M11c9

25問 • 4ヶ月前

ユーザ名非公開

通報

問題一覧

The flight control surfaces on large modern transport aircraft are moved by

Electro-hydraulic Servo actuators.

are fitted on the aircraft wings to help prevent the brakes locking and skidding after touchdown.

Lift dumpers

A series yaw damper moves the

rudder only, when damping Dutch roll.

On some large transport aircraft, when it is close to the stalling angle

slats will extend automatically.

Flutter can be prevented by

mass balance.

Flight control system operation by pneumatic power is sometimes used for

secondary flight controls, such as flaps and slats only.

A 'Q' feel system applied to an elevator system is sensitive to

airspeed and elevator deflection.

Gust locks are most often used on aircraft with control systems which are

cable or push rod operated

Control surface flutter is

most likely to occur at high aircraft speed.

A leading edge devices that extend to the front of the wing for lift augmentation are

slats

Stall strips fitted on the

wing leading edge.

The devices that mounted on trailing edge of wing and deflected to increase curvature of the wing are

flaps.

The control of the aircraft becomes more difficult to operate the system if the aircraft

increase in size and weight.

Elevator trim balances the control forces necessary to maintain the aerodynamic down force on

the tail.

The device that rapidly and noisily vibrates the control yoke

stick shaker.

The wing tip brake can be reseted after energized

only on ground.

Dutch role is movement in

yaw and roll.

To avoid moments bending the root of the wing, the aircraft will be fitted with

symmetrical flight control trim.

During an autopilot controlled turn,

ailerons, rudder and elevators will move.

The purpose of the autopilot servo-motor torque setting is to

prevent control surface runaway

In a fully Fly By Wire Aircraft, ground spoilers are deployed automatically when the aircraft is on ground and

thrust reversers are deployed.

In an autopilot coordinated turn, when the turn angle is reached

the ailerons are faired.

A "series" yaw damper system moves

only the rudder.

The normal law protects the aircraft through the flight envelope , by

Load factor limitation.

Rate Gyro (RG)

(1 degree of freedom) Sensing of aircraft angular rate around all 3 axes (Yaw, Pitch and Roll).

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問題一覧

The flight control surfaces on large modern transport aircraft are moved by

Electro-hydraulic Servo actuators.

are fitted on the aircraft wings to help prevent the brakes locking and skidding after touchdown.

Lift dumpers

A series yaw damper moves the

rudder only, when damping Dutch roll.

On some large transport aircraft, when it is close to the stalling angle

slats will extend automatically.

Flutter can be prevented by

mass balance.

Flight control system operation by pneumatic power is sometimes used for

secondary flight controls, such as flaps and slats only.

A 'Q' feel system applied to an elevator system is sensitive to

airspeed and elevator deflection.

Gust locks are most often used on aircraft with control systems which are

cable or push rod operated

Control surface flutter is

most likely to occur at high aircraft speed.

A leading edge devices that extend to the front of the wing for lift augmentation are

slats

Stall strips fitted on the

wing leading edge.

The devices that mounted on trailing edge of wing and deflected to increase curvature of the wing are

flaps.

The control of the aircraft becomes more difficult to operate the system if the aircraft

increase in size and weight.

Elevator trim balances the control forces necessary to maintain the aerodynamic down force on

the tail.

The device that rapidly and noisily vibrates the control yoke

stick shaker.

The wing tip brake can be reseted after energized

only on ground.

Dutch role is movement in

yaw and roll.

To avoid moments bending the root of the wing, the aircraft will be fitted with

symmetrical flight control trim.

During an autopilot controlled turn,

ailerons, rudder and elevators will move.

The purpose of the autopilot servo-motor torque setting is to

prevent control surface runaway

In a fully Fly By Wire Aircraft, ground spoilers are deployed automatically when the aircraft is on ground and

thrust reversers are deployed.

In an autopilot coordinated turn, when the turn angle is reached

the ailerons are faired.

A "series" yaw damper system moves

only the rudder.

The normal law protects the aircraft through the flight envelope , by

Load factor limitation.

Rate Gyro (RG)

(1 degree of freedom) Sensing of aircraft angular rate around all 3 axes (Yaw, Pitch and Roll).