Helicopter sling-load stability control and release system
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United States of America Patent
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Sep 10, 2013
Grant Date -
Feb 28, 2013
app pub date -
Aug 26, 2011
filing date -
Aug 26, 2011
priority date (Note) -
In Force
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Abstract
A sling load computer-operated hook assembly for helicopter or unmanned aerial vehicle (UAV) use is provided. The hook assembly allows automated pick-up and delivery. The computer hook assembly also (1) directs navigation of the aircraft, (2) finds and engages loads for pickup, (3) controls stability of the sling load enroute, and (4) releases the load at the delivery point. The self-contained feature allows the hook assembly to be moved from aircraft to aircraft. The hook assembly senses weight, motion and position of the load for stability control. An integral GPS unit is used to direct navigation. These data are transmitted to the aircraft autopilot and flight director instruments to provide navigation to the designated points and to control load stability enroute. Mission data for pick-up and release points can be received remotely from a command and control tactical data net. Alternately, mission data can be locally entered.
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