A method of operating an aircraft includes, prior to an in-flight refueling operation, operating the aircraft using fuel from a first fuel tank connected to a fuel delivery system. Subsequently, the in-flight refueling operation is performed over a refueling area while operating the aircraft from another fuel tank, including (1) disconnecting the first fuel tank from the fuel delivery system, (2) jettisoning the first fuel tank, and (3) taking on a replacement fuel tank by (a) capturing the replacement fuel tank from the refueling area and (b) bringing the captured replacement fuel tank onboard the aircraft. The replacement fuel tank is then connected to the fuel delivery system and the aircraft is operated using fuel from the replacement fuel tank.

A system for detecting the tube tip of the flying boom of a tanker aircraft and the receptacle mouth of the receiver for semi-automatic or automatic contact for in-flight aerial refueling with a boom, which does not incorporate signaling devices installed on the receiver aircraft, wherein the system and associated method are robust and ensure that the tanker boom control system is provided with real-time, robust, reliable and simultaneous information, from the tip of the tube thereof and from the receiver aircraft's receptacle mouth, at all times. To this end, the system comprises: 1) light emitters mounted on the tip of the tube thereof, 2) a processing subsystem and 3) two 3D cameras, including a TOF camera or a DOE-type camera (or both), as well as at least one laser L to provide them with their specific functionality.

A system for detecting the tube tip of the flying boom of a tanker aircraft and the receptacle mouth of the receiver for semi-automatic or automatic contact for in-flight aerial refueling with a boom, which does not incorporate signaling devices installed on the receiver aircraft, wherein the system and associated method are robust and ensure that the tanker boom control system is provided with real-time, robust, reliable and simultaneous information, from the tip of the tube thereof and from the receiver aircraft's receptacle mouth, at all times. To this end, the system comprises: 1) light emitters mounted on the tip of the tube thereof, 2) a processing subsystem and 3) two 3D cameras, including a TOF camera or a DOE-type camera (or both), as well as at least one laser L to provide them with their specific functionality.

An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.

An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.

The present invention details a group of focussed means to create points of light of different sizes and colours, that together form figures whose function is to create a sign in front of the eyes of a driver or operator, to provide them with certain information from a remote point. The points of light are created by the ionization of the air in different points in the space where it is desirable to create the sign in question.

The present invention details a group of focussed means to create points of light of different sizes and colours, that together form figures whose function is to create a sign in front of the eyes of a driver or operator, to provide them with certain information from a remote point. The points of light are created by the ionization of the air in different points in the space where it is desirable to create the sign in question.

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

A modular refueling system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular refueling system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules includes an aerial refueling module. The payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the payload modules. The aerial refueling module is insertable into the modular bay to enable the aircraft to provide fuel to recipient aircraft during flight.