A communication system for equipment in airborne operations comprising: at least one first double transceiver and at least one second double transceiver, wherein the at least one first double transceiver is configured to send data to the at least one second double transceiver in two redundant main channels and wherein the data to be sent through each redundant main channel is first compared with each other so as to ensure that the data sent through a first main channel is the same data sent through a second main channel.

An assembly having an aircraft door and auxiliary equipment. The aircraft door and the auxiliary equipment are connected by a flexible deformable bellows having creases. The door comprises a passing through hole and a support joinable to the first end of the bellows. The auxiliary equipment comprises a support joinable to the second end of the bellows and a projecting part. The projecting part is configured to have elevation movement and/or azimuth movement, and the projecting part crosses the interior of the bellows and the hole of the door and protrudes out of the door. At both ends of the bellows a clamp joins and tightens each end of the bellows with the corresponding support. There is a fixed joint between the first end of the bellows and the door and a movable joint between the second end of the bellows and the auxiliary equipment.

A refueling system has a vehicle having a fuel tank connected to a deployable fuel hose, an end effector having controlled flight, the fuel hose connected at an end away from the first vehicle, through the end effector to a fuel connector under the end effector, a second vehicle having a fuel tank coupled through a pumping apparatus to a fueling port on an acquisition apparatus adapted to acquire the end effector and connect the fueling port and the fuel connector of the end effector, and control circuitry enabling controlled flight of the end effector, wherein the end effector is controlled to be acquired by the acquisition apparatus to couple the fuel connector with the fueling port and fuel is provided from the fuel tank of one of the vehicles to the fuel tank of the other of the vehicles through the pumping apparatus.

An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system.

An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system.

Examples of a refueling device for use in in-flight refueling operation are provided. In at least one example the refueling device includes a body, a boom member and a spatial control system. The body is configured for being towed by a tanker aircraft in a forward direction via a fuel hose at least during in-flight refueling operation, the body having a body longitudinal axis and a neutral point. The boom member is carried by the body. The boom member has a fuel delivery nozzle, the fuel delivery nozzle being configured for selectively engaging with a fuel receptacle in a receiver aircraft to enable fuel to be transferred from the fuel hose to the receiver aircraft during such in-flight refueling operation. The spatial control system is configured for selectively providing stability and control to the refueling device. At least during refueling operation the fuel delivery nozzle is longitudinally forward of the neutral point.

A receiver surge test tool (STT) assembly, system and method for receiver surge pressure testing. The receiver STT assembly has a receiver surge test tool (STT) configured to simulate surge pressure conditions of a receiver aircraft, and to measure one or more surge pressures generated when receiving a fuel flow of fuel from a refueling source during the receiver surge pressure testing that is ground based. The receiver STT has a pipe manifold structure with inlet port(s), outlet port(s), and one or more flow lines disposed therebetween. Each flow line includes a flow meter, a pressure transducer, a shutoff valve having varying valve close rates, and a manual back pressure valve. The receiver STT assembly has a control system for controlling open and close positions of the shutoff valve, and the receiver STT, and has a data system for collecting and recording data generated during the receiver surge pressure testing.

The invention is a watercraft to aircraft refueling system (“WARS”). A WARS is a refueling system based from a watercraft, such as a surface ship or submarine. A WARS would typically include an elevation apparatus to lift a refueling hose above the water. The elevation apparatus can compose a lifting or swiveling mechanism. In some embodiments both a lifting and swiveling mechanism is used. The WARS lifts the refueling hose above the water, allowing an aircraft to engage with the WARS. The refueling hose may also include a telescoping mechanism or a rotor apparatus or a pressurized water nozzle system to elevate the refueling hose and assist in engaging a WARS with an aircraft.

The invention is a watercraft to aircraft refueling system (“WARS”). A WARS is a refueling system based from a watercraft, such as a surface ship or submarine. A WARS would typically include an elevation apparatus to lift a refueling hose above the water. The elevation apparatus can compose a lifting or swiveling mechanism. In some embodiments both a lifting and swiveling mechanism is used. The WARS lifts the refueling hose above the water, allowing an aircraft to engage with the WARS. The refueling hose may also include a telescoping mechanism or a rotor apparatus or a pressurized water nozzle system to elevate the refueling hose and assist in engaging a WARS with an aircraft.

A system and method for Automated Aerial Refueling (AAR) may combine unrelated capabilities to provide a high integrity solution to boom manipulation and insertion to couple with a receiver receptacle. Precise positioning systems on each aircraft coupled via data link provide a high integrity relative positioning solution generating a requisite integrity for positioning yet insufficient for boom insertion. High definition cameras onboard the tanker provide multi-wavelength remote vision digital images used to identify the boom fitting as well as the receptacle. Combined with boom position information from the tanker, the system determines pixel position inputs from stereo digital images to precisely identify the boom and receptacle and manipulate the boom to insert the boom fitting into the receptacle. Constant camera generated feedback and updated relative positioning alerts the system and disconnects the boom should the receiver aircraft stray outside the proper position.