Aircraft reinforcing structure
An object of the present invention is to prevent accumulation of moisture which has entered inside a honeycomb sandwich panel used for a stressed-skin structure of an aircraft. A reinforcing structure includes an outer panel constituting an outer shell of a tailplane and a honeycomb sandwich panel reinforcing the outer panel. The honeycomb sandwich panel includes a honeycomb core having a plurality of cells, an outer skin joined on the front side of the honeycomb core and disposed on the side of the outer panel, and an inner skin joined on the back side of the honeycomb core and disposed on the inner side of the tailplane. The inner skin has drainage channels formed therein through which each of the plurality of cells communicates with the outside of the honeycomb sandwich panel.
1. A reinforcing structure of an aircraft comprising an outer panel and a honeycomb sandwich panel, the outer panel constituting an outer shell of an airframe of a wing of the aircraft, the honeycomb sandwich panel reinforcing the outer panel, wherein
the outer panel is composed of an upper outer panel and a lower outer panel disposed on the lower side of the upper outer panel,
the upper outer panel and the lower outer panel are each provided with the honeycomb sandwich panel,
the outer panel is a component separate from the honeycomb sandwich panel,
the honeycomb sandwich panel includes:
a honeycomb core having a plurality of cells;
an outer skin disposed on an inner side of the outer panel; and
an inner skin defining an inner side of the reinforcing structure,
wherein the outer skin of the honeycomb sandwich panel is disposed on the inner side of the upper outer panel or the inner side of the lower outer panel and the inner skin of the honeycomb sandwich panel is disposed away from the upper outer panel and the lower outer panel,
the honeycomb core disposed between the outer skin and the inner skin, the outer skin joined on a front side of the honeycomb core and the inner skin joined on a back side of the honeycomb core, and
the inner skin has drainage channels formed therein through which each of the plurality of cells communicates with an outside of the honeycomb sandwich panel and the outer skin is free of drainage channels.
2. The reinforcing structure according to claim 1 , wherein the drainage channels are holes and each hole corresponds to one of said plurality of cells and penetrates the inner skin in a thickness direction.
3. The reinforcing structure according to claim 1 , wherein the drainage channels are slits which are formed by disposing strip-shaped inner skins at intervals and formed across a plurality of the cells.
4. The reinforcing structure according to claim 1 , wherein the size of the drainage channels are varied among the cells.
5. The reinforcing structure according to claim 1 , wherein the drainage channels corresponding to the lower outer panel has opening dimensions more reduced than those of the drainage channels corresponding to the upper outer panel.
6. The reinforcing structure according to claim 1 , wherein the inner skin is formed from a moisture permeable fiber material and the drainage channels are formed throughout an entire surface of the inner skin.
7. An aircraft comprising the reinforcing structure according to claim 1 .
8. The reinforcing structure according to claim 1 , wherein the outer skin is a component separate from the outer panel.
9. The reinforcing structure according to claim 1 , wherein the drainage channels are configured such that moisture having entered inside of the honeycomb sandwich panel is discharged through the drainage channels to the outside of the honeycomb sandwich panel.
10. The reinforcing structure according to claim 1 , wherein both the outer skin and the inner skin are composed of fiber reinforced plastics.
11. The reinforcing structure according to claim 1 , wherein the wing is a main wing or a tailplane of the aircraft.