초록 ▼

A system and method to enable natural laminar flow over a fluid-dynamic body using a variable camber Krueger flap is disclosed. A sequence of flap positions is deployed where the variable camber Krueger flap is below and aft of the wing leading edge before reaching a configured takeoff and landing p

A system and method to enable natural laminar flow over a fluid-dynamic body using a variable camber Krueger flap is disclosed. A sequence of flap positions is deployed where the variable camber Krueger flap is below and aft of the wing leading edge before reaching a configured takeoff and landing position. The variable camber Krueger flap is positioned in a high position relative to a wing leading edge when the variable camber Krueger flap is fully deployed.

대표청구항 ▼

1. A flap deployment linkage mechanism comprising: a first linkage assembly operable to couple to a flap assembly and an airfoil, the first linkage assembly comprising: a first drive arm coupled to the airfoil, and operable to rotate in a chord-wise plane;a first drive link coupled to the first driv

1. A flap deployment linkage mechanism comprising: a first linkage assembly operable to couple to a flap assembly and an airfoil, the first linkage assembly comprising: a first drive arm coupled to the airfoil, and operable to rotate in a chord-wise plane;a first drive link coupled to the first drive arm and a trailing end of the flap assembly; anda support arm coupled to a middle link portion of the first drive link and rotatably coupled to the airfoil at a common joint;a second linkage assembly operable to couple to the flap assembly and the airfoil, the second linkage assembly comprising: a second drive arm rotatably coupled to the first drive arm;a rotation control arm coupled to the second drive arm and the airfoil, and operable to control a rotation of the second drive arm;a drive transfer arm coupled to a middle flap portion of the flap assembly and rotatably coupled to the airfoil at the common joint; anda second drive link rotatably coupled to a middle transfer arm portion of the drive transfer arm and to the second drive arm; anda flap linkage assembly operable to couple to the flap assembly, wherein: the flap assembly comprises a bullnose member, a trailing end member, and a flexible surface coupled between the bullnose member and the trailing end member; andthe flap linkage assembly comprises: a flap link coupled to the bullnose member, the trailing end member, and the first drive link;a bullnose link coupled to the bullnose member and the first drive link; anda transfer arm link coupled to the drive transfer arm, and the trailing end member. 2. The flap deployment linkage mechanism of claim 1, wherein the flap assembly is positioned in an elevated position relative to the airfoil to provide foreign object deflection protection for the airfoil. 3. The flap deployment linkage mechanism of claim 1, wherein the transfer arm link is further coupled to the flap link. 4. A method to enable natural laminar flow over a fluid-dynamic body using a variable camber Krueger flap mechanism, the method comprising: deploying a sequence of flap positions where a variable camber Krueger flap is below and aft of a wing leading edge before reaching a configured takeoff and landing position; andpositioning the variable camber Krueger flap in a high position relative to the wing leading edge when the variable camber Krueger flap is fully deployed,wherein: the variable camber Krueger flap comprises a bullnose member, a trailing end member, and a flexible surface coupled between the bullnose member and the trailing end member; andthe variable camber Krueger flap mechanism is coupled to the wing leading edge and to the variable camber Krueger flap, and comprises: a flap link coupled to the bullnose member, the trailing end member, and a first drive link;a bullnose link coupled to the bullnose member and the first drive link;a transfer arm link coupled to a drive transfer arm, the trailing end member;a first drive arm coupled to the wing leading edge, and operable to rotate in a chord-wise plane, wherein the first drive link is coupled to the first drive arm and a trailing end of the flap assembly; anda support arm coupled to a middle link portion of the first drive link and rotatably coupled to the airfoil at a common joint. 5. The method of claim 4, wherein the variable camber Krueger flap mechanism comprises a combined single joint deploying the variable camber Krueger flap. 6. The method of claim 4, further comprising positioning the variable camber Krueger flap in a barndoor position providing an aerodynamically favorable position. 7. The method of claim 4, further comprising positioning the variable camber Krueger flap in a landing position. 8. The method of claim 4, further comprising positioning the variable camber Krueger flap in a take-off position. 9. A flap linkage assembly operable to couple to an airfoil and to a flap assembly comprising a bullnose member, a trailing end member, and a flexible surface coupled between the bullnose member and the trailing end member, the flap linkage assembly comprising: a flap link coupled to the bullnose member, the trailing end member, and a first drive link;a bullnose link coupled to the bullnose member and the first drive link;a transfer arm link coupled to a drive transfer arm, the trailing end member;a first drive arm operable to couple to the airfoil, and to rotate in a chord-wise plane, wherein the first drive link is coupled to the first drive arm and a trailing end of the flap assembly; anda support arm coupled to a middle link portion of the first drive link and rotatably coupled to the airfoil at a common joint. 10. The flap linkage assembly of claim 9, wherein the transfer arm link is further coupled to the flap link. 11. The flap linkage assembly of claim 9, wherein the flap assembly is further coupled to the airfoil. 12. The flap linkage assembly of claim 11, wherein the flap assembly is positioned in an elevated position relative to the airfoil to provide foreign object deflection protection for the airfoil. 13. The flap linkage assembly of claim 9, further comprising: a second linkage assembly operable to couple to the flap assembly and the airfoil, the second linkage assembly comprising:a second drive arm rotatably coupled to the first drive arm;a rotation control arm coupled to the second drive arm and the airfoil, and operable to control a rotation of the second drive arm;a drive transfer arm coupled to a middle flap portion of the flap assembly and rotatably coupled to the airfoil at the common joint; anda second drive link rotatably coupled to a middle transfer arm portion of the drive transfer arm and to the second drive arm. 14. The flap linkage assembly of claim 11, wherein the airfoil comprises a wing and the flap assembly comprises a variable camber Krueger flap. 15. The flap linkage assembly of claim 14, wherein a sequence of flap positions are deployed where the variable camber Krueger flap is below and aft of the wing leading edge before reaching a configured takeoff and landing position. 16. The flap linkage assembly of claim 15, wherein the variable camber Krueger flap is positioned in a high position relative to the wing leading edge when the variable camber Krueger flap is fully deployed. 17. The flap linkage assembly of claim 16, wherein the variable camber Krueger flap enables natural laminar flow over the wing.