Variable Speed Flap Retraction and Notification

• US 20090302174A1
• Filed: 10/19/2007
• Published: 12/10/2009
• Est. Priority Date: 12/19/2005
• Status: Active Grant

• Current Assignee: Astronics Advanced Electronic Systems Corporation (Astronics Corporation)
• Original Assignee: Vertical Power, Inc. (Astronics Corporation)
• Inventors: DeVries, Kevin, Dostal, Jake, Ausman, Marc
• Granted Patent: US 8,346,409 B2
• Time in Patent Office: Days
• US Class Current: 244/76.R
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: G01D 2207/10 Displays which are primarily used in aircraft or display aircraft-specific information
• CPC Class Codes: G01D 7/00 Indicating measured values

Abstract

The present invention provides systems and methods for controlling the speed of flap retraction on aircraft, and alerts to the pilot of potentially unsafe flap position. The invention accepts direction from a pilot and senses operation of the aircraft to determine appropriate flap position and flap retraction speed.

Claims

1. A method of controlling flap actuation in an aircraft, comprising:

a. Determining whether a signal to raise the flaps has been supplied, and, if so

b. Determining whether the aircraft engine is operating above a threshold power level, and, if so

c. Raising the flaps at a first rate, and, if not,

d. Raising the flaps at a second rate, greater than the first rate.

10. A method as in claim 1, wherein determining whether the aircraft engine is operating above a threshold power level comprises determining the aircraft engine RPM, the aircraft turbine N1%, the aircraft air speed, the aircraft ground speed, the aircraft fuel supply rate, or a combination thereof.

11. A method as in claim 1, wherein raising the flaps at a first rate comprises supplying a first voltage to an electrical flap actuator, and wherein raising the flaps at a second rate comprises supplying a second voltage to the electrical flap actuator, wherein the second voltage is greater then the first voltage.

12. A method as in claim 1, wherein raising the flaps at a first rate comprises raising the flaps for a first time duration, then hold the flaps substantially immoveable for a second time duration, then raising the flaps for a third time duration.

13. A method as in claim 1, wherein raising the flaps at a first rate comprises supplying hydraulic fluid to a hydraulic flap actuator at a first pressure, and wherein raising the flaps at a second rate comprises supplying hydraulic fluid to the hydraulic flap actuator at a second pressure, wherein the second pressure is greater than the first pressure.

14. A method as in claim 1, further comprising detecting if the flaps are extended beyond a threshold amount, detecting whether the aircraft engine is operating above a threshold power level, and, if both conditions are detected, then communicating an alert to the pilot.

2. A method of communicating an aircraft status to a pilot, comprising detecting if the flaps are extended beyond a threshold amount, detecting whether the aircraft engine is operating above a threshold power level, and, if both conditions are detected, then communicating an alert to the pilot.

3. An apparatus for controlling flap actuation in an aircraft, comprising:

a. A flap actuation system, adapted to move the flaps responsive to control signals;

b. A flap position sensor, adapted to produce a signal representative of the position of the flaps;

c. An engine power sensor, adapted to produce a signal representative of the engine power output;

d. A controller, adapted to accept a “

flaps up”

direction from a pilot, and responsive thereto to supply a control signal to the flap actuation system to raise the flaps at a first rate if the engine power signal indicates an engine power above a threshold and at a second rate, greater than the first rate, if the engine power signal indicates an engine power below the threshold; and

to continue such control signal until the flap position sensor signal indicates that the flaps are in an up position or until the pilot supplies a direction to cease raising the flaps.

4. An apparatus as in claim 3, wherein the direction to cease raising the flaps comprises a “

flaps down”

signal.

5. An apparatus as in claim 3, wherein the engine power sensor is adapted to produce a signal representative of engine RPM, turbine N1%, ground speed, air speed, fuel supply rate, or a combination thereof.

6. An apparatus as in claim 3, wherein the control signal comprises a voltage, and the voltage supplied for the first rate is lower than the voltage supplied for the second rate.

7. An apparatus as in claim 3, wherein the control signal is cycled on and off for the first rate.

8. An apparatus as in claim 7, wherein the control signal is cycled on and off for the second rate, and wherein the ratio of on cycle to off cycle is greater for the first rate than the second rate.

9. An apparatus as in claim 3, wherein the flap actuation system is hydraulic, and wherein the control signal comprises a hydraulic pressure signal that is lesser for the first rate than for the second rate.