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The rudder PCUs also give protection to the rudder control surface against gust loads while the aircraft is on the ground.
RUDDER TRAVEL LIMITER
The rudder travel limiter actuator puts a limit on the movement of the rudder control surface, as a function of airspeed. This
insures that the aerodynamic force on the rudder is not more than the structural limit of the vertical stabilizer. The horizontal-
stabilizer-trim electronic-control unit (HST ECU) controls the movement of the rudder travel limiter-actuator.
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-01-05
PRIMARY FLIGHT CONTROLS (Cont)
CONFIGURATION
CONFIGURATION
WARNING
CONFIG RUDDER TRIM
RUDDER TRIM
YAW DAMPER
RUDDER LIMITER
M
FGC 1 FGC 2
AFT CABLE
QUADRANT AND
FEEL MECHANISM
ARTIFICIAL
FEEL
RUDDER
PEDALS
POWER
CONTROL
UNIT
RUDDER
(POSITION TO EICAS
FLIGHT CONTROL PAGE)
LEGEND
ELECTRICAL
INPUT
MECHANICAL
INPUT
CABLE INPUT
RUDDER
LIMITER
RUDDER
TRIM/YAW
DAMPER
CFO1002002_004
STAB AIL
LWD RWD
RUD
L R
NU
ND
6.6
TRIM
ELEVATOR ELEVATOR
RUDDER
L R
RUD
TRIM
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-01-06 CSP 100-6 REV 1
PRIMARY FLIGHT CONTROLS (Cont)
YAW DAMPER
The yaw damper (YD) provides damping of the aircraft inherent dutch roll characteristic using yaw rate information from
an attitude heading computer. It also provides turn coordination using roll attitude from the attitude heading computer.
Since the yaw damper is installed in a series configuration, yaw damper movement will not move the pilot’s pedals. The
system is mechanically limited to a ±5° of rudder motion.
The yaw damper is active while on the ground if YD has been selected on the flight guidance panel. This allows the flight
crew to observe YD activity for system checks. When the aircraft accelerates above 60 kt IAS, the damping function is
smoothly disabled until weight is off the wheels, at which point it is re-enabled. The yaw damper may be engaged independently
of the autopilot, but if the autopilot is engaged, the yaw damper is automatically engaged.
The functions of the flight guidance YD switch are as follows:
- Engages or disengages the yaw damper, if no detected failures and/or cutout conditions exist
- Disengaging the YD disengages the autopilot
The FGP AP/YD DISC bar is used to the control the YD as follows:
- Provides a positive means of disengagement. The switch is manually positioned and the YD cannot engage when
the bar is in the down (disconnect) position
When the yaw damper channel fails or disconnects, an amber YAW DAMPER FAIL (C) CAS message is displayed.
1
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-01-07
PRIMARY FLIGHT CONTROLS (Cont)
ELEVATORS
Pitch control is provided by the elevators and supplemented by a moveable horizontal stabilizer. Each elevator is hydraulically
powered by two power control units and mechanically controlled via cable runs and quadrants through fore and aft
displacement of either control column. Normally, the control systems are interconnected and there is simultaneous movement
of both elevators. If the elevator split is greater than 7.5°, an ELEVATOR SPLIT (C) CAS message will be displayed.
Elevator position is displayed on the FLIGHT CONTROLS synoptic page. A full-scale deflection of the elevator’s position
indicator corresponds to maximum travel.
Pilot inputs to the elevator are through dual control columns. The control columns are normally connected through a torque
tube, so they rotate in unison.
A control rod transmits pilot commands to the left and right forward quadrants. The left side quadrant assembly includes a
cable interface with the stick pusher servo of the stall protection system.
Separate left and right cable circuits carry the elevator command through the fuselage and terminate at the respective aft
quadrants located in the rear section of the fuselage. The aft quadrants each drive an output rod that is connected to two
control rods in series. The first control rod is connected to a gain changer mechanism, which is a four bar linkage that provides
a non-linear gearing between control column movement and elevator surface. The second rod is connected to a pitch
feel simulator that provides artificial feel forces. Aft of the gain changer mechanism, a series of control rods, levers, and a
torque tube transmit the elevator command to two elevator power control units per elevator.
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