Deployable and tracked solar array mechanism for nano-satellites

摘要

A deployable and tracked solar array mechanism for restraining and releasing deployable solar panel arrays on a spacecraft is provided. The mechanism comprises a solar array drive mountable to the top side surface of the spacecraft. A solar panel array is pivotally attached to the solar array drive and positionable against the spacecraft. At least one notch is formed in at least one of the side edges of the solar panel array. A frame is slidably mounted to the spacecraft around the solar panel array. At least one tab extends from the frame over the solar panel array and releasably restrains the solar panel array. A spring mechanism urges the frame in a direction generally away from the solar array drive assembly. A release mechanism holds the frame against the force of the spring means wherein upon initiation of deployment, the release mechanism disintegrates allowing the spring means to slidably urge the frame in a general direction away from the solar array drive assembly thereby aligning the at least one notch with the at least one tab and releasing the solar panel array from against the spacecraft.