flight_controls_2

flight_controls_2 - General Approach to FCS Actuation...

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General Approach to FCS Actuation System Utilize Experience From F-4 SFCS Program and F15 Force Summing Single-Stage EHSV Failure Monitoring Thin Wing and Vertical Tail Limit Envelope for Aileron and Rudder Actuators Analysis and Simulation Indicated No Carrier Landing Problems With One Aileron or Rudder Inoperative HEH Sept. 2002 21
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Aileron and Rudder Actuator Design Rationale Redundancy Requirement Fail-Operate/Fail-Safe Fail-Safe Defined as Actuator in Flutter Damper Mode Envelope and Weight Penalty Precluded Dual Piston Actuator Study Select Actuator Configuration – Single Piston/Cylinder – Single Electrohydraulic Servovalve (EHSV) – Dual Servo Electronics – Electronic Channel Force Summing in Coils of EHSV Torque Motor – Dual Hydraulic Supply via Upstream Switching Valve HEH Sept. 2002 22
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F/A-18A Aileron Actuator HEH Sept. 2002 23
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F/A18A Stabilator and Trailing Edge Flap Actuator Design Rationale Redundancy for Both Actuators is Two-Fail-Operate/Fail-Safe Fail-Safe for T.E. Flap is Retract to Neutral Fail-Safe for Stabilator is Switch to Mechanical Mode Design Issue - Interface of Quad Electronics With Dual Hydraulics
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flight_controls_2 - General Approach to FCS Actuation...

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