4 Final Report - Emits - ESA
4 Final Report - Emits - ESA
4 Final Report - Emits - ESA
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4 <strong>Final</strong><br />
3000 platform.<br />
<strong>Report</strong><br />
The overall S/C structure has a classical "box" shape with a central cylinder (800 mm) as the main<br />
structural load path to the launcher. The design will fulfil the satellite strength and stiffness<br />
requirements. The instrument is mounted at the top of the platform.<br />
Currently, the instrument is connected to the platform by means of three isostatic mounts. It is<br />
recommended for future work to revisit the instrument mechanical configuration so that it is supported<br />
by four sets of isostatic mounts, turned upside down. This would allow the “head” of an isostatic mount<br />
to be fixed to the top of the shear walls, and thus provide a better load path than what is currently<br />
depicted. Clearly, this topic has to be iterated with the mechanical design of the payload considering<br />
the mechanical load path and thermo-elastic distortions.<br />
It should also be noted that due to the width of the instrument being much larger than the central<br />
cylinder, it is not possible to fix the isostatic mounts in the current configuration directly to the central<br />
cylinder.<br />
Figure 4.5-13. Satellite Configuration showing the main structure<br />
Primary Structure<br />
The satellite primary structure consists of,<br />
• A launcher interface ring<br />
• A central cone/cylinder structure<br />
• 4 shear walls<br />
• ±X Upper and lower floors<br />
• Upper and lower tank floors<br />
• Tank support struts<br />
Doc. No: GOC-ASG-RP-002 Page 4-73<br />
Issue: 2<br />
Date: 13.05.2009 Astrium GmbH<br />
YS/C<br />
XS/C<br />
ZS/C
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