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- Path: sparky!uunet!usc!sdd.hp.com!uakari.primate.wisc.edu!ames!eos!aio!sweetpea.jsc.nasa.gov!russell
- From: russell@sweetpea.jsc.nasa.gov (thomas russell 283-4007)
- Newsgroups: sci.space.shuttle
- Subject: Re: SSF
- Message-ID: <1992Aug21.181303.9135@aio.jsc.nasa.gov>
- Date: 21 Aug 92 18:13:03 GMT
- References: <1872.2A928EDB@catpe.alt.za>
- Sender: news@aio.jsc.nasa.gov (USENET News System)
- Organization: McDonnell Douglas Space Systems Company
- Lines: 73
-
- In Article <1992Aug20.000610.2462@aio.jsc.nasa.gov> kjenks@gothamcity.jsc.nasa.gov
- says:
-
- >SSF will be in a circular orbit, about 250 nautical miles up, at a 28.5
- >degree inclination to the equator. (I'm unsure about the exact
- >altitude, but that's close.)
-
- >The spacecraft will be in one of the less stable "gravity gradient"
- >positions, with one end of the long structure always pointed in the
- >direction of travel, and the modules always pointed at the Earth
- >below. I'll try another ASCII sketch. Think of this as a sequence
- >of pictures, with "0" being the Earth:
- >
- > _
- > / \
- > | 0 0 0 0 0 | 0 0 0
- > / _ \
- >
- > 1 2 3 4 5 6 7 8
- >
- >
- >Picture a stick (SSF) running clock-wise around a ball (Earth).
- > ... <deleted>
-
-
- After the Station Builds reach the Permanently Manned Configuration (PMC),
- it will spend most of its time in an attitude such that the truss is
- purpendicular to the direction of travel. Thus the station rotates about
- its long axis at approx. 6 degrees/min to keep the module pattern oriented
- towards earth. This general attitude is refered to as the Local Vertical
- Local Horizontal (LVLH) orientation. This is only a general attitude because
- the station flys with its principle axes more or less aligned
- with the LVLH frame. Deviations from the principle axis alignment are
- used to generate gravity gradient torque to oppose the small aerodynamic
- torques which are experienced in LEO. This attitude is normally called the
- Torque Equilibrium Attitude (TEA) and must be maintaned to prevent
- momentum saturation of the Control Moment Gyros (CMGs).
-
- To borrow Ken's picture:
-
-
- Velocity into page
-
- O-------> Out of Orbit Plane Direction
- |
- |
- |
- \|/
-
- Earth
-
-
- SSSS SSSS SSSS
- SSSS T T SSSS SSSS /|\ |
- SSSS T T SSSS SSSS \ _ /
- tSSSStttttttttttttttttttttttttttttttttttttttttttttttSSSStttSSSSt
- tSSSStttttttttttttttttttttttttttttttttttttttttttttttSSSStttSSSSt 6 deg/min
- SSSS T nMMMMMMMn T SSSS SSSS rotation
- SSSS T cMMMMMMM T SSSS SSSS
- SSSS SSSS SSSS
-
- Legend: t = truss, S = solar panel, T = thermal radiator,
- n = node, M = module, c = Cupola
-
-
- Clear as Mud right? Hope this helps a little.
-
- The Attitude which Ken refers to is used for orbit reboost prior to PMC.
- The SSF attitude control community refers to it as the Arrow Orientation.
-
- As for the rest of Ken's response, I'll go along with his simple answers...
-
- - Tom Russell / MDSSC-Houston
-