 | TAL-100
Credit - TsNIIMASH
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Oxidizer: Electric. Oxidizer Comments: The many versions of electric engines use electric or magnetic fields to accelerate ionized elements to high velocity, creating thrust. The power source can be a nuclear reactor or thermal-electric generator, or solar panels.
Fuel: Xenon. Fuel Freezing Point: -112 deg C. Fuel Boiling Point: -107 deg C. Fuel Comments: Proposed as propellant for some ion motors.
Engines Using Electric/Xenon
|
Motor
|
Thrust(vac)
kN |
Thrust(sl)
kN |
Isp
sec |
Isp (sl)
sec |
Designed for
|
Status
|
|
NASA-457M
|
|
|
2,326
|
|
|
|
|
|
|
|
|
|
|
|
Aerojet 50kW
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
P78-2
|
0.000
|
|
350
|
|
Upper Stages
|
Flown in 1979.
|
|
|
|
|
|
|
|
|
D-20
|
0.000
|
|
1,400
|
|
|
Development
|
|
|
|
|
|
|
|
|
XIPS-13 0.44 kW
|
0.000
|
|
2,585
|
|
Upper Stages
|
In Production
|
|
|
|
|
|
|
|
|
TAL-38
|
0.000
|
|
2,500
|
|
|
Development
|
|
|
|
|
|
|
|
|
TAL-WSF
|
0.000
|
|
1,350
|
|
|
Development
|
|
|
|
|
|
|
|
|
TAL-100
|
0.000
|
|
1,450
|
|
|
Development
|
|
|
|
|
|
|
|
|
D50
|
0.000
|
|
1,700
|
|
|
Development
|
|
|
|
|
|
|
|
|
XIPS-25 1.3 kW
|
0.000
|
|
2,800
|
|
|
|
|
|
|
|
|
|
|
|
D-100-II
|
0.000
|
|
1,600
|
|
|
Development
|
|
|
|
|
|
|
|
|
NSTAR
|
0.000
|
|
3,100
|
|
|
|
|
|
|
|
|
|
|
|
BPT-2000
|
0.000
|
|
1,765
|
|
Upper Stages
|
In Production
|
|
|
|
|
|
|
|
|
XIPS-25 4.2 kW
|
0.000
|
|
3,800
|
|
|
|
|
|
|
|
|
|
|
|
NEXT
|
0.000
|
|
4,100
|
|
|
|
|
|
|
|
|
|
|
|
P5 Hall thruster
|
0.000
|
|
2,326
|
|
|
|
|
|
|
|
|
|
|
|
TM-50
|
0.000
|
|
3,000
|
|
|
Development
|
|
|
|
|
|
|
|
|
BPT-4000
|
0.000
|
|
1,950
|
|
Upper Stages
|
In Production
|
|
|
|
|
|
|
|
|
HIVHAC
|
0.000
|
|
2,800
|
|
|
|
|
|
|
|
|
|
|
|
11B97
|
0.000
|
|
3,000
|
1
|
Upper Stages
|
Developed 1986-
|
|
|
|
|
|
|
|
|
Hall Electric Thruster
|
0.003
|
|
1,600
|
|
|
Development
|
|
|
|
|
|
|
|
|
BPT-600k
|
0.030
|
|
1,800
|
|
Upper Stages
|
In Development, 2005-2006
|
|
|
|
|
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© Mark Wade, 1997 - 2008 except where otherwise noted.
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