Systems and methods for satellite solar panel deployment

1. A system, comprising:

a satellite body defining:

first, second, third, and fourth major sides;

first, second, third and fourth edge regions disposed between the corresponding first and second, second and third, third and fourth, and fourth and first major sides;

a first solar array comprising a plurality of panels including an innermost panel, a middle panel, and at least one outermost panel, wherein the middle panel is joined with the innermost panel and the outermost panel by first-type hinge mechanisms each having a first rotation axis, wherein the innermost panel is attached to the satellite body by one or more second-type hinge mechanisms each having a second rotation axis substantially parallel to the first rotation axis, and wherein at least the innermost panel is releasably constrained; and

wherein the first solar array is configured to be foldable into a stowed configuration, and planar unrollable into a deployed configuration,

wherein when the first solar array is in the deployed configuration, the innermost panel is immediately adjacent to the satellite body, the middle panel is disposed between the innermost panel and the outermost panel, and the outermost panel is disposed outmost from the satellite body,

wherein during deployment,

the innermost panel first rotates away from the satellite body, while the innermost panel, the middle panel and the outermost panel are held together,

the middle panel and the outermost panel then rotate away from the innermost panel, while the middle panel and the outermost panel are held together, and

the outermost panel then rotates away from the middle panel,

wherein while in the stowed configuration:

the middle panel is placed against the satellite body,

the outermost panel is disposed between the innermost panel and the middle panel, and

the innermost panel surrounds and constrains the middle panel and the outermost panel against the satellite body.

2. The system of claim 1 , wherein the first-type hinge mechanisms are configured to rotate between 0 when stowed and 180 degrees when deployed.

3. The system of claim 1 , wherein the one or more second-type hinge mechanisms are configured to rotate between 0 when stowed and 135 degrees when deployed.

4. The system of claim 1 , wherein

the plurality of panels of the first solar array are constrained against the first major side while in the stowed configuration; and

a first combined rotatable edge of the stowed and planar rolled-up plurality of panels is released during deployment.

5. The system of claim 4 , wherein the first combined rotatable edge of the stowed and planar rolled-up plurality of panels is disposed opposite the one or more second-type hinge mechanisms.

6. The system of claim 4 , further comprising one or more circuits for deployment of the plurality of panels.

7. The system of claim 1 , further comprising a second solar array comprising a second plurality of panels attached to one another therebetween by corresponding first-type hinge mechanisms, wherein a first panel of the second plurality of panels is attached to the satellite body at the third edge region by one or more second-type hinge mechanisms; and

wherein the second solar array is configured to be foldable into a stowed configuration, and planar unrollable into a deployed linear configuration.

8. The system of claim 7 , wherein

the second plurality of panels of the second solar array are constrained against the third major side while in the stowed configuration; and

a second combined rotatable edge of the stowed and planar rolled-up second plurality of panels is released for deployment.

9. The system of claim 8 , wherein the second combined rotatable edge are disposed at the second edge region.

10. The system of claim 1 , wherein while in the deployed configuration, the plurality of panels are configured as a deployed linear array.

11. The system of claim 10 , wherein an axis of the deployed linear array is disposed 135 degrees from respective faces of the first major side and the second major side.

12. The system of claim 1 , wherein the one or more second-type hinge mechanisms constrain the deployed linear array by a hinge spring and a hinge stop.

13. The system of claim 1 wherein at least one of the plurality of panels is configured with substantially the same width as a corresponding width of the first major side.

14. The system of claim 1 , wherein at least one panel of the plurality of panels include solar cells on back and front sides.

15. The system of claim 1 , further comprising a stop mechanism adjacent the first edge and configured to engage with a cam to control a deployment sequence of the plurality of panels.

16. The system of claim 1 , further comprising a second stage mechanism including a second cam and a second stop configured to engage during rotation to prevent unfolding of the outermost panel of the plurality of panels until the middle panel of the plurality of panels has rotated enough beyond a predetermined angle.

17. The system of claim 1 , wherein one or more of the second major side and fourth major side of the satellite body is configured with a fixed first solar panel.

18. The system of claim 1 , wherein the at least one outermost panel of the plurality of panels is disposed and stacked between the innermost panel and the middle panel of the plurality of panels during stowing.