초록 ▼

A lightning protection system, method and aircraft are provided for reducing the flammability of jet fuel spilled during an in-flight refueling operation between a supplying aircraft and a receiving aircraft. An inert gas is injected adjacent to a refueling interface in order to displace oxygen in t

A lightning protection system, method and aircraft are provided for reducing the flammability of jet fuel spilled during an in-flight refueling operation between a supplying aircraft and a receiving aircraft. An inert gas is injected adjacent to a refueling interface in order to displace oxygen in the fuel-air mixture and thereby reduce the ability of the fuel vapor to ignite upon occurrence of an ignition source such as lightning. The refueling system may comprise a boom or a hose and drogue type device.

대표청구항 ▼

What is claimed is: 1. An airborne refueling system on a refueling aircraft, comprising: a refueling device configured to transport at least two fluids; a deployable duct coupled to the refueling device; a deployable conductor coupled to the end of the deployable duct, the conductor having a connec

What is claimed is: 1. An airborne refueling system on a refueling aircraft, comprising: a refueling device configured to transport at least two fluids; a deployable duct coupled to the refueling device; a deployable conductor coupled to the end of the deployable duct, the conductor having a connector configured for temporary coupling to receiver located on a second aircraft, the conductor further having a fuel duct and a second duct wherein the fuel duct is in fluid communication with the refueling device and extends through the conductor and terminates at an end of the connector wherein the second duct terminates at positions on the fuel duct at injecting ducts, corresponding to a plurality of orifices, the orifices configured to inject an inert gas into the fuel duct; and wherein the plurality of orifices are positioned on a surface of the deployable conductor and adjacent to the connector. 2. The airborne refueling system of claim 1, wherein the second duct is coupled to and is in fluid communication with an inert gas system located in the refueling aircraft and extends within the conductor and terminates at one of said plurality of orifices positioned on the conductor. 3. An airborne refueling system on a refueling aircraft, comprising; a refueling device configured to transport at least two fluids; and a deployable conductor having a cylindrical structure defining a fuel duct extending the length of the conductor having a first end and a second end, and a wall having at least one inert gas duct extending longitudinally and substantially parallel to the fuel duct and terminating at injecting ducts, corresponding to a plurality of orifices located on a surface of the fuel duct; and configured to inject an inert gas into the fuel duct. 4. The airborne refueling system of claim 3 further comprising a plurality of ducts each having a first end located on a plenum, the plenum configured to distribute inert gas from an inert gas storage system to the at least one inert gas duct to the injecting ducts connected to the fuel duct and adapted to inject inert gas directly into the fuel duct. 5. The airborne refueling system of claim 3 further comprising a plenum that is located within the conductor and defines a volume around the perimeter of the fuel duct. 6. The airborne refueling system of claim 3 further comprising a duct extending from an inert gas system to a plenum located within the conductor.