Delta 50-820 User Manual Page 14

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Mueller, Ziemer, Hofer, Wirz, O’Donnell 14
Survey of Micro-Thrust Propulsion Options
Cube Sat - 5’th Annual Developers Workshop 2008
Description:
Status:Application:
Hall Thrusters
Electromagnetic thruster concept where ions are
accelerated in crossed electric and magnetic fields to
produce thrust.
Quasineutral plasma increases thrust density compared
to gridded ion thrusters
Uses non-contaminating xenon propellant.
Many Russian models -
this technology was preferred EP
choice in the former Soviet Union. Now being adopted
by nearly every GEO satellite provider worldwide.
TRL 9 at >200 W power. TRL 3 at ~10-100 W.
Hall thruster technology has reached TRL 9 for >200
W models. Over 200 thrusters have flown on
Russian, European, and US space missions since
1971.
Low-power laboratory thrusters (TRL 3) have been
tested. Significant miniaturization of thruster, power
system, and feed system would be needed for
CubeSat
applications
Presently limited to >100 kg spacecraft due to mass,
volume, and power demands for complete
subsystem.
Moderately-high specific impulse (1000-2000 s) trades
well for applications near large bodies where thrust
offsets gravity losses
>100 kg S/C for drag makeup, attitude control, &
orbit insertion
Busek
BHT-200 Hall Thruster
Power: 200 W
Thrust: 13 mN
First US Hall thruster to be
operated in space (TacSat-2,
Dec. 2006)
Supplier Designation
Power
(W)
Thrust
(mN) Isp (s) Efficiency
Mass
(kg)
Dia
(cm) TRL
Busek BHT-200 200 13 1390 44% > 1 2.9 9
KIAE
(Russia)
SPT-25 100-200 5-10 900-1300 25-32% ~ 1 2.5 3
MIT MHT-9 30-200 1-10 300-1500 5-25% < 1 0.9 3
PPPL CHT 50-170 3-6 1200-2000 30-40% < 1 2.6 3
Cylindrical Hall Thruster (CHT)
Princeton Plasma Physics Laboratory
(PPPL)
Power: 50-170 W
Thrust: 3-6 mN
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