초록 ▼

The invention provides in-flight refueling systems with a communication sub-system available in radio silence operations including at least a first digital wireless data link comprising a first RF transceiver and a second RF transceiver coupled, respectively, to first and second antennas located in

The invention provides in-flight refueling systems with a communication sub-system available in radio silence operations including at least a first digital wireless data link comprising a first RF transceiver and a second RF transceiver coupled, respectively, to first and second antennas located in two points inside the boom or the hose of the refueling system or in RF communication with them and connected, respectively, to refueling control units in the tanker aircraft and in the free end of the refueling device by data buses allowing a digital communication between them.

대표청구항 ▼

1. An in-flight refueling system comprising a tanker aircraft, a receiver aircraft, and a refueling device; the tanker aircraft and receiver aircraft comprising fuel tanks; the refueling device comprising an electrical conducting first fuel conduit shielded to ground connected to the fuel tank of th

1. An in-flight refueling system comprising a tanker aircraft, a receiver aircraft, and a refueling device; the tanker aircraft and receiver aircraft comprising fuel tanks; the refueling device comprising an electrical conducting first fuel conduit shielded to ground connected to the fuel tank of the tanker aircraft; the in-flight refueling system comprising a first control unit in the tanker aircraft, a second control unit in a distal end of the first fuel conduit connected to a sensing and managing structure of the in-flight refueling system, and a third control unit in the receiver aircraft; the in-flight refueling system further comprising a communication sub-system including a first digital wireless data link comprising a first RF transceiver and a second RF transceiver coupled, respectively, to first and second antennas located at two points inside the first fuel conduit or in RF communication with the first fuel conduit so that the first fuel conduit can be used as a waveguide for data transmission;the first RF transceiver being connected to the first control unit by a data bus and the second RF transceiver being connected to the second control unit by a data bus for allowing a digital communication between the first and second control units through the first digital wireless data link;the first fuel conduit also comprising first and second RF blocking units at both sides of the first and second antennas for preventing RF propagation outside the first fuel conduit while allowing a fuel flow. 2. The in-flight refueling system according to claim 1, wherein: the refueling device is a boom device deployable from the tanker aircraft and connectable to a receptacle of the receiver aircraft in communication with the fuel tank of the receiver aircraft;the first fuel conduit is a fuel conduit of the boom device. 3. The in-flight refueling system according to claim 1, wherein: the refueling device comprises a probe and drogue device deployable from the tanker aircraft and a probe deployable from the receiver aircraft;the probe and drogue device comprises a hose connected to the fuel tank of the tanker aircraft, a drum to reel the hose and a drogue at a free end of the hose;the probe of the receiver aircraft is connected to the fuel tank of the receiver aircraft;the first fuel conduit is the hose. 4. The in-flight refueling system according to claim 3, wherein the first and second antennas are located at two points inside the hose in, respectively, an end of the hose in the tanker aircraft and in a free end of the hose. 5. The in-flight refueling system according to claim 4, wherein the first antenna is located between the fuel tank of the tanker aircraft and the drum. 6. The in-flight refueling system according to claim 3, wherein the first and/or the second antennas are located in electrical conducting conduits shielded to ground connected to the hose, through a RF non-blocking window, at, respectively, a point of the hose in the end of the hose in the tanker aircraft and/or in the free end of the hose. 7. The in-flight refueling system according to claim 3, wherein the communication sub-system further comprises a second digital wireless data link comprising a third RF transceiver and a fourth RF transceiver coupled to third and fourth antennas located, respectively, inside the hose and the probe of the receiver aircraft or in RF communication with the respective third and fourth antennas so that the probe of the receiver aircraft can be used as a waveguide for data transmission when the probe of the receiver aircraft is connected to the hose; the third RF transceiver being connected to the second control unit by a data bus and the fourth RF transceiver being connected to the third control unit by a data bus;the probe of the receiver aircraft also comprising a third RF blocking unit at one side of the fourth antenna for preventing RF propagation outside the probe of the receiver aircraft;the communication sub-system being arranged for interconnecting the first and second RF data links through the data bus connection between the second and third RF transceivers through the second control unit allowing a digital communication between the first and third control units. 8. The in-flight refueling system according to claim 7, wherein: the third antenna is located inside the hose at a point nearer to the free end of the hose than the second antenna, the second RF blocking unit being located between the second and third antennas;the fourth antenna is located inside the end of the probe in the receiver aircraft. 9. The in-flight refueling system according to claim 7, wherein the third and/or the fourth antennas are located in electrical conducting conduits shielded to ground connected, through a RF non-blocking window, to the hose at a point nearer to the free end of the hose than the second antenna, the second control unit located between them, and/or to a point in the end of the probe in the receiver aircraft. 10. The in-flight refueling system according to claim 1, wherein the RF blocking units comprise metallic honeycomb panels. 11. The in-flight refueling system according to claim 1, wherein the RF transceivers have a maximum emitting power of 5 W/cm2.