Isp=800s. Electric Propulsion Space Experiment) program begun 1989 under the then Air Force Astronautics Lab. Flew once in 1999 on board the ARGOS satellite. More...
  • Hall Electric Thruster TsNIIMASH / Rocketdyne electric/xenon rocket engine. 3 N. Development. Isp=1600s. Satellite orbit raising and station-keeping applications. Electric, pressure-fed. Variable 80 mN - 3.0 N thrust, specific impulse 1600 to 3500 seconds. More...
  • HIVHAC NASA Cleveland electric/xenon rocket engine. 430 mN. Isp=2800s. HIVHAC offered mission benefits compared to the 4000s NEXT engine for deep space missions. More...
  • IAPS Hughes electric/mercury rocket engine. Isp=2500s. Ion Auxiliary Propulsion System work took place in the 1974-1983. Flight ready article prepared, but not flown due to budget cuts. More...
  • Ion Notional electric/mercury rocket engine. 0.275 kN. Study 1981. Conceptual ion engine design of the 1970's for a shuttle-sized upper stage. Isp=5300s. More...
  • LGIT UM electric rocket engine. 20 mN. Isp=1400s. Linear Gridless Ion Thruster, a two-stage device designed to incorporate the efficient ionization process of gridded ion thrusters and the high thrust density of Hall thrusters. More...
  • MPD UM-NASA electric rocket engine. 1.35 kW Hall thruster More...
  • NASA-173GT NASA Cleveland electric rocket engine. Two-Stage Hybrid Hall/Ion Thruster More...
  • NASA-457M NASA Cleveland electric/xenon rocket engine. Isp=2326s. 50 kW Hall thruster developed 2001-on. More...
  • NASA-400M NASA Cleveland electric/krypton rocket engine. 1 N. Isp=4000s. Developed to investigate high-power, high specific impulse Hall thruster operation in 2004. More...
  • NEXT UM-NASA electric/xenon rocket engine. 237 mN. Isp=4100s. NASA Evolutionary Xenon Thruster, 40 cm diameter ion engine, double the beam extraction area of the NSTAR engine. Developed 1998-2003. More...
  • NSTAR NASA Cleveland electric/xenon rocket engine. 92 mN. Isp=3100s. Solar Electric Propulsion Technology Application Readiness program developed this 2.3 kW ion engine as primary propulsion for the Deep Space 1 comet and asteroid rendezvous probe, flew 1998. More...
  • P5 Hall thruster UM-USAF electric/xenon rocket engine. 246 mN. Isp=2326s. 5 kW Hall thruster for research purposes. More...
  • P78-2 Hughes electric/xenon rocket engine. 0.14 mN. Flown in 1979. Isp=350s. The thruster for the Scatha experiment consisted of one electron bombardment engines using xenon propellant. More...
  • PEPL-70 UM-JPL electric rocket engine. 1 kW Hall thruster, SPT type More...
  • Program 661 EOS electric/cesium rocket engine. 8.9 mN. Flew 1962-1964. Isp=7400s. Cesium contact ion propulsion system used on three sub-orbital flight tests aboard Blue Scout Junior launch vehicles. More...
  • PRS-101 Redmond electric/teflon rocket engine. 1.24 mN. In Production. Pulsed plasma thruster system. Completely solid state propulsion. Up to 100 W input power at 28 V DC, thrust to power ratio 12.4 microN/W. Isp=1350s. More...
  • SEPST JPL, Hughes, TRW electric/mercury rocket engine. 88 mN. Isp=3600s. The Solar Electric Propulsion System Technology program of 1960-1980 demonstrated a complete breadboard ion propulsion system that would be applicable to an interplanetary spacecraft. More...
  • SEPS Hughes, TRW, NASA Cleveland electric/mercury rocket engine. 128 mN Isp=3000s. Solar Electric Propulsion Stage program, started in the early 1970s, a goal to provide a primary ion propulsion system operating at a fixed power for Earth orbital applications. More...
  • Sert II NASA Cleveland electric/mercury rocket engine. 28 mN. Flown in 1970. Isp=4200s. The thruster for the Sert-II test consisted of two electron bombardment engines using mercury propellant. More...
  • Sert-I Cesium Hughes electric/cesium rocket engine. 5.6 naN. In Development, 1962-1964. Isp=8050s. 8 cm diameter cesium contact ion engine was designed to operate at 0.6 kW. More...
  • Sert-I Mercury NASA Cleveland electric/mercury rocket engine. 28 mN. Developed 1962-1964. Isp=4900s. 10 cm diameter mercury electron bombardment ion engine used on the first successful flight test of ion propulsion on a Scout X-4 launch vehicle. More...
  • SIT- 5 Hughes electric/mercury rocket engine. 2.1 mN. Isp=3000s. 5 cm diameter mercury ion engine, developed 1970 for attitude control and north-south stationkeeping of geosynchronous satellites. More...
  • Snapshot EOS electric/cesium rocket engine. 8.5 mN. In Development, 1962-1964. Isp=5100s. Launched on Blue Scout Junior launch vehicle on Snapshot test; a contact ionization engine; thruster anode diameter was 5 cm. More...
  • T-140 Pratt and Whitney electric rocket engine. 3 kW Hall thruster More...
  • T-220 Pratt and Whitney / Keldysh Research Center electric rocket engine. Development began in 1997 of this 10 kW Hall thruster Program concluded in 2000 following a 1000 hour erosion characterization. More...
  • TAL-100 TsNIIMASH electric/xenon rocket engine. 34 mN. Development. Isp=1450s. Hall effect thruster with anode layer. Export version of D-100-I thruster developed under NASA/BMDO contract. Taken to engineering model stage. More...
  • TAL-WSF TsNIIMASH electric/xenon rocket engine. 12 mN. Isp=1350s. Hall effect thruster with anode layer. Export version of D-55 thruster developed under NASA/BMDO contract for flight test under RHETT-II program. Used for satellite orbital altitude maintenance. More...
  • TAL-38 TsNIIMASH electric/xenon rocket engine. 8 mN. Development. Isp=2500s. Hall effect thruster with anode layer. Export version of D-38, developed under NASA contract for satellite station-keeping and attitude control. Taken to engineering model stage. More...
  • TM-50 TsNIIMASH electric/xenon rocket engine. 250 mN. Development. Isp=3000s. Hall effect thruster with anode layer, designed for satellite orbital raising. Taken to engineering model stage. More...
  • XIPS-25 4.2 kW Hughes electric/xenon rocket engine. 165 mN. Isp=3800s. 25 cm diameter xenon engine system for orbital circularization, station-keeping, attitude control, and momentum dumping for its HS 702 spacecraft. More...
  • XIPS-25 1.3 kW Hughes electric/xenon rocket engine. 63 mN. Isp=2800s. XIPS-25 program, conducted by Hughes, developed thrusters, BBPPUs, and a feed system pressure regulator for stationkeeping of 2500 kg class communication satellites. More...
  • XIPS-13 0.44 kW Hughes electric/xenon rocket engine. 17.8 mN. In Production. Isp=2585s. HS 702 operational communications satellites each employed four of these 0.44 kW xenon ion thrusters. More...

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