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drift angles, it flashes rapidly to indicate that it does not accurately indicate flight path (velocity vector
is ²HUD limited²).
With GPS operating, if the INS velocity data becomes unreliable, the mission computer utilizes GPS
information. If INS velocity data becomes unreliable the mission computer utilizes FCC air data
function information and the last available wind data to compute the velocity vector and this degraded
velocity vector is indicated by a slow flashing of the symbol. In the NAV master mode, the velocity
vector may be caged to the vertical center line of the HUD by the cage/uncage switch on the throttle.
When it is caged, a ghost velocity vector is displayed at the true velocity vector position if that position
is more than 2° from the caged position. The flight path/pitch ladder and steering information are
referenced to the caged position. The ghost velocity vector flashes when limited. The flight path/pitch
ladder is referenced to the waterline symbol when the velocity vector is caged.
11. Flight path/pitch ladder. The vertical flight path angle of the aircraft is indicated by the position
of the velocity vector on the flight path/pitch ladder. The horizon and flight path/pitch angle lines
represent the horizon and each 5° of angle between plus and minus 90°. Positive pitch lines are solid
and are above the horizon line. Negative pitch lines are dashed and are below the horizon line. The
outer segments of the lines point toward the horizon. Each line is numbered and the numbers rotate
with the lines so that inverted flight can easily be determined. To aid in determining flight path
angle when it is changing rapidly, the pitch lines are angled toward the horizon at an angle half that
of the flight path angle. For example, the 50° pitch line is angled 25° toward the horizon. In level
flight, the pitch lines are not angled. The zenith is indicated by a circle and the nadir is indicated by
a circle with an X in it. Aircraft pitch angle can be determined by comparing the tops of the altitude
and airspeed boxes (which represent the aircraft waterline) with the pitch ladder when the wings are
level, but the flight path/pitch ladder normally rotates about the velocity vector and determination
of pitch angle may be difficult at high roll angles.
12. Vertical velocity readout. This value is displayed above the altitude box and indicates vertical
velocity in feet per minute. This is displayed in the NAV master mode only. Descent is indicated by
A1-F18EA-NFM-000
I-2-142 ORIGINAL
a minus sign.
13. HUD landing symbology. When any two landing gear are down, the Mach number, g, and peak
g are deleted and an AOA bracket, extended horizon bar, waterline symbol, and energy caret appear.
The center of the AOA bracket represents the optimum approach AOA. The bracket moves lower
with respect to the velocity vector as AOA increases and moves higher as AOA decreases. When the
energy state of the aircraft is in equilibrium, the energy caret points to the ²right wing² of the
velocity vector and the aircraft neither accelerates or decelerates. With an energy deficit, the energy
caret moves lower with respect to the velocity vector and the aircraft decelerates; with excess energy,
the energy caret moves higher and the aircraft accelerates.
14. Waypoint/OAP, mark point, TACAN, or target data. Waypoint/OAP and mark data consists of
range (horizontal), and the steer-to point identifier (W, O, or M) and number located on the lower
right corner of the HUD. TACAN data consists of slant range and a Morse code identifier located
on the lower right corner of the HUD. When a steer-to point is designated, range remains displayed
and the steer-to point identifier changes to TGT.
15. Coupled steering symbology. While coupled steering is engaged CPL SEQ#, CPL WYPT, CPL
TCN, CPL BNK, CPL ASL, CPL HDG, or CPL P/R appears on the right side of the HUD display
above the navigation data.
16. ILS symbology. When ILS steering is selected, an azimuth deviation bar (localizer) and elevation
deviation bar (glideslope) appear on the HUD.
17. ZTOD, LTOD, ET, and CD time. The ZTOD, LTOD, ET, or CD time is displayed on the lower
left corner of the HUD. These timers are mutually exclusive. Only one timer is available for display
on the HUD at a time. When the FIRAMS real time clock power up BIT passes, ZTOD does not need
to be entered, but when the FIRAMS real time clock power up BIT does not pass, ZTOD must be
entered. ET initializes to zero minutes and seconds. CD initializes to six minutes and zero seconds.
18. Command heading marker. When waypoint/OAP or TACAN direct great circle steering is
selected, the command heading marker is displayed just below the heading scale.
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本文链接地址：
NATOPS Flight Manual 飞行手册 1(104)
