Control moment gyro for attitude control of a spacecraft

B - Operations – Transporting – 64 – G

Patent

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Details

B64G 1/28 (2006.01) G01C 19/02 (2006.01) G05D 1/08 (2006.01)

Patent

CA 2479566

The invention relates to a control moment gyro comprising a wheel support structure (12) which is mounted on a base (10) by means of a motor, which is used to rotate the support structure around a first axis (z), and bearing a wheel (14) which is equipped with means of driving the wheel spinner at a high speed around a second axis (x) perpendicular to the first. The aforementioned support structure or gimbal comprises a tubular part which rotates on the base and a flange which is disposed on only one side of the wheel and which is fixed to (i) said wheel and (ii) the tubular part. The diameter of the wheel and the point at which the wheel is fixed to the flange are proportioned such that the wheel penetrates the tubular part.

L~actionneur gyroscopique comprend une stucture support de roue (12) montée sur une embase (10) par un moteur permettant de la faire tourner autour d~un premier axe (z) et portant une roue (14) munie de moyens permettant d~entraîner la toupie de la roue à vitesse élevée autour d~un second axe (x) orthogonal au premier. La structure support ou cardan comporte une pièce tubulaire tournant sur l~embasse et un flasque placé d~un seul côté de la roue et fixé d~une part à la roue, d~autre part sur la pièce tubulaire. Le diamètre de la roue et l~emplacement de fixation de la roue sur le flasque sont proportionnés de façon que la roue pénètre dans la pièce tubulaire.

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