Self-locking and reversible mechanism for deploying the diverging portion of a rocket engine nozzle
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United States of America Patent
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-
Feb 1, 1994
Grant Date -
N/A
app pub date -
May 28, 1992
filing date -
May 30, 1991
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
The deployment mechanism comprises three identical operative assemblies mounted on a fixed main frame. Each operative assembly comprises a linear actuator and first and second links disposed in such a manner as to ensure self-locking in a deployed position by causing the axes of the following three hinges to pass to or slightly beyond a dead point where they are in alignment: the hinge between the main frame and a first zone of the first link; the hinge between the upstream end of the second link and a second zone of the first link; and the hinge between the downstream end of the second link and a link support mounted on the deployable portion of the nozzle. The actuator is secured and anchored to a non-deployable portion of the nozzle and it includes a drive member whose free end is hinged to a third zone of the first link, and it is deactivated in both of the final positions, i.e. when the deployable portion is deployed and when it is retracted.
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