| 摘要 |
A dual-axis hinge assembly comprising mechanical devices which provide integrated synchronous rotation of a support element, such as a space antenna shaft (20), attached to a vertical hinge shaft (35) about its own axis while simultaneously pivoting the support shaft (35) about a horizontal hinge shaft (28) having a second axis which extends in a direction perpendicular to the axis of the vertical hinge shaft (35). 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 a space antenna (30) to pivot on the horizontal hinge shaft (28) from restrained position to deployed position and to simultaneously turn on its own axis about the vertical hinge shaft (35) axis when the restraint is removed, to aim the antenna reflector disk (30) in a predetermined direction. <IMAGE> |
