Particle-filled wing-to-body fairing and method for reducing fairing vibrations
A wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in an aircraft, spacecraft, or vehicle may include a honeycomb center having a cavity which is at least partially filled with particle material.
1. A fairing structure for reducing noise due to fairing structure vibrations in at least one of an aircraft and a spacecraft comprising:
said fairing structure disposed between a body of said at least one of an aircraft and a spacecraft and an airfoil projection extending from said body, said fairing structure attached to said body only over an area substantially adjacent to said airfoil;
a honeycomb center comprising a cavity which is at least partially filled with particle material; and
a plurality of layers surrounding the honeycomb center.
2. The structure of claim 1 wherein the fairing structure is a wing-to-body fairing.
3. The fairing of claim 1 wherein the cavity comprises an open cell pattern at least partially filled with the particle material.
4. The fairing of claim 1 wherein the particle material comprises at least one of Volcanic Ash, Plastic, Perlite, Sodium-Potassium, and Aluminum-Silicate.
5. The fairing of claim 1 wherein the particle material comprises a plurality of particles, wherein each particle has a size in a range of 1 to 300 micro meter.
6. The fairing of claim 1 wherein the particle material fills in a range of 60 to 90 percent of the cavity.
7. The fairing of claim 1 wherein the honeycomb center comprises at least one of Aluminum, Nomex, Metal, Cotton, and a Composite.
8. The fairing of claim 1 wherein the fairing structure is attached to at least one of an aircraft and a spacecraft for reducing fatigue and noise.
9. The fairing of claim 1 wherein the particle material is moveably disposed within the cavity to transform kinetic energy into heat in order to reduce noise and vibrations in the frequency range of less than 400 Hz.
10. The fairing of claim 1 wherein the plurality of layers comprise Fiberglass layers.
11. The fairing of claim 1 wherein between two to five layers surround the honeycomb center.
12. The fairing of claim 1 wherein the fairing structure is at least one of angled and curved.
13. A method of reducing fairing vibrations in at least one of an aircraft and a spacecraft comprising:
providing a wing-to-body fairing comprising a honeycomb center having a cavity;
at least partially filling said cavity with particle material;
surrounding the honeycomb center with a plurality of layers; and
attaching said wing-to-body fairing to a wing and a body of at least one of an aircraft and a spacecraft in order to reduce fairing vibrations, said fairing attached between said wing and said body, said fairing structure attached to said body only over an area substantially adjacent to said airfoil.
14. The method of claim 13 wherein the layers are made of Fiberglass.
15. The method of claim 13 wherein between two to five layers enclose the honeycomb center.
16. The method of claim 13 wherein the provided wing-to-body fairing is at least one of angled and curved.
17. The method of claim 13 further comprising the step of attaching the honeycomb center to the plurality of layers.
18. The method of claim 17 wherein the step of attaching the honeycomb center to the plurality of layers comprises adhering the honeycomb center to the plurality of layers.
19. The method of claim 13 wherein the cavity comprises an open cell pattern, and the step of at least partially filling said cavity with the particle material comprises filling in a range of 60 to 90 percent of the cavity with the particle material.
20. The method of claim 13 wherein the particle material comprises at least one of Volcanic Ash, Plastic, Perlite, Sodium-Potassium, and Aluminum-Silicate.
21. The method of claim 13 wherein the particle material comprises a plurality of particles, wherein each particle has a size in a range of 1 to 300 micro meter.
22. The method of claim 13 wherein the step of attaching said wing-to-body fairing to the wing and to the body comprises at least one of adhering and fastening.
23. The method of claim 13 further comprising the step of moving the particle material within the cavity to transform kinetic energy into heat to reduce wing-to-body vibrations in said at least one aircraft and spacecraft.
24. The method of claim 23 wherein the reduced wing-to-body vibrations have a frequency of less than 400 Hz.
25. The method of claim 13 further comprising the step of moving the particle material within the cavity to transform kinetic energy into heat to reduce fatigue and noise in said at least one aircraft and spacecraft.