Multi-frequency Helmholtz resonator system

1. An inlet duct for an aircraft, comprising:

an interior surface of at least one side of the inlet duct;

a plurality of resonator chambers coupled with the interior surface and configured to dampen sound, the plurality of resonator chambers comprising:

a first chamber comprising a first longitudinal portion and a second longitudinal portion, the first longitudinal portion and the second longitudinal portion defining a first interior space, the first and second longitudinal portions coupled by a first bend region; and

a second chamber comprising a third longitudinal portion and a fourth longitudinal portion, the third longitudinal portion and the fourth longitudinal portion defining a second interior space, the third and fourth longitudinal portions coupled by a second bend region;

wherein the first longitudinal portion is parallel to and shorter than the third longitudinal portion, the second longitudinal portion is parallel to and shorter than the fourth longitudinal portion;

wherein the first chamber is nested within the second chamber,

wherein the first interior space has a first volume and the second interior space has a second volume different than the first volume.

2. The inlet duct of claim 1 , wherein a length of the first longitudinal portion is different than a length of the second longitudinal portion and a length of the third longitudinal portion is different than a length of the fourth longitudinal portion.

3. The inlet duct of claim 1 , wherein the first longitudinal portion is half as long as the second longitudinal portion.

4. The inlet duct of claim 1 , wherein the first and second longitudinal portions of the first chamber are at an angle of approximately 90 degrees.

5. The inlet duct of claim 1 , wherein a first end of the first chamber is substantially flush with a second end of the second chamber.

6. The inlet duct of claim 5 , wherein a third end of first chamber is substantially flush with a fourth end of the second chamber.

7. The inlet duct of claim 1 , wherein the first chamber is nested within the second bend region of the second chamber.

8. The inlet duct of claim 7 , wherein the plurality of resonator chambers further comprises a third chamber having a third bend region, the second chamber nested in the third bend region of the third chamber.

9. The inlet duct of claim 1 , wherein the first chamber has a first diameter and the second chamber has a second diameter, the first and second diameters being different.

10. The inlet duct of claim 1 , wherein the first chamber has a first cross-sectional shape and the second chamber has a second cross-sectional shape.

11. The inlet duct of claim 10 , wherein the first cross-sectional shape is different than the second cross-sectional shape.

12. The inlet duct of claim 1 wherein the first and second chamber are part of an array of resonator chamber modules.

13. A resonator array comprising:

a plurality of resonator chambers comprising:

a first chamber including a first longitudinal portion and a second longitudinal portion, the first longitudinal portion and the second longitudinal portion defining a first interior space, the first and second longitudinal portions coupled by a first bend region; and

a second chamber comprising a third longitudinal portion and a fourth longitudinal portion, the third longitudinal portion and the fourth longitudinal portion defining a second interior space;

wherein the first chamber is nested within the second chamber; and

wherein the first interior space has a first volume and the second interior space has a second volume different than the second volume.

14. The resonator array of claim 13 , wherein an overall length of the first chamber is shorter than an overall length of the second chamber.

15. The resonator array of claim 13 , wherein the first chamber has a first diameter and the second chamber has a second diameter, the first and second diameters being different.

16. The resonator array of claim 13 , wherein the first chamber has a first cross-sectional shape and the second chamber has a second cross-sectional shape.

17. The resonator array of claim 16 , wherein the first cross-sectional shape is different than the second cross-sectional shape.

18. The resonator array of claim 13 , wherein the first and second chambers are tuned to dampen different frequencies of sound.

19. A method of manufacturing a sound dampening inlet duct for an aircraft, the method comprising:

inserting a material dispensing head into an inlet duct;

adding material, with the material dispensing head, onto an interior wall of the inlet duct; and

forming, with the added material, an integrated multi-frequency array of interconnected resonator chambers on the interior wall of the inlet duct;

wherein the integrated multi-frequency array of interconnected resonator chambers comprises a plurality of first chambers having a first volume and a plurality of second chambers having a second volume;

each first chamber comprising a first longitudinal portion and a second longitudinal portion, the first longitudinal portion and the second longitudinal portion defining a first interior space, the first and second longitudinal portions coupled by a first bend region; and

each second chamber comprising a third longitudinal portion and a fourth longitudinal portion, the third longitudinal portion and the fourth longitudinal portion defining a second interior space, the third and fourth longitudinal portions coupled by a second bend region; and

wherein the first longitudinal portion is parallel to and shorter than the third longitudinal portion, the second longitudinal portion is parallel to shorter than the fourth longitudinal portion, and each first resonator chamber is nested within a second resonator chamber.

20. The method of claim 19 , wherein the inlet duct is positioned in an aircraft.