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Meeting	ACGS Committee Meeting 105 - Lake Tahoe - March 2010
Agenda Location	5 SUBCOMMITTEE D -- DYNAMICS, COMPUTATIONS, AND ANALYSIS 5.3 Transport Aircraft Rudder Force/Feel System Piloted Simulations
Title	Transport Aircraft Rudder Force/Feel System Piloted Simulations
Presenter	Roger Hoh
Affiliation	Hoh Aeronautics
Available Downloads*	presentation
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Abstract	This work was motivated by several instances of rudder over-control in up-and-away flight in transport aircraft, one of which resulted in loss of the vertical stabilizer and a fatal accident. The objective of this work is to develop rudder control system design criteria to minimize the tendency for over-control in large transport aircraft. Basic rudder control system design and sizing is constrained by the control power required for crosswind landings and directional control following an engine failure on takeoff. Rudder travel is necessarily limited with increasing airspeed so that full travel does not exceed the strength of the vertical stabilizer. Several significantly different methods for reducing rudder travel have been employed by manufacturers of transport aircraft. These rudder-limiting methods are studied in a 2-phase moving base piloted simulation to determine if there is a fundamental property that leads to an increased tendency for over-control. Variations in rudder control system parameters included shape of the force-feel system, breakout, maximum pedal force, maximum pedal travel, rudder control power, and yaw damper mechanization. Results showed that short rudder pedal travel significantly increases the tendency for over-control, whereas the other noted parameters were much less significant. There is evidence that yaw damper design is also critical but more work is required to better understand this. Large forces on the vertical stabilizer are traced to over-control when attempting to augment aileron with rudder. There was no evidence of PIO as a factor.