A method and apparatus for controlling a movement of a control surface comprises a first linkage system, a second linkage system, and an actuator system. The first linkage system is connected to a first location of a control surface. The second linkage system is connected to a second location of the
A method and apparatus for controlling a movement of a control surface comprises a first linkage system, a second linkage system, and an actuator system. The first linkage system is connected to a first location of a control surface. The second linkage system is connected to a second location of the control surface. The first location is closer to a leading edge of the control surface than the second location. The actuator system is configured to move the first linkage system and the second linkage system.
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1. An apparatus comprising: a first linkage system connected to a first location of a single control surface, wherein the single control surface is connected to a wing of an aircraft, the first linkage system configured to move a leading edge of the single control surface relative to the wing of the
1. An apparatus comprising: a first linkage system connected to a first location of a single control surface, wherein the single control surface is connected to a wing of an aircraft, the first linkage system configured to move a leading edge of the single control surface relative to the wing of the aircraft, and wherein movement of the leading edge of the single control surface relative to the wing of the aircraft by the first linkage system is a fowler motion;a second linkage system connected to a second location of the single control surface, wherein the first location is closer to the leading edge of the single control surface than the second location; andan actuator system configured to move the first linkage system and the second linkage system independently of each other. 2. The apparatus of claim 1, wherein the second linkage system is configured to move a trailing edge of the single control surface. 3. The apparatus of claim 2, wherein movement of the trailing edge by the second linkage system changes an angle of the trailing edge relative to the leading edge. 4. The apparatus of claim 1, wherein the first linkage system and the second linkage system are connected to the wing of the aircraft by the actuator system. 5. The apparatus of claim 1, wherein the actuator system comprises: a first actuator associated with the first linkage system and configured to move the first linkage system to move the single control surface; anda second actuator associated with the second linkage system and configured to move the second linkage system to move the single control surface, wherein the first actuator moves the first linkage system independently of the second actuator moving the second linkage system. 6. The apparatus of claim 1, wherein the actuator system comprises a number of actuators selected from a group comprising at least one of a hydraulic actuator and a rotary actuator. 7. The apparatus of claim 1, wherein the first linkage system is configured to tilt the single control surface. 8. The apparatus of claim 1, wherein the single control surface is selected from a group comprising a flap, an aileron, a rudder, an elevator, a flaperon, a spoiler, and an airbrake. 9. A method for controlling a movement of a single control surface, the method comprising: operating an actuator system associated with the single control surface, wherein the actuator system is configured to move a first linkage system connected to a first location of the single control surface and to move a second linkage system connected to a second location of the single control surface independently of each other, wherein the first location is closer to a leading edge of the single control surface than the second location, wherein the single control surface is connected to a wing of an aircraft; andmoving the single control surface into a position using the actuator system, wherein moving the single control surface into the position using the actuator system comprises moving the leading edge of the single control surface relative to the wing of the aircraft using the first linkage system, and wherein movement of the leading edge of the single control surface relative to the wing of the aircraft by the first linkage system is a fowler motion. 10. The method of claim 9, wherein the step of moving the single control surface into the position using the actuator system further comprises: moving a trailing edge of the single control surface using the second linkage system. 11. The method of claim 10, wherein the step of moving the trailing edge of the single control surface using the second linkage system further comprises: moving the trailing edge of the single control surface using the second linkage system to change an angle of the trailing edge relative to the leading edge. 12. The method of claim 9, wherein the first linkage system and the second linkage system are connected to the wing of the aircraft by the actuator system. 13. The method of claim 9, wherein the actuator system comprises a first actuator associated with the first linkage system and a second actuator associated with the second linkage system and wherein the step of moving the single control surface into the position using the actuator system further comprises: moving the first linkage system using the first actuator to move the single control surface into the position; andmoving the second linkage system using the second actuator to move the single control surface into the position, wherein the first actuator moves the first linkage system independently of the second actuator moving the second linkage system. 14. The method of claim 9, wherein the actuator system comprises a number of actuators selected from a group comprising at least one of a hydraulic actuator and a rotary actuator. 15. The method of claim 9, wherein the step of moving the single control surface into the position using the actuator system further comprises: moving the first linkage system using the actuator system to tilt the single control surface. 16. The apparatus of claim 1, wherein the actuator system comprises a first actuator and a second actuator, wherein the first actuator connects the first linkage system to the wing, and wherein the second actuator connects the second linkage system to the wing. 17. The method of claim 9, wherein the actuator system comprises a first actuator and a second actuator, wherein the first actuator connects the first linkage system to the wing, and wherein the second actuator connects the second linkage system to the wing.
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