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Flap/slat actuation system for an aircraft

  • US 5,743,490 A
  • Filed: 02/16/1996
  • Issued: 04/28/1998
  • Est. Priority Date: 02/16/1996
  • Status: Expired due to Term
First Claim
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1. In an aircraft having right and left wings extending in opposite directions from a centerline of said aircraft, each of said wings including a flight control panel thereof movable to its respective wing, an actuation system comprising:

  • a) a right wing control panel actuator having a rotatable input for receiving a driving torque;

    said right control panel actuator being operably connected between said right wing and said flight control panel of said right wing for moving said right control panel relative to said right wing when said driving torque is applied to said rotatable input of said right control panel actuator;

    b) a left wing control panel actuator having a rotatable input for receiving a driving torque;

    said left control panel actuator being operably connected between said left wing and said flight control panel of said left wing for moving said left control panel relative to said left wing when said driving torque is applied to said rotatable input of said left control panel actuator;

    c) power drive means operably connected between said rotatable inputs of said right and left control panel actuators for providing driving torque simultaneously to said inputs of said actuators for symmetrically positioning said right and left control panels relative to said right and left wings respectively;

    said power drive means including a power drive unit having a first output operably connected by a right driveline portion of said power drive means to said right control panel actuator, and further having a second output operably connected by a left driveline portion of said power drive means to said left control panel actuator;

    said right driveline portion of said power drive means including a selectively engagable right asymmetry brake disposed between said power drive unit and said right control panel actuator for stopping rotation of said right driveline when said right asymmetry brake is engaged;

    said left driveline portion of said power drive means including a selectively engagable left asymmetry brake disposed between said power drive unit and said left control panel actuator for stopping rotation of said left driveline when said left asymmetry brake is engaged; and

    d) control means operably connected between said control surfaces and said asymmetry brakes for sensing an asymmetry between the positions of the right and left control panels relative to their respective right and left wings, and for engaging said asymmetry brakes when said asymmetry between the positions of the right and left control surfaces exceeds a predetermined maximum allowable value.

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