A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and compris
A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.
대표청구항▼
1. A method to enable high-lift over a fluid-dynamic body using a variable camber Krueger flap deployment linkage mechanism, the method comprising: deploying a variable camber Krueger flap through a sequence of flap positions including:positioning the variable camber Krueger flap below and aft of a
1. A method to enable high-lift over a fluid-dynamic body using a variable camber Krueger flap deployment linkage mechanism, the method comprising: deploying a variable camber Krueger flap through a sequence of flap positions including:positioning the variable camber Krueger flap below and aft of a wing leading edge; andpositioning the variable camber Krueger flap in a fully deployed position in which at least a portion of the variable camber Krueger flap is above and fore of the wing leading edge;wherein the variable camber Krueger flap has a bullnose member and a trailing end member,wherein the variable camber Krueger flap deployment linkage mechanism comprises a flap linkage assembly coupling a first linkage assembly and a second linkage assembly to the Krueger flap, the flap linkage assembly comprising a flap link coupled to the bullnose member and the trailing end member,wherein the first linkage assembly is coupled to the flap linkage assembly and an airfoil, the first linkage assembly comprising: a first drive arm configured to couple to an actuator coupled to the airfoil, and configured 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 configured to rotatably couple to the airfoil at a rotation joint,wherein the second linkage assembly is coupled to the flap assembly and the first drive arm, the second linkage assembly comprising a drive transfer arm coupled to the flap assembly,wherein the flap link, the first drive link, the first drive arm, and the drive transfer arm form a four bar linkage, andwherein the middle link portion is located between a first end of the first drive link and a second end of the first drive link. 2. The method of claim 1, further comprising positioning the variable camber Krueger flap in a barn door position providing an aerodynamically favorable position. 3. The method of claim 1, further comprising positioning the variable camber Krueger flap in a stowed position. 4. The method of claim 1, wherein the second linkage assembly further comprises: a middle connection segment configured to couple the drive transfer arm to the trailing end of the flap assembly; anda bullnose link configured to couple the drive transfer arm to the bullnose member of the flap assembly. 5. The method of claim 1, wherein the flap assembly comprises the bullnose member, the trailing end member, and a flexible surface coupled between the bullnose member and the trailing end member. 6. The method of claim 1, further comprising positioning the variable camber Krueger flap in the fully deployed position during at least one of takeoff or landing of an aircraft comprising the variable camber Krueger flap. 7. The method of claim 1, further comprising varying a shape of a camber of the variable camber Krueger flap based on a flight condition. 8. The method of claim 7, wherein the flight condition includes at least one condition selected from the group consisting of a takeoff condition, a cruise condition, an approach condition, and a landing condition. 9. The method of claim 7, wherein the flight condition includes at least one condition selected from the group consisting of an aircraft speed, a flight control surface position, an angle of attach, a Mach number, and an altitude. 10. The method of claim 7, wherein the variable camber Krueger mechanism comprises a shape memory alloy that varies the shape of the camber responsive to an ambient temperature. 11. The method of claim 1, further comprising the actuator and the airfoil. 12. The method of claim 1, wherein the variable Krueger flap further comprises: a flap trailing end link coupled to the trailing end member and the flap link, the flap link coupled to the trailing end member via the flap trailing end link,wherein the first drive link coupled at the first end to the first drive arm and coupled at the second end to the trailing end member of the variable camber Krueger flap via the flap trailing end link,wherein the drive transfer arm is coupled to a middle flap portion of the flap link,a middle connection segment coupled to the drive transfer arm and to the flap trailing end link, anda bullnose link configured to couple the drive transfer arm to the bullnose member. 13. A method to enable high-lift over a fluid-dynamic body using a variable camber Krueger flap deployment linkage mechanism, the method comprising: positioning, using the variable camber Krueger flap deployment linkage mechanism, a variable camber Krueger flap in a stowed position below and aft of a wing leading edge;moving, using the variable camber Krueger flap deployment linkage mechanism, the variable camber Krueger flap from the stowed position to a barn door position; andmoving, using the variable camber Krueger flap deployment linkage mechanism, the variable camber Krueger flap from the barn door position to an elevated position in which at least a portion of the variable camber Krueger flap is above and fore of the wing leading edge;wherein the variable camber Krueger flap has a bullnose member and a trailing end member,wherein the variable camber Krueger flap deployment linkage mechanism comprises a flap linkage assembly coupling a first linkage assembly and a second linkage assembly to the Krueger flap, the flap linkage assembly comprising a flap link coupled to the bullnose member and the trailing end member,wherein the first linkage assembly is coupled to the flap linkage assembly and an airfoil, the first linkage assembly comprising: a first drive arm configured to couple to an actuator coupled to the airfoil, and configured 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 configured to rotatably couple to the airfoil at a rotation joint,wherein the second linkage assembly is coupled to the flap assembly and the first drive arm, the second linkage assembly comprising a drive transfer arm coupled to the flap assembly,wherein the flap link, the first drive link, the first drive arm, and the drive transfer arm form a four bar linkage, andwherein the middle link portion is located between a first end of the first drive link and a second end of the first drive link. 14. The method of claim 13, wherein, in the barn door position, the variable Krueger flap is in an aerodynamically favorable position subjected to high loads generated by aerodynamic forces acting on the variable camber Krueger flap. 15. The method of claim 13, further comprising varying a shape of a camber of the variable camber Krueger flap based on a flight condition. 16. The method of claim 15, wherein the flight condition includes at least one condition selected from the group consisting of a takeoff condition, a cruise condition, an approach condition, and a landing condition. 17. The method of claim 15, wherein the flight condition includes at least one condition selected from the group consisting of an aircraft speed, a flight control surface position, an angle of attack, a Mach number, and an altitude. 18. The method of claim 15, wherein the variable camber Krueger deployment linkage mechanism comprises a shape memory alloy that varies the shape of the camber responsive to an ambient temperature. 19. A non-transitory computer-readable medium having stored thereon, program instructions that when executed by a processor, actuate an actuator to cause a variable camber Krueger deployment linkage to perform a set of acts comprising: positioning a variable camber Krueger flap in a stowed position below and aft of a wing leading edge; andmoving the variable camber Krueger flap from the stowed position to an elevated position above and fore of the wing leading edge in the elevated position;wherein the variable camber Krueger flap has a bullnose member and a trailing end member,wherein the variable camber Krueger flap deployment linkage mechanism comprises a flap linkage assembly coupling a first linkage assembly and a second linkage assembly to the Krueger flap, the flap linkage assembly comprising a flap link coupled to the bullnose member and the trailing end member,wherein the first linkage assembly is coupled to the flap linkage assembly and an airfoil, the first linkage assembly comprising: a first drive arm configured to couple to an actuator coupled to the airfoil, and configured 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 configured to rotatably couple to the airfoil at a rotation joint,wherein the second linkage assembly is coupled to the flap assembly and the first drive arm, the second linkage assembly comprising a drive transfer arm coupled to the flap assembly,wherein the flap link, the first drive link, the first drive arm, and the drive transfer arm form a four bar linkage, andwherein the middle link portion is located between a first end of the first drive link and a second end of the first drive link. 20. The non-transitory computer-readable medium of claim 19, wherein the set of acts further comprises: moving the variable camber Krueger flap from the stowed position to a barn door position; andmoving the variable camber Krueger flap from the barn door position to the elevated position,wherein, in the barn door position, the variable Krueger flap is in an aerodynamically favorable position subjected to high loads generated by aerodynamic forces acting on the variable camber Krueger flap.
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이 특허에 인용된 특허 (8)
Sakurai, Seiya; Fox, Stephen J.; Reyes, Victor; Charles, Kara Marie, High-positioned 3-position variable camber krueger.
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