An aircraft wing slat is formed from composite materials using lay-up and vacuum bagging techniques. The slat lay-up comprises a central honeycomb core sandwiched between upper and lower composite skins, a pre-cured spar and pre-cured stiffeners. After the lay-up is cured and removed from a lay-up m
An aircraft wing slat is formed from composite materials using lay-up and vacuum bagging techniques. The slat lay-up comprises a central honeycomb core sandwiched between upper and lower composite skins, a pre-cured spar and pre-cured stiffeners. After the lay-up is cured and removed from a lay-up mold, leading edge strengthening ribs and a preformed composite nose skin are installed to complete the slat.
대표청구항▼
What is claimed is: 1. A wing slat for aircraft, comprising: an upper, composite skin comprising an upper skin forward edge; a lower composite skin wherein the lower skin comprises a downwardly curved forward edge extending forwardly beyond the upper skin forward edge; a central, honeycomb core sec
What is claimed is: 1. A wing slat for aircraft, comprising: an upper, composite skin comprising an upper skin forward edge; a lower composite skin wherein the lower skin comprises a downwardly curved forward edge extending forwardly beyond the upper skin forward edge; a central, honeycomb core section sandwiched between the upper and lower skins; and, a composite nose skin forming the leading edge of the slat and extending between forward edges of the upper and lower skins. 2. The wing slat of claim 1, wherein the upper skin and the central core section are each tapered. 3. The wing slat of claim 1, further comprising a composite spar at the forward end of the central core section and disposed between upper and lower skins. 4. The wing slat of claim 3, wherein the spar has a generally C-shaped cross section. 5. The wing slat of claim 3, wherein the spar include first, second and third legs respectively bonded to the upper skin, the central core section and the lower skin. 6. The wing slat of claim 1, further comprising a plurality of stiffeners secured to the lower skin, the stiffeners being spaced along the length of the slat and extending in a fore-to-aft direction. 7. The wing slat of claim 6, wherein the stiffeners are bonded to the curved forward edge of the lower skin. 8. A composite slat for an aircraft wing, comprising: an upper composite skin comprising an upper skin forward edge; a central, wedge shaped composite core; a lower composite skin having a downwardly curved forward edge extending forwardly beyond the upper skin forward edge; a spar between the upper and lower skins, and disposed forward of the central core; composite stiffeners bonded to the curved forward edge of the lower skin; and, a composite nose skin forming the leading edge of the slat and extending between forward edges of the upper and lower skins. 9. The composite slat of claim 8, wherein the spar is bonded to the upper skin, the lower skin and the central core. 10. The composite slat of claim 8, wherein the central core is wedge shape in cross section. 11. The composite slat of claim 8, wherein the stiffeners are curved and spaced apart along the length of the slat. 12. The composite slat of claim 8, wherein the lower skin extends forwardly beyond the central core, and the stiffeners are disposed between the forward edge of the central core and the forward edge of the lower skin. 13. The composite slat of claim 8, further comprising a plurality of ribs bearing against the lower skin and covered by the nose skin. 14. The composite slat of claim 8, wherein: the spar includes an upper leading edge, and the nose skin includes a trailing edge covering and secured to the leading edge of the spar. 15. A wing slat for aircraft, comprising: an upper, composite skin comprising an upper skin forward edge; a lower composite skin wherein the lower skin comprises a downwardly curved forward edge extending forwardly beyond the upper skin forward edge; a central, honeycomb core section sandwiched between the upper and lower skins; a composite spar at the forward end of the central core section and disposed between upper and lower skins and, a composite nose skin forming the leading edge of the slat and extending between forward edges of the upper and lower skins. 16. The wing slat of claim 15, wherein the upper skin and the central core section are each tapered. 17. The wing slat of claim 15, wherein the spar has a generally C-shaped cross section. 18. The wing slat of claim 17, wherein the spar include first, second and third legs respectively bonded to the upper skin, the central core section and the lower skin. 19. The wing slat of claim 15, further comprising a plurality of stiffeners secured to the lower skin, the stiffeners being spaced along the length of the slat and extending in a fore-to-aft direction. 20. The wing slat of claim 19, wherein the stiffeners are bonded to the curved forward edge of the lower skin. 21. The wing slat of claim 15, wherein: the spar includes an upper leading edge, and the nose skin includes a trailing edge covering and secured to the leading edge of the spar. 22. The wing slat of claim 15, further comprising a plurality of ribs bearing against the lower skin and covered by the nose skin.
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이 특허에 인용된 특허 (5)
Hirahara Makoto,JPX ; Isano Yasuo,JPX ; Shimizu Ryuhei,JPX ; Amaoka Kazuaki,JPX, Composite airfoil structures and their forming methods.
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