Hinge-locking mechanism for deployable solar array
AssigneeXplore Inc.
InventorsBrian Riskas, Brandon Van
Life of this patent
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Abstract
Artificial satellites are dependent on solar arrays to produce the power needed to support the functional components of the satellite. The present invention is directed to a hinge-locking mechanism designed to maximize the photovoltaic real estate of a solar array of an artificial satellite. The hinge-locking mechanism facilitates the deployment of the solar array upon the artificial satellite entering orbit. The hinge-locking mechanism utilizes a tapered pin with an internal spring resting against an asymmetrically oval shaped cam of a common pivot point. The hinge-lock trades kinetic energy of a solar panel for spring compression to permanently lock the solar array in place upon deployment while reducing the shock load and maximizing deployed stiffness.
Claims17
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;
- 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;
- a passive release beam;
- and
- at least one hold-down bracket connected to the at least one solar panel;
- 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 at least one hold-down bracket restricts movement of the passive release beam until the at least one hold-down bracket is released;
- wherein the passive release beam is operable to deploy the at least one solar panel upon release of the 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;
- a passive release beam;
- 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 the passive release beam is connected to the at least one solar panel;
- wherein the at least one hold-down bracket restricts movement of the passive release beam until the at least one hold-down bracket is released;
- wherein the 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.
Dependencies are inferred from the claim text.