| 摘要 |
PURPOSE: To obtain a self-locking and reversible deployment mechanism for deploying a deployable diverging portion of a rocket engine nozzle which is simply operated, lightweight and reliable. CONSTITUTION: Each of three identical operative assemblies A, B and C mounted on a fixed main frame 112 comprises a linear actuator 107 and first and second links 105, 106 disposed in such a manner as to permit axes of three hinges to pass to or beyond a dead point where the hinges are in alignment. The three hinges are respectively the hinge between the main frame and a first zone 111 of the first link; the hinge between the upstream end 113 of the second link and a second zone of the first link; and the hinge between the downstream end 114 of the second link and a link support 115 mounted on a deployable portion 4 of a nozzle. The actuators are secured to non-deployable portions 1, 2, 3 of the nozzle. A free end of a drive member 107b is hinged to a third zone 110 of the first link, and the actuator is deactivated in a deployed or retracted position.
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