| 摘要 |
A yaw fin deployment apparatus provides a continuous depolyment force to the fin during the entire range of deployment. A shaft, a movable sleeve bearing for riding along the shaft, a strut connected between the sleeve bearing and the fin, and a lanyard for continuously pulling the sleeve bearing along the shaft are provided. The momentum created when the ejection seat separates from the aircraft is transmitted to the lanyard, to the sleeve bearing, and to the strut for deploying the fin. A pulley is attached to the seat and is located near the aft end of the shaft and guides the lanyard to assure that the actuation force exerted on the sleeve bearing is in a direction parallel to the axis of the shaft. When the fin is fully deployed, the lanyard separates from the sleeve bearing through a split ring at the bottom of the sleeve bearing. A primary spring-loaded latch located at the aft end of the shaft locks the fin in a fully deployed position. A secondary spring-loaded latch located between the aft end and the fore end of the shaft prevents a partially deployed fin from returning to the stowed position. An energy attenuating cone-shaped bushing is located at the aft end of the shaft supplies a continuous and gradually increasing braking resistance for the sleeve bearing to bring it to a halt when the fin is fully deployed.
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