초록 ▼

A system for detecting the status of a tube for fuel transfer. It includes a nozzle for a telescoping tube employed in air to air refueling and transfer of fuel on a tanker aircraft with a system that detects the status of the connection of the nozzle with respect of a receptacle in a receiving airc

A system for detecting the status of a tube for fuel transfer. It includes a nozzle for a telescoping tube employed in air to air refueling and transfer of fuel on a tanker aircraft with a system that detects the status of the connection of the nozzle with respect of a receptacle in a receiving aircraft, the system detecting the characteristics of the status of the connection of the nozzle in the receptacle by direct measurement of parameters in the nozzle itself of the tanker aircraft.

대표청구항 ▼

1. A system employed in air for air refueling and transfer of fuel from a tanker aircraft to a receiving aircraft, said system comprising: a telescoping tube having a first end configured to connect to said tanker aircraft;a nozzle coupled to a second end of the telescoping tube and configured to co

1. A system employed in air for air refueling and transfer of fuel from a tanker aircraft to a receiving aircraft, said system comprising: a telescoping tube having a first end configured to connect to said tanker aircraft;a nozzle coupled to a second end of the telescoping tube and configured to connect to a receptacle in said receiving aircraft; anda detection system that detects a status of a connection of said nozzle with respect to said receptacle in the receiving aircraft, wherein said detection system including a detection device provided in said nozzle and which detects characteristics of the status of the connection of said nozzle in said receptacle by direct measurement of only parameters in the nozzle itself of the tanker aircraft. 2. A system in accordance with claim 1, wherein said detection device comprises a device deployed in the nozzle that detects insertion of said nozzle into said receptacle of the receiving aircraft, said device comprising a coil and an electronic sensor that measures a value or a variation of an inductance in a coil. 3. A system in accordance with claim 2, wherein the coil is excited from voltage with a frequency higher than 20 KHz, having an amplitude of less than approximately 3 V. 4. A system in accordance with claim 1, further comprising a proximity sensor attached to a body of said nozzle that measures a displacement of a piston with a ramp to close or open a cutoff valve of nozzle. 5. A system in accordance with claim 4, further comprising a magnet attached to the piston with the ramp, wherein said magnet functions together with said proximity sensor. 6. A system in accordance with claim 5, wherein said magnet is a magnet made of rare earth materials and said sensor is a Hall effect sensor. 7. A system in accordance with claim 1, wherein said nozzle further comprising at least one measuring device and a sensor placed in at least one of a plurality of latches of the nozzle such that triggers of the receptacle act on the measuring device when the nozzle is inserted into the receptacle then activating the sensor for the measuring device. 8. A system in accordance with claim 7, wherein the measuring device comprises an articulated piece on a same axis as latches of nozzle. 9. A system in accordance with claim 7, wherein the sensor comprises a microswitch with a hermetically sealed capsule for working in an explosive atmosphere. 10. A system in accordance with claim 1, wherein said nozzle further comprising at least a force sensor placed underneath at least one latch of the nozzle that close over triggers of the receptacle so as to measure a force exercised by at least one trigger of the receptacle on said at least one latch. 11. A system in accordance with claim 1, wherein said nozzle further comprising a device that detects whether some latches of the nozzle that close on some triggers of the receptacle are found free or blocked with respect to said triggers of the receptacle. 12. A system in accordance with claim 11, wherein the device comprises an electronic device that excites a solenoid with which an inductance is measured to determine a displacement of at least one piston with a ramp shaped cam of a blocking mechanism that frees opening or closing of triggers. 13. A system in accordance with claim 12, further comprising a sensor integrated into said nozzle that detects the displacement of the piston with the ramp shaped cam of a blocking mechanism that opens or closes triggers. 14. A tanker aircraft that comprises a system in accordance with claim 1. 15. A system in accordance with claim 1, wherein said detection device is provided only in the nozzle.