Supply system for an aircraft, use of a shielded supply line in an aircraft and an aircraft with a supply system

Patent metadata

Field	Value
Publication number	US-9305731-B2
Application number	US-201314051580-A
Country	US
Kind code	B2
Filing date	Oct 11, 2013
Priority date	Oct 11, 2012
Publication date	Apr 5, 2016
Grant date	Apr 5, 2016

Abstract

A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded.

First claim

The invention claimed is:

1. A supply system for supplying energy in an aircraft, the supply system comprising:
at least one electrical line,
a source of direct electrical current connected to the at least one electrical line,
an electrically conductive shield, and
a detection unit having at least first and second electrical inputs,
wherein the at least one electrical line comprises at least one core connectable to a pole of the current source,
wherein the shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield,
wherein at least one port of the detection unit is connected to the at least one core,
wherein said detection unit is adapted for detecting a differential current over the at least one core or an absolute current between two of the shield, the at least one core and a ground potential;
wherein said detection unit is adapted for generating a warning signal if a predetermined threshold value for the detected current value is exceeded; and
wherein the detection unit is coupled with at least one switch in the at least one core for interrupting the current transferred by the at least one core if the warning signal is generated.

2. The supply system according to claim 1 , wherein a first port of the detection unit is connected to the at least one core at a first longitudinal position and wherein a second port of the detection unit is connected to the same core at a second longitudinal position; and
wherein said detection unit is adapted for detecting a differential current between the first port and the second port.

3. The supply system according to claim 1 , further comprising a ground terminal,
wherein the at least one electrical line comprises at least first and second cores,
wherein the first core is connectable to a positive pole, the second core is connectable to a negative pole and the shield is connectable to the ground terminal; and
wherein one port of the detection unit is connected to at least one of the first and second cores and another port of the detection unit to the ground terminal.

4. The supply system according to claim 1 , wherein the at least one electrical line comprises at least first, second, and third cores for transferring an alternating current with three phases,
wherein the detection unit comprises first, second, and third ports each connected to one of the at least first, second, and third cores, and
wherein the detection unit comprises a summation transformer for detecting a sum over the effective currents of all cores.

5. The supply system according to claim 1 , wherein the source of electrical current comprises a fuel cell with at least one hydrogen line arranged adjacent to the at least one electrical line for providing hydrogen to the fuel cell.

6. The supply system according to claim 5 , wherein the hydrogen line comprises an electrically conducting material and is connected to a ground terminal.

7. The supply system according to claim 1 , wherein the source of electrical current is an alternating current source.

8. An aircraft, comprising at least one electrical load and a supply system, the supply system comprising:
at least one electrical line,
a source of direct electrical current connected to the at least one electrical line,
an electrically conductive shield, and
a detection unit having at least first and second electrical inputs,
wherein the at least one electrical line comprises at least one core connectable to a pole of the current source,
wherein the shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield,
wherein at least one port of the detection unit is connected to the at least one core,
wherein said detection unit is adapted for detecting a differential current over the at least one core or an absolute current between two of the shield, the at least one core and a ground potential;
wherein said detection unit is adapted for generating a warning signal if a predetermined threshold value for the detected current value is exceeded; and
wherein the detection unit is coupled with at least one switch in the at least one core for interrupting the current transferred by the at least one core if the warning signal is generated.

9. The aircraft according to claim 8 , comprising a fuselage at least partially made from a carbon fiber reinforced material.

10. A method for protecting a supply system in an aircraft, comprising the steps of:
providing a supply system with
at least one electrical line connected to a direct current source,
an electrically conductive shield, and
a detection unit having at least two electrical inputs,
wherein the at least one electrical line comprises at least one core connectable to a pole of the current source,

wherein the shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield,
wherein at least one port of the detection unit is connected to the at least one core and wherein at least another port of the detection unit is connected to at least one of the shield and the at least one first core,
detecting a differential current over the at least one core or an absolute current between the shield and a ground potential;
generating a warning signal if a predetermined threshold value for the detected current value is exceeded; and
interrupting the current transferred by the at least one core if the warning signal is generated by at least one switch in the at least one core.

Assignees

• Airbus Operations Gmbh

Inventors

• Schult Jens
• Stengel Torsten
• Fouquet Nicolas

Classifications

• G01R31/008

  on air- or spacecraft, railway rolling stock or sea-going vessels · CPC title

• H01H83/02 Primary

  operated by earth fault currents (H01H83/14 takes precedence) · CPC title

• H02H5/10

  responsive to mechanical injury, e.g. rupture of line, breakage of earth connection · CPC title

• H02H3/16

  responsive to fault current to earth, frame or mass (with balanced or differential arrangement H02H3/26 {; monitoring earth connection H02H5/105}) · CPC title

• H02H3/28

  involving comparison of the voltage or current values at two spaced portions of a single system, e.g. at opposite ends of one line, at input and output of apparatus {(for transformers H02H7/045)} · CPC title