发明名称 |
Self-locking and reversible mechanism for deploying the diverging portion of a rocket engine nozzle |
摘要 |
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.
|
申请公布号 |
US5282576(A) |
申请公布日期 |
1994.02.01 |
申请号 |
US19920890650 |
申请日期 |
1992.05.28 |
申请人 |
SOCIETE EUROPEENNE DE PROPULSION |
发明人 |
CHATENET, LUC H.;DESCLOS, PIERRE |
分类号 |
B64G1/00;F02K9/97;(IPC1-7):F02K9/97 |
主分类号 |
B64G1/00 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|