4 Final Report - Emits - ESA
4 Final Report - Emits - ESA
4 Final Report - Emits - ESA
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4 <strong>Final</strong><br />
Instrument<br />
Prop. Tanks<br />
PDHT<br />
Electronics<br />
Instrument<br />
Electronics<br />
Star<br />
Tracker<br />
IMU<br />
IMU<br />
Electronics<br />
SADM<br />
<strong>Report</strong><br />
Figure 4.5-3: Internal Configuration<br />
Battery<br />
PSR<br />
SPU<br />
He-Tank<br />
(in central tube)<br />
Reaction<br />
Wheels<br />
Doc. No: GOC-ASG-RP-002 Page 4-51<br />
Issue: 2<br />
Date: 13.05.2009 Astrium GmbH<br />
SCU<br />
ADE5<br />
S-Bd<br />
Transponder<br />
PLIU<br />
SADM<br />
Coarse IMU<br />
4.5.2 Electrical Architecture<br />
The electrical architecture satisfies the need for high reliability and availability. A low risk approach is<br />
followed which means that heritage from previous projects is used whenever possible. Geostationary<br />
heritage can be derived from the Eurostar platform series and specifically from the COMS satellite<br />
which already implements meteorological and communication services on a 3-axis stabilized<br />
geostationary satellite, similar to the GEO-Oculus mission.<br />
Minimum complexity is achieved by separation of the electrical architecture into functional modules<br />
consisting of elements independent of the mission needs and customized elements which are tailored<br />
for mission specifics especially in the payload section. As such, the architecture references already<br />
the hardware breakdown as used on Eurostar for the bus elements while still giving flexibility for<br />
mission specific adaptations on platform side.<br />
High autonomy and reliability is satisfied by the redundancy concept within the overall electrical<br />
architecture and the on-board computer. It provides redundant modules and bus systems thus<br />
minimizing the amount of single point failures. Autonomy is also a key requirement on<br />
telecommunication satellites and therefore inherently available.<br />
Growth potential is achieved by a scalable electrical architecture. This is given by a scalable solar<br />
array in terms of amount of panels, regulator stages, battery size and regulator capability as well as<br />
adaptability of the amount of command and data handling interfaces from and to the on-board<br />
computer.<br />
For the payload side, a mission specific architecture is necessary due to the data rates of the<br />
instrument. Therefore, MIL-1553 bus has been selected for instrument TM/TC between SCU
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