A method for compensating for aerodynamic radial loads applied to a drogue coupling of a hose and drogue air to air active refueling system including: deploying a refueling hose from a tanker aircraft, wherein the drogue coupling is at a distal end of the hose and the drogue coupling is connected to a hose end control unit which includes at least three fins extending outward into air flowing over the hose end control unit; sensing acceleration of the hose end control unit and/or the drogue coupling, generating an acceleration signal with data representing the sensed acceleration; determining at least one deflection angle for at least one of the three fins based on the acceleration signal, and rotating at least one of the three fins by the at least one deflection angle.

An apparatus comprising: a port cap operable to be coupled to a hydraulic motor/pump, the port cap comprising a first fluid port, a second fluid port and an access port; a first transducer coupled to the port cap through the first fluid port; a second transducer coupled to the port cap through the second fluid port; and a resolver coupled to the port cap through the access port, the resolver comprising a splined shaft to couple to an output shaft of the hydraulic motor/pump when the port cap is coupled to the hydraulic motor/pump. A system including a hydraulic motor/pump, a drive system controller and a port cap and a method of determining hose velocity, hose position, motor/pump torque and hose tension using data gathered at port cap.

An apparatus comprising: a port cap operable to be coupled to a hydraulic motor/pump, the port cap comprising a first fluid port, a second fluid port and an access port; a first transducer coupled to the port cap through the first fluid port; a second transducer coupled to the port cap through the second fluid port; and a resolver coupled to the port cap through the access port, the resolver comprising a splined shaft to couple to an output shaft of the hydraulic motor/pump when the port cap is coupled to the hydraulic motor/pump. A system including a hydraulic motor/pump, a drive system controller and a port cap and a method of determining hose velocity, hose position, motor/pump torque and hose tension using data gathered at port cap.

A method of operating a supply aircraft for in-flight recharging comprises: transmitting a deploy command signal from a communication unit of the supply aircraft to a communication unit of a receiver aircraft, to cause a line and drogue to deploy from the receiver aircraft; controlling at least one of the supply aircraft and the drogue to engage the drogue with a first end of an electrical cable of the supply aircraft, a second end of the electrical cable being connected to the supply aircraft; and transmitting a return command signal from the communication unit of the supply aircraft to the communication unit of the receiver aircraft, to cause the line and drogue to return to the receiver aircraft with the first end of the electrical cable. The supply aircraft is located behind the receiver aircraft and the deploy command signal is for causing the line and drogue to deploy rearwardly of the receiver aircraft.

A method of operating a supply aircraft for in-flight recharging comprises: transmitting a deploy command signal from a communication unit of the supply aircraft to a communication unit of a receiver aircraft, to cause a line and drogue to deploy from the receiver aircraft; controlling at least one of the supply aircraft and the drogue to engage the drogue with a first end of an electrical cable of the supply aircraft, a second end of the electrical cable being connected to the supply aircraft; and transmitting a return command signal from the communication unit of the supply aircraft to the communication unit of the receiver aircraft, to cause the line and drogue to return to the receiver aircraft with the first end of the electrical cable. The supply aircraft is located behind the receiver aircraft and the deploy command signal is for causing the line and drogue to deploy rearwardly of the receiver aircraft.

A personnel rescue system has a winch subsystem comprising a first tether deployable and retrievable with a powered winch, a powered and controllable end effector attached at a deployable end of the first tether, a second tether attached by a first end to the end effector, a personnel harness attached at a second end of the second tether; and control apparatus in communication with the end effector, the control apparatus operable to maneuver the end effector vertically and laterally, carrying the personnel harness to a subject to be rescued.

A satellite refueling system has a refueling satellite carrying fuel, a fuel hose connected to the fuel carried by the refueling satellite, with a maneuverable end effector at a deployed end of the fuel hose, the end effector comprising a fuel supply nozzle connected to the fuel hose, a plurality of thrusters on the end effector providing thrust in a plurality of directions, an imaging device on the end effector capturing images in an immediate environment of the end effector, and computerized circuitry operating individual ones of the plurality of thrusters in response to the images captured by the imaging device. The refueling satellite deploys the fuel hose, and the computerized circuitry operates the thrusters to maneuver the end effector, bringing the fuel supply nozzle to a location to deliver fuel.

A stabilizing system for a winch cable has a winch cable deployed and suspended from a helicopter, a cargo support attached at a deployed end of the winch cable, an end effector attached to the winch cable, the end effector comprising thrusters directed in a plurality of directions orthogonal to a vertical axis of the winch cable, first control circuitry in the helicopter, and second control circuitry in the end effector. Thrust of individual thrusters is controlled through the first and second control circuitry maintaining the axis of the winch cable vertical, damping swinging of the cable.

An imaging system has a tether sub-system deployable and retrievable from an aircraft, an imaging device attached at a deployable end of the tether, and control apparatus comprising control and communication circuitry receiving images captured by the imaging apparatus and storing the images. The tether is deployed to a predetermined length, the aircraft is piloted in a flight pattern causing the imaging device at the deployed end of the tether to attain a fixed position proximate an imaging target, and the control apparatus is operated to capture images of the target.

A data delivery system has a tether deployable from an aircraft having a first data repository, a transmission pod at a deployed end of the tether, the transmission pod having first wireless communication circuitry, a communication conductor in parallel with the tether connecting the data repository in the aircraft with the first wireless communication circuitry in the transmission pod, and a receiving station on ground surface having a receiving antenna, second wireless communication circuitry compatible with the first wireless communication circuitry in the transmission pod, and a second data repository. The tether is deployed from the aircraft in a manner to position the transmission pod stationary proximate the receiving station antenna, and data is downloaded from the data repository in the aircraft to the data repository in the receiving station via the communication conductor and the wireless communication circuitry in the transmission pod.