An aircraft includes a wing. The wing includes an aileron pivotally connected to a trailing edge of the wing, and a Lam aileron pivotally connected to the trailing edge of the wing. The aircraft includes a motor connected to the Lam aileron and configured to rotate the Lam aileron. The aircraft incl
An aircraft includes a wing. The wing includes an aileron pivotally connected to a trailing edge of the wing, and a Lam aileron pivotally connected to the trailing edge of the wing. The aircraft includes a motor connected to the Lam aileron and configured to rotate the Lam aileron. The aircraft includes a controller configured to detect a deflection of the aileron from a neutral position, calculate a target deflection for the Lam aileron using the deflection of the aileron, and cause the motor to rotate the Lam aileron to the target deflection.
대표청구항▼
1. An aerodynamic control system for roll control of an aircraft around a longitudinal axis of the aircraft, the aerodynamic control system comprising: a wing having a rear portion, the wing having a top surface and a bottom surface;a first aileron pivotally attached to the top surface of the wing a
1. An aerodynamic control system for roll control of an aircraft around a longitudinal axis of the aircraft, the aerodynamic control system comprising: a wing having a rear portion, the wing having a top surface and a bottom surface;a first aileron pivotally attached to the top surface of the wing at the rear portion, the first aileron being configured to rotate upwards from a first aileron neutral position and downwards from the first aileron neutral position;a second aileron pivotally attached to the top surface of the wing at the rear portion, the second aileron being configured to rotate upwards from a second aileron neutral position, but not being able to rotate downwards from the second aileron neutral position;a motor connected to the second aileron and configured to rotate the second aileron;a sensor configured to detect a deflection of the first aileron; anda controller coupled to the sensor and configured to: receive the detected deflection of the first aileron from the sensor,calculate a target deflection for the second aileron using the deflection of the first aileron, andcause the motor to rotate the second aileron to the target deflection. 2. The aerodynamic control system of claim 1, wherein calculating the target deflection includes setting the target deflection of the second aileron equal to the detected deflection of the first aileron. 3. The aerodynamic control system of claim 1, wherein calculating the target deflection includes: when the first aileron is deflected upwards from the first aileron neutral position, setting the target deflection of the second aileron equal to the detected deflection of the first aileron; andwhen the first aileron is deflected downwards from the first aileron neutral position, setting the target deflection of the second aileron to a second aileron neutral position. 4. The aerodynamic control system of claim 1, wherein the controller is configured to determine a speed of the aircraft, and wherein the target deflection of the second aileron is at least partially determined by the speed of the aircraft. 5. The aerodynamic control system of claim 4, wherein calculating the target deflection includes, when the speed of the aircraft is above a threshold, setting the target deflection of the second aileron to a second aileron neutral position. 6. The aerodynamic control system of claim 1, wherein the controller is configured to determine a dynamic pressure of air surrounding the aircraft, and wherein the target deflection of the second aileron is at least partially determined by the dynamic pressure. 7. The aerodynamic control system of claim 1, wherein calculating the target deflection includes applying a scaling factor to the detected deflection of the first aileron. 8. The aerodynamic control system of claim 7, wherein the scaling factor is at least partially determined by a speed of the aircraft. 9. The aerodynamic control system of claim 1, wherein the second aileron extends along about 63% to about 78% of a span of the wing. 10. The aerodynamic control system of claim 1, including a flap panel pivotally connected to the bottom surface of the wing opposite the second aileron. 11. An aircraft, comprising: a wing, the wing including: an aileron pivotally connected to a trailing edge of the wing;a Lam aileron pivotally connected to the trailing edge of the wing;a motor connected to the Lam aileron and configured to rotate the Lam aileron; anda controller configured to: detect a deflection of the aileron from a neutral position of the aileron,calculate a target deflection for the Lam aileron using the deflection of the aileron, andcause the motor to rotate the Lam aileron to the target deflection. 12. The aircraft of claim 11, wherein calculating the target deflection includes setting the target deflection of the Lam aileron equal to the detected deflection of the aileron. 13. The aircraft of claim 11, wherein calculating the target deflection includes: when the aileron is in an up position, setting the target deflection of the Lam aileron equal to the detected deflection of the aileron; andwhen the aileron is in a down or neutral position, setting the target deflection of the Lam aileron to a neutral position of the Lam aileron. 14. The aircraft of claim 11, wherein the controller is configured to determine a speed of the aircraft, and wherein the target deflection of the Lam aileron is at least partially determined by the speed of the aircraft. 15. The aircraft of claim 14, wherein calculating the target deflection includes, when the speed of the aircraft is above a threshold, setting the target deflection of the Lam aileron to a neutral position of the Lam aileron. 16. The aircraft of claim 11, wherein the controller is configured to determine a dynamic pressure of air surrounding the aircraft, and wherein the target deflection of the Lam aileron is at least partially determined by the dynamic pressure. 17. A method for controlling an aerodynamic control system for roll control of an aircraft around a longitudinal axis of the aircraft, the method including: detecting a deflection of a first aileron, the first aileron pivotally attached to a wing of the aircraft, the first aileron being configured to rotate upwards from a first aileron neutral position and downwards from the first aileron neutral position;calculating a target deflection for a second aileron using the deflection of the first aileron, the second aileron being pivotally attached to the wing, the second aileron being configured to rotate upwards from a second aileron neutral position, but not being able to rotate downwards from the second aileron neutral position; androtating the second aileron to the target deflection. 18. The method of claim 17, wherein calculating the target deflection includes setting the target deflection of the second aileron equal to the detected deflection of the first aileron. 19. The method of claim 17, wherein calculating the target deflection includes: when the first aileron is deflected upwards from the first aileron neutral position, setting the target deflection of the second aileron equal to the detected deflection of the first aileron; andwhen the first aileron is deflected downwards from the first aileron neutral position, setting the target deflection of the second aileron to a second aileron neutral position. 20. The method of claim 17, including determining a speed of the aircraft, and wherein the target deflection of the second aileron is at least partially determined by the speed of the aircraft.
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이 특허에 인용된 특허 (4)
Lam Lawrence Y. ; Lam Michael, Aileron for fixed wing aircraft.
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