Sealant testing for aircraft fuel tanks

Patent metadata

Field	Value
Publication number	US-9939358-B2
Application number	US-201514864469-A
Country	US
Kind code	B2
Filing date	Sep 24, 2015
Priority date	Sep 24, 2015
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

An apparatus and a method for simulating a mechanical stress applied to a sealant from a lightning strike upon an aircraft is provided. The apparatus comprises a specimen, a test fixture, and a capacitor. The specimen comprises an electrically non-conductive sealant for an aircraft fuel tank having a cylindrical shape, and an electrically conductive wire centered axially within the sealant. The test fixture secures the specimen during testing. The capacitor is electrically coupled to the test fixture, and simulates a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant.

First claim

The invention claimed is:

1. A system comprising:
a specimen, comprising:
an electrically non-conductive sealant for a fuel tank of an aircraft having a cylindrical shape; and
an electrically conductive wire centered axially within the sealant;

a test fixture configured to secure the specimen during testing;
a capacitor electrically coupled to the test fixture that is configured to simulate a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant; and
a sensor configured to measure a voltage at the wire over a time interval, to measure the current applied by the capacitor to the wire over the time interval, and to calculate an energy deposited into the sealant when vaporizing the wire based on the voltage, the current, and the time interval.

2. The system of claim 1 wherein:
the wire has exposed portions proximate to ends of the sealant that electrically couple the specimen to the test fixture.

3. The system of claim 1 wherein:
the wire has a diameter between 100 μm and 300 μm.

4. The system of claim 3 wherein:
the wire comprises aluminum.

5. A method, comprising:
fabricating a specimen that comprises an electrically non-conductive sealant for a fuel tank of an aircraft and an electrically conductive wire centered axially within the sealant, wherein the sealant has a cylindrical shape;
securing the specimen in a test fixture;
simulating a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant; and
calculating an energy deposited into the sealant when vaporizing the wire by:
measuring a voltage at the wire over a time interval;
measuring the current applied to the wire over the time interval; and
calculating the energy deposited into the sealant based on the voltage, the current, and the time interval.

6. The method of claim 5 wherein:
the wire has a diameter between 100 μm and 300 μm.

7. The method of claim 6 wherein:
the wire comprises aluminum.

8. The method of claim 5 wherein fabricating the specimen further comprises:
centering the wire axially within a cylindrical cavity of a mold;
filling the cylindrical cavity with liquid sealant; and
curing the liquid sealant.

9. A system, comprising:
a mold for fabricating a specimen, the mold configured to center an electrically conductive wire axially within a cylindrical cavity of the mold, and to receive an electrically non-conductive liquid sealant for a fuel tank of an aircraft within the cylindrical cavity;
the mold configured to separate along a plane through a long axis of the cylindrical cavity to expel the specimen upon curing the sealant;
a test fixture configured to secure the specimen during testing;
a capacitor electrically coupled to the test fixture that is configured to simulate a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant; and
a sensor configured to measure a voltage at the wire or a time interval, to measure the current applied by the capacitor to the wire over the time interval, and to calculate an energy deposited into the sealant based on the voltage, the current, and the time interval.

10. The system of claim 9 wherein:
the wire has a diameter between 100 μm and 300 μm.

11. The system of claim 9 wherein:
the wire has exposed portions proximate to ends of the sealant that electrically couple the specimen to the test fixture.

12. A system comprising:
a specimen, comprising:
an electrically non-conductive sealant for a fuel tank of an aircraft having a cylindrical shape; and
an electrically conductive wire centered axially within the sealant;

a test fixture configured to secure the specimen during testing;
a capacitor electrically coupled to the test fixture that is configured to simulate a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant; and
a sensor configured to measure a surface velocity of the sealant when vaporizing the wire, and to calculate an energy deposited into the sealant when vaporizing the wire based on the surface velocity, a density of the sealant, and a wave speed of the sealant.

13. The system of claim 12 wherein:
the wire has exposed portions proximate to ends of the sealant that electrically couple the specimen to the test fixture.

14. The system of claim 12 wherein:
the wire has a diameter between 100 μm and 300 μm.

15. The system of claim 14 wherein:
the wire comprises aluminum.

16. A method, comprising:
fabricating a specimen that comprises an electrically non-conductive sealant for a fuel tank of an aircraft and an electrically conductive wire centered axially within the sealant, wherein the sealant has a cylindrical shape;
securing the specimen in a test fixture;
simulating a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant; and
calculating an energy deposited into the sealant when vaporizing the wire by:
measuring a surface velocity of the sealant when vaporizing the wire; and
calculating the energy deposited into the sealant based on the surface velocity, a density of the sealant, and a wave speed of the sealant.

17. The method of claim 16 wherein:
the wire has a diameter between 100 μm and 300 μm.

18. The method of claim 17 wherein:
the wire comprises aluminum.

19. The method of claim 16 wherein fabricating the specimen further comprises:
centering the wire axially within a cylindrical cavity of a mold;
filling the cylindrical cavity with liquid sealant; and
curing the liquid sealant.

20. A system, comprising:
a mold for fabricating a specimen, the mold configured to center an electrically conductive wire axially within a cylindrical cavity of the mold, and to receive an electrically non-conductive liquid sealant for a fuel tank of an aircraft within the cylindrical cavity;
the mold configured to separate along a plane through a long axis of the cylindrical cavity to expel the specimen upon curing the sealant;
a test fixture configured to secure the specimen during testing;
a capacitor electrically coupled to the test fixture that is configured to simulate a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant; and
a sensor configured to measure a surface velocity of the sealant when vaporizing the wire, and to calculate an energy deposited into the sealant when vaporizing the wire based on the surface velocity, a density of the sealant, and a wave speed of the sealant.

21. The system of claim 20 wherein:
the wire has a diameter between 100 μm and 300 μm.

22. The system of claim 20 wherein:
the wire has exposed portions proximate to ends of the sealant that electrically couple the specimen to the test fixture.

Assignees

• Boeing Co

Inventors

• Sweet William J
• Housen Kevin R
• Damazo Jason Scott
• Day Arthur C

Classifications

• G01N19/04

  Measuring adhesive force between materials, e.g. of sealing tape, of coating · CPC title

• G01N3/313 Primary

  generated by explosives · CPC title

• B29C33/123

  for centering the inserts · CPC title

• B29C39/10

  incorporating preformed parts or layers, e.g. casting around inserts or for coating articles {(coating a surface by casting in general B05D1/30, B29C39/126 takes precedence)} · CPC title

• G01N2203/006

  Crack, flaws, fracture or rupture · CPC title