| 摘要 |
A low-energy locking hinge mechanism operable with a spacecraft to support a deployable device, and to facilitate the deployment and locking of the deployable device, the hinge mechanism comprising: (a) a support base configured to couple to a structure of the spacecraft; (b) means for securing a deployable device to the support base, the deployable device being configured to rotate about a pivot axis; (c) a one-way clutch supported about the support base and operable with the means for securing, the one-way clutch being configured to facilitate one-way rotation of the deployable device from a stowed position to a deployed position, and to lock the deployable device in the deployed position, the one-way clutch having an inherent actuatable locking function configured to prevent backward motion; and (d) an actuation member operable with the one-way clutch to deploy the deployable device from the stowed position to the deployed position, the actuation member comprising an actuation energy sufficient to actuate the locking function of the one-way clutch within a zero-gravity environment.
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