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(fèi)者

fully aft, the spoilers retract to their -4.5” position and
the stabilizer trailing edges return to the trim position.
This decreasesth e rate of descent.
2.24 AUTOMATIC FLIGHT CONTROL SYSTEM
The AFCS (FO-12) augments the aircraft’s natural
damping characteristics and provides automatic commands
for control of attitude, altitude, heading, and approachm
odes selectedb y the pilot. All AFCS functions
are integrated into the primary flight control system. A
BIT capabilityi s providedt o exercisein -flight monitoring
and to conduct an automatic operational readiness test
for preflight checks. AFCS rates and authorities are
tabulated in Figure 2-67.
2.24.1 Stability Augmentation System. Stability
augmentation is provided for all three aircraft axes
(pitch, roll, and yaw). Control surface commands are
generatedb y the roll, pitch, and yaw computers in response
to inputs from AFCS sensors.
Computer outputs are fed through the flight control
system dual-series actuators that drive the control system
mechanical linkages in series (no stick motion) to
produce surface motion. Stability augmentation is controlled
by the three STAB AUG switches on the upper
half of the AFCS control panel (Figure 2-68). SAS is
engagedb y placing theses witchest o ON during normal
poststart procedures. The PITCH and ROLL STAB
AUG switches are solenoid held and the YAW STAB
AUG switch is a manually operated toggle switch.
PITCH and YAW SAS switches should normally remain
in ON throughout the flight. Roll SAS reduces
departure resistance and shall be placed OFF prior to
conducting maneuvering flight above 15 units AOA.
Pitch and roll SAS axes consist of two redundant channels
that provide fail-safe operation.
Yaw SAS consists of three electronic channels to
provide fail-safe operational capability.
2.24.2 Voltage Monitor Control Unit. TheVhJCU
detects abnormal voltage transients in the aircraft
electrical supply systema ndr educest he voltage to a low
enough level to allow the AFCS to detect it and
disengaget he SAS. If the VMCU detectsa low-voltage
2-109 ORIGINAL
NAVAIR Ql-Fl4AAD-1
Figure 2-67. AFCS Rates and Authorities
condition of 97 volts or less in the ac, phase A supply,
the unit will activate a relay to drop the voltage to zero
and maintain that level for a minimum of 1.25 seconds
plus the duration of the detected low-voltage condition.
Activation of the VMCU because of a low-voltage condition
results in the simultaneous illumination of the
following lights for the duration of the transient:
1. PITCH STAR 1 and 2
2. ROLL STAR 1 and 2
3. YAW STAR OP and OUT
4. SPOILERS
5. HZTAILAUTH
6. RUDDER AU-l-I-I
7. AUTO PILOT
8. MACH TRIM.
2.24.2.1 VMCU Operation. While the VMCU is activated,
all spoilers will be commanded to 4.5”, all SAS
and AFCS ti~ctions will be turned off, and the PITCH and
ROLL STAR AUG switches drop to OFF. When normal
supply voltage is sensed,t he VMCU is deactivateda nd
normal power is restoredto the phaseA bus, all lights will
go out, except the RUDDER AUTH light at low speeds
and the HZ TAIL AUTH light at high speeds,a nd SAS
will be available for the yaw axis since the YAW STAR
AUG switchr emainsO N. SAS operationo f the tenraining
axis will be available when the PITCH and ROLL STAR
AUG switches are set to ON and the illuminated light(s)
will reset with the MASTER RESET pushbutton.
2.24.2.2 VMCU Check. The VMCU is checked
prior to flight during the poststart procedure. The voltage
drop obtained when the emergency generator is
turned off is sufftcient to activate the VMCU and illuminate
the affected caution and advisory lights.
2.24.3 Autopilot. The autopilot is controlled by four
switches on the lower half of the AFCS control panel
(Figure 2-68) and the autopilot reference and nosewheel
steering pushbutton on the stick grip. With all three SAS
axes engaged, autopilot operation is commanded by
placing the ENGAGE/OFF switch to ENGAGE. No
warmup period is requited. The autopilot may be engaged
with the aircraft in any attitude. If, however, aircraft
attitude exceedst i0” in pitch and i60” in roll, the
autopilot will automatically return the aircrafi to these
limits. Normally, IMU is the prime reference and attitude
heading reference system (SAHRS) a backup.
2.24.3.1 AFCS Series Actuator. The AFCS series
actuatori s a dual-channels etvoactoatort hat is controlled
and commanded by the AFCS computers to
provide a low-authority input that can be mechanically
overridden by the pilot. Each servo of the dual actuator
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：F-14D 飛行手冊 Flight Manual 1(115)