1、深航機務培訓中心民航維修專業英語27 FLIGHT CONTROL制作人：鄭得如審核人：孔玲紅課件版權歸深航機務培訓中心所有Description of Primary Flight Controls1Electrical Flight Control System32Power Supply33GeneralPrinciple Roll Control Yaw Control Pitch Control based on ELAC and SEC combine the roll rate control, turn coordination and Dutch roll damping f

2、unction aileron and 2 spoilers used for load alleviation hydromechanical keep the aircraft in flight during a temporary complete loss of electrical powersome rudder control functions are achieved by FAC based on ELAC and SEC closed loop control of the load factor provide flight envelope protectionTh

3、e roll control is achieved by one wing tip aileron augmented by four spoilers on each wing Aileron Manually control：side stick controller Automatically control: autopilot or load alleviationEach aileron can be powered by two servocontrols signalled by two ELACs.ELAC 1 & ELAC 2 active standby (dampin

4、g mode) fail active fail fail both in damping mode Spoiler Manual control/ Automatic control Each spoiler is controlled by one servocontrol signalled from the SEC 1,2 or 3.FailureResultElectricalThe associated surface is hydraulically held downHydraulicThe servocontrol is hydraulically locked in one

5、 directionBothThe symmetrical surface is automatically inhibitedTheir functions roll spoiler (2 to 5) speedbrake (2 to 4) load alleviation (4 and 5) ground spoiler (1 to 5)The pitch control is achieved by two mechanically independent elevators andthe trimmable horizontal stabilizer (THS). Elevator M

6、anual control: side stick controller Automatic control: autopilot Each elevator can be driven by two electrohydraulic servocontrols signalled by ELACs or SEC 1 or SEC 2.SituationsResultsNormalELAC 2 active, ELAC 1 standbyHigh load-factor demandOne servocontrol may stall, the second one operatesELAC

7、2 failsELAC 1 controls, then SEC 2, SEC 1Electrical control lossThe servocontrol are automatically switched to a centering mode and hold the surface in the neutral positionHydraulic supply lossDamping mode automatically engaged THS Manual control: handwheels Automatic control THS is moved and held b

8、y a THS actuator which is normally driven by 3 electrical motors. One motor is operative at a time and the other 2 are in stand-by. Motor 1 is controlled by ELAC 2, motor 2 by ELAC 1 or SEC1, motor 3 by SEC 2. Overriding mechanism The yaw control is mainly achieved by rudder.Rudder The rudder is act

9、uated by 3 servo controls which is signalled from the pedals. Manual control/ Automatic control Electrical trim actuator two yaw damper electrohydraulic servoactuators travel limitation unit Controlled by FAC 1, FAC 2 is in standby. spring rod and ressure relief valveGeneralPrinciple Roll Control Ya

10、w Control Pitch Control based on ELAC and SEC combine the roll rate control, turn coordination and Dutch roll damping function aileron and 2 spoilers used for load alleviation hydromechanical keep the aircraft in flight during a temporary complete loss of electrical powersome rudder control function

11、s are achieved by FAC based on ELAC and SEC closed loop control of the load factor provide flight envelope protection The roll and pitch controls are based on two different types of digital computers.（P107, general principle）Base on 基于，以為依據Useful Expressions定語從句 The roll control of the aircraft is a

12、chieved by one wing tip aileron augmented by four spoilers on each wing.（P107，aileron） 飛機的橫滾控制是由翼尖的副翼實現的，由各機翼上的四個擾流板進行輔助。 （which is）augmented by .省略引導詞的定語從句 In the event of a hydraulic failure, the servocontrol is hydraulically locked in one direction to prevent the surface from raising. （P107, spoi

13、ler）In the event of 萬一，倘若，如果發生Prevent from doing 防止發生，保護免受傷害，阻止 An overriding mechanism gives the priority to the mechanical control over the electrical control.（107，THS) overriding mechanism超控裝置 give the priority to 優先，以為主Description of Primary Flight Controls1Electrical Flight Control System32Powe

14、r Supply33 The Electrical Flight Control System (EFCS, includes the ELACs, the SECs, the Flight Control Data Concentrators (FCDCs) and vertical accelerometers.EFCS 電子飛行控制系統FCDC飛行控制數據集中器Control law: normal, alternate, direct lawRoll normal law: aileron, spoiler 2-5, rudderRoll direct law: aileron, sp

15、oiler 2-5Alternate yaw control: direct control of rudder roll and yaw controlPitch normal law: elevator, THSPitch alternate law: elevator, THS if operativePitch direct law: elevator pitch controlPosition of spoiler 2 to 4 speedbrake controlGround spoiler controlAutomatic full deployment of all spoil

16、ers at touch downAileron and spoiler 4 & 5 flap and slat control load alleviation This (Load alleviation) is the control of theailerons and spoiler surfaces 4 and 5, based on thevertical load factor to minimize the structural loads on the wing caused by gusts.（P110）減載功能是基于垂直負載系數，對副翼和4、5號擾流板進行控制，減少由風

17、引起的、作用在大翼上的結構負載。Useful Expressions The laws are reconfigured to keep the loadalleviation capability should an aileron or spoilersurface become inoperative, or operates at areduced maximum rate, or in the event of a doublefailure of accelerometers.Should 虛擬語氣，if Removal of the pitch trim control locking tool. 拆卸俯仰配平控制鎖工具。 Installation of the flap/slat cont