| 摘要 |
The apparatus stabilizes loads beneath helicopters to prevent undesirable load movement while allowing in-flight optimization of the load's center of gravity to reduce drag and increase banking capability and top speed. An anchoring bracket secures the apparatus to the helicopter. The apparatus comprises an upper section that controls load pitch and lateral movement and a lower section that controls load height during unloading. A pitch regulator comprises a c-shaped yoke with upper and lower collars penetrated by a hollow shaft and elevator. A lateral movement regulator comprises a coupling and a y-shaped chassis. The coupling comprises a central sleeve captivated between the upper and lower collars and a motor permitting selective rotation about the elevator. The chassis secures to the coupling via a ball and socket and a middle suspension system captivated between coupling and suspension plates. Spaced apart terminal chassis arms support the load via a bearing wing. A winch spools a cable with an load stop resting on a foot. The foot front is pivotally secured to the pitch regulator while the back is pivotally secured to the wing. The wing and the elevator control load pitch. As the elevator retracts or extends, the wing moves arcuately upwardly or downwardly to move the load center of gravity longitudinally forwardly or rearwardly to control load pitch. An optional lower section controls load height during unloading. A hoist band passing through a pulley system with actuators that variably space the pulleys variably controlling effective band length.
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