Mueller, Ziemer, Hofer, Wirz, O’Donnell 3
Survey of Micro-Thrust Propulsion Options
Cube Sat - 5’th Annual Developers Workshop 2008
Propulsion Challenges for Cubesats
VACCO ChEMS
™
Thruster Module
Aerojet “Dawgstar”
PPT
FalconSAT
III
S/C Mass
(kg)
S/C Typ.
Dimension
*
(m)
Moment
of Inertia
(kg m
2
)
Required Impulse Bit (Ns)
Minimum
Thrust for
Slew
(mN)
17 mrad (1
o
) 0.3 mrad (1 arcmin) 0.02 mrad (5 arcsec)
20 s 100 s 20 s 100 s 20 s 100 s
1 0.1 0.017 1.4 x 10
-4
2.9 x 10
-5
2.5 x 10
-6
5.1 x 10
-7
1.7 x 10
-7
3.4 x 10
-8
0.06
10 0.3 0.150 4.3 x 10
-4
8.5 x 10
-5
7.5 x 10
-6
3.0 x 10
-6
1.0 x 10
-6
1.0 x 10
-7
1.75
20 0.4 0.533 1.1 x 10
3
2.3 x 10
-4
2.0 x 10
-5
4.0 x 10
-6
1.3 x 10
-6
2.7 x 10
-7
4.65
*
Assume cubical spacecraft shape
Representative Microspacecraft
Attitude Control Requirements:
•
Cube Sats
are standardized
spacecraft buses 10 x 10 x 10 cm
in size and 1 kg in mass.
•
Multiple cube buses (up to 3) have
been built.
•
Power is user supplied, but typically
no more than a few Watts per cube
using no deployable arrays so far.
•
Substantial challenges exist in
placing propulsion systems on
cubesats
within the mass, size, and
power design cosntraints.
•
Some propulsion options have been developped for cubesats
and other microsats, but none have flown on cubesats to date.
•
An existing micro-thrust propulsion data set has been filtered
for propulsion systems that are or may be (with some
additional development) suitable to Cube Sats.
Komentarze do niniejszej Instrukcji