Helicopter Sling-Load Stability Control and Release System
First Claim
1. A helicopter sling-load control system comprising:
- a sling-load assembly having a computer-operated hook, connected to and controlled by a server computer assembly; and
at least one external controller configured as a client in communication with said server computer assembly.
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Accused Products
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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Citations
28 Claims
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1. A helicopter sling-load control system comprising:
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a sling-load assembly having a computer-operated hook, connected to and controlled by a server computer assembly; and at least one external controller configured as a client in communication with said server computer assembly. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26)
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27. A helicopter sling-load control system comprising:
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a synthetic line assembly for attachment to suspension lugs of a helicopter; a computer-operated hook assembly attached to said synthetic line assembly; a client server computer located in said computer-operated hook assembly; an accessory bus connected to the client server computer; a load cell connected to said accessory bus providing payload data to said client server computer; a plurality of orientation sensors providing yaw, roll and pitch data to said client server computer; a global positioning system sensor connected to said accessory bus; a hook actuator solenoid connected to said accessory bus providing physical operation of the computer-operated hook. a wireless aircraft controller client communicating with said client server computer said controller providing flight control data to an aircraft autopilot; a pilot wireless controller client communicating with said client server computer providing for pilot operation of said hook; a crew chief wireless controller client communicating with said client server computer providing for crew chief operation of said hook; a ground crew wireless controller client communicating with said client server computer; a payload wireless controller client communicating with said client server computer; a radio-frequency identification device connected to said server computer accessory bus; a radio frequency identification device communicating with the radio frequency identification device attached to the server computer accessory bus; and a lock-mode pin located on said computer-operated hook assembly communicating with said radio frequency identification receiver, said pin unlocking operation of the hook when within range of the radio frequency identification device.
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28. A helicopter sling-load control system comprising:
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a sling-load assembly having a computer-operated hook, connected to and controlled by a server computer assembly; an accessory bus attached to the server computer assembly; a global positioning system sensor connected to said accessory bus; a joint tactical information distribution system transmitter receiver connected to the server computer accessory bus for theatre communications; a wireless local area net providing communications between the hook and clients; an orthogonal configuration of three micro-mechanical-electrical sensors providing inertial acceleration and position of said hook; an orthogonal configuration of 3-axes gyros providing inertial attitude, roll, pitch, and yaw, of said hook; a plurality of external controllers configured as clients and communicating with the server computer assembly; and at least one of said external controllers is configured for an aircraft instrument and autopilot interface.
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Specification