Satellite Configuration Design - Finite Element Analysis for Satellite Structures - page 39

E

Battery cell module

Magnetorquer Mx

Reaction wheel My

Power conditioning unit

X

Cells leveling unit

Reaction wheel My

MEI signal processing
unit "2 units"

On-board digital
computing complex
"3 modules"

X-band electronic
module

Z

Fig. 2.18 General layout of Small Sat in the Y-direction without solar panels or heat shields

lunch vehicle interface, but the limited packaging volume prevents this. Although
the on-board digital computing complex is heavy (11.1 kg), it is mounted at the
forward end to balance mass distribution.
Finally, the results of our efforts in the packaging process for Small Sat
configuration are presented in the form of configuration layouts. These layout
drawings show as many details of the configuration. Moreover, these will become
the basis for much effort on the part of subsystem and structural designers.
Figures 2.13 , 2.14 , 2.15 and 2.16 show different views of Small Sat's preliminary
stowed configuration. Figures 2.17 , 2.18 , 2.19 , and 2.20 show different views of
the general layout of Small Sat without solar panels and heat shields. Figure 2.21
shows different views of the preliminary deployed configuration for Small sat.

2.7.5 Mechanical Interfaces

Satellite configuration design should provide easy access between the satellite and
both of the launch vehicle adapter and mechanical ground support equipment