曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
the EADI, see figure 24-21. The azimuth and elevation deviation bars are referenced to the velocity
vector. When the waterline symbol is displayed, the deviation bars are referenced to it. As shown, the
deviation bars are deflected full scale and the aircraft is below glide slope and to the left of course. The
azimuth bar is deflected full scale for azimuth deviations of ±6° to ±20°. The elevation bar is deflected
full-scale down for elevation deviations of 1.4° to 20°, and full-scale up for deviations of -1.4° to -3°.
If a valid azimuth or elevation signal is not received by the ICLS, the corresponding bar is not
displayed.
ICLS steering is automatically provided when the ACL mode is selected and valid ICLS steering
signals are received.
24.6 DATA LINK SYSTEM
All information on the data link system, except for the automatic carrier landing mode, is contained
in A1-F18EA-TAC-100. For typical Automatic Carrier Landing procedures, refer to Chapter 8.
24.6.1 Automatic Carrier Landing Mode. The system for automatic landing of aircraft onto the
aircraft carrier deck is comprised of the AN/SPN-42 or AN/SPN-46 installed aboard the carrier and
Automatic Carrier Landing (ACL) equipment installed in the aircraft. The aircraft data link system is
the ACL component over which steering commands are received from the carrier for guidance of the
aircraft.
A1-F18EA-NFM-000
VII-24-52 ORIGINAL
The data link automatic carrier landing (ACL) mode is available only when the NAV master mode
is selected. The ACL steering commands may be coupled to the flight control computer for fully
automatic approaches to touchdown, or the pilot may elect to use the steering displays for a manually
controlled landing. The traffic control (T/C) mode is a submode of ACL. The T/C mode provides data
link heading commands to aid the pilot in reaching the marshal point and/or it may be used for
azimuth alignment from marshal until ACL acquisition. These heading commands can be coupled to
the flight control computer for automatic lateral axis control or can be used for manual steering aids.
Figure 24-20. ICLS Initialization
A1-F18EA-NFM-000
VII-24-53 ORIGINAL
Figure 24-21. ICLS Steering
A1-F18EA-NFM-000
VII-24-54 ORIGINAL
Two uplinked control messages (label 5 and label 6) are uniquely addressed to a specific aircraft and
received by the data link for ACL mode (and T/C submode) control and display. The label 5 message
is used only for T/C mode, while both label 5 and label 6 are required for ACL modes 1, 1A, and 2
control and display. The contents of the uplinked label 5 and label 6 messages follows:
Label 5 Message
Command Altitude
(feet)
Displayed on SA display.
Command Airspeed
(knots)
Displayed on SA display.
Command Rate of
Descent
(feet per minute)
Displayed on SA display.
Command Heading Displayed on SA and HUD.
Group 1 Discretes ACL RDY, CMD CNT, LND CHK, NOT
CMD, W/O, and CHG CHNL.
Group 2a Discretes Monitor Altitude and Altitude Change
Warning Receipt of either discrete causes the Command
Altitude and Command Rate of Descent to be
underlined on the SA display.
Group 2b Discretes Monitor Speed and Speed Change Warning.
Receipt of either discrete causes the Command
Airspeed to be underlined on the SA display.
Group 2c Discretes ADJ A/C, VOICE and 10 SEC.
Label 6 Message
Vertical Glide Slope Error Used for data link HUD situation display.
Lateral Glide Slope Error Used for data link HUD situation display.
Mode Status Discrete Indicates that uplinked longitudinal and lateral
axes commands may be used for mode 1 approach.
Longitudinal Axis Command
(altitude rate in feet/second)
Used by FCS for longitudinal axis control.
Lateral Axis Command
(roll angle in degrees)
Used by FCS for lateral axis control.
The ground station also periodically uplinks two universal test messages (UTM-3A and UTM-3B).
These two messages have a canned constant content and carry a universal address, rather than being
addressed uniquely to a controlled aircraft, as are the label 5 and label 6 messages. During ACL mode
A1-F18EA-NFM-000
VII-24-55 ORIGINAL
test, the data link is commanded to accept these two UTM as part of the determination of onboard
ACL capability.
24.6.1.1 ACL Mode Displays. The ACL mode displays consist of the SA display on the DDI and the
data link situation display on the HUD. The following paragraphs contain a general description of the
displays related to the ACL mode. A more explicit definition of the utilization of these displays is
presented in ACL Mode Operation, this chapter.
24.6.1.1.1 SA Display. Figure 24-22 shows the ACL and T/C information which may be displayed on
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
NATOPS Flight Manual 飞行手册 2(109)
