Patent ID: 10435182

Abstract:
Techniques for two-axis articulation of a deployed spacecraft solar array are disclosed. In one aspect, an arrangement mechanically coupling a solar array with a sidewall of a body of a spacecraft includes a proximal appendage, a distal appendage rotatably coupled with the proximal appendage by way of a hinge, and a closed cable loop (CCL) system coupled with the proximal appendage and the distal appendage. In an on-orbit configuration, a long axis of the proximal appendage defines an α axis that is substantially orthogonal to the sidewall. The hinge includes CCL disengagement mechanism configured to de-couple the CCL system from the proximal appendage and the distal appendage and a rotation driving mechanism configured to cause the distal appendage to rotate about a β axis when the proximal appendage is in the on-orbit configuration, the β axis being not aligned with the α axis.