초록 ▼

Embodiments of an aerodynamic structural insert frame comprise a leading edge, a trailing edge opposite the leading edge, and at least one cavity between the leading edge and trailing edge, wherein the aerodynamic structural insert frame is configured to deflect upon activation by an external stimul

Embodiments of an aerodynamic structural insert frame comprise a leading edge, a trailing edge opposite the leading edge, and at least one cavity between the leading edge and trailing edge, wherein the aerodynamic structural insert frame is configured to deflect upon activation by an external stimulus; at least one deformable buckling member extending the distance between opposite edges of the cavity, wherein the deflection of the aerodynamic structural insert frame is configured to trigger deflection of the deformable buckling member; a pivot region; and at least one stopper bar attached to and extending from one edge of the cavity a distance less than the distance between opposite edges of the cavity, wherein the stopper bar is configured to stop the deflection of the aerodynamic structural insert and the buckling member when the stopper bar strikes an opposite edge of the cavity.

대표청구항 ▼

1. An aerodynamic structural insert comprising: an aerodynamic structural insert frame having a leading edge, a trailing edge opposite the leading edge, and at least one cavity between the leading edge and trailing edge, wherein the aerodynamic structural insert frame is configured to deflect upon a

1. An aerodynamic structural insert comprising: an aerodynamic structural insert frame having a leading edge, a trailing edge opposite the leading edge, and at least one cavity between the leading edge and trailing edge, wherein the aerodynamic structural insert frame is configured to deflect upon activation by an external stimulus;at least one deformable buckling member extending the distance between opposite edges of the cavity, wherein the deflection of the aerodynamic structural insert frame is configured to trigger deflection of the deformable buckling member;a pivot region; andat least one stopper bar attached to and extending from one edge of the cavity a distance less than the distance between opposite edges of the cavity, wherein the stopper bar is configured to stop the deflection of the aerodynamic structural insert and the buckling member when the stopper bar strikes an opposite edge of the cavity. 2. An aerodynamic structural insert of claim 1 wherein said deflection occurs at a first predetermined amount of said external stimulus, and a return to an original shape occurs at a second predetermined amount of said external stimulus. 3. An aerodynamic structural insert of claim 2 wherein said second predetermined amount of said external stimulus is less than said first predetermined amount of said external stimulus. 4. An aerodynamic structural insert of claim 2 wherein said deflection is a nonlinear shape change, the non-linear shape change being a stepwise shape change. 5. An aerodynamic structural insert of claim 2 wherein said external stimulus is a wind gust, sustained high wind speed, sustained high relative air velocity, or turbulence. 6. An aerodynamic structural insert of claim 2 further comprising at least one attachment component configured to facilitate coupling to an aerodynamic structure. 7. An aerodynamic structural insert of claim 1 further comprising a skin surface disposed about the aerodynamic structural insert frame. 8. An aerodynamic structural insert of claim 7 wherein said skin surface is a pre-strained deformable composite. 9. An aerodynamic structural insert of claim 7 wherein said skin surface comprises shape memory polymer. 10. An aerodynamic structural insert of claim 7 wherein said skin surface comprises a high-strain fabric-reinforced composite. 11. An aerodynamic structural insert of claim 1 wherein the buckling member is selected from the group consisting of a polymer, fiber reinforced polymer composite, engineered plastic, and metal. 12. An aerodynamic structural insert of claim 1 wherein said aerodynamic structural insert is installable on a wind turbine blade, aircraft wing, or helicopter rotor. 13. An aerodynamic structural insert of claim 1 further comprising a sliding structure which is slideable with the deflection of the buckling member. 14. An aerodynamic structural insert of claim 13 wherein the sliding structure comprises a receiving notch and a bar which is slideable within the receiving notch upon deflection of the buckling member. 15. An aerodynamic structural insert of claim 1 wherein the aerodynamic structural insert frame comprises at least one distributed honeycomb disposed between the leading and trailing edge. 16. An aerodynamic structural insert of claim 15 wherein the honeycomb comprises aluminum. 17. An aerodynamic structural insert of claim 15 wherein the aerodynamic structural insert frame comprises ribs disposed between the leading edge and the trailing edge.