There should be images in the Mechanical Systems Workbook and the Mechanical Systems section of the SCOM.
SSU Development Thread (2.0 to 3.0)
- Thread starter Urwumpe
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Just don't make it permanent. We need these for proper SC support which is not too far away I hope.
I was thinking a permanent part of the texture, a part that could not be removed easily.
SiameseCat
Addon Developer
I don't think we're replacing any textures in code. I think Donamy wants to display the cavities in the texture only for the moment, and in a later revision the mesh can be edited to include the cavities.
I just thought we could get a head start on the Centaur implementation. Just let me know when anyone feels like taking it on.
Donamy
Addon Developer
What does it look like in the bay for flight ?
Just like in the STS-26 photo. It's an open cavity for the various fluid/gas lines on the CISS to be routed through. The actual exterior panel had 6 penetrations, 3 length-wise and 2 height-wise. This was only for the port side which serviced the hydrogen system of the Centaur.
The starboard side had the same open cavity for the oxygen vent and dump line, but no actual penetrations on the exterior panel. The actual penetration for the dump port was located below the so called midbody payload umbilical panels which is what these panels are called.
Photo of the port side midbody payload umbilical panel and hydrogen dump port can be seen in the this top photo: http://www.orbiter-forum.com/showthread.php?p=481215&postcount=158
The top left arrow points to the hydrogen dump port while the top right arrow points to the port midbody payload umbilical panel with the 6 penetrations. The two bottom arrows point to cavities for the RBUS Carrier Panel feet cavities where the feet of the RBUS Carrier Panel is attached to the orbiter. You can see similar cavities on the aft engine compartment for the TSM Carrier Panel feet.
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This is how the same cavities are covered today:
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And the distance between the forward and aft ET attach points is 21.42744 m (843.6 in)? I need to know this for the resized ET(s).
After more careful checking, I have 23.57374m (928.1 in). This is according to the SLWT System Definition Handbook published by Lockheed Martin in December 1997. Coordinates given are Xo1317 for the aft and Xo388.9 for the FWD.
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I thought that it was implied by asking about the distance between the FWD/aft attach points. But the advice is taken.Remember to say explicitly that you only mean distance in X-direction (Z in Orbiter), otherwise Pytagoras might want to have a word with you.
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