CRJ2000 Flight Controls CRJ2000 飞行操纵

航空发表于 2011-5-19 00:12:13

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航空发表于 2011-5-19 00:12:24

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 发表于 2011-6-28 20:34:37

谢谢！看看，学习一下吧

lixy250 发表于 2011-7-13 10:06:39

看看，谢谢

bocome 发表于 2011-7-31 07:10:56

CRJ2000 Flight Controls CRJ2000 飞行操纵

kohn 发表于 2013-12-15 13:50:32

好东西啊，先下载来看看。

ace_hi 发表于 2014-4-3 08:25:18

kankan,:lol:lol

tonyblairer 发表于 2014-5-27 18:20:51

很好的资料，谢谢分享

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CRJ2000 Flight Controls CRJ2000 飞行操纵