Deployment mechanism with integral actuation device
AssigneeMaxar Space LLC
InventorsJillian Gorsuch, Gregory Dudder
Life of this patent
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Abstract
An apparatus includes an integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring. In a spacecraft application, a spacecraft appendage may be coupled with a deployment mechanism, the deployment mechanism including at least one integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring.
Claims13
An apparatus, comprising an integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring, wherein:
- each of a proximal end of the torsion spring and a distal end of the torsion spring extend from a wall of the rigid portion and a central portion of the torsion spring is flexibly disposed with respect to the rigid portion;
- and
- the central portion includes a coupling feature that includes a threaded or press fit interface for mating to a spacecraft appendage.
A spacecraft, comprising:
- a spacecraft appendage;
- and
- a deployment mechanism connected to the spacecraft appendage, the deployment mechanism including at least one integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring, wherein:
- each of a proximal end of the torsion spring and a distal end of the torsion spring extend from a wall of the rigid portion and a central portion of the torsion spring is flexibly disposed with respect to the rigid portion;
- and
- the central portion includes a coupling feature that includes a threaded or press fit interface for mating to a spacecraft appendage.
Dependencies are inferred from the claim text.