Patent ID: 9550584
Date: 2017-01-24
CPC Classifications: B64G

Claim:
1. A deployable thin membrane structure capable of being used with a spacecraft, the deployable thin membrane structure comprising: a flexible membrane structure; and a deployment mechanism for transitioning the flexible membrane structure from an undeployed state in which the flexible membrane structure is substantially incapable of providing a desired function to a deployed state in which the flexible membrane structure is capable of providing the desired function; wherein the deployment mechanism includes a plurality of pantograph structures, each associated with a different portion of the flexible membrane structure; wherein each of the plurality of pantograph structures includes first and second arms that each extend from a first terminal end to a second terminal end, the first and second arms pivotally connected to one another at an intermediate pivot location that is in between the first and second terminal ends of each of the first and second arms; wherein the second terminal ends of the first and second arms of each of the plurality of pantograph structures operatively engage the flexible membrane structure; wherein, when the plurality of pantograph structures are in the undeployed state, the first terminal end of the first arm is substantially adjacent to the second terminal end of the second arm and the first terminal end of the second arm is substantially adjacent to the second terminal end of the first arm for each of the plurality of pantograph structures; wherein, when the plurality of pantograph structures transition from an undeployed state towards a deployed state, (a) the first terminal ends of the first and second arms move closer to one another, (b) the second terminal ends of the first and second arms move closer to one another, (c) the second terminal end of the first arm moves farther from the first terminal end of the second arm, and (d) the second terminal end of the second arm moves farther from the first terminal end of the first arm for each of the plurality of pantograph structures; wherein the deployment mechanism includes a guide structure for engaging each of the plurality of pantograph structures and coordinating the transition of the plurality of pantograph structures with respect to one another; wherein the guide structure includes a rotor adapted to rotate about an axis; wherein the first terminal end of the second arm is pivotally connected to the rotor at a rotatable pivot location spaced from the axis for each of the plurality of pantograph structures; and the first terminal end of the first arm is pivotally connected at a fixed pivot location that is fixed relative to the axis for each of the plurality of pantograph structures.