Satellite Configuration Design - Finite Element Analysis for Satellite Structures - page 47

Table 2.5 Mass properties for the whole configuration of Small Sat in both stowed and
deployed configurations
Small Sat mass properties Satellite stowed

configuration

Satellite operating
configuration

Mass (kg) 205

Center of mass (mm)
X

-1.65 ± 10 -1.65 ± 10

Y 0.51 ± 10 0.51 ± 10

Z 487.26 ± 10 467.72 ± 10

Mass moments of inertia (kg.m 2 )
Ixx 26.69 ± 1 31.04 ± 1

Iyy 33.64 ± 1 37.41 ± 1

Izz 22.09 ± 1 27.93 ± 1

Ixy -0.01 -0.01

Ixz 0.19 0.19

Iyz 0.06 0.06

deployed (operating) configuration are calculated relatively to axes aligned with an
orbital coordinate system. The origin of both coordinates coincides with the
satellite's center of mass.

References

1. Sarafin TP, Larson WJ (eds) (1995) Spacecraft structures and mechanisms—from concept to
launch. Microcosm Press and Kluwer Academic Publishers, Torrance, CA
2. Dnepr SLS User's Guide, Issue 2, Nov. 2001. http://www.kosmotras.ru