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Figure 22-2.
22.1.1 TARPS Pod. The TARPS pod (Figure 22-2)
is 207.5 inches long and weighs approximately 1,625
pounds including sensor equipment. The pod is nonjettisonabie
and is mounted to the aircraft on weapon station
5 with an integral pylon adapter. The adapter
provides the pod with sensor control signals, data annotation
signals, electrical power, and ECS support from
the aircraft. Circuit breaker protection is provided
through the ac left and right main circuit breaker panel.
The pod is designed for carriage throughout the flight
envelope.
22.1.2 Serial Frame Camera. The serial frame
camera can be directed in flight either to the forward
oblique position to obtain photogmphs of the area as
seen by the pilot, or to a vertical position for use as a
backup sensor in the event the panoramic camera fails
or for mapping missions.
The serial camera mount assembly holds the camera
and provides the capability to move the camera in flight
from the vertical position to the forward position. Controls
for the camera positioning are on the CPS.
22.1.3 Panoramic Camera. The panoramic camera
offers full horizon-to-horizon panoramic imagety over
a broad velocity/above ground level mission envelope.
22.1.4 infrared Line Scanner Set. The IRLS provides
a film record of termin being traversed by the
aircraft. Scanning optics receive IFt energy from the area
under surveillance. Electrical signals, representing the
scanned area, are recorded on black and white film. The
IRIS is roll stabilized to %?O’ in NFOV and ~4~ in
WFOV. If normal INS and SAHRS modes are not avaiiable,
lR imagery may be degraded because of poor roll
stabilization.
22.1.5 Data Display System. The DDS performs
two basic TARPS functions. It provides coded annotation
on the sensor film for future interpretation of the
recorded intelligence data and supplies necessary control
signals to the individual sensors.
ORIGINAL 2212
22.1.6 TARPS Environmental Control System.
The ECS supplies conditioned air for pod cooling and
heating and for defogging the camera windows.
22.1.7 Control indicator Power Distribution
Unit. The CIPDU provides power and signal distribution
as well as fail indicators for each of the various ood
sensorsa nd major pod equipment to guide mainten&e
personnel in the identification of faulty WRAs. The
CIPDU also provides the verification of proper operation
following corrective maintenance for preflight
checkout purposes.
22.1.8 Controller Processor Signal Unit. The
CPS (Figure 22-3) and cockpit displays provide the controls
and information required by the RIO and pilot for
operation and checkout of TARPS. The CPS is in the aft
cockpit left console and contains the primary TARPS
controls and indicators. Using the CPS with the multifunction
displays, the RIO has full control of TARPS. A
description of the CPS controls and their functions are
provided in Figure 22-3.
22.2 DISPLAY SYSTEM
As described in Chapter 2, the display system provides
the following:
1. Selection of waypoint to be reconnoitered and
steering mode (point-to-point, command course,
or mapping) to be employed.
2. Display of reconnaissances teeringc uesa nd camera
status to the HUD when valid steering is selected
and the aircrafl is not in A/A with a weapon
selected.
3. Display of reconnaissance steering cues on the
VDI when the VDI is selected.
4. Command steering displays using the reconnaissance
steering symbol and reconnaissancec ommand
heading marker.
5. Displays of reconnaissanceT ARPS sensors tatus
and camera solution cues to crew on the MFD
RECON DATA status format.
6. Display of target waypoint (reference point) data
on the IvlFD RECON DATA status format.
7. Display of waypoint reconnaissancep arameters
(command crossing angle, target length, map
lines, map separationd istance( map offset)) on two
formats.
NAVAIR 014=14AAD-1
TARPS POD ON
STATION 5
/
SrATlC ORO”N0 LINE
Figure 22-2. TARPS Component Location
ORIGINAL
NAVAIR 01.Fl4AAD-1
@----
a----
_...
Figure2 2-3. ControllePr rocessoSri gnaUl nit (Sheet1 of 6)
ORIGINAL 22-4
NAVAIR 01.F14AAD-1
NOMENCLATURE FUNCTION
0 FRAME lights Green FRAME IigM flashes once per camera cycle when serial frame camera
l Amber is activated and no failure exists. Amber FRAME light illuminates if failure
l Green exists in serial frame camera and green FRAME light goes off.
0 MOUNT light Illuminates indicating mount fallure. This occurs when serial frame camera
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F-14D 飞行手册 Flight Manual 3(43)
