| 摘要 |
Dual-axis hinge assemblies comprising mechanical devices which provide integrated synchronous rotation of a support element, such as a space antenna shaft, attached to a vertical hinge shaft about its own axis while simultaneously pivoting the support shaft about a horizontal hinge shaft having a second axis which extends in a direction perpendicular to the axis of the vertical hinge shaft. The hinge assembly is adapted to be mounted parallel to a side surface of a spacecraft body and restrained by a holddown device, and is biased to cause the space antenna to pivot on the horizontal hinge shaft from restrained position to deployed position and to simultaneously turn on its own axis about a vertical hinge shaft when the restraint is removed, to aim the antenna reflector disk in a predetermined direction.
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