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Electric/Xenon

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Fuel Freezing Point: -112 deg C. Fuel Boiling Point: -107 deg C.

BPT-2000 Redmond electric/xenon rocket engine. In Production. Hall effect thruster. Nominal power input 2200 W at 350 V.

BPT-4000 Redmond electric/xenon rocket engine. In Production. Hall effect thruster. Nominal power input 4500 W at 350 V.

Dawn American asteroid probe. Asteroid belt unmanned probe designed to first orbit and survey the asteroid Vesta, and then fly on to the largest asteroid, Ceres. Orbit asteroids Ceres and Vesta. Multiple asteroid lander built by Orbital Sciences Corporation (OSC) for NASA, USA. Launched 2007.

Deep Space 1 American asteroid probe. Deep Space 1 (DS1) was a primarily a technology demonstration probe powered by an ion engine, although the spacecraft also flew by asteroid and cometary targets.

ERTA stage Electric/Xenon propellant rocket stage. At the beginning of the 1990's a new type of nuclear generator was studied, that would have a capacity of 150 kW in the transport role and provide 10-40 kW to power spacecraft systems while coasting. This was designated ERTA (ElecktroRaketnovo Transportnovo Apparat).

Hall Electric Thruster TsNIIMash / Rocketdyne electric/xenon rocket engine. Development. Satellite orbit raising and station-keeping applications. Electric, pressure-fed. Variable 80 mN - 3.0 N thrust, specific impulse 1600 to 3500 seconds.

KK Russian manned Mars expedition. Study 1966. Work on the TMK project continued, including trajectory trade-off studies and refinement of the design.

Marpost Russian manned Mars expedition. Study 2000. In December 2000 Leonid Gorshkov of RKK Energia proposed a manned Mars orbital expedition as an alternative to Russian participation in the International Space Station.

Mars 1986 Russian manned Mars expedition. Studied 1978-1986. NPO Energia resumed study of a Mars project once development began of the new Energia booster in place of the cancelled N1.

Mars 1989 Russian manned Mars expedition. Study 1989. In 1989 yet another Mars project was proposed by NPO Energia.

MEK Russian manned Mars expedition. Study 1969. The Mars Expeditionary Complex (MEK) was designed to take a crew of from three to six to Mars and back with a total mission duration of 630 days.

NEXT UM-NASA electric/xenon rocket engine. NASA Evolutionary Xenon Thruster, 40 cm diameter ion engine, double the beam extraction area of the NSTAR engine. Developed 1998-2003.

P5 Hall thruster UM-USAF electric/xenon rocket engine. 5 kW Hall thruster for research purposes.

STCAEM NEP American manned Mars expedition. Study 1991.

STCAEM SEP American manned Mars expedition. Study 1991. The solar electric propulsion (SEP) Mars transfer concept was the only non-nuclear advanced propulsion option in the STCAEM study.

TAL-100 TsNIIMash electric/xenon rocket engine. Development. Hall effect thruster with anode layer. Export version of D-100-I thruster developed under NASA/BMDO contract. Taken to engineering model stage.

TAL-38 TsNIIMash electric/xenon rocket engine. Development. 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.

TAL-WSF TsNIIMash electric/xenon rocket engine. 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 WSF satellite orbital altitude maintenance.

TMK-E Russian manned Mars expedition. Study 1960. Feoktistov felt that the TMK-1 manned Mars flyby design was too limited. His design group proposed in 1960 a complete Mars landing expedition, to be assembled in earth orbit using two or more N1 launches.