Deployable and tracked solar array mechanism for nano-satellites

A method for restraining and releasing deployable solar panel arrays on a spacecraft, the spacecraft having a first side surface, a second side surface, a third side surface opposite the first side surface, a fourth side surface opposite the second side surface, a top surface, and a bottom surface, the method comprising:

• mounting a solar array drive assembly to the top side surface of the spacecraft;
• providing a first solar panel array having a first center panel;
• pivotally attaching a first panel to one side edge of the first center panel;
• pivotally attaching a second panel to the other side edge of the first center panel opposite the first panel;
• pivotally attaching the first center panel to the solar array drive assembly;
• positioning the first solar panel array with the first center, first, and second panels in a folded state;
• wherein at least one side edge of each of the first center panel, first panel, and second panel defining at least one notch, the notches aligning with one another when the first center, first, and second panels are in a folded state;
• slidably mounting a first frame with at least one first tab to the first side surface of the spacecraft;
• positioning the at least one first tab from the first frame over the first solar panel array with the first center, first, and second panels in the folded state so that the first solar panel array is held adjacent to the first side of the spacecraft;
• biasing the first frame with a potential force, generated using a first spring, in a direction towards the bottom side of the spacecraft;
• holding the first frame in a first position and against the potential force of the first spring;
• releasing the hold on the first frame to cause, using the first spring, the first frame to slide from the first position to a second position towards the bottom side of the spacecraft so that the at least one notch defined by the at least one side edge of each of the first center, first, and second panels aligns with the at least one first tab and the first solar panel array can be deployed away from the first side surface of the spacecraft.

A deployable and tracked solar array mechanism for restraining and releasing deployable solar panel arrays on a spacecraft, the spacecraft having a first side surface, a second side surface, a third side surface opposite the first side surface, a fourth side surface opposite the second side surface, a top surface, and a bottom surface, the mechanism comprising:

• a solar array drive assembly mountable to the top side surface of the spacecraft;
• a first solar panel array and a second solar array panel, each solar array panel having a center panel, a first panel pivotally attached to one side edge of the center panel, and a second panel pivotally attached to the other side edge of the center panel opposite the first panel, the center panels pivotally attached to opposite sides of the solar array drive assembly, the first solar panel array positionable against the first side surface of the spacecraft, the second solar panel array positionable against the third side surface of the spacecraft;
• a plurality of notches formed in at least one of the side edges of each of the first, second, and center panels of each of the first and second solar panel arrays, the notches of the first solar panel array aligning with one another when the panels of the first solar panel array are folded, the notches of the second solar panel array aligning with one another when the panels of the second solar panel array are folded;
• a first frame slidably mountable to the first side surface of the spacecraft;
• a second frame slidably mountable to the third side surface of the spacecraft;
• a plurality of first tabs extending from the first frame and over the first solar panel array when the first, second, and center panels are folded and in an undeployed position substantially parallel and adjacent to the first frame, the number of first tabs corresponding to the number of notches in each of the first, second, and center panels of the first solar panel array, the first tabs releasably restraining the first solar panel array in a folded and undeployed position substantially parallel and adjacent to the first frame;
• a plurality of second tabs extending from the second frame and over the second solar panel array when the first, second, and center panels are folded and in an undeployed position substantially parallel and adjacent to the second frame, the number of second tabs corresponding to the number of notches in each of the first, second, and center panels of the second solar panel array, the second tabs releasably restraining the second solar panel array in a folded and undeployed position substantially parallel and adjacent to the second frame;
• a first spring actuator for urging the first frame from a first position at which the plurality of first tabs are unaligned with the notches in each of the first, second, and center panels of the first solar panel array when the first, second, and center panels are in a folded and undeployed position substantially parallel and adjacent to the first frame to a second position at which the plurality of first tabs are aligned with the notches in each of the first, second, and center panels to allow the first, second, and center panels to deploy away from the first frame;
• a second spring actuator for urging the second frame from a first position at which the plurality of second tabs are unaligned with the notches in each of the first, second, and center panels of the second solar panel array when the first, second, and center panels are in a folded and undeployed position substantially parallel and adjacent to the second frame to a second position at which the plurality of second tabs are aligned with the notches in each of the first, second, and center panels to allow the first, second, and center panels to deploy away from the second frame;
• a first release mechanism, wherein the first release mechanism is capable of being in a first state in which the first spring actuator has stored energy and the first frame is in the first position and a second state in which the first spring actuator is allowed to apply at least some of the stored energy to the first frame to move the first frame from the first position to the second position, wherein the first release mechanism disintegrates in transitioning from the first state to the second state;
• a second release mechanism, wherein the second release mechanism is capable of being in a first state in which the second spring actuator has stored energy and the second frame is in the first position and a second state in which the second spring actuator is allowed to apply at least some of the stored energy to the second frame to move the second frame from the first position to the second position, wherein the second release mechanism disintegrates in transitioning from the first state to the second state.