Shielding arrangement for aircraft wiring

Patent metadata

Field	Value
Publication number	US-12037133-B2
Application number	US-202218071862-A
Country	US
Kind code	B2
Filing date	Nov 30, 2022
Priority date	Nov 30, 2021
Publication date	Jul 16, 2024
Grant date	Jul 16, 2024

Abstract

An aircraft is disclosed include wiring configured to carry electrical power; and an electromagnetic shielding arrangement which provides an enclosure around the wiring and is configured to block electromagnetic emissions from the wiring. The electromagnetic shielding arrangement includes a first shield; a second shield which can move relative to the first shield; and a gap between overlapping portions of the shields. The gap is configured to enable air to flow into or out of the enclosure via the gap.

First claim

The invention claimed is:

1. An aircraft comprising: wiring configured to carry electrical power; and
an electromagnetic shielding arrangement which provides an enclosure around the wiring and is configured to block electromagnetic emissions from the wiring, the electromagnetic shielding arrangement comprising: a first shield; a second shield which can move relative to the first shield; and a gap between overlapping portions of the shields, wherein the gap is configured to enable air to flow into the enclosure via the gap and into contact with the wiring, thereby cooling the wiring.

2. An aircraft according to claim 1 , further comprising a propulsion motor, wherein the wiring is configured to carry electrical power for the propulsion motor.

3. An aircraft according to claim 2 , further comprising: a wing; an engine structure including the propulsion motor; and a pylon connecting the engine structure to the wing, wherein the first shield is connected to the pylon and the second shield is connected to the engine structure.

4. An aircraft according to claim 1 , further comprising a rectifier and a generator, wherein the wiring connects the rectifier to the generator, one of the shields is connected to the rectifier, and the other shield is connected to the generator.

5. An aircraft according to claim 1 , wherein the wiring is configured to generate electromagnetic emissions at a signal wavelength; and the gap has a dimension which is less than the signal wavelength, thereby inhibiting transmission of the electromagnetic emissions through the gap.

6. An aircraft according to claim 5 , wherein the gap has a dimension which is less than the signal wavelength at all points.

7. An aircraft according to claim 1 , wherein the gap has a dimension which is greater than 1 mm.

8. An aircraft according to claim 1 , wherein the shields are metallic.

9. An aircraft according to claim 1 , wherein the gap is configured to enable air to flow out of the enclosure via the gap.

10. An aircraft according to claim 1 , wherein the gap comprises a channel with parallel walls.

11. An aircraft according to claim 1 , wherein the wiring comprises first wiring configured to carry electrical power at a first phase; second wiring configured to carry electrical power at a second phase; and third wiring configured to carry electrical power at a third phase.

12. An aircraft according to claim 11 , wherein the first, second and third wiring are surrounded by common harness shielding outside the enclosure; and the common harness shielding is terminated so that the common harness shielding does not extend inside the enclosure.

13. An aircraft according to claim 1 , wherein the wiring is configured to carry electrical power at a first phase; and the aircraft propulsion system further comprises: second wiring configured to carry electrical power at a second phase; and a second electromagnetic shielding arrangement which provides a second enclosure around the second wiring and is configured to block electromagnetic emissions from the second wiring, the second electromagnetic shielding arrangement comprising: a third shield; a fourth shield which can move relative to the third shield; and a second gap between the third shield and the fourth shield, wherein the second gap is configured to enable air to flow into or out of the second enclosure via the second gap, thereby cooling the second wiring.

14. An aircraft according to claim 1 , wherein the wiring is configured to carry electrical power at a power level higher than 100 kW, or at a power level higher than 1 MW.

15. An aircraft propulsion system comprising: a propulsion motor; wiring configured to carry electrical power for the propulsion motor; and an electromagnetic shielding arrangement which provides an enclosure around the wiring and is configured to block electromagnetic emissions from the wiring, the electromagnetic shielding arrangement comprising: a first shield; a second shield which can move relative to the first shield; and a gap between the first shield and the second shield, wherein the gap is configured to enable air to flow into the enclosure via the gap and into contact with the wiring, thereby cooling the wiring.

16. An aircraft according to claim 1 , wherein the gap is configured to enable air to flow out of the enclosure via the gap.

17. An aircraft propulsion system according to claim 15 , wherein the gap is configured to enable air to flow out of the enclosure via the gap.

Assignees

• Airbus Sas

Inventors

• Fulcher Thomas

Classifications

• B64D27/34

  All-electric aircraft · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D45/02 Primary

  Lightning protectors; Static dischargers · CPC title

• B64D27/402 Primary

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• H02K7/1807

  Rotary generators (H02K7/006 takes precedence) · CPC title