An unmanned air vehicle system includes an unmanned air vehicle including a camera unit, a pilot terminal capable of piloting the unmanned air vehicle, and a display that displays images captured by the camera unit. The camera unit includes a first camera that captures a first image and a second camera that captures a second image. An angle of view of the first camera is narrower than an angle of view of the second camera.

In one embodiment, an aerial collection system includes an image collection field vehicle that travels at street level and an image collection aerial vehicle that travels in the air above the street. The aerial vehicle collects image data including at least a portion of the field vehicle. The field vehicle includes a marker, which is identified from the collected image data. The marker is analyzed to determine an operating characteristic of the aerial vehicle. In one example, the operating characteristic in the marker includes information for a flight instruction for the aerial vehicle. In another example, the operating characteristic in the marker includes information for the three dimensional relationship between the vehicles. The three dimensional relationship is used to combine images collected from the air and images collected from the street level.

A system and method for payload management for a UAV/aircraft is disclosed. UAV/craft may be configured for a mission with aerodynamically-exposed payload to be delivered from originator to destination on a route in operating conditions. UAV/aircraft may provide an aerodynamic profile indicative of the expected aerodynamic performance in view of considerations such as flight characteristics and effects; a base aerodynamic profile without payload and a loaded aerodynamic profile with payload may be determined. The system and method may comprise estimation/determination and assessment/transaction of a freight charge for the mission based on aerodynamic profile and other considerations; freight charge may comprise a surcharge or penalty based on performance using unit reference points and factors/considerations. UAV/aircraft system can be configured and operated/managed to interface with the system; missions may be optimized based on freight charge or other considerations. The system comprises an interface with UAV/aircraft and data sources and/or networks for data communications.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The tail is removably coupled to the fuselage. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor.

An aircraft control apparatus (20) includes a display unit (210), a display (220), an input unit (230), a selection unit (240), and a command generation unit (250). The command generation unit (250) acquires an image that has been generated by an image capture unit (350) of an aircraft (30). The display unit (210) displays, on the display (220), the image acquired by the command generation unit (250). The image includes at least one electric wire or at least one pipe that could be an inspection target. The input unit (230) displays, according to an input from a user, a line within the image displayed on the display (220). The selection unit (240) selects an inspection target by use of the line displayed by the input unit (230). The command generation unit (250) generates command information for the aircraft to photograph the inspection target while moving along the inspection target, and transmitting the command information to the aircraft (30).

A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.

A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.

An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

A gimbal mount for a sensor having an outer and inner gimbal mount to stabilize vibrations in a wide frequency band without having to statically balance the sensor. A direct drive is provided for at least one drive of an outer axis of rotation of the outer gimbal mount and an amplified piezo actuator is provided for at least one drive of an inner axis of rotation of the inner gimbal mount. The at least one outer axis of rotation is provided for vibration stabilization in a first range of the frequency band to be stabilized and the at least one inner axis of rotation stabilization is provided for vibration stabilization in a second range in the frequency band to be stabilized. The outer gimbal mount and the inner gimbal mount are embodied as mechanically rigid constructions which transmit vibrations in the frequency band to be stabilized essentially without damping.

Various embodiments of the present disclosure provide a helicopter-mediated system and method for launching and retrieving an aircraft capable of long-distance efficient cruising flight from a small space without the use of a long runway.