Time domain reflectometry aircraft fuel gauge

Patent metadata

Field	Value
Publication number	US-9567093-B2
Application number	US-201314442966-A
Country	US
Kind code	B2
Filing date	Nov 6, 2013
Priority date	Nov 16, 2012
Publication date	Feb 14, 2017
Grant date	Feb 14, 2017

Abstract

An aircraft fuel tank system comprising an aircraft fuel tank and a time domain reflectometry (TDR) fuel gauge for measuring a filling level of fuel in the aircraft fuel tank. The TDR fuel gauge comprises an electromagnetic signal generator and a cable, the cable comprising a first cable part and a second cable part which are coupled in series to the signal generator. The first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank. The first and second cable parts are arranged such that for at least one filling level the first cable part extends down into the fuel from an ullage space at a first location and the second cable part extends up out of the fuel into an ullage space at a second location which is spaced apart from the first location.

First claim

The invention claimed is:

1. An aircraft fuel tank system comprising an aircraft fuel tank;
and a time domain reflectometry (TDR) fuel gauge installed in the aircraft fuel tank for measuring a filling level of fuel in the aircraft fuel tank, the TDR fuel gauge comprising an electromagnetic signal generator and a cable, the cable comprising a first cable part a second cable part and a third cable part which are coupled in series to the signal generator, wherein:
the first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank;
the first and second cable parts are arranged such that for at least one filling level of the fuel in the fuel tank the first cable part extends down into the fuel from an ullage space at a first location and the second cable part extends up out of the fuel into an ullage space at a second location which is spaced apart from the first location; and
the fuel tank has two opposite side walls and an upper or lower wall extending between the side walls, and each of the first, second and third cable parts of the cable runs substantially along the length of a respective one of the two opposite side walls and the upper or lower wall.

2. The system of claim 1 wherein the first and second cable parts are arranged such that for the at least one filling level the first cable part extends at an acute angle to the horizontal at the first location where it extends down into the fuel and/or the second cable part extends at an acute angle to the horizontal at the second location where it extends up out of the fuel.

3. The system of claim 1 wherein the first cable part runs substantially along the length of respective one of the two opposite side walls of the fuel tank and the second cable part runs substantially along the length of the other of the two opposite side walls or to the upper or lower wall of the fuel tank.

4. The system of claim 3 wherein the second cable part runs substantially along the length of the other of the two opposite side walls of the fuel tank.

5. The system of claim 3 wherein the second cable part runs substantially along the length of the upper or lower wall of the fuel tank, which is adjacent to the respective one of the two opposite side walls of the fuel tank, which it meets at a corner.

6. The system of claim 1 wherein the three cable parts of the cable are attached to the two opposite side walls and to the upper or lower wall.

7. The system of claim 1 wherein the cable further comprises a fourth cable part in series with the signal generator and the first, second and third cable parts of the cable; and the four cable parts of the cable each run along a respective one of the two opposite side walls and the upper and lower walls.

8. The system of claim 1 further comprising a processor arranged to determine a time of receipt of reflected electromagnetic pulses received from the first and second cable parts.

9. The system of claim 1 comprising a further TDR fuel gauge installed in the aircraft fuel tank for measuring a filling level of fuel in the aircraft fuel tank, the further TDR fuel gauge comprising an electromagnetic signal generator and a cable, the cable comprising a first cable part and a second cable part which are coupled in series to the signal generator, wherein the first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank, wherein the first and second cable parts are arranged such that for at least one filling level of the fuel in the fuel tank the first cable part extends down into the fuel from an ullage space at a third location and the second cable part extends up out of the fuel into an ullage space at a fourth location which is spaced apart from the third location, and wherein the third and fourth locations are each spaced apart from the first and second locations.

10. The system of claim 9 wherein the TDR fuel gauge and the further TDR fuel gauge collectively generate three or more fuel level measurements which define a surface which will depend on a volume of fuel in the tank as well as a pitch and roll of the tank relative to the horizontal, and the system further comprises a processor arranged to estimate the volume of fuel in the tank in accordance with the three or more fuel level measurements.

11. An aircraft comprising a system according to claim 1 .

12. The aircraft of claim 11 wherein the fuel tank is a wing tank in a wing of the aircraft.

13. The aircraft of claim 12 wherein the aircraft has a plane of symmetry and at least part of the cable within the wing tank extends away from the plane of symmetry.

14. The aircraft of claim 13 wherein the cable and the wing tank each have a span normal to the plane of symmetry, and the span of the cable is more than 70% of the span of the wing tank.

15. The aircraft of claim 13 wherein the wing tank along with the first and/or second cable part is angled upwardly or downwardly as it extends away from the plane of symmetry.

16. The aircraft of claim 11 wherein the fuel tank has a forward wall and an aft wall, relative to the forward motion of the aircraft, and wherein each TDR fuel gauge passes through the forward wall or the aft wall.

17. A method of measuring a filling level of fuel in an aircraft fuel tank with a time domain reflectometry (TDR) fuel gauge, the TDR fuel gauge comprising a signal generator and a cable, the cable comprising a first cable part a second cable part and a third cable part which are coupled in series to the signal generator, wherein the fuel tank has two opposite side walls and an upper or lower wall extending between the side walls, and each of the first, second and third cable parts of the cable runs substantially along the length of a respective one of the two opposite side walls and the upper or lower wall, the method comprising transmitting an input electromagnetic pulse from the signal generator into the cable; receiving a first reflected electromagnetic pulse from the first cable part where it extends down into the fuel from an ullage space at a first location; receiving a second reflected electromagnetic pulse from the second cable part where it extends up out of the fuel into an ullage space at a second location, and determining a time of receipt of the first and second reflected electromagnetic pulses.

18. The method of claim 17 further comprising receiving a further reflected electromagnetic pulse from the cable where it passes through a transition between water and fuel; and determining a time of receipt of the further reflected electromagnetic pulse.

19. The method of claim 17 further comprising estimating a volume of the fuel in the fuel tank in accordance with the time of receipt of the first and second reflected electromagnetic pulses.

20. A method according to claim 17 for measuring a filling level of fuel in an aircraft fuel tank with the time domain reflectometry (TDR) fuel gauge and a further TDR fuel gauge, the further TDR fuel gauge comprising a signal generator and a cable, the cable comprising a first cable part and a second cable part which are coupled in series to the signal generator, the method comprising for each TDR fuel gauge transmitting an input electromagnetic pulse from the signal generator into the cable; receiving a first reflected electromagnetic pulse from the first cable part where it extends down into the fuel from an ullage space at a third location; receiving a second reflected electromagnetic pulse from the second cable part w

Assignees

• Airbus Operations Ltd

Inventors

• Haskins Richard
• Lam Joseph K-W

Classifications

• B64D37/00

  Arrangements in connection with fuel supply for power plant (refuelling during flight B64D39/00) · CPC title

• B64D37/005 Primary

  Accessories not provided for in the groups B64D37/02 - B64D37/28 · CPC title

• G01F23/284 Primary

  Electromagnetic waves · CPC title

• B64D37/04

  Arrangement thereof in or on aircraft · CPC title

• G01F22/00

  Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for · CPC title