Talk:Control moment gyroscope

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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 (talk) 15:56, 13 March 2008 (UTC)

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 (talkcontribs) 15:18, 29 May 2013 (UTC)

Vela satellite question[edit]

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 (talkcontribs)

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 (talkcontribs)