초록

A wing-to-body fairing for aircraft is formed from a sandwich structure having integrated vibration damping.

대표청구항 ▼

1. A vibration damped aircraft fairing, comprising: first and second skins;a honeycomb core sandwiched between the first and second skins and having cells defining a plurality of cavities within the core; and,a vibration damping filler in the cells for damping vibrations in the fairing, the filler c

1. A vibration damped aircraft fairing, comprising: first and second skins;a honeycomb core sandwiched between the first and second skins and having cells defining a plurality of cavities within the core; and,a vibration damping filler in the cells for damping vibrations in the fairing, the filler comprising a foam and a plurality of individual particles, the filler movable when vibrated to dissipate vibrational energy within the fairing. 2. The aircraft fairing of claim 1, wherein the filler fills approximately 60 to 90 percent of the volume of the cells. 3. The aircraft fairing of claim 1, wherein each of the first and second skins are composite laminates. 4. The aircraft fairing of claim 3, wherein the second skin includes a face sheet impregnated with a highly damped epoxy resin, the face sheet more flexible than the second skin. 5. The aircraft fairing of claim 1, wherein the individual particles include at least one of: volcanic ash,plastic,perlite,sodium-potassium, andaluminum-silicate. 6. The aircraft fairing of claim 1, wherein the foam has a density between approximately 5 and 9 pounds per cubic feet. 7. The aircraft fairing of claim 1, wherein the individual particles each has a size in a range of approximately 1 to 300 microns. 8. The aircraft fairing of claim 1, wherein the honeycomb core is formed from at least one of: aluminum,Nomex®,metal,cotton, anda composite. 9. The aircraft fairing of claim 1, wherein the panel is configured to form a win-to-body fairing. 10. A method of reducing noise in an aircraft cabin caused by vibration of a wing-to-body fairing on the aircraft, comprising: providing a cavity within the fairing; andintroducing a vibration damping filler into the cavity for dissipating vibration energy in the fairing so as to partially fill the cells of the honeycomb with a vibration damping foam and a plurality of individual damping particles. 11. The method of claim 10, wherein: providing a cavity within the fairing includes sandwiching an open cell honeycomb between two skins. 12. The method of claim 10, wherein partially filling the cells includes filling approximately 60 to 90 percent of the volume of the cells. 13. A wing-to-body aircraft fairing having vibrations reduced by the method of claim 10. 14. A vibration damped wing-to-aircraft aircraft fairing, comprising: first and second laminated composite skins, one of the skins including a face sheet impregnated with a highly damped epoxy resin, the face sheet more flexible than the one of the skins;a honeycomb core sandwiched between and bonded to the first and second skins and including a plurality of open cells;a damping foam partially filling the cells and having a density between approximately 5 and 9 pounds per cubic feet; and,a plurality of individual damping particles movable within and partially filling the cells,the particle each having a size between approximately 1 and 300 microns, and including at least one of volcanic ash, plastic, perlite, sodium-potassium, and aluminumsilicate, the foam and the particles filling between approximately 60 to 90 percent of the volume of the cells. 15. A method of fabricating a wing-to-body aircraft fairing having reduced vibration, comprising: laying up a composite panel, including sandwiching an open cell honeycomb core between two composite laminate skins and impregnating one of the skins with a high damping resin;partially filling the cells of the core with vibration damping foam;partially filling the cells of the core with vibration damping particles;bonding the core to the skins;forming the layup over tooling into the shape of a fairing; and, curing the formed layup. 16. The aircraft fairing of claim 1, wherein at least one skin comprises carbon fiber. 17. The aircraft fairing of claim 1, wherein the honeycomb core comprises substantially hexagonal cells. 18. The aircraft fairing of claim 1, wherein the particles comprise metallic particles selected from one of iron, steel, lead, zinc, magnesium, copper, aluminum, tungsten, or nickel. 19. The vibration damped wing-to-aircraft aircraft fairing of claim 14, wherein at least one composite skin comprises carbon fiber. 20. The method of claim 11, wherein at least one skin comprises carbon fiber. 21. The method of claim 11 further comprising positioning a face sheet proximate at least one skin, the face sheet more flexible than the skin. 22. The method of claim 15 further comprising positioning a face sheet proximate at least one of the laminate skins, the face sheet more flexible than the at least one of the laminate skins.