Hinge-locking mechanism for deployable solar array

A satellite solar panel system, comprising:

• at least one solar panel;
• at least one hinge-lock;
• and
• a passive release beam;
• wherein the at least one hinge-lock includes at least one female ear component connected to a central pivot point and at least one tapered pin;
• wherein the central pivot point includes at least one bore operable to receive the at least one tapered pin;
• wherein the at least one female ear component is connected to the at least one solar panel;
• wherein the passive release beam is connected to the at least one solar panel;
• wherein the passive release beam is operable to deploy the at least one solar panel upon release of at least one hold-down bracket;
• wherein the at least one female ear component and the at least one tapered pin are operable to rotate with respect to an axis of rotation of the central pivot point;
• and
• wherein the at least one tapered pin is operable to move in a substantially linear path perpendicular to the axis of rotation of the central pivot point to penetrate the at least one bore of the central pivot point upon the deployment of the at least one solar panel.

A satellite solar panel system, comprising:

• at least one solar panel;
• at least one hinge-lock;
• and
• at least one hold-down bracket;
• wherein the at least one hinge-lock includes at least one female ear component connected to a central pivot point and at least one tapered pin;
• wherein the central pivot point includes at least one bore operable to receive the at least one tapered pin;
• wherein the at least one female ear component is connected to the at least one solar panel;
• wherein a passive release beam is operable to deploy the at least one solar panel upon release of the at least one hold-down bracket without a motor;
• wherein the at least one female ear component and the at least one tapered pin are operable to rotate with respect to an axis of rotation of the central pivot point;
• and
• wherein the at least one tapered pin is operable to move in a substantially linear path perpendicular to the axis of rotation of the central pivot point to penetrate the at least one bore of the central pivot point upon the deployment of the at least one solar panel.