Delta 50-820 User Manual Page 13

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Mueller, Ziemer, Hofer, Wirz, O’Donnell 13
Survey of Micro-Thrust Propulsion Options
Cube Sat - 5’th Annual Developers Workshop 2008
Description:
Status:Application:
JPL Miniature Xenon Ion (MiXI) Thruster
Electrostatic thruster. Ions are generated in a plasma
discharge by electron bombardment and accelerated
through extraction grids by DC electric field.
High specific impulse (3000 s), propellant eff (>70%), and
power eff (>40%), and non-contaminating propellant.
Much smaller (3 cm) and lower power than conventional
ion thrusters.
Typical MiXI performances:
TRL 4. Laboratory development/component verification
Based on proven (TRL 9) Ion engine technology (i.e.,
Boeing’s 13 and 25 cm thrusters (116 thrusters on 29
GEOSATS) and NASA’s 30 cm NSTAR (DS-1, DAWN).
Extensive flight history of larger-scale thrusters (SERT I
-
1964, SERT II -
1970, Boeing XIPS 1997-present,
NSTAR 1999-present)
Power processing unit (PPU) to be developed. PPU
challenges minimized by low power levels.
Miniature feed system to be developed.
Mass/complexity will be reduced with simple
proportional flow control.
For main delta-v propulsion of 30-100 kg spacecraft if
power > 20 W is used.
Well-suited for near-Earth/lunar/interplanetary
missions where high delta-v is needed due to
relatively high specific impulse (3000 s).
Low thrust requires long mission trip times -
spiral
trajectories.
Special applications include formation flying of a
constellation of spacecraft, or drag make-up in low
Earth orbits.
~30-100 kg S/C main propulsion, formation flying
3-cm Dia. MiXI Thruster
MiXI in Operation in JPL Test Lab
Supplier Designation
Thrust
(mN)
Thruster
Mass (kg)
Dia (cm) Isp (s)
Power
(W)
JPL MiXI 0.01-1.5 0.2 3
2500-
3200
13-50
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