Electromagnetically heating a conductive medium in a composite aircraft component
Nondestructive examination is performed on a composite aircraft component including a composite body and a conductive medium. The conductive medium is substantially more conductive than the composite body. The nondestructive examination includes applying an electromagnetic field that penetrates the composite body and heats the conductive medium, and creating a thermal image of the conductive medium to reveal conductivity information about the conductive medium.
1. A method of performing nondestructive examination of a composite aircraft component including a composite body and conductive medium, the conductive medium being substantially more conductive than the composite body, the method comprising:
applying an electromagnetic field that penetrates the composite body and heats the conductive medium; and
creating a thermal image of the conductive medium to reveal conductivity information about the conductive medium.
2. The method of claim 1 , wherein the electromagnetic field induces eddy currents in the conductive medium.
3. The method of claim 2 , wherein the electromagnetic field is applied by a coil, and wherein excitation frequency of the coil is in the range of 100 kHz to 400 kHz.
4. The method of claim 1 , wherein a directional electromagnetic field is applied to heat the conductive medium.
5. The method of claim 1 , wherein the aircraft component includes at least two layers of conductive media at different depths, and wherein frequency of the electromagnetic field is varied to heat a selected layer.
6. A method of repairing a composite aircraft structure that carries an electromagnetic effect protection article, the method comprising:
applying a patch to a damaged area of the electromagnetic effect protection article, the patch including a conductive layer that is electrically connected to the electromagnetic effect protection article;
applying the electromagnetic field to an area that encompasses the patch and creating a thermal image of the area, the field applied and the image created according to claim 1 ; and
examining the thermally imaged area to identify any electrical discontinuities between the patch and the electromagnetic effect protection article.
7. A method of performing non-destructive examination of a circuit that is embedded in a composite aircraft component, the method comprising:
applying the electromagnetic field to an area that encompasses the circuit and creating a thermal image of the area, the field applied and the image created according to claim 1 ; and
examining the thermally imaged area to determine conductivity information about the embedded circuit.
8. The method of claim 7 , wherein examining the thermally imaged area includes examining thermal gradients to identify discontinuities in circuit traces.
9. The method of claim 7 , wherein examining the thermally imaged area includes examining trace thickness to evaluate a process used to manufacture circuit traces in the circuit.
10. The method of claim 7 , wherein examining the thermally imaged area includes determining a resistivity profile of traces in the circuit.
11. The method of claim 1 , wherein creating the thermal image includes taking a difference of images to highlight features of interest.
12. The method of claim 1 , further comprising creating eddy currents in the composite body to heat the body; wherein the thermal image also identifies defects in the composite body.
13. The method of claim 1 , further comprising using a mathematical model of the component to optimize the heating and imaging.
14. A method comprising performing nondestructive examination on a composite aircraft component including a fiber-based composite body and a layer containing metal, including:
applying an electromagnetic field to an area of interest on the component, the electromagnetic field inducing eddy currents in the layer; and
creating a thermal image of the area to reveal conductivity information about the metal in the layer.
15. The method of claim 14 , wherein the layer is an upper layer that provides EME protection for the component; wherein the component also includes a lower layer containing metal traces, and wherein eddy currents are selectively induced in each layer and a thermal image of each layer is created.
16. The method of claim 14 , wherein the layer is part of a patch, the patch repairing a damaged area of the component, the layer adhered to an electromagnetic effect protection article of the component; and wherein the thermal image of the area indicates whether the layer makes a good electrical connection with the electromagnetic effect protection article.
17. The method of claim 14 , wherein the layer includes metal traces of an embedded circuit; and wherein the thermal image of the area indicates conductivity information about the traces.
18. A method of performing non-destruction examination of metal traces that are embedded in a composite aircraft component, the method comprising:
applying an electromagnetic field to an area over the traces, the electromagnetic field inducing eddy currents in the traces;
creating a thermal image of the area; and
examining the thermal image to determine conductivity information about the traces.
19. The method of claim 18 , wherein examining the thermally imaged area includes examining thermal gradients to identify discontinuities in the traces.
20. The method of claim 18 , wherein examining the thermally imaged area includes examining trace thickness to evaluate a process used to manufacture the traces.