System and method for spacecraft attitude control

Details System and method for spacecraft attitude control System and method for spacecraft attitude control

G - Physics

01

C

G01C 19/22 (2006.01) B64G 1/28 (2006.01) B64G 1/32 (2006.01) B64G 1/36 (2006.01) B64G 1/38 (2006.01) F16C 11/12 (2006.01) F16D 3/56 (2006.01) F16D 3/72 (2006.01)

Patent

CA 2338459

A momentum management system (10) for spacecraft attitude control. The momentum management system (10) includes a rotor (14) that provides control torques to a spacecraft. A drive (25) is provided to rotate the rotor (14), and a torque generation device (27) to impart torque to the rotor (14). A gimbal assembly (12) couples the drive (25) to the rotor (14). The gimbal assembly (12) has a spinning gimbal (18), and attaches to the drive (25) and the rotor (14) through the use of flexure joints (20). These flexure joints (20) permit the rotor (14) to tilt in two axes relative to a drive shaft (22), through a range of angles from about 0 degrees to about 7 degrees under the control of the torque generation device (27).

Cette invention a trait à un dispositif de gestion de quantité de mouvement (10) pour attitude d'astronef. Ce dispositif de gestion comporte un rotor (14) fournissant des couples de commande à un astronef. Un moteur (25) met en rotation le rotor (14) et un dispositif de génération de couple (27) imprime un couple au rotor (14). Une suspension à la cardan (12), qui couple le moteur (25) au rotor (14), possède une suspension à la cardan mise en giration (18) et se rattache au moteur (25) ainsi qu'au rotor (14) au moyen de joints à charnière (20). Ces joints (20) permettent au rotor (14) de s'incliner selon deux axes relativement à un arbre d'entraînement (22) et sous des angles variés allant de 1 degré environ à 7 degrés environ et ce, sous le contrôle du dispositif de génération de couple (27).

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