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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

)

Required Impulse Bit (Ns)

Minimum

Thrust for

Slew

(mN)

17 mrad (1

) 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

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.

1 2 3 4 5 6 7 8 ... 18 19

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