曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

Each primary control system consists of cable run circuits connected to quadrants. The
quadrants receive input from primary control command (flight compartment) using
control rod assemblies. The cable circuit output transmits command to the
hydraulically powered primary control surfaces, using control rods and artificial feel
assemblies.
Lateral control is accomplished by a dual mechanical aileron control system
hydraulically powered by two power control units (PCUs) per aileron. Four
multifunction spoilers per side assist the ailerons in roll control (see SPOILER
SYSTEM this chapter). Aileron disconnect is provided for anti-jam protection.
Artificial feel and centering are incorporated within the system.
Pitch control is provided by a dual mechanical elevator control system, hydraulically
powered by two power control units (PCUs) per elevator. Pitch disconnect is provided
for anti-jam protection. Variable pitch artificial feel is provided to vary the load on the
elevator control wheel as a function of airspeed and horizontal trim setting.
Yaw control is provided by means of three hydraulic PCUs to the rudder. Rudder travel
limiting as a function of airspeed is provided to limit loads on the structure. The rudder
system uses dual cable circuits (aft fuselage) to protect the system from effects of
engine rotor burst.
GX_10_001
Aileron
Elevator
Rudder
Aileron
For Training Purposes Only
Sept 04
10-3
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
Flutter damping for the primary flight controls is provided through the PCUs internal
operation. Ground gust damping (gust locks) is provided through PCUs on the
elevators, ailerons and rudder. The PCUs provide gust damping, when the hydraulic
systems are depressurized.
The roll disconnect mechanism allows the flight crew to isolate the left and right
control wheel and cable system from each other. Roll disconnect separates the control
wheel interconnect (torque tube) system. Single side aileron control is then available
(either left or right aileron), using the operable wheel path, along with full
multifunction spoiler control.
Pitch disconnect will operate automatically in the event of a cable jam in one circuit.
When sufficient force is applied, approximately 50 pounds, the roller will ride up on
the cam, allowing the use of the free circuit. Here, however, the disconnect mechanism
does not lock out. The spring-loaded roller continues to ride up and down along the
cam as inputs are provided to the elevator. Therefore, operation of the unjammed
circuit requires the pilot to maintain the disconnect pressure on the column.
GX_10_002
Elevator Aft
Quadrant/Pitch
Feel Units
Rudder
Limiter
Aileron
PCU
Elevator
Autopilot
Servo
Aileron
Trim
Aileron
Autopilot
Servo
Forward
Rudder
Quadrant
Stick
Pusher
Forward Actuator
Aileron
Quadrant
Rudder
Pedal
Aileron Aft
Quadrant/
Artificial Feel
Aileron
PCU’s
Rudder Aft
Quadrant
Rudder
Trim/Yaw
Dampers
Rudder
PCU’s
Elevator
PCU’s
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-4 For Training Purposes Only
Sept 04
SECONDARY FLIGHT CONTROLS
The secondary flight controls consist of the flap/slat system, multifunction spoilers,
ground spoilers and various trim systems.
Two computers (Flight Control Units (FCUs)) provide control to the hydraulically
powered spoiler PCUs and the electrically powered horizontal stabilizer trim actuator.
These computers also control a pitch feel system and rudder travel limiting system.
SPOILER SYSTEM
Eight multifunctional spoiler panels are electrically controlled and hydraulically
actuated by a single PCU on each surface. The multifunction spoilers are used for inflight
operation as roll assistance, symmetrically for proportional lift dump and on
ground for ground lift dumping.
Four ground spoiler panels are electrically controlled and hydraulically actuated by a
single actuator on each surface and are used for ground lift dumping only.
TRIM CONTROL
Lateral trim is accomplished by a dual position switch on the center pedestal that
operates an electric trim actuator located at the aft quadrant. The lateral trim will cause
rotation of the control wheel neutral position.
Directional trim is achieved by a single rotary switch on the pedestal that operates an
electric trim actuator at the summing unit in the vertical fin. Directional trim is
summed into the pilot pedal command, and no pedal displacement occurs.
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰(zhàn)者手冊5(118)