Abstract: Systems, apparatus, and methods are provided for retrieving data from remotely deployed sensor systems. Flight control systems are also provided for maintaining the orientation of a high gain antenna affixed to an aircraft relative to a stationary or nearly stationary transceiver.

Abstract: A method and apparatus for charging energy supplies in an unmanned aerial vehicle (UAV). The present invention relates to a UAV that comprises an inductive charging device that utilizes the electromagnetic field emanated by overhead/utility power lines, to charge the energy supplies. The UAV also includes a releasable latch for holding power lines to allow for the perching of the UAV on power lines during the charging process. The latch and the inductive charging device may be provided on a single device, a battery augmentation trap (BAT). The UAV may be perched in an upright orientation to allow for takeoff after the charging of energy supplies on the power line.

Abstract: Red, green and white colored lights are emitted from navigation orientation indicating light emitting devices mounted within a helicopter rotor blade near its tip. The light emissions from such devices are under control to respectively indicate passage of the rotor blade through limited arcuate portions of the travel path of the rotor blade end tip. Operational control over the light emitting devices is effected by data processing of outputs from air-speed responsive sensors on the blade end tip.

Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination.

Abstract: Side-slip of an aircraft during flight is detected through a pair of pressure sensors fixedly mounted on opposite lateral sides of the aircraft fuselage. Pressure measurement signals at said sensors are fed to electronic circuitry within the aircraft for generating magnitude and frequency signals reflective of the side-slip that are applied to a pair of vibrators respectively mounted on the undersides of a pair of pilot foot pedals located within the cockpit. The foot pedals are connected by linkage to the tail rudder on the aircraft fuselage. The varying magnitude and frequency of vibrations applied to the rudder foot pedals by the vibrators enables the pilot to immediately sense side-slip through the feet on the pedals. In response to such side-slip sensing, one of the pedals may be timely depressed for side-slip corrective angular displacement of the rudder.