Mueller, Ziemer, Hofer, Wirz, O’Donnell 6
Survey of Micro-Thrust Propulsion Options
Cube Sat - 5’th Annual Developers Workshop 2008
Description:
Status:Application:
Cold Gas Thrusters
•
Pressurized gaseous propellant is vented through a
valve and nozzle to produce thrust.
•
Relatively simple, low cost technology.
•
Typically using N
2
as propellant, but any gas can be
used.
•
Benign propellants -
no contamination risks.
•
No power requirements except for valve.
•
Very low Isp -
< 100 sec.
•
Heavy tankage due to pressurized gas.
•
Typical performances range from 4.5 mN -
105 N thrust,
10 g to 0.4 kg mass, 1 -
50 W power. Isp propellant
dependent, typically 65 sec for N
2
(see Table next sheet).
TRL 9. Flight proven technology.Attitude control and very limited delta-v.
•
Cold gas technology has been used in space since
the 1960s.
•
Proven technology -some remaining leakage
concerns by some customers.
•
Several commercially available thruster options from
two remaining US vendors (Moog, Marrotta). VACCO
providing novel butane thruster technology (separate
sheet).
•
Newer developments on chip based thrusters (TRL 3)
and stepper motor valves covering range of thrusts
from 1 µN to 1.2 mN (Moog), and ultra-low power
thrusters (1 W, Marotta, 0.1W VACCO)
•
Application primarily to ACS and very limited delta-v
only due to low Isp.
•
Very small, light-weight components, but potentially
high system weight due to heavy, high pressurant
tanks may pose integration difficulties to CubeSats.
•
Several benign propellant options make these
thrusters a choice for contamination sensitive
environments (sensitive optics, IR cooled S/C).
•
Long mission durations may pose risks due to long
term leakage concerns.
Moog 58X125A (4.4 mN)
Moog 58E142 (0.12 N)
Moog 50-820 (52 -
105 N)
Marotta
Cold Gas Thruster
(0.05 -
2.36 N)
Moog Torque Motor on-a-Chip
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