Talk:Control moment gyroscope

I was under the impression that control moment gyroscopes could not be saturated like a reaction wheel. The limitation on a CMG is the rate of torque change per second (based on the gimbal actuator). —Preceding unsigned comment added by 129.186.192.110 (talk) 15:56, 13 March 2008 (UTC)Reply

Agreed, someone is editing who doesn't know what they're talking about. CMGs don't spin up or down to change orientation so there is no saturation problem. Whoever added the part about the ISS is confused. — Preceding unsigned comment added by Dkelly1966 (talk • contribs) 15:18, 29 May 2013 (UTC)Reply

A cluster of CMGs certainly can become saturated. I’ve added a section on how this happens.--SteepLearningCurve (talk) 17:49, 8 April 2016 (UTC)Reply

I'm describing the Advanced Vela satellite series for the TRW article. Encyclopedia Astronautica describes it as having the first "dual-spin, zero-momentum attitude control system" which I translate (using some relabeled hyperlinks) as a dual-gimbal control moment gyroscope attitude control system with no net angular momentum. Can anyone check this translation? Thanks, Overjive (talk) 02:07, 26 May 2010 (UTC) —Preceding unsigned comment added by Overjive (talk • contribs)

I found answers to my questions on-line: [1] and [2] Overjive (talk) 15:07, 29 May 2010 (UTC) —Preceding unsigned comment added by Overjive (talk • contribs)

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The bot-modified url did link to the archived title; but it's subscription access only and that doesn't seem to work with archived articles. I've replaced the whole link with http://arc.aiaa.org/doi/pdf/10.2514/2.4489 which does work. It's still subscription (though you may have automatic access if you have a university user id).--SteepLearningCurve (talk) 00:48, 1 April 2016 (UTC)Reply

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I just added a CN tag to this statement:

"For the space station, the gravity gradient torque approach is preferred because it requires no consumables or external hardware and because the gravity-gradient torque on the ISS can be very high."

The cite is old from 1990 - the first ISS module was launched in 1998, it was a theoretical study and proposal, and I can't find a citation to say that it is done that way. Instead they seem to use thrusters for attitude control when they need to desaturate the control moment gyros. Robert Walker (talk) 03:33, 6 May 2017 (UTC)Reply

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