Title:
【発明の名称】ミサイル制御フインの迅速着脱用カップリング機構
Document Type and Number:
Japanese Patent JPS63501239
Kind Code:
A
Abstract:
A coupling mechanism for quick attach/disconnect of a control fin to a missile which does not require the use of a separate tool to make the attachment. A first coupling member 24 is mounted on the control fin actuator rod 16. A force regulating means comprised of a spring 28 and retainer bracket 58 are attached to the first coupling member. A second coupling member 26 and a pivotable lever arm 38 are formed as part of the control fin. When the second coupling member is loosly fitted upon the first coupling member, rotation of the lever arm will engage the force regulating means thereby deflecting the spring 28. The reactive force of the spring is exterted through the lever arm, through the control fin, and causes the second coupling member to firmly and securely engage the first coupling member. A means is provided to lock the lever arm in place so as to retain the first and second coupling members in the firmly engaged position even through extreme aerodynamic maneuvers. The lock is easily disengaged manually should it be necessary to remove a control fin from the missile.
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Inventors:
Herman, Werner
Mars, Albert
Mars, Albert
Application Number:
JP50509586A
Publication Date:
May 12, 1988
Filing Date:
September 22, 1986
Export Citation:
Assignee:
Hues Aircraft Company
International Classes:
B64C9/02; F16B2/14; F42B10/06; F42B10/64; (IPC1-7): B64C9/02; F16B2/14; F42B15/027
Foreign References:
| US3117520A | 1964-01-14 | |||
| GB1438932A | 1976-06-09 |
Attorney, Agent or Firm:
Takehiko Suzue