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system does not provide center frequency resolution for
detected signals. It then compares these signals parameters
to the threat library stored in the emitter identification
data (EID) files. If a match occurs, the digital processor
send the appropriate symbol data to the indicator and a
corresponding computer-synthesized voice warning message
to the helicopter ICS. If the received signal parameters
do not match a threat in the EID files, the processor
generates a symbol “U” to indicate an unknown threat. It
executes and evaluates the results of an IBIT routine, providing
an indication of results on the indicator. Also, it processes
threat data inputs from the AN/AVR-2, AN/
APR-44(3), and AN/AAR-47 systems for display on the
indicator and annunciation over the ICS.
d. The blade antenna senses C/D lo-band RF and
routes it to the C/D band amplifier portion of the digital
processor. The RF signal is filtered, limited, and detected
by the C/D band amplifier with the resultant video being
analyzed for the presence of a threat in the C/D band.
This analysis occurs in conjunction with the hi-band signal
analysis to determine the threat type and current
threat mode (scan. acquisition, track, launch, etc.)
e. The RSDS employs a removable user data module
(UDM) which is mounted in the digital processor. The UDM
contains the classified portion of the system operational flight
program (OFP) and the classified emitter identification
data(EID) files. The EID files contain the threat library which
includes threat signal parameters, threat symbols, and
threat audio data. The UDM can be removed at the unit level
and reprogrammed to accommodate new and changing
threats. It allows the RSDS to be tailored to the specific
theatre of operation and/or current mission requirements.
Removal of the UDM from the digital processor declassifies
the RSDS.
TM 1-1520-240-10
4-1-2
NOTE
Threat symbols (except for U) shown on indicator
illustrations are for illustration purposes
only. Actual threat symbols are classified.
f. The indicator displays threat symbols corresponding
to threat signals detected and identified by the system.
Threat relative position from the helicopter is shown on the
indicator. Symbol position relative to the center of the indicator
shows the threats lethality. The highest priority threats
(most lethal) are shown nearest the center. The 12 outer
edge markings on the indicator graticule represent clock
positions relative to helicopter heading. The system displays
a maximum of seven threat symbols. If the number of
threats in the environment exceeds the number the system
can display, only the seven highest priority threats will be
displayed. If a detected threat cannot be identified as a
specific threat type, it is displayed as an unknown (symbol
U). Search radars and fire control radars operating in search
mode are displayed as strobes at the edge of the indicator.
The position of the strobe on the display represents the
relative bearing of the search radar from the helicopter. New
threats appear in boldface on the display. Threats that dropout
of the environment are ghosted on the display for 10
seconds before being dropped. A ghosted symbol appears
as though drawn with a dotted line.
g. Threats are announced by voice messages over
the helicopter ICS. Either of the two voice message formats
can be selected using page 2 of the CDU ASE
control layer. RWR AUDIO 1 or normal (full message
format) selects full audio. RWR AUDIO 2 or terse (shortened
message format) provides shorter audio messages
and reduces the audio clutter in dense signal environments.
Both modes provide specific threat type or threat
position voice messages.
h. When dense signal environments cause the system
to operate in a degraded (less sensitive) mode, the
system informs the operator by flashing the plus (+) symbol
on the RSDS indicator and the voice message
“Threat Detection Degraded” will be heard over the ICS.
When the system sensitivity returns to normal, the plus
(+) symbol in the center of the RSDS indicator stops
flashing and the voice message “Threat Detection Restored”
will be heard over the ICS.
i. The RSDS, LDS, and MWS all execute periodic
built-in-test (PBIT) routines during normal operation to
verify operational status with the results of these tests
being reported to the digital processor. Failures of PBIT for
these three systems are indicated by the presence of an “F”
replacing the plus (+) symbol in the center of the RSDS
　
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