ADDITIONAL DATA ON THE COMMAND CONTROL SYSTEM OF THE SOVIET BSNA-75M (FAN SONG) RADAR

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00247A000200060001-1
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 22
• Document Creation Date: December 27, 2016
• Document Release Date: January 14, 2014
• Sequence Number: 1
• Publication Date: August 14, 1964
• Content Type: REPORT

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CENTRAL INTELLIGENCE AGENCY
This material contains information affecting the National Defense of the United States within the meaning of the Espionage Laws, Title
18, U.S.C. Secs. 793 and 794, the transmission or revelation of which in any manner to an unauthorized person is prohibited by law.
COUNTRY
SUBJECT
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USSR
Additional Data on the Command
Control system of the Soviet
RSNA-75M (FAN SONG) Radar
REPORT
DATE DISTR.
NO. PAGES
REFERENCES
14 August 1964
9 50X1-HUM
DATE OF
INFO.
PLACE &
DATE ACQ.
THIS
IS
UNEVALUATED
INFORMATION. SOURCE GRADINGS ARE DEFINITIVE.
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Excluded from automatic
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STATE I DIA I ARMY I NAVY I AIR I NSA 1XIX MCI
OSI (30 copies)
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(Note: Field distribution indicated by "#".)
INFORMATION REPO
NFORMATION REPORT
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COUNTRY
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August 1964
USSR
Additional Data on the Command
System of the Soviet RSNA-75M
-(FAN SONG) Radar
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2. Except for the designation of the radar, which has been
transliterated in the Subject, above, the Cyrillic designation
for all units has been retained.
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Control Boards
1. The controls and instruments are concentrated on control boards
to permit centralization of such operations as: determining
state of readiness of the.equipment; switching the station
and transmitter on and off; setting the combat and monitoring
operation modes; giving permission for independent monitoring
of the vans; performing functional.monitoring.of'the:video
Channel PIM -selecting the proper guidance method; launching
the missiles; and returning the coordinate units of the missile
and command. generating system to their-original. state. .
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2. Front panels of the 466A,, 064, and 1162M units mounted in the
guidance cabinet of the 3A van are used as, control desksw.
? The.following devices are mounted on?the.front_panel-of unit
66A:' the station and transmitter signaling device for the
switches, in the form of light registers,and_pilot lights.which
indicate the readiness of the Station to be switched on from
the remote control unit, and readiness of the station and
transmitter. power supply units. Station.loud.7speaking?
communication switches and controls. - telephone keys enabling
switching the SA van telephone sets.of.gic7 anyvan, power
plant and launcher without a switchbdard.- The switch providing
for transmission of a. command about preparation of this plant
or that number of launchers, preparation;or.readiness of launchers#
is indicated on this desk, by the pilot lights. The switch changing
over the guidance station transmission.- from the dummy,antenna
to the antenna proper. Located on the?front-panel of unit 1464
are the following: devices allowing the station to be changed
over to combat operation or to tho centralized monitoring operating
mode, and also to change over, some vans to,:the local monitoring
operating mode. .Controls and. instruments providing centralized
monitoring of the station video channel and control command
transmitter,equipment. On. ?the, 4162M unit Iront panel are located:
angular and range guidance handwheel,s, launch controls. and ?
return' commands applied through three channels of the missile
coordinate units and command generating system with. the
'respective signaling. Guidance method selectors. On and off
switch buttons for synchronizing the launcher with signaling.
The station range and band- selector switch. On and off
switches of the transmitter instantaneous automatic gain control
with signaling system. Also located on the front panel of unit
VI 62M are scales of indicating.selsyns?showing the position
of the station and launchers-scan.sector bisector,and. a launcher
indication switch.1
Start launcli7 Control.System
3. In the SA van of the PCHA-75M. radar are located on 0/7 control
desk and the 141) -A unit of the CA-75M batalIionmissi1e battery
/giC7: These .units represent part of the 'launch -control,system..
Tne?antiaircraft guided missile launch control system automatically
performs by remote control the preparatory and starting operations.
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The launch control system provides for: firing missiles
from six launchers; maintaining continuous combat readiness
of two launchers attached to the missile battery; bringing the
missiles mounted on the launchers to launch readiness within
two minutes, with simultaneous transition of launchers from
loading angle to any angle required for firing at the target;.
Launching the missile *ithin not more than two seconds after the
launch commartihas been given; transmitting signals to the guidance
operator's control desk to provide data on the combat readiness
of the missiles and launchers, and readiness of the missile
battery control channel for firing; transmitting signals
warning the launcher servicing crew, two minutes prior to the
launch, about the beginning of preparation of the missile for
launch.
Station Operating Conditions
4. The main combat operating conditions of the station are as
follows: search for and detection of the target; guidance
of the scan sector bisector and range gates to the target;
target -tracking (manual and automatic); launching and automatic
tracking of the missile.
5. To detect targets : at long range the station operates
on a repetition frequency of 1250 cps. Under this condition
the transmitter triggering pulses of 1250 cps are transmitted
from the synchronizer and the receiving channel passbald narrows
to 3-4 Mc/s. The scan sector bisector is directed to the target
by means of the 2 and p handwheels of the guidance unit (062M).
In this operating condition, through a pair of se/syns
(transmitting and receiving) operating as a transformer, the
handwheel rotation produces an error signal voltage which is
processed. by the synchrodrives (0 62M and y165m). The stable
speed drive imparting the effort to the output s4ft connected
with the receiving selsyn is used as drivesigic7,..Whe tracking
drive output shaft carries /giC7 the transmitting selsyns, the
rotation angle of which is Yon-owed up by the antenna power
synchrodrive. In this case, the antennas are controlled only
in position. When the target appears within the station scan
sector the target mark should be observed on the guidance indicator
scopes.
6. In the guidance operating mode, the indicator vertical marks
are locked with the scan sector bisector. Alignment of vertical
marks of the guidance indicators (in planesE.and dB) with the .:.
middle of the target mark indicates that the scan sector bisector
has been guided to the target. The circuit of the target angular
coordinate unit servosystem (unit K73) is opened. The integrator
Input is grounded via a low value resistor. Voltage fixed value
corresponding to the position of the tracking gates in the
center of the scan sector is fed from the integrator output. The
gates are set precisely in the center of the sector by the .
operator of the Pi van, by comparing therposition of the
vertical marks from the coordinate units with the position of the
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vertical marks from the induction antenna transmitter on the
manual tracking indicator scakes.n. The induction transmitter
pulse corresponds to the middle of the scan sector. Range
guidance is by means of handwheel4 of unit 062M. The
handwheel is coupled with the potentiometer, the voltage of
which is fed to the variable delay circuit of the opened range-
tracking system (K71). In this the integrator is grounded via
a low value resistor. When matching the horizontal mark with
the echo blip the guidance operator, by varying the voltage
level, changes the pulse time position, thus guiding the
tracking gates to the target.
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7. If the, target azimuth is known only approximately, the target
is detected by a sector search method-. In this case the-;
station scan sector swings in azimuth within an 'angle of 4 200.
Also, it, is possible to swing the, center. throughout 360?.? The
azimuth synchrodrive (i/163M), in this case, acts according.to
the sum of two voltages: mismatching voltage between the
guidance transmitting selsyn ( t462M) and the receiving
selsyn (/1 63M) and sinusoidally modulated voltage, obtained from,
the V162M unit sector search rotating selsyn.
8. In cases where there are no data on the direction from which
the target enters the effective range of the radar, a circular
search ?method is used. In this case, constant?amplitude?voltage
which drives the antenna transmitters and the MA van in a
clockwise rotation at a speed of 16 degrees per second, is fed
,to the stable speed drive of unit -063M.
9. After, .the target is.detected and the station scan 'sector
bisector is aligned with it, the guidance operator sends. the
Command (by pushing the button) to the launchers to synchronize
them with the antenna system. When the target comes within the
required range, the antenna control is handed overnto the manual
.tracking operators who track the target by moving the scan sector,
keeping the target mark at the electronic mark nross lines. .
When the target comes within closer range) Me guidance operator
begins operating at a repetition frequency of 2500 'cps and with
the target receiVing channel passband equal to 4.5 - 6 Mc/s.
10. In the manual tracking mode the vertical mark is also .locked with
the station scan sector bisector. In this case the summary
values of the following two voltages are applied, to the input
of, the stable speed drive: the voltage prOpOrtional to the
rotation angle of the manual tracking unit handwheel, and that
? proportional to the derivativeof this angle. Such a circuit
provides target tracking in speed and in position. The angular
coordinate unit operation in the manual track:ing mode does not
differ from that in. the guidance operating condition except that
the low value resistor coupling the integrator input with the
chassis increases in value. When a previous operation mode is
changed over to the target range manual tracking operation mode
the guidance voltage is no. longer applied to the open tracking
system and the 'integrator is disconnected frOM the "ground".
The range tracking of the target is carried out in speed and
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in position by means of the unit 061 handwheel. The handwheel
rotating action is imparted to the potentiometer from which
the speed voltage is taken and fed to the error signal amplifier
of unit K71. The position voltage is obtained from the same
potentiometer and through the capacitor is introduced into the
integrator circuit. The operator controls the range pulse
position by aligning the manual tracking horizontal mark with
the target echa mark (the range sweep scale being 60 km). In
case the 5-km sweep scale is set, the operator keeps the target
mark between two horizontal marks.
11., Under a condition free from jamming the manual tracking operators
may switch to automatic tracking when the vertical mark locks
with the center of the echo mark. The manual.tracking operators
control the scan sector position in elevation and azimuth so
that the vertical mark is aligned with the notched mark on the
indicator scope (the notch corresponds to the scan sector
bisector). In the automatic tracking mode, the error signal
amplifier input of the target angular coordinate unit is
disconnected from the "ground" and the tracking system circuit
is closed by connecting the integrator to the error signal
amplifier output. The center of the tracking gates follows
up the target packet center throughout the scanning sector.
The position of the gate pulses is controlled by the signal.
voltage generated in the discriminator. The magnitude and
sense of this voltage are determined by the direction of the
misalignment and the value of the enveloping packet center with
reference to the center of the gate pulses. When the range target
automatic tracking is switched on, the manual tracking handwheel
of unit V161 is disconnected from the control circuit by means
of the electromagnetic joint. Transmission of the speed voltage
to the error signal amplifier input of unit K71 is stopped and
the integrator is connected to the error signal amplifier output,
thus closing the circuit of the range tracking system. The
error signal voltage generated by the discriminator controls
the position of the gates. The error signal is proportional
to the value of the mismatch between the gate joint and the target
video pulse center. If the target elevation is less than 5.50,
it is guided and tracked in elevation by the manual tracking
operator who'displaces the angular gates with the antenna being
fixed. In this case, the vertical mark is obtained from the
middle of the raster and aligned with the target echo mar.
When the scan sector bisector reaches an ele7ration of 5,5 the
pilot switbh cuts out the circuit of the stable speed drive motor
winding, thus fixing the position of the elevation antenna.
The total value of two voltages is fed to the AC amplifier and
then to the phase detector. One of these voltages is proportional
to the rotation angle of the manual tracking handwheel and the
other to its derivatives (unit M65M).
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12. The DC signal from the phase detector is fed to the angular
?coordinate unit integrator of the target (K73). From the
integrator the voltage is fed to the comparison circuit which
generates the pulse characterizing the vertical mark position
with respect to the station scan sector. This pulse is fed to
the pulse-shaping circuit, which generates the angular gates,
the command generating system pulse and the vertical mark
triggering pulse. All these pulses are locked with each
other. Transition to automatic target tracking is accomplished
in a way similar to that in other operating modes. The
coordinate unit operation in the automatic tracking mode in the
case of a low altitude target does not differ from the operation
with an elevation exceeding 5.50. In this case none of the
signal from the phase detector of the manual tracking unit is
applied to the integrator. When the target pip crosses the
center of the indicator scope, it is necessary to depress the
low altitude button of 065M unit which bypasses the pilot
switch. When the low altitude button is pushed the elevation
antenna is controlled by the handwheel 1465M unit (it may also
be controlled by handwheel e of unit 062M). After the antenna
is disconnected from the pilot switch the vertical mark in the
manual tracking operation will be locked to the view sector "
bisector.
13. Having handed over the control of the target tracking to the -
manual tracking operators the guidance operator sets the switch
(ripn) on the unit V32 panel in one of the extreme positions.
At this time there appears on indicators E. or, the image of the
horizontal mark presented by the unit determining the range. of
the impact point (unit U187). If the unit P187 horizontal mark
is within the destruction zone the guidance operator may launch
the missile of the respective channel. When determining the
moment of launch the guidance operator simultaneously selects
the method of guiding the missile to the target.' The selected
method is set in unit 062M. Prior to launching the missile
.by any channel the guidance operator makes sure that the ?
launcher is synchronized (light register "synchronize" should
be on) and that the missile is ready to be launched (light
register "ready" should shine). The missile takeu'off is
indicated by light register "ready" which should go out, and
the missile tracking may be judged by the motion of the: slave
gate and the missile echo mark. When the missile approaches
the target the single command (radio /TroximitY7 fuse arming
command) is transmitted; this is indfoated by The single ?command
red lighton unit V164 which should light up. In case the
launched missile doe il not destroy the target, the operator may
launch the next missile via another channellafter making sure
that the horizontal mark of un:,t tA87 is located within the
destruction zone.
14.. If the station has engaged a group target the operator may launch
three missiles, with six-second intervals between launchings,
observing the cycle circuit operation by the lighting of the light
"cycle" on unit 002M. When the launcher (with missile) is
ready to be fired, the "launcher readiness" (ground) command is
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fed to the P3 and Tit relays (unit i4621.),. ;The relays, operate .
and are then blocked, thus preparing the circuit for launch.
When the button "launch" is pushed, a current of +26 volts
is supplied through closed contacts 3 and 4 of relay P4 to the
winding of relay P9)blocking through the return elements
(button "return") and the normally closed contact of relay P10.
When the combat operation command is sent, P1 and P2 of unit
Vt 64 operate causing their contact to close. After relay P9
of unit162M is energized, command "ground" is fed to the
command transmitter system to change over the transmitter
operation from the dummy to the antenna proper. Another current
of +26 volts is applied via contacts 7,8,9, and 10 of unit
'AA 62M (relay P9) to the AA van (command "launch") and, via
relay winding (relay 168) of _the on control desk. In this
way the command "ignition" pass circuit is preapred.. When
the command transmitter is changed over to the antenna, +26 volts
are fed to the P3 relay winding of unit 064 making contacts
1, 2 close. Through these'contacts?the +26-volt zurrent (ignition)
is fed to the on control desk,: b.rt(1. after successively flowing
across the normally opened contacts of the "launch" relay, the
signal ready blocking relay (relay 164), and the synchronization
signal blocking relay (relay 163), is 'finally fed to the
launchers in the form of command "launch".
15 After the missile has left the launcher, transmission of
command "launcher readiness" tsa,relaysTP4 and P3 of unit Pi62M ?
is discontinued. The circuit is returned to the initial position
by means of the return elements either automatically (when +26
volts are supplied from the command generating system time
mechanism to relay P10 winding) or mechanically by button return. .
Prior to launching the missile the K72 missile range coordinate
unit operates in the slave gate setting mode. The integrator
is connected to the output of the slave gate setting circuit
generating the voltage which provides the necessary fixed delay
in the variable delay circuit. Thus, in the slave gate
setting mode the tracking gates occupy the definite initial
position. Unit K72 is changed over to the automatic tracking
operating condition automatically with the help of the lock-on
circuit at the moment the missile passes the point corresponding
to the initial position of the range tracking gates. When the
"launch" button of unit 1)162M is pressed, command "launch" is
fed to the lock-on circuit. Five seconds after missile launch
(missile independent flight time) the lock-on circuit is ready
to lock-on the missile. After the missile signal is aligned with
the second tracking gate, the discriminator generates the voltage
to switch on the lock-on circuit. The latter feeds the command
for switching on the automatic gain control circuit of the
receiver and transfers the unit to the automatic tracking mode.
One-half second later the iok-on circuit transmits the command
for switching on the angular unit automatic tracking control
and the command for switching the radio control which, in turn,
switches the rotation mechanism in the command generating device
and connects the command generating system output to the command .
transmitter input. Simultaneously the delay circuit (34 second)
is triggered which sends the command to switch over the bands of
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the angular unit and the range tracking system as well as ?
to change the angular system from wide to narrow gates. Prior
to launch of the missile, coordinate units (like the range
unit) operate in the slave setting mode. The tracking system
circuit is open at this time, the integrator input is grounded
through the low value' resistor and fixed voltage makes it
possible to set the tracking gate center on the bisector of
the scan sector. In the slave gate setting operation mode the
width of the two tracking gates occupies the scan sector of the
station. After the command for switching on the automatic track-
ing operation mode is received from unit K72, the tracking system
circuit closes and the gates follow the missile signal.
16. In addition to the combat operating mode, the station may
? operate in the monitoring operating mode needed during operation
monitoring, periodical inspection, maintenance, etc. Unlike
the combat operation, in this operation mode the launch command
is not fed to the launchers, the station centralized monitoring
simulating equipment is connected and independent equipment
tests may be performed for indi%7idual vans.
Comment:
1. This listing of equipment is essentially as received.
Adequate punctuation between items was lacking in the
original.
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Attachment
CONTROL BOARDS
THE STATION CONTROL BOARDS CONCENTRATE THE CONTROLS AND INSTRUMENTS
ENABLING TO CHECK THE STATION EQUIPMENT READINESS FOR CENTRALISED
SWITCHING TO SWITCH ON AND 01111 THE STATION AND TRANSMITTER IN A
CENTRALISED WAY TO SET COMBAT AND MONITORING OPERATION MODES OF THE
STATION TO PRESENT THE PERMISSION FCR INDEPENDENT MONITORING OF THE
CABINS, TO PERFORM THE CENTRALISED FUNCTIONAL MONITORING OF VIDEO
CHANNEL, PF1K, TO SELECT THE NEEDED GUIDANCE METHOD, TO LAUNCH MISSILES,
TO RETURN THE COORDINATE UNITS OF THE MISSILE AND COMMAND GENERATING
SYSTEM TO INITIAL STATE, FRONT PANELS OF dilIT 066A, P164, 062M
MOUNTED IN THE GUIDANCE CABINET OF CABIN ARE USED AS CONTROL
DESKS. THE FOLLOWING DEVICES ARE MOUNTED ON THE FRONT PANEL OF UNIT
066A: THE STATION AND TRANSMITTER SWITCHES, SIGNALLING DEVICE, IN
THE FORM OF LAMP REGISTERS AND PILOT LAMPS INDICATING THE READINESS
OF THE STATION TO BE EiWITCHED ON FROM THE REMOTE CONTROL UNIT READINESS
OF THE STATION AND THE TRANSMITTER POWER SUPPLY UNITS. STATION LOUD SPEAKING
COMMUNICATION SWITCHES AND CONTROLS -- TELEPHONE KEYS ENABLING TO
SWITCH THE YA CABIN TELEPHONE SETS OF ANY CABIN, POWER PLANTS AND
LAUNCHERS WITHOUT A SWITCH BOARD. THE SWITCH PROVIDING APPLICATION
AcCOMMAND ABOUT PREPARATION OF THIS PLANT OR THAT NUMBER OF LAUNCHERS,
PREPARATION OR READINESS OF LAUNCHERS IS INDICATED ON THIS DESK BY THE
PILOT LAMPS. ihE SWITCH CHANGING OVER THE GUIDANCE STATION TRANSMISSION
FROM THE EQUIVALENT ANTENNA TO THE ANTENNA PROPER. LOCATED ON THE
FRONT PANEL OF UNIT V164 ARE THE FOLLOWING: -- DEVICES ALLOWING THE
STATION TO BE CHANGED OVER TO COMBAT 0?ERATION OR CENTRALISED MONITORING
OYERATING MODE AND ALSO TO CHANGE OVER SOME CABINS TO LOCAL MONITORING
OPERATING MOLE. -- CONTROLS AND INSTRUMENTS PROVIDING CENTRALISED
RFCIET
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*MONITORING OF THE 'STATION VIDEO CHANNEL AND CCNTROL COMMAND TRANSMITTER
EQUIPMENT. ON THE 062M UNIT FRONT PANEL ARE LOCATED: -- ANGULAR AND
RANGE GUIDANCE HANDWHEELS - CONTROLS OF LAUNCH AND RETURN COMMANDS
APPTJED THROUGH THREE CHANNELS OF THE MISSILE COORDINATE UNITS AND
,7,
COMMAND GENERATING SYSTEM WITH THE RES1JECTIVE SIGNALDPG. -- GUIDANCE
METHOD SELECTORS. --ON--OFF SWITCH BUTTONS OF SYNCHRONIZING THE
LAUNCHER WITH SIGNALLING. --THE STATION RANGE AND BAND SELECTOR
SWITCH. --ON AND OFF SWITCHES OF THE TRANSMITTER INSTANTANEOUS
AUTOMATIC GAIN CONTROL WITH SIGNALLING SYSTEM. BESIDES ON UNIT q62M
FRONT PANEL ARE LOCATED SCALES OF INDICATING SELSYNS SHOWING THE POSITION
OF THE STATION AND LAUNCHERS VIEW SECTOR BISECTOR AND A LAUNCHER
INDICATION SWITCH.
START CONTROL SYSTEM. IN CABINLYA OF TM PCHA-75M STATION ARE LOCATED
ON on CONTROL DESK AND THE PW-A, UNIT OF THK CA-75M BATTALLION MISSILE
BATTERY. THESE UNITS REPRESENTS A PART OF THE START CONTROL SYSTEM.
ANTI AIRCRAFT GUIDED MISSILE START CONTROL SYSTEM AUTOMATICALLY
PERFORMS THE REMOTE CONTROL OF THE PREPARATORY AND STARTING OPERATIONS.
Thh START CONTROL SYSTEM PROVIDES: FIRING MISSILES FOR SIX LAUNCHERS
CONTINUOUSLY MAINTAINING COMBAT READINESS OF TWO ALLOWANCES ATTACHED
TO THE MISSILE BATTERY BRINGING THE MISSILE MOUNTED ON THE LAUNCHERS
TO FIRING READINESS WITHIN TWO MINUTES WITH SIMULTANEOUS TRANSITION OF
LAUNCHERS FROM LOADING ANGLE TO ANY ANGLE REQUIRED FOR FIRING AT THE
? TARGET, PERFORMING OF TBE LAUNCH OF A. MISSILE WITHIN THE TIME NOT
EXCEEDING a SECONDS AFTER TEE LAUNCH COMMAND IS APPLIED, PRESENTING SIGNALS
TO THE GUIDANCE OPERATOR'S CONTROL DESK TO PROVIDE SIGNALLING ABOUT CCNBAT
READINESS OF THE MISSILES AND LAUNCHERS AND READINESS OF Tlib MISSILE
BATTERY CONTROL CHANNEL FOR FIRE,
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Attachment
PRESENTING SIGNALS WARNING THE LAUNCHER SERVICING CREW TWO MINUTES
PRIOR TO THE LAUNCH ABOUT THE BEGINNING OF PREPARATION OF THE MISSILE
FOR LAUNCH,
STATION OPERATING CONDITIONS. STATION MAIN COMBAT OPERATING CONDITIONS
ARE THE FOLLOWING: SEARCH FOR AND DETECTION OF THE TARGET, GUIDANCE
OF VIEW SECTOR BISECTOR AND RANGE GATES AT THE TARGET, TARGET TRACKING
(MANUAL AND AUTOMATIC TRACKING), START AND AUTOMATIC TRACKING OF THE
MISSILE LAUNCHED. TARGET DETECTION AT LONG RANGE IS CARRIED OUT WHEN
THE STATION OPERATES AT 1250 CPS REPETITION FREQUENCY. UNDER THIS
CONDITION THE TRANSMITTER TRIGGERING PULSES OF 1250 CPS ARE PRESENTED
FROM THE STATION SYNCHRONIZER AND THE RECEIVING CHANNEL PASS BAND
GETS NARROW UP TO 3 -- 4 MC/S. THE VIEI: SECTOR BISECTOR IS DIRECTED
TO THE TARGET BY MANS OF HANDWHEELS AND OF THE GUIDANCE UNIT
(4 5). IN 'MIS OPERATING CONDITION BY MEANS OF A PAIR OF SELSYNS
(TRANSMITTING AND RECEIVING) OPERATING AS A TRANSFORMER THE HAND
WHEEL ROTATION IS TRANSFORMED INTO ERROR SIGNAL VOLTAGE PROCESSED BY
TBE SYNCHRO DRIVES 00162M AND 1/65M. THE STABLE SPEED DRIVE IMPARTING
THE EFFORT TO THE OUTPUT SHAFT CONNECTED WITH THE RECEIVING SELSYN
IS USED AS DRIVES. THE TRACKING DRIVE OUTPUT SHAFT CARRIES THE
TRANSMITTING SELSYNS WHOSE TURNING ANGLE IS FOLLOWED UP BY THE ANTENNA
POWER ingfitiSYNCHRO DRIVE. IN THIS CASE THE ANTENNA ARE CONTROLLED
ONLY IN POSITION. WHEN THE TARGET APPEARS WITHIN THE STATION VIEW
SECTOR THE TARGET MARK SHOULD BE OBSERVED ON THE GUIDANCE INDICATOR
SCREENS. IN THE GUIDANCE OPERATING MODE THE INDICATOR VERTICAL MARKS
ARE LOCKED WITH THE VIEW SECTOR BTSECTOR. ALIGNMENT OF VERTICAL MARKS
OF THE GUIDANCE INDICATORS (IN THE PLANES E. AND 0 ) WITH THE MIDDLE
SFERFT
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" AiTc?c,KULtintlin
50X1 -HUM
OF THE TARGET MARK INDICATES THAT THE VIEW SECTOR BISECTOR HAS BEEN
GUIDED TO THE TARGET. IN THIS CASE THE CIRCUIT OF THE TARGET ANGULAR
COORDINATE UNIT SERVO SYSTEM (UNIT K73) IS OPENED. THE INTEGRATOR
INPUT IS EARTHED VIA SMALL VALUED RESISTOR. VOLTAGE FIXED VALUE
CORRESPONDING TO THE POSITION. OF THE TRACKING GATES IN THE CENTER OF
THE VIEW SECTOR IS PRESENTED FROM THE INTEGRATOR OUTPUT. THE GATES
ARE SET PRECISELY IN THE CENTRE OF THE SECTOR BY CABIN UA OPERATOR
BY COMPARING THE POSITION OF THE VERTICAL MARKS FROM THE COORDINATE
UNITS WITH THE POSITION OF THE VERTICAL MARKS FROM THE INDUCTION
ANTENNA TRANSMITTER ON THE MANUAL TRACKING INDICATOR SCREENS
S tk,:. 11 FT
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THE INDUCTION TRANSMITTER PULSE CORRESPONDS TO THE MIDDLE OF VIEW SECTOR.
RANGE GUIDANCE IS PERFORMED BY MEANS OF HAPDHEEL A OF UNIT 1A62M. THE
HANDV:113EL IS COUPLED WITH THE POTENTIOMETER WHOSE VOLTAGE IS FED TO THE
VARIABLE DELAY CIRCUIT OF THE OPPMD RANGE TRr-,CKING SYSTEM (K71). IN
TIS THE IHTEGRATOR IS EARTHED VIA A SMALL VALUED RESISTOR. WHEN
MATCHING HORIZONTAL MARK 'ITR THE ECHO BLIP THE GUIDANCE OPERATOR BY
VARYING TIE VOLTAGE LEVEL, CHANGES THE PULSE TIME POSITION THUS GUIDING
TEE TRCFING GATES TO THE TARGET. IF THE TARGET AZIMUTH IS KN3T1J ONLY
APPROXIMATELY T.;EN THE TARGET IS DETECTED BY A SECTOR SEARCH METHOD.
I THIS CSE THE STATION VIE 1 SECTOR IS SWINGING IN AZIMUTH WITHIN AN
ANGLE OF t 200. BESIDES IT IS POSSIBLE TO MOVE SWINGING CENTRE THROUGHOUT
3600. THE AZIMUTH SYNCHRO DRIVE ( 146.3M) IN THIS CASE ACTS ACCORDING
TO THE SUM OF TO VOLTAGES: MISMATCHING VOLTAGE BETWEEN THE GUIDANCE
TRANSMITMO SELSYN ( 1416-2M) AND THE RECEIVING sELayw ( Mom) ,--
VOLTAGE MODULATED SINUSOIDALLY OBTAINED FROM ME UNIT 1462M SECTOR
SEARCri ROTATING SELSYN.
IN THE CASES WHEN THERE IS NO DATA ABOUT THE DIRECTION IN WHICH THE
TARGET ENTERS TIE STATION EFFECTIVE ZONE, USE IS MADE OF A CIRCULAR
SEARCH METHOD. IN THIS CASE CONSTANT AMPLITUDE VOLTAGE DRIVING ANTENNA
TRANSMITTEAS AND CkBIK nA.A. TO ROTATE LOCIC4I.SE WITH THE SPEED OF 16
DEGREE PER SECOND, IS FED TO THE STABLE SPEED DRIVE OF UNIT wom_
AFTER THE TARGET IS DETECTED AND THE STATION VIEW SECTOR BISECTOR IS
ALIGNED WITH IT TTE GUIDANCE OPERATOR PRESENTS THE COMMAND ( BY PUSHING
THE BUTTON) TO TLT: LAPNCERS TO SYNCHRONISE TTEM 717ITH THE ANTENMG
SYSTEM. AFTER TUE TARGET REACHES THE REQUIRED RANGE THE ANTENA CONTROL
SECRET
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IS HANDED OVER TO THE MANUAL TRACKING OPERATORS WHO TRACKS THE TARGET
BY DISPLACING THE ViE4 SECTOR KEEPING THE TARGET MARK AT THE ELECTRONIC
MARK CROSS LINES. WHEN THE TARGET APPROACHES A POINT OF A SHORTER
LINE RANGE, THE GUIDANCE OPERATOR, STARTS OPERATING IN A MODE CONSISTING
IM THE OPERATION WITH 2500 CPS REPETITION FREQUENCY AND WITH THE TARGET
RECEIVING CHANNEL PASSBAND EQUAL TO 4.5 -- 6 Mcis. IN THE MANUAL
TRACKING MODE THE VERTICAL MARK IS ALSO LOCKED WITH THE STATION VIEW
10
SECTOR BISECTOR. IN THE PRESENT CASE APPLIED I'D THE INPUT OF THE STABLE
SPEED DRIVE ARE THE SUEMARY VALUE OF THE FOLLOWING TWO VOLTAGES THE
VOLTAGE PROPORTIONAL TO A TURNING ANGLE OF THE MANUAL TRACKING UNIT
HANDWHEEL AND THAT PROPORTIONAL TO THE DERIVATIVE OF THIS ANGLE. SUCH
A CIRCUIT PROVIDES TARGET TRACKING IN SPEED AND IN POSITION. THE ANGULAR
COORDINATE UNIT OPERATION IN ME MANUAL TRACKING MODE DOES NOT DIFFER
FROM THAT IN THE GUIDANCE OPERATING CONDITION EXCEPT FOR THE FACT THAT
THE LOW VALUED RESISTOR COUPLING THE INTEGRATOR INPUT WITH THE CHASSIS
INCREASES IN VALUE. WHEN A PREVIOUS OPERATION MODE IS CHANGED OVER TO
THE TARGET? RANGE MANUAL TRACKING OPERATION MODE THE GUIDANCE VOLTAGE
IS NO LONGER APPLIED TO THE OPEN TRACKING SYSTEM AND THE INTEGRATOR IS
DISCONNECTED FROM THE "GROUND". THE RANGE TRACKING OF THE TARGET IS
CARRIED OUT IN SPEED AND IN POSITION BY MEANS OF UNIT 1461 HANDWHEEL.
THE HANDWHEEL ROTATING ACTION IS IMPARTED TO THE POTENTIOMETER FROM
WHICH SPEED VOLTAGE IS TAKEN AND FED TO THE ERROR SIGNAL AMPLIFIER OF
UNIT K71. THE POSITION VOLTAGE IS OBTAIFED FROM THE SAME POTENTIOMETER
AND THROUGH THE CAPACITOR IS INTRODUCED INTO TEE INTEGRATOR CIRCUIT.
THE OPERATOR CONTROLS THE RANGE PULSE POSITION By ALIGNING THE MANUAL
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-ULEILSEtrittliii;
TRACKING HORIZONTAL MARK WITH THE TARGET ECHO MARK (THE RANGE SWEEP
SCALE BEING 60 KM), IN CASE 5 KM SWEEP SCALE IS SET THE OPERATOR
KEEPS THE TARGET MARK BETWEEN T40 HORIZONTAL MARK..
UNDER INTERFERENCE FREE CONDITION THE MANUAL TRACKING OPERATORS MAY
SWITCH ON THE AUTOMATIC TRACKING, WHEN THE VERTICAL MARK WILL BE LOCKED
WITH THE CENTRE OF THE ECHO MARK. THE MANUAL TRACKING OPERATORS CONTROLS
THE VIEW SECTOR POSITION IN ELEVATION AND AZIMUTH SO THAT THE VERTICAL
MARK IS ALIGNED WITH THE NOTCHED MARK ON THE INDICATOR SCREEN (THE
NOTCH CORRESPONDS TO THE VIEW SECTOR BISECTOR). IN AUTOMATIC TRACKING
MODE THE ERROR SIGNAL AMPLIFIER INPUT OF THE TARGET ANGULAR COORDINATE
/E
UNIT IS DISCONNECTD FROM THE "GROUND" AND THE TRACKING SYSTEM CIRCUIT
IS CLOSED BY CONNECTING THE INTEGRATOR TO THE ERROR SIGNAL AMPLIFIER
OUTPUT. THE CENTER OF THE TRACKING GATES FOLLOWS UP THE TARGET PACKET
CENTRE THROUGHOUT THE SCANNING SECTOR. THE POSITION OF GATE PULSES IS
CONTROLLED BY MEANS OF THE SIGNAL VOLTAGE GENERATED IN THE DISCRIMINATOR.
THE MAGNITUDE AND SENSE OF THIS VOLTAGE ARE DETERMINED BY THE MISALIGNMENT
DIRECTION AND VALUE OF THE ENVELOPING PACKET CENTER WITH REFERENCE TO
THE CENTRE OF THE GATE PULSES ? WHEN THE RANGE TARGET AUTOMATIC TRACKING
IS SWITCHED ON UNIT M61 MANUAL TRACKING HANDWHEEL IS DISCONNECTED FROM
CONTROL CIRCUIT BY MEANS OF THE ELECTROMAGNETIC JOINT. APPLICATION OF
THE SPEED VOLTAGE TO THE ERROR SIGNAL AMPLIFIER INPUT OF UNIT K7I IS
STOPPED AND THE INTEGRATOR IS CONNECTED TO THE ERROR SIGNAL AMPLIFIER
OUTPUT THUS CLOSING THE CIRCUIT OF THE RANGE TRACKING SYSTEM. ERROR
SIGNAL VOLTAGE GENERATED BY THE DISCRIVINATOR CONTROLS POSITION OF THE
GATES. THE ERROR SIGNAL IS PROPORTIONAL TO THE VALUE OF MISMATCH BETWEEN
THE GATE JOINT AND THE TARGET VIDEO PULSE CENTER. IF THE TARGET
o THEN IT IS GUIDED AND TRACKED IN ELEVATION
ELEVATION IS LESS THAN 5.5 IPPFT
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BY THE MANUAL TRACK OPERATOR WHO DISPLACES ANGULAR GATES WITH THE ANTENNA
BEING FIXED. IN THIS CASE THE VERTICAL MARK IS OBTAINED FROM r4t,,f,A
MIDDLE OF THE RASTER AND ALIGNED WITH THE TARGET ECHO MARK. WHEN THE
VIEW SECTOR BISECTOR REACHED 5.5 ELEVATION THE PILOT SWITCH CUTS OUT
THE CIRCUIT OF THE STABLE SPEED DRIVE MOTOR WINDING, THUS FIXING THE
POSITION OF THE ELEVATION ANTENNA. THE TOTAL VALUE OF TWO VOLTAGES
IS FED TO THE AC AMPLIFIER AND THEN' TO THE PHASE DETECTOR. ONE OF THESE
VOLTAGES MAW #fgfti PROPORTIONAL TO MANUAL TRACKING HANDWHEEL
TURN ANGLE AND THE OTHER TO ITS DERIVATIVES (UNIT 1465M).
ET
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THE DC SIGNAL FROM PHASE DETECTOR IS APPLIED TO IkNGULAR COORDINATE UNIT
INTEGRATOR OF THE TARGET (K73), .FROM THE INTEGRATOR THE VOLTAGE IS
E ,
PRESENTED TO THE 0004100; COMPARISON CIRCUIT GENERATING THE PULSE
CHARACTERIZING THE VERTICAL MARK POSITION WITH RESPECT TO THE STATION
VIEW SECTOR. THIS PULSE IS FED TO THE PULSE SHAPING CIRCUIT GENERATING
ANGULAR GATES, COMMAND GENERATING SYSTEM PULSE AND VERTICAL MARK
TRIGnERING PULSE. ALL THESE PULSES ARE LOCKED WITH EACH OTHER. r.
TRANSITION TO THE TARGET AUTOMATIC TRACK IS ACCOMPLISH IN SIMILAR WAY
U N IT
TO THAT KNOWN IN OTHER OPERATING MODES. THE COORDINATE OPERATION IN
A
THE AUTOMATIC TRACKING MODE IN THE CASE OF LOW FLYING TARGET DOES NOT
DIFFER FROM THE OPERATION WITH ELEVATION EXCEEDING 5.5?. IN THIS CASE
NONE OF TRE SIGNAL FROM THE PHASE DETECTOR 0; MANUAL TRACKING UNIT IS
APPLIED TO THE INTEGRATOR. WHEN THE TARGET PIP CROSSES THE INDICATOR
SCREENS CENTER IT IS NECESSARY TO DEPRESS UNIT 1/165M LOW ALTITUDE
BUTTON WHICH BYPASSES THE PILOT SWITCH. WHEN THE Daw ALTITUDE BUTTON
IS PPS1TED THE ELEVATION ANTENNA IS CONTROLLED FROM UNIT 1A65M'HANDWHEEL
(IT MAY ALSO BE CONTROLLED BY HANDWHEEL E OF UNIT 1162M). AFTER THE
ANTENNA IS DISCONNECTED FROM THE PILOT SWITCH THE VERTICAL MARK IN THE
MANUAL TRACK OPERATION WILL BE LOCKED TO THE VIEW SECTOR BISECTOR.
HAVING HANDED OVER THE CONTROL OF THE TARGET TRACKING TO THE MANUAL
TRACKING OPERATORS THE GUIDANCE OPERATOR SET SWITCH OW (flpn) ON
UNIT 1432 PANEL IN ONE OF THE EXTREME POSITIONS. AT THIS TIME ON
INDICATORS E. OR p APPEARS THE IMAGE OF THE HORIZONTAL MARK PRESENTED
BY THE UNIT DETERMINING THE RANGE OF TRE IMPACT POINT (UNIT 107).
IF UNIT 1,187 HORIZONTAL MARK IS WITHIN THE DESTRUCTION ZONE THEN THE
GUIDANCE OPERATOR MAY LAUNCH THE MISSILE OF THE RESPECTIVE CHANNEL.
DETERMINING THE LAUNCH MOMENT THE GUIDANCE OPERATOR SIMULTANEOUSLY
rrrnrT
MOO
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94, 16. tn.
?
Attachment
SELECTS THE METHOD OF GUIDING THE EISSILE TO THE TARGET. THE SELECTED 50X1-HUM
METHOD IS SET IN UNIT 1462M. PRIOR TO LAUNCHING THE MISSILE THE GUIDANCE
OPERATOR By ANY CHANNEL MAKES SURE THAT THE LAUNCHER IS SYNCHRONISED
(LAMP REGISTER "SYNCHRONISE" SHOULD LIGHT.) AND THE MISSILE IS READY
TO BE LAUNCHED (LAMP REGISTER "READY" SHOULD SHINE). THE MISSILE TAKE
OFF IS INDICATED BY LAMP REGISTER READY WHICH SHOULD GO OUT AND THE
MISSILE TRACKING MAY BE JUDGED BY MOTION OF SLAVE GATE AND MISSILE
ECHO MARK. WHEN THE MISSILE APPROACHES THE TARGET THE SINGLE COMMAND
IS PRESENTED (RADIO FUSE ARMING COMMAND) THAT IS INDICATED BY THE
SINGLE COMMAND.RED LAMP ON UNIT 1464 WHICH SHOULD LIGHT UP. IN THE
CASE THE LAUNCHED MISSILE HAS NOT DESTROYED THE TARGET THE PEN
OPERATOR MAY LAUNCH THE NEXT MISSILE VIA ANOTHER CHANNEL PRELIMINARY
MAKING SURE THAT THE HORIZONTAL MARK OF UNIT 1487 IS LOCATED WITHIN
THE DESTRUCTION ZONE. IF THE STATION IS ENGAGED WITH A age1F0 GROUP
TARGET THE OPERATOR MAY LAUNCH THE THREE MISSILES WITHIN SIX SECONDS
INTERVAL BENEEN LAUNCHINGS OBSERVING THE CYCLE CIRCUIT OPERATION
BY LIGHTNING OF LAMP "CYCLE" ON UNIT 14 62M. THE MISSILE START
SWITCHING DIAGRAM IS ON FIG 31. WHEN THE LAUNCHER WITH MISSILE IS
READY TO BE FIRED COMMAND " LAUNCHER READINESS" (GROUND) IS PRESENTED
TO THE RELAY P3 AND p4 (UNIT 1462M). AFTER THAT THE RELAYS OPERATE
AND THEN THEY ARE BLOCKED THUS PREPARING THE CIRCUIT FOR PERFORMING
THE LAUNCH. WHEN THE BUTTON "START" IS PUSHED +26 V VOLTAGE THROUGH
CLOSED CONTACTS 3, 4 OF RELAY P4 SUPPLIED TO THE WINDING OF RELAY P9
BLOCKING THROUGH THE RETURN ELEMENTS (BUTTON "RETURN) AND NORMALLY
CLOSED CONTACT OF RELAY P10. WHEN THE COMBAT OPERATION COMMAND IS
APPLIED P1 AND P2 OF UNIT W64 OPERATE MAKING THEIR CONTACT CLOSE.
v;rAFT
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Attadhment
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AFTER RELAY P9 OF UNIT 162M IS ENERGIZED COMMAND "GROUND" IS FED TO
THE COMMAND TRANSMITTER SYSTEM TO CHANGE OVER TRT TRANSMITTER OPERATION
OUILAI4v Artrre OA/
FROM THE tiRMEEEW7 TO ANTENNA PROPER. APART FROM THAT A VOLTAGE OF
+26 v VIA CONTACTS 7, 8, 9, 10 OF UNIT VI62M (RELAY P9) is APPLIED
TO CABIN AA (COMMAND "START") AND VIA RELAY P2 CONTACT (UNIT 1464)
THE START COMMAND IS APPLIED TO TPE START RELAY WINDING (RELAY 168)
OF THE on CONTROL DESK. IN THIS WAY COMMAND "IGNITION" PASS CIRCUIT
Is PREPARED. WEN THE COMMAND TRANSMITTER Is CHANGED OVER TO THE
ANTENNA +26 VOLTAGE IS FED TO THE P3 RELAY WINDING OF UNIT 1464 MAKING
CONTACTS 1, 2 ARE CLOSED. THROUGH THESE CONTACTS +26 V VOLTAGE
(IGNITION) Is FED TO on CONTROL DESK THEN succEssIVELy FLOWS ACROSS
NORMALLY OPENED CONTACTS OF RELAY "START", SIGNAL READY BLOCKING RELAY
(RELAY (64) SYNCHRONIZATION SIGNAL BLOCKING RELAY (RELAY 163) AND IN
THE FORM OF COmMAND "LAUNCH" +26 V Is FED TO THE LAUFICNERS.
AFTER THE MISSILE HAS TAKEN OFF APPLICATION OF cOMAND "LAUNCHER
READINESS, TO RELAYS P4, P3 OF UNIT 146211 if#004041####W#1461514#16
IS CEASED. THE CIRCUIT Is RETURNED TO THE INITIAL POSITION BY MEANS
OF THE RETURN ELEMENTS EITHER AUTOMATICALLY (wFEN +26 V VOLTAGE Is
SUPPLIED FROM THE COMMAND GENERATING SYSTEM TIME MECHANISM TO RELAY
Plo WINDING) OR MECHANICALLY BY BUTTON RETURN. PRIOR TO THE LAUNCHING
OF THE MISSILE THE 1(72 MISSILE RANGE COORDINATE UNIT OPERATES IN SLAVS
GATE SETTING MODE. IN THIS CASE TF E INTEGRATOR IS CONNECTED TO THE
OUTPUT OF THE SLAVE GATE SETTING CIRCUIT GENERATING THE VOLTAGE
PROVIDING A NECESSARY FIXED DELAY IN THE VARIABLE DELAY CIRCUIT. THUS
IN THE SLAVE GATE SETTING MODE THE TRACKING GATES OCCUPY THE DEFINITE
INITIAL POSITION. UNIT K72 IS CHANGED OVER TO THE AUTOMATIC TRACK
OPERATING CONDITION MJTOMAPICALLY WTTH THE IMP
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OF THE EncK mEcTRCUTT
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: CIA-RDP80-00247A000200060001-1
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E, R E
Attachment
AT THE MOMENT WHEN THE MISSILE PASSES THE POINT CORRESPONDING TO THE 50X1 -HUM
INITIAL POSITION OF THE RANGE TRACKING GATES. WHEN UNIT 1.462M BUTTON
START IS PRESSED COMMAND START IS APPLIED TO THE LOCK ON CIRCUIT.
FIVE SECONDS AFTER THE MISSILE TAKE OFF (THE MISSILE INDEPENDENT
FLIGHT TIM) THE LOCK ON CIRCUIT IS READY TO LOCK ON THE MISSILE.
AFTER THE MISSILE SIGNAL IS ALIGHNED WITH SECOND TRACKING GATE THE
DISCRIMINATOR GENERATES THE VOLTAGE SWITCHING ON THE LOCK ON CIRCUIT.
THE LATTER PRESENTS THE COMMAND FOR SWITCHING ON THE AUTOMATIC GAIN
CONTROL CIRCUIT OF THE RECEIVING DEVICE AND TRANSFER THE UNIT TO THE
AUTOMATIC TRACKING MODE. 0.5 SEC LATER THE LOCK ON CIRCUIT PRESENTS
THE COMMANDS FOR SWITCHING ON THE ANGULAR UNIT AUTOMATIC TRACKING CONTROL
AND THE COMMAND FOR SWITICHING THE RADIO CONTROL WHICH IN TURN SWITCHES
THE TWISTING MECHANISM IN THE COMMAND GENERATING DEVICE AND CONNECTS
THE COMMAND GENERATING SYSTEM OUTPUT TO THE COMMAND TRANSMITTER INPUT.
SIMULTANEOUSLY THE DELAY CIRCUIT (3.3 SEC) IS TRIGGERED WHICH PRESENTS
THE COMMAND TO SWITCH OVER THE BANDS OF THE ANGULAR UNITS AND RANGE
TRACKING SYSTEMS AS WELL AS TO CHANGE OVER TO THE ANGULAR SYSTEM FROM
WIDE TO NARROW GATES. PRIOR TO THE START OF THE MISSILE COORDINATE
UNITS (LIKE THE RANGE UNIT) OPERATEIN THE SLAVE SETTING MODE. THE
TRACKING SYSTEM CIRCUIT IS OPEN AT THIS TIME, THE INTEGRATOR INPUT
IS CONNECTED TO THE GROUND THROUGH TM SMALL VALUED RESISTOR AND
FIXED VOLTAGE OBTAINED FROM THE DIVIDER IS FED TO ITS OUTPUT. THIS
VOLTAGE MAKE IT POSSIBLE TO SET THE TRACKING GATE CENTRE ON THE BISECTOR
OF THE VIEW SECTOR. IN THE SLAVE GATE SETTING OPERATION MODE THE
WIDTH OF THE TWO-TRACKING GATES OCCUPIES THE VIEW SECTOR OF THE STATION.
AFTER THE COMMAND FOR SWITCHING ON THE AUTOMATIC TRACKING OPERATION
MODE IS RECEIVED FROM UNIT K72, THE TRACKING SYSTEM CIRCUIT CLOSES
uruT
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AND THE GATES FOLLOW VIE MISSILE SIGNAL. APART FROM THE COMBAT
OPERATING MODE THE STATION MY OPERATE IN THE STATION MONITORING
OPERATING MODE NEEDED FOR OPERATION MONITORING PERIODICAL INSPECTION
AND MAINTENENCE ETC. UNLIKE THE COMBAT OPERATION IN THIS OPERATION
MODE THE START COMMAND IS NOT APPLIED TO THE LAUNCHERS, THE STATION
CENTRALISED MONITORING SIMULATING EQUIPMENT IS CONNECTED AND
INDEPENDENT EQUIPMENT TEST MAY BE ALLOWED FOR SEPARATE CABINS.
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