CRJ2000 Flight Controls CRJ2000 飞行操纵

航空

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航空

FLIGHT CONTROLS
CRJ 2000
Conventional
 Control wheels
 Control columns
 Rudder pedals
 Control surfaces actuated
 Hydraulically or
 Electrically
 Divided into “primary” and “secondary”
CRJ
PRIMARY FLIGHT CONTROLS
ELEVATORS
RUDDER
SPOILERONS AILERONS
Spoilerons: roll assist
SECONDARY
FLIGHT CONTROLS
STABILIZER
TRIM
GROUND
SPOILERS FLAPS
FLIGHT
SPOILERS
AILERON &
RUDDER TRIMS
Note: CRJ 200 does not have leading edge flaps.
Only the 700.
SECONDARY
FLIGHT CONTROLS
Inboard & outboard flaps
CRJ 200 FLIGHT CONTRLS
Spoilerons act in conjunction
with ailerons to provide
roll control < 300 kts
Systemredundancy
Hydraulic logic
 Each aileron & spoileron powered by 2 hydraulic systems
 Rudder & elevators power from all 3 hydraulic systems
 Critical: takeoff
ELEVATOR
STABILIZER
RUDDER
CLEAN WING…NO LE DEVICES
GROUND LIFT DUMP
LANDING FLAPS
Primary Flight Controls
 Mechanically controlled….. hydraulically
actuated
 Except Spoilerons…..electrically
controlled….hydraulically actuated
 Hydraulic actuation through Power Control
Units (PCU’s)
 Gust dampening through PCU’s
See Handout
MONITOR
ED2
EICAS primary page, status page
and FLT CONTROL synoptic page
LIFT DUMP DEPLOYED
Ground spoilers only deploy
on the ground as part of
the ground lift dumping
function to slow the aircraft
during landing.
Spoilerons & flight spoilers
also deploy on the ground
to assist in the ground lift
dumping function.
Roll Disconnect
Mechanism
ROLL (lateral) CONTROL
on
Flight
Spoileron
Flight Spoiler
Left and Right Control Paths
Spoileron ECU’s
Torque Tube Interconnect
Disconnect
ROLL DISCONNECT
HANDLE
In event of an
aileron control jam
Roll Disconnect and SELECT
 Left and right controls
separated.
 Capt controls left aileron
and right spoileron.
 FO controls right aileron
and left spoileron.
 ROLL SELECT pushed
on unjammed side gives
control over both
spoilerons.
PCU RUNAWAY
TENSION REGULATOR/
BREAKOUT DEVICE
AUTOMATIC SPOILERON SHIFT
TO GOOD AILERON
AILERON TRIM
ELECTRICALLY BIASES
AILERON ARTIFICIAL FEEL
AND CENTERING MECHANISM
YOKE DOES NOT MOVE
Electrically operated
Manually controlled
Using trim selector on center pedestal
Spring loaded to center position
RUDDER
CONTROL
CAPT AND FO PEDALS MOVE TOGETHER
NO DISCONNECT CAPABILITY
BREAKOUT MECHANISM
assisted by
YAW DAMPERS
TRIM
Rudder Trim
Electrically operated/Manually controlled
Rudder trim does not displace pedals.
Yaw dampers controlled by
Flight Control Computers (FCC)
At least one Yaw Damper must be
engaged for autopilot operation
NL (nose left)
NR (nose right)
YD1 / YD2: yaw damper channel
ENGAGE one or other
PITCH CONTROL
LEFT AND RIGHT ELEVATORS
2 separate control systems
CAPT LEFT…..FO RIGHT
TORQUE TUBE
DISCONNECT

PITCHTRIM
angle of incidence positioned by screw jack
DUAL ELECTRIC JACKSCREWS
2 electric motors
PITCHTRIM
PRIORITY
 PILOT TRIM
 AUTOPILOT TRIM
 MACH TRIM
Compensates for Mach Tuck
above .4 M
Max 250 kts w/oMach Trim
stab trim disconnect
red button (top-back)
nose up/down
black button
AT LEAST ONE TRIM CHANNEL
REQUIRED
3 TRIM RATES
.5/SEC: MANUAL or AP w/Flaps Moving
.1/SEC: AP w/o Flaps Moving
.03-.06/SEC: Mach Trim engaged
SECONDARY
FLIGHT CONTROLS
STABILIZER
TRIM
GROUND
SPOILERS FLAPS
FLIGHT
SPOILERS
AILERON &
RUDDER TRIMS
Note: CRJ 200 does not have leading edge flaps.
Only the 700.
SECONDARY
FLIGHT CONTROLS
FLAPS
DOUBLE-SLOTTED FOWLER
INDBOARD/OUTBOARD
FLAP
CONTROL
LEVER
Flaps
 Electric (flap electronic control unit: FECU)
 Flaps have 5 positions
 0 degrees
 8 degrees
 20 degrees
 30 degrees
 45 degrees Land
 Gates at 8 Deg
and 20 Deg
Takeoff

FLAP OPERATION
 2 Electric Motors drive single flap gearbox
 Single motor failure causes flaps to move at half speed
 FLAPS HALF SPEED status page of EICAS & on FLT CONTROLS
synoptic page
 Vfe: 8/20 Deg……215 KIAS
30 Deg……185 KIAS
45 Deg……170 KIAS
 Flaps down displayed on ED1 (similar to Gear display)
Overspeed clacker will sound
if too high for setting
Primary
page
Flap position bar
and readout no.
FLIGHT SPOILERS
 Single panel on each wing
 Electrically controlled
 Hydraulically actuated
 Provide speed control in the air
and Lift Dump on the ground
 Extends from 0 to 50 degrees.
 8 Detents
 IF above 79% N1 with spoilers
deployed a caution message will
appear.
Extension prohibited with flaps greater than 30 degrees
Use above 15,000 ft prohibited.
En route use prohibited.
Four spoiler panels ea. wing
one spoileron (outer panel)
one flight spoiler
two ground spoilers (inner)
Ground Lift Dumping
 Deployment of: spoilerons, flight spoilers, ground spoilers
 Deploy to destroy lift and create drag during
landings and aborted takeoff’s
 Normally automatic upon touch down on basis of:
 thrust lever position; engine N1 signal; radio altitude; wheel
speed; PSEU/WOWconditions
 Retract upon advancing the throttles
GROUND
LIFT DUMPING
GROUND
SPOILERS
SPOILERONS
AND
FLIGHT SPLRS
ARMING SWITCH = ARMED
THRUST LEVERS = IDLE
WEIGHT ON WHEELS = ON GROUND
WHEEL SPEED = SPUN UP
RADIO ALTIMETER = < 7 FT.
GLD ARMING
 GLD SWITCH – AUTO (automatic arming)
 Arms ground lift dumping system automatically when airplane is in
landing configuration
 N1 above 79%
MANUAL ARM
AUTO
DISARM
GLD DEPLOY LOGIC
 L and R Thrust Levers Idle
and
 Flt and Gnd Spoilers (2 of 3)
1. L or RWOW
2. RA below 5 ft
3. Wheel speed above16 kts
 Spoilerons
1. L and RWOW
and (1 of 2)
2. RA below 5 ft
3. Wheel speed above 16 kts
BOTTOM LINE: IDLE POWER—BOTH WHEELS ON THE GROUND
GLD AUTO RETRACTION
 L or R Thrust Lever below 79% N1
 Wheel speed below 45 kts for 10 seconds
 WOWgreater than 40 seconds
BOTTOMLINE: SLOWED DOWN, LOW
POWER
 If go-around is attempted, either Thrust Lever
advanced above idle auto retracts GLD
 ALSO: MANUAL DISARM with GLD Switch
 STICK SHAKER. The entire control wheel
column will shake when approaching a stall
 STICK PUSHER. The control wheel will push
itself forward to prevent the stall.
STALL
PROTECTION
PILOT INTERFACE
STALL PROTECTION COMPUTER (SPC)
AOA information
and Airspeed
to compute the stall angle trip points
Inputs:
STALL STALL
Arming of mechanism
BOTH pilot’s & copilot’s
Visual
Aural
Feel (stick shaker)
STALL PROTECTION
FEATURES
 APPROACHING
STALL
Continuous Ignition
Stick Shaker
Activated
AP Disengaged
 JUST PRIOR TO
STALL
StallWarbler
STALL Lights
Pusher Activated
STICK SHAKER
STICK PUSHER
AP/SP DISC
Flight Control Summary
 Aircraft control still possible with
Control jam
Electrical failure
Failure of any two hydraulic systems
One or both engines fail
 Aircraft equipped to handle wide airspeed range
Double-slotted Fowler flaps for T/O & Land
Spoilerons reduce wing stress and adverse yaw
Flight spoilers control speed in descent
Ground lift dump destroys lift and enhances braking
The
End

ericgyf

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lixy250

看看，谢谢

bocome

CRJ2000 Flight Controls CRJ2000 飞行操纵

kohn

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ace_hi

kankan,

tonyblairer

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