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
eyeball-out g threatens aircrew incapacitation.
As yaw rate decreases during recovery from very
high yaw-rate departures (above 100” per second, or
where sustained eyeball-out g is sensed), the aft stick
and full lateral stick recovery controls result in somewhat
different recovery characteristics. If these recovery
controls are maintained below a yaw rate of
approximately 100° per second, large AOA oscillations
may be experienced as well as oscillations in roll and
pitch. The overall recovery may feel very rough and
oscillatory. If these recovery controls are maintained
below approximately 80’ per second, recovery will be
delayed and the potential for yaw rate reversal and progressive
departure in the opposite direction is greatly
increased. For this reason, the control stick which was
maintained at? into the turn should be moved forward
and into the turn when sustained eyeball-out g is no
longer sensed. Further recovery can then be accomplished
as previously described.
ORIGINAL Il.14
NAVAIR 01.FMAAD-1
F-14 DEPARTURE RECOVERIES
AIRCRAFT CONFIGURATION:
(2) FUSELAGE-MOUNTED PHOENIX
(2) PYLON SPARROWS
(2) SIDEWINDERS
(2) 290-GALLON EXTERNAL TANKS
DATE: MAY 1995
DATA BASIS: FLIGHT TEST
STICK FORWARD STICK FULL
FULL LATERAL STICK INTO AND AFT
INTO TURN RUDDER OPPOSITE
RUDDER OPPOSITE ROLL SAS OFF
40
STICK FORWARI
RUDDER
OPPOSITE
0 50 100 150 200
YAW RATE - DEGlSEC
REGION t STICK - FORWARD/NEUTRAL LATERAL
RUDDER-OPPOSITE TURN NEEDLE/YAW
REGION 2 NO RECOVERY:
STICK - INTO TURN NEEDLE,YAW
REGION 3 SUSTAINED EYEBALL OUT G SENSED:
STICK FULL INTO AND AFT, RUDDER OPPOSITE
REQUIRED FOR RECOVERY
Figure 1 l-4. F-14 Departure Recovery Diagram
II-15 ORIGINAL
NAVAIR 0%F14AAD.1
pi&-I
Maintaining aft and lateral stick recovery
controls below approximately 100” per second
yaw rate can result in large AOA excursions
and oscillations in roll and pitch, which
may complicate recognition of recovery
t?om an upright departure and delay recovery.
Maintaining these controls below approximately
80” per second will delay
recovery and increase the potential for yawrate
reversala nd progressived eparturein the
opposite direction.
11.7.9.1 Spin Arrow Displays. At yaw rates
greater than 30” per second, the spin arrow displays
(Figure 11-5) have priority and override all other display
formats on the MFDl and the TID. MFD2 and MFD3
display the VDI format. When a yaw rate exceeding 30”
per second is detected, the current format on these displays
is overridden by the spin indicator format. In this
format, the spin arrow points in the direction of the spin.
Above the spin arrow in the MFD format, vertical tape
displays provide airspeed, altitude, and AOA indications.
If required, an indication of left or right engine
stall is provided. A moving caret shows yaw rate from
30” to 180” per second. If the yaw rate exceeds 180” per
second, the caret is pegged.
Note
l IfMFDl is not operating, the spin indicator
format is displayed on MFD2.
l If INS and SAHRS failures occur while
the spin arrow format is displayed, the
pointer on the yaw-rate scale is removed
from the MFD, the spin arrow is frozen,
and an “X” is superimposed over the
spin arrow. The airspeed, AOA, and altimeter
scales are not obscured (Figure
1 l-6)
At yaw rates over 30” per second, the TID display is
blanked and the spin arrow appears pointed in the direction
of yaw. If the yaw rate exceeds 90” per second,
the spin arrow will flash at a 4-times-per-secondr ate.
A fixed scale from 30° to 110” per second increasing
in the direction of yaw in increments of 20 will be
displayed below the spin arrow. A diamond will be
positioned above the numbers to indicate the existing
yaw rate. For yaw rates in excess of 110” per second,
the diamond will travel past 110 and be positioned over
a + sign.
Note
l The primary reference for the spin arrow,
the INS, is valid for yaw rates up to 300°
per second; the backup reference, the
SAHRS, is valid for the same yaw rates.
l If INS and SAHRS failures occur while
the spin arrow format is displayed, the
pointer on the yaw rate scale is removed
from the TID and a breakaway X is superimposed
over the spin arrow display (Figure
1 l-6).
11.7.10 Flat Spin. The only true upright, fully developed
spin in the F-14 is the flat spin. It is recognized
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
F-14D 飞行手册 Flight Manual 2(67)
