SOVIET MANUALS FOR EQUIPMENT CARRIED ON THE MIG-21F-13 AIRCRAFT, INCLUDING THE ASP-5ND SIGHT

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP82-00038R001700230001-9
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 422
• Document Creation Date: December 22, 2016
• Document Release Date: February 17, 2011
• Sequence Number: 1
• Publication Date: July 21, 1965
• Content Type: REPORT

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IN FORMATI ON REPORT .
CENTRAL INTELLIGENCE AGENCY
This material contains Information trtfeotins the National Defense of the United 8tstes within the meaning of the Espionage Laws, Title
It. A.B.O. 6eos. 793 and 794, the trananiwion or revelation of wbiob in any manner to an unauthorised person Is prohibited by law.
NO FOREIGN DISSEM
COUNTRY USSR REPORT
SUBJECT Soviet Manuals for Equipment DATE DISTR. 41 July 1965
Carried on the MIG-21F-13 Aircraft,
Including the ASP'-SND Sight NO. PAGES
DATE OF
INFO.
PLACE &
DATE ACQ.
50X1-HUM
Soviet English-langage an is
associated with the K-13 air-to-air
aircraft
data are given.
Attachment Noo Description
1 Temperature Pickup P-S of Free Air Electric
Thermometer, 15 pages.,
2 Range Computer VRD-2A,No. 015.99.94, 0 eratin
and Maintenance Instructions, 21 pages and
pages of figure .
;Attack and Slip Angles Transmitter Type
DUAS- Description and Ins a ation
Instructions, pages I us 3 pages o Ligures.
Aircraft Automatic Si t T e ASP-5N
Technical escript~on~ p pages. TTiis sight
is employed with the R-30 cannon, ARS-57M (S-SM)
and KARS-57 (S-5K) rockets, and guided
missiles US (sic), andbay operate inlcon-
'junction with the SRD-5MK (KVANT) range-only
- I-
rr Overload Warning Unit MP-28A, 24 pages-and ~6
pages o figures.
NO FOREIGN DISSEM
csou. I
r.d.d.d b.- ?.,.~..w
d....gwd..9 ..d
STATE CIA ARMY NAVY AIR NSA OCR SAC
Navy , Airffl-Q., Army/F5-1-C
(Notes Field distribution lndkoted by "#".)
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TEMPERATURE PICKUP fl
OF FREE AIR ELECTRIC THEgA1O,%1'ETER
S CRc
150X1-HUM
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page
Purpose and Standard Equipment ..:a............a. 3
operation Prinoitle .~.w eee?eee.eoeae...eeoeleeo~oe
Couotraotion .e.....e....ee..e.Soh s..ae......1?S .. ?
Basic Specifications ?....?.......:ee.e...o.? '? ..
Assembling ?....e....eee....ee......e.s.???.. ee e 8
A. Pickup Assembly .ooeseeeoeseeaeeseeeeoesee ..?ee 10
Wiring ?....e.o.. a:em??..?........?.....ep..~.. 10
B.
VI. Troubles and Remedies ?eoooe?eo???eoea'oaieooeliee.o? 11
o.?oe,eeeve??ee.oo.ee',
VII. Maintenance ????e??e?e0 eose.. 12
VIII. Test procedure ..........?me?eeve...w.woe.e.....A.e23
A. Error Check ..., .:............o...o.~...?....o a
B. Insulation Resistance Check ?se.soeev.e.e.0?ge. 14.
IX. unpaoking and Storage .. ?. e.? ?..e.?..:?..'..ea.. 15
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II
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DISSEM
NO FOREIGN
JTemperature pickup (pig.1) is designed for remote measur-
ing of ambient air stagnation temperature complete with the TH1
indicator or other equipment.
The set of temperature pickup 1I?5 includes: ,
1. Temperature pickup 11 5 i...coee.?...e.....eee R poi
eee.o,eaes.eo,oooeosa.e oOp~'
2. Certificate ............ ,
Ti. OPERATION PRINCIPLE
The operation of temperature iokup 1I-5 is based on properties
of metals (nickel wire, in pertiou,ar) to change el?otrio reeist-
anoe with temperature flu lion. Each temperature value me sured
corresponds to a definite value of eleotrio resistanoe.
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t `
5~ t
nv ; ~Ik'i P ?: W~ a~ C'~tA w..".i~ rv~'~+T~t6~ f~ Aih, :~ tid 7 r+'t ,i r . , i . ~..
_ 77777777777
r
III 50X1-HUM
Electric .raaistor of the the al element of the ten peraturre,
pickup in disposed at the ',narrow eotio8 of the pickup (Pig?2)
representing ,a convergent-diverge t nozzle. The > rowwest socati"on
of the:nozal, ie called oriticala
The oonvergent-divergent nozzle po aseeeea the fob! loving;.
l subso; i? speed is acoelor $ed
property; an airflow running at a
l
in the convergent. seotion and deo leratod, ;in the' divergent (30;o-
Lion whereas, a ouporconio airflow io doO9 tad in tho oo + rgont
section and aooelerated in. the d'orgen? seotionm
FIG. 2. TEMPERATURE PICKUP DIAGRAM
Consequently, the operation of the temperature pickup is
based'on that during the flight the air enters the pickup
confuser (convergent section of the nozzle), and sinoee the moment.
the airflow speed equals M Q Oo5_(M number equals the ratio of
flight.speed V to sound speed a, laeo M irrespective of
further speed increase, at the convergent critical section of the
pickup critical conditions set up, which are characterized by the
sound local speed.
in critical conditions the ratio of the temperature, sebeed
by the thermal element of the pio1up9'. to the temperature of
completely stagnated airflow 'is a1 constant value which equals
,where T is a temperatures sensed by the pickup thermal
element, ex-pressed in degrees of absolute ~,,eOBYQ .,.
(oB), ?iaoo. d.~ C9 tT -+ 2/3?(tT is a ,tempera wive
sensed' by the pickup thermal element g expressed
in 0C);
.
~ is a temperature of oonapletely stagnated airfldw.
expresoed''in degrees of 'absolute, scab (oi~)a lase
SECRET
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50X1-HUM,
To a ?~ 273? (t0
ie a temperature Of completely
staagr ated airflow capresoed in ?C)?
Stagnation temperature is a t6mperature of. or air at a
critical paints I .e. at the point of an object at', hatch a:Lr speed
equals zero.
Conners on of kinetic energy into potential one (enthalpy)
and vice versa may occur au a reeu.t of oompreeuion ow m neion
of the airflow in the narrowing on !!Widening 3 duet
The kinetic energy of the conv
arto
into the potential
energy.(entbal P
Py) s and the air temperature booomea oqual to the
stagnation temperature.
Thus, the temperature of the air-at the eritjoal ? eotSloaaa'l ie
not equal to the temperature of the andieturbcd a aaflovA ,d*
e. oeedo it ' by value AV2 which depends, o*B the aP;oo ~of the
inoomiug airflow.
Tile air temperature at' the cri;tlaaal, eootion 16 woforrod o
as stagnation temperature To
where AV i.e a dynamio addition to ' ?tea?apora tutu;
A k s f
is a true temperature
T true
truo of dogrnos of
absolute scale (?K)0
Besides, the dsraa a of glow a to goat ?n and tompera tuna ri
of the air streaming over obJeo o i a1 r 0) '10 ??(ityo 0
the air vi6codity at thin'bound . or i:of to
gnats a
formed at the curfaoo of a t"iva m1 ?dj DUO?
U the boundary Jay'
r peer , h
-zero (apt the au; aoa
of the piokup thermal element) ote 6o
46 corltl,*62 speed va'a- uo? t;J
'Owing to the difference ft :,o .oe
~ A ~e oont~ NOW air
layers in the vioinity of the ther=W1 w~1 s' er1 a
??l
' ` '
iaotion aria e8 whichawefiber
Ds . opt ofIe at
_ ~.p _ I s 3
? a "+ "~a'`"a.'rrj
`~hO ambient air
a k ""
e
t
I
M
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pert ' a$ aaaya~r '$~ ? , h A
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The pickup meaoureo the airflow temperature Ooneed by ite
thermal element
1 ?peed 11 w 0 (quality factor F~ a 1)0 the pickup me? Turco true
To determine, a true temperature of the ambient ar the 201-
Quality factor f is defined from the Chart (pig03) dapend1n
on the M number determined inetrumentally0 Qualit ?aot(ar N is
calculated theoretically and i' proved expert nt1;gym
The above expressions chow that on the g roue at, when the flight
temperature of the ambient airs
Temperature pickup 11-5 (Pig.4) designed to . 2aaoura a absent
air temperature le non-detaohablo In oonotruotion it oonoiato of
the following baeio components: thI orwal elemcbt 2 homai 60 diffuser 1, ooni SECRET
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N0 . FOREIGN DIM.-,
(b) checking the hestipg circuits for operation,
(o) checking the vanes for jam?ingI
(d) checking, by moving the vanes, the potentiometers
for output relative resistance.
SECRET
NO FOREIGN DISSEM
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9q
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Fig. 3. Electric Circuit Wagrw of Trrtosnitter
1 -Picot-stoic tube Iwadma; 2 - soile of slip aymminrr b+tbti 3.- MsIs of
attack uan.diner has lsq 4 - ?,,gls of our poesodemeari 3 - ss& of seed.
Potentiometer.
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AIRCRAFT AUTOMATIC, SIGHT
TYPE ASP-5N D
TECHNICAL DESCRIPTION
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AIRCRAFT AUTOMATIC SIGHT
TYPE ACII-SHA
TECHNICAL DESCRIPTION
SECRET
NO FORM' DISSEM
50X1-HUM
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C O N T E N T S
Pag
Part 1
Chapter I. SIGHT. SET
1. Sight Units .................................. 9
2. Aooompanying Papers .......................... 9
Chapter II. PERFORMANCE
1. Taotioal Data 10
2. Optioal Data .............................. .12
3. Bleotrioal Data ........................... 12
4. Operating Data ............................ 12
5. Weight .................................... 14
6. Dimensions ................................ 15
Chapter III. FIRE CONTROL PROBLEM AND DEDUCTION
OF OPERATING FORMULAS
1. General Fire Control Problem 16
2. Deduction of Operating Formulae Computed
by Sight ....e.e....~......o ...............ee? 22
A. Correotion for Target Notion
(angle of lead) ............, ............... 24
B. Correction for Projeotile Drop
(elevation angle) ......................... 26
Co Correction for Aircraft Slipping ..e....... 28
D. Indicated Time Formula Computed
by Sight .................................. 29
B. Operating Formulas Computed by Sight ...... 30.
3. Sight Functional Diagram at Firing Mode
,of Operation ................................. 32
4. Firing at Ground Targets ..........?.......... 34
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NO FOREIGN DISSEM ...,. 4
Chapter IV. SIGHT MAIN IINITS, THEIR PRINCIPLE
OF OPERATION AND FUXCTIONIJG
?
. 1. Main Gyro
se........e..e.~e..........e.....e.e?
2. Zero Gyro ...............e.................,.e.
3. Zero Gyro Amplifier(YU) ......................
4e Electron Relay P9 ..e..eeee...e........s....o...
5? Altitude Unit ........................,...?.?...
M
6. Voltage Regulator CE-4 ...e ..............e.....
A. Circuit Diagram ................?............
Be Voltage Stabilisation Process .........?.?...
7. Parameter Automatic Follow-Up System .:??....?.
'8. Automatic Introduction of Range .......e........
9. Manual Introduction of Range ..~ ...............
10. Range Indication Circuit ......................
11. Indicated Time Follow-up System .......,..e....
12. Introduction of Attack and Slip Angles ...ee...
13. Construction of Aircraft Slip Corrections ?....
A. Construction of Aircraft Slip
Correction Horlsontal Component, ........?....
Be Construction of Aircraft Slip Correction
1Vertioal Compoi.ant ...................... ...
14. Introduction of &Llistio Characteristics
of Employed Weapov .......ee.?..e..a.e.e..e.o..
15. Setting of Sight C,,eration Modes ..........,-..
Chapter Y. DESCRIPT~IN OF SIGHT KEY DIAGRAM
'1. Illumination a n d Na.-ning L ps ................
2. Sight Heaters ...... a......... ?...e............
A. Sight Head Heater ......e..........?...i.?..
Be Zero Gyro Heater ......................
3. Look Switch ????
4. Eleotromagnetio Lind. ;)r Circuit ...............
5. Damping circuit ...`, ..........................
6. Electric motors of 11"t Head And Zero Gyro .,~.
7. Purpose of Contacts l f 04M Operation. Modes
Change-Over Relays ?.?'?..?..?.........?..?.....
8. Operation of Sight w:.enI ? pirIng Shelia
and Itookets .......,??I
T-SPUTITRIM
36;
42 t.
48'
53,1
60
61
62'
65
66.,
68
71:
73
74 ,
r?
77'
78
78
79
82
82
84
85
85.
86
86
86
8?
8?
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 Chapter VI. SIGHT D83IGx
11. Sight Head ...............?.........
A. Sight Head Optical Systeas ...................
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(1) Relays PC-13-10 ....
(2) Relays P11-5 and PH-?
(3) Heater Relay 4U-Asey :.-323 ? ............. 129
50X1-HUM
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8. Sight Head Gear Train .e...~..e.........0...? 96
C. Sight Head Design ........................... 97
(1) Housing with Objective and Refleotor
97
(2) Front Cover with Gyro Unit. 00.0.0.90.0000 98
(3) Plano-Parallel Plate Unit ............... 100
(4) ReRr Cover with Sight Reticle Cirole'
Follow-Up Unit .......................... 102
(5) Bracket with Light Filter 696066600094090 105
2. Computer ...................................o... 106
A. Computer Unit. Gear Train ................... 146
Be Computer Des oript ion ....... 0 . 0 0 0 0 0 , 0 . 0 0 ? . ? 0 . 107
3. Zero Gyro ...................................... 111
A. Zero Gyro ................................... 111
(a) Gyro with Eleotrio Motor 111
(b) Inductive Transmitter 113
(o) Gyro Correotion System ....o ............. 114
Be Zero Gyro Base Plate 115
4. Zero Gyro Amplifier ............................. 116
5. Control Box .................................... 118
A. Distribution Box 118
Be Relay Box ........................e.......... 119
6. Altitude unit .................................. 120
A. Altitude Unit Gear Train .................... 120
Be Description of Altitude Unit 121
7. Relay with Base Plate .......................... 123
Be Voltage Regulator CH-4 ......... ................ 124
9. Brief Description of Electric Motors,
Types ? )II 4M, A r--6 and 2-3. 5M ? ....... o o .... 127
10. main Components of Sight Cirouit ............... 128
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NQ FOREIGN DI~$ M .,
50X1-HUM
--- 6 ----
Part 11 .Page
Chapter I. BZQOI2BIIXPT8 ?OR BIGHT NOW3 X11
AND ARR/NO r 01 AIRORAPP
1. General Requirements ........................... 131
2. Special RequirNents .....?..........?.........? 132
3. eight Laying Inatruotions .... ..............?..?. 133
Chapter II. MATCRING slGBT ICU- ,51%
UNITS PROVIDING FOR ?IRB CONTROL
PBOBLU SOLUTION
1. Retching the Sight with Bader Ranging Units ??
??
135
2e Ratohing the Sight with AYAC Tranasittei' .???
??
136
Chapter III. IUSP]WTIOX AND CHBCLDIG 08 BIGHT
A. Outside Inapeotion of Sight on Aircraft .e..e
137
Be Cheoking of Bight ..........?..??so*.??ee.?e?
138
Chapter IT. CCI BAT IMPLO?1[g/T 01P SIGHT
.10 Switching Procedure ???.???,oe?.e?e??eee??..?ee?? J39
2. Sight Operating Inatruotions e.?e?..?e.....?ee?? 139
A. Attach on Airborne Targets ?..?e?.:e..???..? .140
Be Attacks ca Ground Targets ..................~. 143
C. Bight Operation at Boabing .................. 145'
Chapter V. Bgpzoyggj 0? 8PTAA BBT
AID IADMUOB 0? BIGHT
1? Tools ...? .......................?...........:.?
2e Aooessorie/ ?ee.??????o?...???.??.???ee???i?..?? 146
4
? Spare Parts 146'
.................................... 147
Chapter VI. ROUTINE nim
A. Ileotrio rotors At-4u and 8e Bleotrio Rotor ?????????????
130
~ 3.511 ..~.r?????;?..i.s.?.
00 Lnbrioation . 0
f
153
~:;
o
sight Bead Gyro ihaiversai
Joitit Azles and Central Bearing
? ?. ? e e ? 0. e.. a
D. jilatirieatleQ
r
158
o
zero
Gyro %,versal Join
Ailed and Osatrai Bearing ..e....:.
aecL1r
Malt Dow
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NO. FOREIGN DISSEM .
Page
Chapter VII. INSTRUCTIONS ON SIGHT OPBR TI0N
AND MAINTENANCE
Chapter VIII. TEST EQUIPMENT KDSCA POR CHIDCII1G
SIGHT ACH -5HA
1. Main Data on KDSCA Bquipment ..................e... 165
2. Check of Sight with Test Equipment Set Kll5CA ....... 16?
Chapter IX. TRANSPORTATION AND STORAGE OP BIGHT
1. Servioe Life and Storage Guaranteed 00.000000.000009176
2. Transportation ................................?????176
3? Sight Storage ......................................180
4. Main Changes in Sight Design Bffeoted from
Beginning of Sight Manufaoture ?...? ................180
APPENDIX 1. Trouble-Shooting Chart ?.......e....'.....?183
APPENDIX 2. Cheok Tables ..............................196
APPENDIX 3. List of Parts Pertaining to Key Diagram 0..199
APPENDIX 4. Sleotrio Diagrams of Sight
Main Cirouits .............o...............212
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50X1-HUM
Part I
Sight ACA_SHjj is mounted on fighters to ensure accuracy
of firing fixed oannou mounts, launching rockets and dropping
bombs in a dive.
Sight ACA-5HJ is a version of the ACA--5H sight raod.tfied
with a view to increasing its accuracy when firing rockets
and improving its operation.
Sight ACA-5HA is a complex optical and eleotro-meohanioal
unit that should be treated with utmost care.
Before operating the eight one should thoroughly study
its Construction, operation and maintenance regulations.
Sight ACfi-5HJ Technical Description consists of two
parts. The first part deals with the sight pertormanoe,
operation and construction. The second part describes eight
Mounting and arrangement on the aircraft' operating regula-tione. Chen-' n
8 procedure, testing equipment operating
instructions and eight employment in combat.
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r
M
1r,,1i1
~7-' ~ ,~. 11
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50X1-HUM
Chapter I
910HE
The complete set of sight ACf-5HA includes might units,
accessories, spare parts, tools, ?reoting not and papers.
(a) Sight head
(b) 'Computer
1. SIGHT. UNITS
(o) Zero gyro with base plate
(d) Zero gyro amplifier
(e) Control box
(Z) Altitude unit
(g) Electron relay with brio plate
(h) Bracket with light filter
(i) Voltage regulator
5HA - Assy. It
5HA o.Aesy 42,
5HA. Aasy 3,
5HA Assy 4,
5HA Assy 55;
5HA - Assy 6
5HA - Asey ?,
5HA - Amour 119
CH-4
X The sight is manufaoturel with removable ballistic
unit C-5U in the control be c.
2. ACCOMPA!YIBG PAPRRS
(a) Sight Technical Desoripiion ............... 1 copy
(b) Sight Certificate ........................ 1 copy
Sight accessories, spare pars, tools and erecting eel;
items are listed in Part II of Present Description.
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NO FOREIGN DISS10
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T - 10 50X1-HUM
Chapter II
PER ORMANC$
1. TACTICAL DATA
1. Sight ACA-5HA is to be employed when firing
cannon HP-30, launching rockets and dropping bombs in a dive.
2. The sight continuously and automatically computes the
total angular correotion of firing and shifts its sighting
line in respect to the Neapon axis through this total angle.
3. The sight oomputf3 the total
angular correction within
the specified limits al the following conditions of firing:
(a) at airborne t~ets_;_
range to target 200 - 2000 m.
flight altitude 500 25,000 m.
ambient temperati:;e -60?C to +50?C
target speed 500 - 2250 km/hr
own speed 500 .. 2500 km/hr
(b) at_ round to gat
diving angles
range to target
flight altitude
own speed
target speed
20? - 500
200. - 2000 me
500 - 1500.n.
600 - 900 km/hr
0 - 90 km/hr
4. In vase of dive )ombi ?
the si
ht i
g
s employed as a
simple collimating a at with h the
down in the plane of alroraft symmetry in8 line being shifted
lead angle. In this i se to provide for the
the lead angle ig not
ran
e
-
g
+sva 30' to 100.
5. The maximum ttal angular correotion ooepnted
sight .? 13 by the
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6. The eight computes angular corrections only for Ono
type of weapon, The sight Modes-of operation arcontrolled
by the selector switched on the sight head bracket.
7. Bight ACIi-MA is employed with the :following weapons
(a) cannon IM-30;
(b) rockets - APO-57M (C-5y), KAPC_5? (C_5K);
(o) guided missiles YC.
Due to presence of replaceable ballistic unite, to we
the eight for the preolse launching
only" a new ballintio unit shoulbe manufactured. of a now type . of rocket,
4. When launching rockets APO-57 (C-5n) the sight should
operate in conjunction with attack and slip angles trans-
mitter AYAC.
9. Sight ACf-5}[J may operate in conjunction with radio
range iindero CPA-51,1K (I DAIIT) and with any other range
finder provided the relationship of the output voltage and
circuit oonneotiona are preserved.
Range finders ensure an automatic introduction of the
target range into the sight.
10. The sight provides also for manual ranging effeotecl by
an outer-base optical range finder.
Target dimensions, picked up by the eight, range from 7
to 70 m.
11. The eight has a movable retiole circle of variable
diameter with a pip in the centre.
The retiole circle varies its diameter from 1?150 to 80
only at combinations of bases and ranges indicated in Fig.2.
12. With the gyro in FIXED (HEflog.) position, the circle
may be formed whose angular value of radius changes from 11
to 70 mile by actuating the BASE CIRCLE (BA$A - K01MUO)
handle. In this instance follow the procedure and regulations
for firing at air-borne and ground tar eta"
standard collimating sights. 8 prescribed for
13. The eight computes angular corrections within the
specified limits:
at t ? +20?C in 3 min.
at t . -400C in 10 min.
at t ? -50?C In 14 min.
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50X1-HUM
The time neosssary for eight heating im included into this
value.
14. The target motion synohronisee with the retiole9 pip
movement in 3 - 5 eeo.
Brightness of circle image at least 30 stilbe
Brightness of ventral pip at least 36 stilbs.
3. ELECTRICAL DATA
1. The sight precisely computes angular corrections when fed
2. OPTICAL DATA
ObJeotive diameter 95 W2
Objective focal length 200 mm
Exit pupil distance 375 mm C as as measured
from the o entre of
the refleotor)
Pip diameter
Width of circle line
with D.C. of 27 V 710%t single-phase A.C. of 115 V T5%, 400 4.p.a.
At a-voltage of 115 Y``+10% the eight is still serviceable. 11
2. The power, consumed by the eight, comprises: I
D.C. current
at normal conditions 300 W
at t ? -400C and below 400 W
A.C. current 120 Y/A
3. The sight oomputing systems employ gyroscopio Waits,
type AC11, and potentiometrio bridge-type circuits, oonsum
ing D.C. and employing electron relays as sensing elements
and the reversing eleotromagnetio couplings as follow'-up
elements.
4. The might computing circuits are fed with a regulated
voltage of 22 10.3 V D.C.
4. OPERATING DATA
1. The sight operation mods-is set by the aeleotor,s arrang-
ed on the eight head bracket.
When changing over the mode of operation the selectors
say be set to the following positions:
0 .. PC AM - for rook.t lanalohing when oper ptj the
light via AYAC transmitter;
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iR FDI
11 1, I'l 1111.1 1%
fl l,. rlJt)'r~ ~'i
~;'~.J,.(- ,:~ ' 114~r,'i ~t 1.11 ~3'~ 111.
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0 PC H for rocket launching when operating the 19ight 50X1-HUM
via altitude unit;
0 HP-30 - for oannon firing;
S - for dive bombing.
2. Sight changing over for operation with the ranger
finder of this or that type is performed on the ground by
actuating special selectors in the. control box and oos-put6r.
3. The sight is out in to'automatlo ranging by setting
the RADAR - OPTICS (PAMO - OrIT. )I switch on the eight
head braoket to the RADAR (PAUO) position. The sight e
be changed over to manual ranging either automatically,
when the range finder signal TARGET LOCK UP disappears,
or manually by setting the RADAR - OPTICS switch to the
OPTICS position.
4. Setting, type P0, in performed on the
ground by plac-
ing an appropriate ballietio unit into the sight control
box.
5. Range, altitude and indicated time are visually
followed on the ground by proper ooalee of the computer and
the altitude unit through oonneoting the radar ranging unit simulator end special vacuum set to the eight..
6. In flight the target range may be visually oheoked
by the range indicator mounted on the eight head bracket.
7. When the radar ranging unit looks up a target, green
warning lamp LOCK-UP (3AXBAT), mounted on
the eight halad,
goes on.
U. Break off is oheoked by red warning lamp BREAK OPP
(BWXOA) arranged on the sight head. The lamp goes on fl, 80 at a target range of 600?40 m. and keeps on burning at
less range.
9. The eight field of vision is ohooked by the oamera
gun, type CM-45.
10.,The testing equipment, (MCA) is to be attached to
reference oonneotors provided in the control box and the zero gyro amplifier.
The manufacturi plant produces sights ~ p ACA.-SRA
equipped with infra-red sighting 'devise CKB-52 intended to
deliver aimed fire at-night.
The sighting devise oonatruio.
t1on and operation are outlined in separate
descriptions).
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4111W W_
- -- 14 ---
50X1-HUM I
Special optical attachment (03C) projects the eight
reticle pip to the objective of the infra-red sighting
device. 'infra,-re
gig.3 shown mutual arrangement of the sight heads
sighting device, and optical attachment unit.
device the
Due to mounting of the infrerTesighting ? following
sight head and its bracket have undergone
changes
1. The sight head body has a slot to secure the optical
attachment unit.
2. The shape of the sight reflector provides for a suitabli
arrangement of the sighting device in respect to the pilot's
eyes
3. The light-filter bending radius is increased to clear
the optical attachment unit when the light filter is not to
the inoperative position.
The sighting procedures do not change when the sight
operates in conjunction with the infra-red sighting devio(u.
5. WRIGHT
1. Sight units weight:
(a) sight head . . . . . . . . . . . . . . . . + . . . . . e . . . . . . m . gel kg.
(b) computer .......?....? .................?. 6.0 kg
(o) zero gyro with base plate 5.1 kg
(d) zero gyro amplifier ?.........e.......... 4.2 kg
(e) control box ?ee.e.?..o......????.s..o...e. 9.5 kg
(t) altitude unit o.o...?e?..o.?....?o.o.e..
.e 2.2 kg
(g) electron relay .....................+..
.. 3.2 kg
(h) voltage regulator ?o.e....e..s......ee.o? 405 kg
(i) bracket with light filter ............0.. 3.7 kg
(4) range manual introduction potentiometer .. 0.04 kg
2. Maximum sight set weight 30.0 kg
3? Maximum weight of sight not in packing
box .........................e............ 125.0 k9
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15
6. DIMSIONS
Sight units overall diieneionss
(d) zero gyro amplifier ..o..a......o
(q)' control box
..o.?..?..o?.?...?s..
(t) altitude?unit e?s.??s??.?...e?e.o
(g) electron relay ................?.
(Ii) voltage regulator ...............
(i) bracket with light filter .......
(o) zero gyro with base plate
(a) sight head .e...?.s.....Y......?o
(b) computer o??e??oo????e...~.s....?
..~o._....._,.
262x363x278 mm
220=157x246 ma
235x132x153 mm
218x1302160 mm
262x162$136 mma
192=115x115 mm
2352103x154 ?`
270x160x150 ma
234z278x269 mm
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50X1-HUM
Chapter III
P1 CONTROL EROBLEM AND DEDUCTION OF OPERATING FORMULA3
1. GENERAL PIRB CONTROL PROBLEM
When firing shells and rockets the sight should enEure the
position of the weapon necessary for ongAgin2; the target.
To hit the target one should exactly know how the
projectile travels after departing the gun (law of projectile -3
motion) and the distance that the target covers during the
period of projectile flight (law of target motion). The law
of projectile motion makes it possible to direct the gun
in such a way as to hit the given point of apace. The law of
target motion enables the gunner to make allowance for, the
target travel during the period of projectile flight. To hit
the target it is necessary to compute on the target
traiaotory the point which will be simultaneously reached by
the target and the projectile. Considering at the moment. of
tire the collision point as a given point it is possible to
set the weapon so that the projectile travels through this
point.
Hence, the problem of aiming at a moving target is conventiag 1
onally divided into two parts:
(1) determination of proieotiler--with-target collision
point;
(2) aiming at a given point of collision.
The tighter weapon is rigidly secured to the airframe and
its axis may be set in parallel to the aircraft fore--and
aft axis or as some constant angle to it in the aircraft plane
of symmetry.
Therefore, the target will be engaged provided that
an
angle Is formed by the fighter fore-and-aft axis and the
movable sighting line. Sight ACf_5HJI eolvea the fire control
problem by autometioally sad continuously oomputing this
al
d
d
e
os
ifferent tiring condition aad defleoting the
1
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17 --
The solution of the fire control problem boils down to
the calculation of target travel and the projectile drop
due to gravity as it covers the predicted. range. The
influence of the aircraft slip angle on the projectile path
should be also taken into account.
As it is known from mechanics, the movement of any body
may be determined only in relation to another given body.
When solving the fire control problem for a fighter, the
air is considered to be a reference body. Hence, hereter
in this description the target and projectile movement will
be considered In ,.,reference to air.
Movement of thtarbet as the projectile covers the
predicted range is compensated for by deflecting the cannon
in the same direction through a certain angle relative to
the righting line at the moment of firing. This angle is
termed angle of lead.
For the time of projectile flight the moving target will
travel from point Ao, where it wan at the moment of firing,
to another point Ay (Flg.4). To engage the moving target the
cannon should be directed forward in line with target
movement no as to allow the target and the projectile to
collide.
In other words, it is necessary to make allowance for
the target speed. Point Ay, where the target and the
projectile should collide, is called the predicted point
or point of collision.
To determine the point of collision the law of target
motion should be regarded. When firing, the law of target
motion is taken into account by assuming this or that
hypothesis of the target movement. In case with
sight ACII-511A the target travel during the time of
projectile flight is assumed to be straight and uniform
(yq oonet).
This assumption is quite natural in case with a fighter
shooting at a bomber as the heavy-weight bomber can not
sharply change its speed during the time of ;?rojeotile
flight. Accordingly, point of collision Ay is situated on
the extension of vector. I at distance L i'roa Initial
point Ac. Triangle OA0Ay is termed a predaiotion triangle
and its component.:
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.rw' yr'
L - linear prediction,
initial range,
predicted range.
ea the target moveg atraightly,and uniformly, the
linear prediction equals:
L - vn ? ty
where ty - time of projeotile flight to the predicted point
The prediction triangle is formed by lead angle 4,
and target course angle q.
Angle ' may be determined by applying the sine theorem
to the prediction triangles
____
s q I
projectile flight is projectile mean velootty yoP
M YoP
Y
At present conditions of firing the lead angle does not
exceed 150. Therefore,it is possible to assume
that sin pr+. Then the formula of the lead angle baoopess
V sin q
(1)
v
op
This formula can not be used to compute the lead angle in
the automatio eight, type ACf-50. Hence, the lead angle 141
expressed by the values which may be directly measured
while aiming.
One of such values in angular velocity of the lice of
sight (on). The angular velocity of the line of sight is
the rotative speed of the line connecting the firing airoratt!
with the target (1Pig.5).
This vain. may be directly and precisely measure at
sighting.
pied the expression for th) angular velocity of tbo
line of slgb-t supposing that the sight somputes gay angle and that the sighting`is properly o cied out, As?~.s
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known from mechanics, the angular velooity of rotation of
line 1 in space equals the difference. between the lateral
velocities of the section ends divided by the section
length (1ig.6). Lateral velocities Vn2 and V a" the
components of the section ends velocities perpendicular to
the section length. Use this rule to compute the angular
velocity of the line of sight.
From the prediction triangle (11g.?);
Vn2 -V1 ? sinq
Vn, - V1 ? s in 4, a V1 4,
VQ?sinq-V1 ?+
therefore, u4 ?-------
0
This formula indicates that value VA *sin q any be
expressed by the angular velocity of the line of sight:
VA ?ain q - ?A0 +V1 ?4,
Using formula (1) arrive att
--- 19 ---
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Vtt ? e i.n q w 1a . AO + V1. +
Vop Vop
(2)
A0
Vcp - Vl
The multiplier of w11 expressed in time units, is termed
computed time and designated by Tp.
Formula 4, ^ w4 ? Tp (3)
is used to compute the lead angle in sight ACII-5HA.
At given ballistics, the computed time is determined by
range A and altitude H. Therefore, at given balliatioe, the
lead angle depends on three values:
wH; Ili H.
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The amount of the elevation angle depends on firing
?tion angle in the vortioal plane.
-predicted range is compensated for by constructing the elcra..
The gravity drop of the projectile as it covers the
altitude and projectile muzzle velocity. However, when
a a S (4)
Projectile drop S is a ballistic function of the range,
by the relationships
conditions, weapon ballistic characteristics and is determined, j,,,
-the deflection of the line of eight from the aircraft fore-
constructing angle asp it is necessary to make allowance for:4i
up v V tW
op 1
ax a a c1' 1.1
elevation angle is to be fed into the eight.
get the required angle of lead.. the eerreete& value of +ha
computed value of the lead angle calculated by the eight. Tod
elevation angle. This causes a change of the computed angular
velocity of the line of sight, and hence, a change of the
lead angle plane, but in the plane deflected through the
of sight is effected through turning the aircraft not in theI
Divide the elevation angle into two oomponents,
or
zontal corrections.
-4144 vertical oor
reotiona, and all the angular oorreotions in the wing plane ..
h
s
Hereafter, all the angular corrections
in the airorat$
plane of eymaetry will be oonventionally to
by using two components:
adz - vertical component (in the airoraft
plane of
symmetry);
horizontal component (in the plane perpendicular to
the aircraft plane of symmetry).
The elevation angle should be constructed in the vertical'?
plane. In sight ACfl-5111A the space position of the vertical ,j
plane is not determined, so the elevation angle is oonstruoti
ax ^ a 'op 3 Vop 8
ap? ^ . _r
vop vl lty vop as yl~ "~" (6)
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Projectile gravity drop Sl (Pig-8) live in the vertical
plane. The projeotion of the projeotile drop on the plane,
.perpendicular to the aircraft axis, equalan
AC .3. i ooeX
Divide section AC in the plane perpendicular to the axis
of the banked aircraft into two components running along
axes I and Ti
AA - AC ? cone AB - AC . nine
Hence, when dividing the elevation angle into two
components, the latter are expressed as follows:
a~ A 000U? 000 A
s
AE .--1 sin06ooeR
Ay
where e - angle of bank;
A - angle of diving.
Thun, the components of the elevation angle equal:
ax - az? coee?oos A (7)
ax.- sine?ooo A (8)
The aircraft angle of attack and slip angle affect the
,projectile velocity at the point of departure. Due to the
angle of attack the projectile trajeotory deflects down in
the fighter plane of symmetry whereas due to the slip angle
it defleoto in the wing plane in the direction of slipping.
Mark the angle, through which the projectile trajectory
deflects at the moment of departure due to the angle of
attack a as as (Fig.9).
Applying the sine theorem and considering that angles a
and pa are rather small, we have:
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T 50X1-HUM
.~j
To make allowance for the attack and slip anglers the sight
should compute the angular Corrections with the aid of exprea.
sions (9) and (10).
V
pQ. ?p
Vol
Mark the angle, through which the projectile trQieotory
deflects due to the aircraft slip angle 0, as po. Then
some angle termed a total angular correction.
Thus, to solve the fire control problem the weapon axe
should be deflected with respect to the in. of sight through
~o - projectile muzzle velocity vectors
~1 - fighter velocity vector,
Vol - projectile total muzzle velocity vector,
a - fighter angle of attack,
pa - correction for the fighter anglo of attack.
The total angular correction includes corrections for
target motion, projectile drop, and fighter slipping (Pig.lo),'
Sight ACR-51Q computes corrections in two planes: in the
aircraft plane of symmetry and in the wing plans.
The total angular oorreotion egaale:
d+e-4,+ubp +p1
where - angular correction for fighter slipping.
2. DEDUCTION OF OPERATING PORMULAS COMRITED By SIGUr
A. Correction for Targe i tipn (Maly of lead)
The Piously obtained theoretical relationship for
the Computation of lead angle 41 ^ Wd? Tp ^ u .
Is
difficult to be-solved. Y?p gl
In sight ACfl-9j the lead angle is computed b
a free gyro. The aiming by means of
is effected by a movable sighting
line through turning the weapon (aircraft
chooses the siroraft ) ~?? The pilot
angular velocity so as to have the
sigbtina line directed at the target. With a
traoking of the target, the sight syn, ~?
angular Velocity of line ti'v-*Is at an
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- 23
When tracking the target, the angular velocities of the
fighter and of the line of eight are connected by the
relationship uuo - rugs + 4,, In case of a synohronaus track.,
tng of tie target,,the relationship beooses
wo - eiq+* (11)
This relationship is easy to be understood from Pig.ll.
ao - aq + where
ao and aq - angles determining the position of the aivorafi;
axis and of the line of sight in relation to the selected
reference line.
+ - lead angle.
In case with the angular velocities, we have:
ao-a~+4, orwo -u~+d? there
b - rate of lead angle change.
When the fighter is turning, the gyro processes in the
direction of the aircraft movement with' speed gip and its
axis always lags from the aircraft axis through angle pp
(P1g.12).
The rate of precession equals:
wup - wo - 4p , where
? - rate of mismatching angle change.
raking allowance for equation (11), we arrive at:
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(12)
(14)
To ensure the adequate oontrollability of the line of
eight, semi-automatic optical sights are pro7ided with
optical transmission ratio depending on mutual arrangement of
the optical elements (gyro mirror, reticle, objective).
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. utp - 91 + 4, - p
The gyro theory states that
1
A ? "'RP
angular rate of the gyro precession.
Substituting uL we have:
(13)
i.e. the mismatching angle in in direct proportion to the
? p~
^~ ? (u + 4 -w)
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The optical system transmission faotor is designated,
by p and equals
p . a , where:
? - angle of lag of the gyro axis from the aircraft axiei
- lead angle.
Introduction of factor p into formula (14) gives:
+ m (wg++ -p+)
4- ' (wg - K 4, ) T
M
b
em
e 4 W - ? i ntroduoea an .rror into The lead angle
computation. However, the analysis has proved that the.
absence of this member (K - 0), though resulting in preoisi
synchronization of the line of sight and target movement,
as the sight reticle (and, henoe, the line of sight) would
become too movable.
With g > 0 the line of sight is a sort of damped, i.e.
the sight reticle becomes lees movable and is easier to be
controlled. Therefore, coefficient Y, termed a damping rati
should exceed zero.
It is evident that the maximum angle of lead, that may
be computed by the eight constructed by this pri
noi
le
.
p
,
depends on the gyro axis maximum deflection angle ;pmx and
transmission faotor p.
However, the both values
following considerations.
The increase of the gyro maximum deflection
.a rise to technical diffiotilties connected with ghee gives
increased dimensions, and adversely affects the precision
of the gyro operation. The decrease of factor
reduction of the damping ratio and worsens LW149 condi..
tions. Therefore, it is desirable that the ratio p does not go down below the rated iraiueo
sion
110 ?
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The adequate controllability of the line of sight may be
also obtained by changing gyro flexibility through oreating
an additional moment proportional to the angular velocity
of the aircraft axis.
When the gyro is acted upon by the additional moment, the
additional shifting of the gyro axis odours. Due to the high
transmission factor of the optical system, the line oT sight
is similarly shifted.
The ACQ-5HR sight, whose gyro is acted upon by thee, main
and additional moment., computes angle 4 as follows
- 4'OCH - 4'Aon
O+Aou - angle formed due to acting on the gyro by the gyro
unit correction coils moment proportional to the aircraft
axis angular velocity.
where
wo - aircraft angular velocity;
TO - changed indicated time;
P - proportionality factor.
When substituting T' for T, the angle of deflection of the
sighting line from the sight axis, provided that the oorreo--
tion coils moment does not act upon the gyro, equals
4'oc$ ( - a) (17)
Using equations (11) and (16), we have:
4-(wu-Yb )T?-P?wA?T'-
^( Ka T1P(w,+4- T
- [ w, -.gI t , 4' ] T' (1 - P)
To hatre the total angle 4, equal to the computed
angle of lead, the following equations should be observed:
TO (1-P) -'T and P - K1
1 - P
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NV f'VKCIVN viaavn,
::-
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where: Yz .. required damping ratio ensuring the beet target'
the damping ratio
traoking conditions. In sight ACII Sfi~
egnals.0.2. It is ensured by the optical system tranemisei
.factor p (partially) and by the correction ao0sent, dreated
by the sera gyro. IL ? 1.066; P ^ 0.11167?
Thum, eight 1CH-5HA solves the following formula of the
lead angle:
The main component of the angle of lead +00 is wholly
constructed in the plane of target tracking. Prom now on,
for the sake of convenience, we shall proceed with the
assumption that the lead angle is constructed by two
oomponehts:
To asks an allowance for the projectile drop, the sight.
should compute the following angular corrections:
ax s ax ?cos 0 ?oos 1
arm -,a2-sin ? coo
The construction of angles aZ p and aZ r by these for?ar1ass
would result in complicated construction of the sight,
which should he furnished with the transmitters of the
dive and bank angles, geometrical plotters and other
devices. Therefor., the toraalas are changed so as to
compute the angles without considerable oomplioation of
the sight,
The formulae for aZ is rearranged in the following way.
Assume that at dive angle ). and bank 9 the fighter mater)
? turn with angular velocity wo (P1g.135.
In we of a correct taro (wit t slipping) lifting
fwoe P coaatesbslanoes the oomponaut of the atrorett
WSi d * O f asdd o.ntz'ifugsl f"" F
af! 1 Q~ a ~? ?
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x a I (ALT + D) - ga?T + 2B
Composing oonatant coefficients, arrive aft
( .SIT' +8
The angle equal to e'T is constructed by the sight
together with the vertical omapnnent of the additional a
of lead.
The expression for the lead angle vertical 'component
becomes
- (w4B - t 4B ) T' - -P-w08 + a'T
Constant member b' is computed in conjunction with the
vertical correction for the aircraft slipping. .
0. Correction for AiEoraft Slitroing
As it was already disoussed , the correction for the air:
craft slipping is composed of two ooaponents A. and A., I
which depend on the fighter angles of attack and slip in tk~
wing plane.
y
pa l.:. a
Vol
where:
V
00 :L p p
T0l
a - fighter angle of attack;
fighter angle of slip (in the wing plane).
Pig.9 shows that value pa (or po) depends on the oorre
tion of fighter speed VI and projectile aassle velooity To
At the moment of firing the nuasle velocity of the rifled
'cannon projectile considerably exceeds the fighter epee.
Therefore, the value- of these angles ie so small 'that they
may be practically disregarded and the Projectile direction
of Path may be considered to be aligned with the d
a? the aircraft (weapon) axis. direction
The rooket launch }
in6 speed-is considerably loos than the fighter speed, therefore, at a 'certain all,
Path will deflect from the airorsft foe'
through a considerable eagle whisk?oaanot
diat4e
6+ ed %
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 .. + ;raYTR~Lf,1 r't . a1~'?') ti' r+'~ l d~ l 7 a kl i,
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Coefficient A as well as functions ip (IIo ) and f (Ii)
are different for eaoh type of projectiles.
B. Operating Formulas Computed by Sight
As it was mentioned above, the-angular corrections are
ooaposed of the vertical and horizontal components.
1. The operating formulas of the lead angle ooaponente area
*D - (WLW - B ? TO - P?wOB 'T' (18)
2. The elevation angle operating formulas are:
(19)
(20)
(21)
3. The operating formulas for fighter slip oorreotions
are:
Pa ^ A?a
(22)
(2'3)
4. In aocordanoe with operating formulas (18), (19), (20),
(21), (22), (23) we obtain the operating formulas for total
angular oorreotions:
d ^[ wUB - ()L -0 1) 4-BI ?T'- P?wCBOT' + a'T + B' + A'u
4Er - I W - (P - 1) `r, ?T'- P?Wcr 'T' - P' ?w0r T' + A?a
Bat wo - w q + 4 , so we have :
- (WCM - l+ p ? ?B) TO (1-P) + &'T'+ B' +
}Zr ( wqr - -11++PP' 'Or ) (1-P-PI)?T' + A?0
Narking P-1 +P - S an9 -1+P-P' e
1 - P B 1-P-P' pr
SEA: RET
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we arrive at:
(WUB IB ' 4a )'T+a'T+ X'+ AM
r
1-r
of xP .
+r
) ?T+A'
In sight ACH-5HA KB - 0.2 and Kr . 0.4118.
The operating ,formulas for the total oorreotion appear apt S
4~B 0 (w0.248 )?T+a'T+B' +A'a
~Er a. 0.85 (wUX - 0.41184r )'T + Asp
(24)
.
(25)
The components of the lead angle are constructed by the
main gyro with participation of the zero gyro.
The variable portion a'T of the elevation angle vertical
component and aircraft slip correction A?a are constructed
together with the respective oomponente of the additional
lead angle through the employment of the zero gyro.
The values of coefficient a' for different balliotio
characteristics are as follows:
HP - 30 a' . 0.24
APC-57 u C-51 a' as 0.29
The constant portion B' of the elevation angle vertical
component is constructed together with the aircraft angle
of attaok oorreotion through turning the Plano-parallel plate
(oorreotions are computed only for re rockets).
The values of ooeffioiente B' and A for different bala.
listio characteristics are as follows:
APC-57u -5M) A - 0.75 B' _ 0.267?
KAPC-57 (c-5K) A m 0.54 1W 1.8?
When tiring with rockets C-5k, used against ground
targets, the average value of u equal to aop ? 1.7670 is
introduced into the sight, whereas the elevation angle
vertical component and angle of attack oorreotiou, are
compensated for by the expression B'+A?u op which
introduces their constant values.
The operating Xormulas -for indicated time T appear as:
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T - A+(y (A0) z (H' I
For .different ballistic oharaoteristios expression (26)
has the following seaningst
T30 - 0.5 + v ( A0 ) 30- f (8)3o
where +v AO ) 30 - 1.22 ? P (AO )HO - 0.2162
f (8)30 f (H)HO - 0.225
if (A0)20 - 1.81A - 0.49 (when A 10,6 kn.)
9 A0)30 0.6A2 + 1.09A - 0.274 (when A > 0.6 km.)
f (8)110 - 1.248 - 0.0554?H + 0.oo14SH2 (Ho bi.)
) po [f(H)po - 0.321]
T51 - 1.05 + 1.3055. (a o
where:
9 ( AO)po - 0.27035?A2 + 1.7057? 0.6472'( Aoki.)
f (H)po - 1.2159 + 0.00052947.82 - 0.032325.H (Hp ka.)
In case with rockets C-5X the indloated tins is oonsidei.
ed to.be constant and equal to T - 3 sec.
3. SIGHT FUNCTIONAL DIAGRAM AT FIRING
MODE OF OPERATION
The final result of the sighting process during air
shooting is the construction of the total angular oorreo-
tion composed of the lead angle, elevation angle, and
correction for aircraft slipping (when firing rockets).
Pig.14 represents the functional diagram of the sight
operation in oars of firing rockets; Pig.15 represents the
functional diagram of the eight operation in cast of oaanon
firing.
Solid lines in the diagram are used to indicate
electrical oonneotions, dash and dot lines - meohanjoQ
oonneotions, dotted lines - assemblies and units that an
not included into the sight oovplete not.
r - sight main gPro;
HP - sight sero.gyro;
? taro gyro amplifier;
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33
W( and MA - magnetic corrector and inductive transmitter
of zero gyro;
AYAC - attack and slip angles transmitter;
a and a - angle of attack and slip angle;
aT A - initial range to target;
0
H - flight altitude;
T - computed time;
wq and we - angular.velooities of the line of eight and
of the fighter;
S - target wingspan (base);
d - angular size of the reticle diameter of the
outer-base optical range finder;`
J conet - 22-V voltage,D.C. supplied to the main winding
of the zero gyro magnetic corrector;
J 3036 - 115-Y voltage, A.C.,400 c.p.a. supplied to the
exciting winding of the zero gyro inductive transmitter,,
.The diagrams show that to solve the fire control problems
the following parameters are to be fed into the eight:
relative angular velocity of the target wu; fighter angular
velocity 10c; initial range to target ,A0; flight altitude H;
angle of attack aaT; slip angle a and ballistic character-
istics of the weapon. To measure the range by the outer-base
optical range finder, the target wingspan 1 ;(base) is to be
fed into the sight.
Target relative angular velocity wa is measured by the
sight head gyro unit only in conditions of continuous follow-
ing the target by the line of sight, as in this case the
angle, through which the gyro axis deflects from the fighter
fore-and-aft axis, is proportional to the angular velocity
of the target.
Fighter :angular velocity we is computed by the zero gyro
with the amplifier. Angular velocity wa in fed into the sight
computing circuit in the form of current proportional to wo.
Range A0 is measured by the radar ranging unit or by the
outer-base optical range finder and is introduced into the
eight in the form of voltage depending on ,Zj0.
Altitude H is measured by the barometric altitude trans-
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"50X1-HUM``;
oT"i1,9 ~ 7
0
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--- 34 ~--
mitter and fed into the eight in the form of resistance
which is a function of H.
Angles of attack a
and slip an
l
aT
g
es p are measured
by MC and are introduced into the eight in the form of
voltages depending on a8T and p.
The projectile ballistics is compensated for by rated
resistors connected to the appropriate portions of the
computing circuit.
The target wingspan ( base ) is introduced into the
sight manually by turning the lever of the base potentio-
meter. In so doing, the resistance proportional to the
target wingspan, is fed into the computing circuit.
The most of the sight input parameters as well as sight
operating voltage, generated by the proper transmitters and
power sources, are fed into the distributor where the
electrical circuits are commutated.
Using the fed parameters the sight computing unit8
compute the following values:
(1) :umpu.ted time T;
(2) angular correction for target prediction;
(3) elevation angular correction;
(4) angular correction for fighter slipping (only,
for PC rockets).
4. FIRING AT GROUND TARGETS
Firing at ground targets with the employment of
eight ACf-SH,j has no principal differences from tirin
at airborne targets. The only difference g
firing C-5g rockets the target In that when
time Tp as well as elevation angles a?ar18 e not measured a~~d
assumed to be
constant (Tp - 3 sec.).
Besides, when delivering fire at ground target
eight computes th
th
,
e
e vertical component
of th
e fighter
slip correction, which is a
functi
on
of the angle Of attack I :?
rated for certain firin
oonGitione ions
g
wh
9 en fi
r'g at ground
targets, the angle of attack equal
e
a 1046?
op
The total elevation
angle and correcti
+ I
on for the ae?~g?
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--- 35
angle of attaok equal 2?49(when firing with x.-37
(C-59) rookete.
The above oorreotion OOZT po s to the following
firing oonditionet
plight altitude H 600 a>w.;
Range to target Ai 1200 a.;
Diving angle A 30?.
Fighter speed Yl ? 750 kw/hr.
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Chapter IV
SIGHT MAIN UNITS. THEIR PRINCIPLE OF OPERATION
AND FUNCTIONING
1.MAIN GYRO
In eight ACf1-5HAT( the angular velocity 1s mea&ured and the
lead angle ie ^omputed by means of a free gyro. Gyro is a
rapidly spinning symmetrical body (rotor) possessing one
fixed point. Gyro has a property to keep its orientation
in space constant, provided no external forces are applied
to It. Being acted by the moment of external forces tending to
turn the gyro about some axis misaligned with the spin axis,
the gyro will rotate in the plane perpendicular to that
moment. This rovement of the gyro in called precession.
The direction of precession is determined by the following
rule: when the external force direction is turned through 900
about the gyro spin axis in the direction of rotor spinning,
the direction of force will indicate the direction of preces-
sion (N.$. Zhukovsky's rule).
The main gyro is intended to compute the angle of lead.
The gyro construction is presented in Fig.16.
The gyroscopic unit consists of two main parts: a gyro
proper and an electromagnet. The gyro proper consists of
axle 2, one end of which mounts dome 4, the other and mirror l in a special mounting. The gyro is freely suspended
from pulley 12 by gimbal 13. The pulley is driven by the
electric motor through spring belt 11.
The gimbal ensures three degrees or gyro freedoms gyro
rotor can rotate in the vertical and horizontal Planes about
the respective axles of the gimbal and is spinning about its
own axis. Point Of where the gimbal axes inters)ot, is
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located on the gyro spin axis-,and coincides with the gyro
rotor C.O. and with the centre of the dome spherical surface.
The electromagnetic unit oonalsts of housing 8 (sumufao-.
turgid in the form of a sleeve), four pores 6, and oover 3
with pole 5. The sleeve, cores and oover with pole are made
of permalloy possessing adequate magnetlo oonduotivity- 4
Cores 6 and pole 5 are arranged opposite to eaoh other
looking as if one continues the other. In the gap between
them a gyro dome is plaoed. Arranged between the sides' and,
cores of housing 8 is a main coil with winding 10. The
second portion of winding 10 is wound on pole 5. Wound on
winding 10 is negative winding (Ky3) 9.
Cores 6 carry four additional coils of gyro correction
with windings 7.
The electromagnetic unit is intended to create forces-
acting on the gyro.
When current flows through the winding of the main coil,
a iignetio field is developed in the space around the
winding, i.e. magnetic lines of force arise. The more in
number of turns and current intensity, the stronger In the
magnetic field. The magnetic lines of force of the coil
field are always closed when leaving the coil or entering
it. Therefore, the magnetic field produced by the main coil
has the shape of four closed magnetic fluxes. Bach magnetic
flux flows through the core, outs the gap between the core
and the pole, and hence, the gyro dome, and is closed
through the cover and housing.
The electromagnetio unit provides for a complete symmetry
of the four pores in relation to axis AA which is the axis
of the electromagnetic system.
Pig-17 represents four magnetic fluxes intersecting the'
gyro'dome. When the mapetio lines of force are out by the
rotating gyro dome, made of an eleotro-oonduoting material
(aluminium), small currents, known as eddy currents, appear
in the points of intersection. The magnetic field developed
by these currents interact with the original magnetic field
(oppose it), hence, a. force is set up in the point of gyro
dome cutting the magnetic flux, which opposes the dome
rotation.
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- 38
I
50X1-HUM
So, the interaction of the eddy current magnetic fluxes
with the electromagnetic unit magnetic fluxes gives a rise
to forces acting on the gyro dome, i.e. on the axle of the
gyro rotor. These forces are presented in Pig.l?-.and?
marked as P19 P29 P31 and P4. The magnitude of each force is
a function of the magnetic flux flowing through the Dore,
and of the linear speed at which the gyro dome outs this
flux. The following relationship exists between the mentioned
values
KO 2?V
0
00 magnetic flux;
V - linear speed at which the dome nuts the m gaetic
flux (due to gyro spinning);
S -- proportionality factor.
The magnetic flux depends on the number of coil turns
and on the intensity of the current flowing through Its,
00. K1 IOW
where
I - current intensity;
W - number of turns;
I?W - ampere-turns of the coil;
Bl - proportionality factor.
Dome linear speed V. under the poles depends on the angular`
velooity of the gyro spinning ? and on distance a - the
distance from the gyro axis to the core oentre. This speed
equals!
V ..1??
Then the relationship for force P becomes
r ^ ax (I.W2) b
where N . KK12A - proportionality factor.
This means that each of the four forces P19 P2, P3, P41
whioh oppose the dome rotation, is proportional to the
square of ampere-turns in the coil sad to the distance ?rc
the point of force application (oore oentre) to the gyro
,axis. When the axis of the magnetio system oaiaoides with
--SECRET-.------
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t f~
1'li
~
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--- 39-
10
the gyro axis, all the four forces are equal as the asgnetio
flulea and distances a are equal. Henoe, the dome is acted
upon by four forces equal in magnitude and equidistant from
the spin axis (Fig.18) which do not produce the resultant
force, but create the braking moments overcome by the gyro
electric motor*
when the axis of the magnetic system aisaligns with the
gyro axis (gyro axis ZZ ii turned olookwiss in plane X
plane of horisontal cores - thrpag angle ip in relatioi to
aagnetio system axis AA), forces P as well as distances a
are not equal (Fig.19).
At this conditions
a4 ' a2' a3 > ale P4 - P29 P3 '' Pl.
The resultant of.foroe P' exceeds zero and is directed
along the straight line parallel to axis yT to the aide of
greater force P3.
This resultant ants on the gyro and makes it process in
the plane perpendicular to the force direction, to-the side
of the greater force, i.e.foroo P3 (Pig.l9).
When the gyro preoeeeeu, It tends to align its axis
with magnetic system axis AA.
The more is mismatching angle T (in Fig-19 -
distanoo AA - ZZ), the greater is resultant P', and, hence,
the angular velocity of the gyro precession.
When the amount of angle 9 becomes less, force P' and
gyro precession velocity decrease. With angle 9 s 0, F' W 0
and i, - 0. Hence, the force, acting on the gyro, and
the gyro precession angular velocity are proportional to
$isaatohing angle ip and to the square of amp.r -turns.
p' a p(,W)2,p
The moabnt of resultant force P':
Mp ? F1(I.W)2(p
Moment Yp is oounterbalanoed by gyrosoopio moment MrI
Mr Y F2?wnp
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As the momenta are equal, we arrive at:
Wnp - F3 (x.W)2.~v
p, pl, FZ and F3 " coefficients.
Marking P3?(T'W)2 - A, we haves wlip A ;,-~
wherefrom Y r r-Wnp
Thus, at a constant magnetic flux mismatching angle If
is directly proportional to the angular velocity of gyro
axis spinning. The gyro axis processes in the direction of
the gyro frame rotation lagging behind from the frame axis
of symmetry through angle T.
Therefore, such gyroscopic systems have been termed
systems with lagging gyro.
The magnetic system pores of the gyro unit are provided
with additional coils which create an additional angle of
deflection of the gyro axis from the airoraft fore-and-.aft
axis. When the current flows through the windings of the
additional coils, the magnetic field is developed around
them, which interacts with the main coil magnetic field.
The windings of the additional coils are so connected that
the main magnetic flux of one core decreases while that of
the opposite core increases. The magnetic fluxes of the
opposite cores being unequal, the gyro will be acted upon
by the forces which are also unequal. The resultant of then
forces acts on the gyro making it preoess. The gyro will
preoess till the resultant of all the forces equals zero,
As a result of the precession, the gyro axis deflects
through a certain angle wAcn-
Fig.20 represents the scheme of forces acting on the Ej"
when the current flows through the windings of the vertical
additional coils at the following conditions:
9 - 0 (Fig.20a) 9 ? TAOA (Pig.20b)
The value of the additional
angle of the gyro axis
deflection depends on the correlation between the main avid
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F 7
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mmse. 41
additional magnetic fluxes or, which is the same, on the
correlation between the ampere-.tug Of the main and
additional ooils.
The larger is the current flowing across the windings of
the additional coils and the more is the number of the coil
turns, the greater is the angle through which the gyro axis
deflects. As the magnetio system cores are arranged by p$ii
in the vertical and horizontal planes, the additional angle
is constructed by the eight in the torn of two components. II'
the current in the gyro additional windings 18 changed as a
.function of the aircraft angular velocity and value TO
(funotion T), the additional angle will be' constructed in
accordance with the following relationship:
4'AOn" 1''wO'T'
The total angle of the sighting line deflection should bes
? = 4~OCH +AOA = (wu e 4) T
The current in the main coil is changed as a function of T
by using potentiometer 117 whose brush travels proportionally
to time T. The connection diagram of potentiometer IT7 and
of the gyro main coil (consisting of two partas Kyl, and $y2)
is presented in Fig.21.
R73,
first portion of the main prediction
coil (wound on the pole of the gyro
cover).
second portion of the main prediction
coil (wound together with coil 7 on
a brass frame). 3
1073, R779 8077 "fixed resistors.
l ~, aT,878- oompeniaating resisters (for temperature
3 compensation).
K - reference connector terminals to measure
the prediction ourrt,it.
Resistors 878, R73! $077 are arranged in the control box;
8073 and lI - in the computer, and R77 . in the eight head. 07
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t' i
~illh
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--- 42
In the operating gyro the allowance should be made for
different outside moments, acting on the gyro (ventilation
moment, friction in bearings, etc.
Due to these moments,'
the instrument error in computing angled may extremely vary
in various sights. To make allowance for the outside moments .
each gyro is furnished with coil Y3 , whose
Betio flux
opposes the main coil magnetic flux and
may vary tude. To control the current flowing through coil oil "Yadjusting resistors R30 and 8030 are incorporated in the
sight head.
0
2. ZERO GIRO
The zero gyro is intended to measure and to transmit
aircraft turn angular speed w 0 whose vector is arbitrarily
directed in the plane normal to the gyro axis.
The speed is measured in the wing plane and in the air-
craft symmetry plane to obtain its horizontal and vertical
components.
The zero gyro differs from the gyro dealt with in the
previous section and used for computing lead angle in that
it is provided with an inductive transmitter of mismatohjYig
angles-between the axes of the aircraft and the gyrosoope. ?
Fig-22 shows the diagram of the zero
the vertical component of the aircraft angular for measuring:
The horizontal com anent of the ~8ul speeedspeed.
P angular speed is measured
by means of a similar circuit arranged in the plane normal
to that discussed above.
As in the previous case, one end of zero gyro axle
Ties aluminium dome 4 with aloof 5 came
unit (111K) placed opposite. Main oo~il~leofotherreOtion system
device is similar to the main coil of aggU?tio
but is eupplie8 with D.C. Voltage; ? the sight head gyro'
magnetic flux 0 o of the p?lessneat]y, the
Perrmanemanent.
Correction coils 2 located on
oorreotion device the oores?of the Magnetic,
are eerier-connected In pad". The, ars
out in in such a way that one coil of the pair decre
the main magnetic flux of the system while the other +aass
iaoreasis it.
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The other and of the gyroscope axle carries armature
6 made of permalloy. Placed opposite the armature is the
inductive transmitter KA. The latter is a four pole system,
each pole being made as H-shaped magnetic conductor 8. pitted
onto the magnetic conductor cores are eight coils with
windings. Your of coils ?, set on four magnetic oonduotora
are primary excitation coils connected in series, their free
ends being connected to the A.C. source. Remaining four
ooile 9 (secondary coils) are serves-connoted in paira but
directed in opposition, their free ends being connected to
the input of the zero gyro amplifier
YHI'.
Angular speed w 0 1s measured as follows.
With the gyro set to the zero position, the inductive
reactances of the circuits formed by the coils of two
opposite cores of the inductive transmitter are equal, and
the secondary windings of these coils produce voltages equal
in value but having opposite phases. In this instance, the
total voltage supplied to the amplifier input has the zero
value and there is no current induced in the magnetic coils.
Thus, the moment acting on the gyro equals zero.
When the aircraft turns with certain angular speed wo,
the gyro spin axis starts lagging behind the aircraft axis
and, hence, behind the magnetic system axis, and a mismatch-
ing angle grows. This disturbs the equality of the
reactances of the circuits formed by two opposite cores of
the inductive transmitter, as the portions of the core
poles overlapped by the armature are different. Therefore,
the voltages induced by the secondary windings of the
inductive transmitter are different too. The output of the
inductive transmitter yields the voltage difference that
is delivered to the phase-sensitive amplifier. The operation
of the latter is described below.
From the amplifier output, the current flows to the
magnetic corrector correction windings, its direction being
dependent on the voltage phase across the amplifier input.
The current appearing in the coils of the zero gyro and the
current flowing in main coil 1 ( nro ) create the moment
generating the angular speed of the gyro precession.
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50X1-HUM'
(I
The gyro spin axis deflection grows as long as the gyro
precession spend is below the angular speed of the aircraft
turn.
Simultaneously, the correction moment acting on-the gyro
and the angular speed of the gyro precession will inoreaee.
When the zero gyro spin axis has deflected from the
inductive transmitter axis (aircraft axis) through a oertaia
angle depending upon the aircraft angular speed, the correo.
tion moment reaches the value at which the angular speed of
the zero gyro precession equals the angular speed of the
aircraft turn. Thus, the moment or rather the correction
current, the moment depends upon, serves as a measure of thi
angular speed. In case of small angles of the gyro spin axis
deflection, the moment Is practically a linear funotlen of
the current in the correction windings. Hence, the value of
the correction current is proportional to the aircraft tun
angular speed measured (the maximum angle of the zero gyro
deflection does not exceed 30' that is why the gyro is
called -zero gyro ).
As the angular speed of the gyro precession is equal to
the angular speed of the aircraft turn, the relation of tho
gyro spin is expressed by:
H1?0ell sH.000A*Ke
where :
Hl - gyro kinematic moment;
S - constant coefficient,
-be - magnetic ?lux generated by the gyro main coil;
AOK - flux oreated by the gyro correction coils.
The main coil of'the zero gyro correction eysteu reoeiva
the permanent voltage, therefore, magnetic flux mo is
constant, too. From the above relation, magnetic flux atW
and thus the value of the current in. the zero gyro correc-
tion coils are proportional to the aircraft turn speed:
In . DZ . wcs
Th
t
e curren
in the additional coils of t
gyro must be proportional to time T and we:
IAg ^ B . -wCB V T' ' B1' WCB ' V' T
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1 I'~
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Ohange of current IAB in the function of w0B is
obtained by connecting the additional coils of the sight
head gyro to the circuit of the zero correction coils where
the current is proportional to was, The circuit of the
additional coils is connected in series with the zero pry
correction ooi.ls, and, therefore, the current in the addi-
tional coils is proportional to wCB.
The current is multiplied by V T by means of by-pass
resistor n9. The potentiometer resistance change law is taken
so that the turn of the potentiometer slide proportional to T
changes the current in the gyro additional winding according
to the law:
IAB a B1wo?Y T
When the zero gyro is employed to compute at. T component
of the elevation angle, factor a' may be termed apparent
angular speed. This angle is computed according to the
principle true for the additional angle in the vertical plans
when following up the lead angle.
While computing the a'? Toomponent of the elevation angle,
the zero gyro operates in the following way.
Apart from the correction windings, the vertical poles of
the zero gyro magnetic correction device carry additional
windings 3 (KKrn) which pass the current proportional to
factor a'. In this event, the gyroscope is actuated by a
moment that deflects the zero gyro spin axis. When the gyro
spin axis deviates, the vertical channel secondary windings
of the inductive transmitter produoe the voltage difference
delivered to the zero gyro amplifier. The current proportional
to v-Alue a' is fed to correction coils 2 (K )from the
amplifier output. In this instance, the moment acting on the
gyro, due to the current running in coils 3 (Kara) is
balanced by the moment 'due to the current running in
coils 2 (Kara), and the gyro axis will deflect through a
definite angle.
The zero gyro functions differently when computing the
additional angle of lead and the vertical component of the
elevation angle. In the first case, the aircraft angular
speed induces currents. in the zero gyro correction coils,
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and in the second case, the moment created by the additional
coils of the zero gyro induces the currents, i.e. when
computing the vertical component of the'elevation angle
the. apparent angular speed is created as if by additional
coils of the zero gyro and is proportional to factor a'.
Thus, in the case of the aircraft angular speed in the
vertical plane, and with the rg circuit energized, the
vertical correction coils of the zero gyro pass the ourrent
proportional to the sum of speeds:
'KB a E1 (WCB + as).
The eight head gyro deflects in the vertical plane
through additional angle ~Aon and through the variable
component of elevation angle a''T.
Different ballistics require different current propor-
tional to factor a', and the change is obtained by outting
in ballistic resistor' connected in series with coils 3
(K1rn). In the case of oannona, the resistors are connected
by means of relay contacts P2-5; in the case of rockets, by
means of setting a proper ballistic unit and nutting in
relay contact P3_S .
The eight has two channels for connecting the additional
coils as the zero gyro measures the two components of the
aircraft turn angular speed. The horizontal channel differs
from the vertical channel in that:
(1) The horizontal channel is provided with additional
coils Burn (instead of coils H
horizontal component of the airHrd craftuslip for
correction and
for check d
ing the horizontal channel serviceability by
means of checking unit FX5C .
(2) Resistor 8215.18 connected to the vertical channel
circuit by the contacts of relay P1. When the damping
button In depressed, relay P15 operates 'and 22-V voltage
is supplied to the vertical correction oirouit through
resistor B215.
This provides for maintaining the average
elevation angle vertical oo:a value of the
ponent, hence, the time,
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48
3. ZERO GYRO AMPLIFIER (Yin')
lA
The zero gyro amplifier (yHr) is an electron emplifier
comprising two Independent craannele of a similar design.
Each channel amplifies signals in proportion with the
horizontal or vertloal component of speed we.
The amplifier generates the correction currents propor-
tional to Its input voltages which the zero gyro inductive
transmitter feeds to the amplifier horizontal channel along
wires 002 and 126, and to its vertical channel, along
wires 002 and 125 (Fig.23).
The direction of the'current at the amplifier output for
every channel is determined by the voltage phase which in turn
depends on the direction of the zero gyro armature deflection
and, hence, on the direction of the angular speed.
The current intensity at the amplifier output is propo;N
tional to the input voltage amplitude which is in turn
proportional to the doviation angle of the zero gyro armature .
and thereby to the angular speed value.
Wires 6:,, 69 of the horizontal channel carry the correction
current-.9 fed from the amplifier output to the zero gyro oor-
reotion windings Rrr and to the additional windings 1r
of the sight head, and wires 71, 79 of the vertical ohannel,
to windings KHre and K .,respectively.
Every channel of the amplifier comprises two stages; A.C.
voltage amplification stage and the power amplification stag.,
the latter serving at the same time as a phase-seneitive
rectifier. The stages are connected by transformer-type
connection.
The voltage amplifier for every channel utilizes half of
valve J15 (twin triode 6HIH).
Interstage transformer Tp-2 serves as a load for the
horizontal channel of the voltage amplifier, and trans-
former Tp'3 for the vertical channel.
The anode circuits of the voltage amplifiers of both ohe-mDe1U
receive 120 V D.C. from the full-wave rectifier based on
valve A6 (kenotron 644H).
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-. 50 so-
Thus, the grid serves as a control eleotrode whose
potential is changed to govern the anode ourrent.
The grid of valve 115 receives two voltageez bias
voltage Uo, generated by anode current flowing along
resistor R4(R8) and voltage Uax from the zero gyro induotive
transmitter.
Capacitor C3(C5) is intended to smooth the ripple voltage'
generated by resistor R4(R8).
The grid receives the negative bias voltage through grid
leak resistor R3(R7).
Operation of the horizontal amplification channel is dealt
with below.
The anode current changes if the grid receives
voltage UBX of different signs fed by the zero gyro
inductive transmitter.
The anode current in the primary winding of trans-
fon4er Tp2-I changes to transform increased voltage in the
secondary windings of transformers Tp2-II and Tp2-III propor-
tional to the voltage running from the zero gyro inductive
transmitter. Capacitor C13 is a filter of high frequencies
decreasing their effect on the next stage.
? Power amplifier. The power amplifier is based on
w s w w
valves AI and A2 (twin triodes of 61i12C type) for the
horizontal channel, and on valves 313,1114 for.the vertical
channel. The anode circuits of the valves of the horizontal
ohannel power amplifier are fed with 230 V A.C. from the
winding of power transformer Tpl-II.
Negative bias ( -30 V to -40 V) is supplied to the grids
of valves Al and 112 80 that the anode currents across the
grids approximate to zero when the grids of valve 15
are tree, from individual selenium rectifiers BC-1. BC-
of the BCH type fed with A.O. voltage from the windings
of transformer Tpl-IV, Tpl-V. The selenium reotifiers arcs
connected so that the circuit of resistors W,.=,
R9 (R1l) passes the current in one direction only anc" these
resistors decrease the voltage delivered (with the plus
sign) to the cathode and (with the minus sign) to the grl,dd
of the respective valves through transformers Tp4..II,
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Tp2-II (Tp4-III,'Tp2-III). Capaoitors C6, 07.are intended
for smoothing the ripple current flowing from the amplifiers.
Adjustable resistors DC-1000 connoted to the oirouit of
? the valve cathodes. serve for regulating the output currents
due to automatic bias delivered to the valve grids and, for
regulating the value of the negative feedback.
The power amplifier is assembled 00 that the grids are in
the phase, and the anodes - in antiphaee. Let us assume that
points H on the windings of the transformers Tpl-II, ?p2-II,
Tp2-III yield positive potentials at the given moment, and
points K - negative potentials. In this instance, the grids of
valves h, 2 receive positive potential, anodes of valve n2-
positive potential, too, and anodes of valve. A, - negative
potential. The anode current flows through valve ,12, as
positive potentials are applied simultaneously to the anode
and to the grid of the valve in question. Both valves of this
stage supply current to the common load (resistor R6,oorreo-
tion circuit comprised of ooile Kau* Krr and other
resistors) generating in it currents of the required direo-
tion depending on the valve anode and grid where positive
potentials match. The matching depends on the phase of the
signal sent by the zero gyro inductive transmitter to the
amplifier input.
Discussed below are two oases of zero gyro amplifier
operation.
Case I.- angular speed of the aircraft is zero. In this
Instance, the armature of the zero gyro is placed symmetrio-
ally relative to the magnetic conductors of the inductive
transmitter, and the secondary windings of the latter
induce voltages of the same value but shifted 1800 out of
phase. The difference of the voltages is zero. No A.C.
voltage is fed to the-grid of valve 159only D.C. voltage
flows through the valve. The voltage across the windings of
transformers Tp2-II and Tp2-III is zero. The ourrent does
not pass through valves Il, and ]I2, as the selenium
reotifiars send to their grids the negative bias (-30
to -40 v) outting the valves off-
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- 52 -?-~
50X1-HUM
Case 2 - the angular speed of the aircraft is other than
zero. With the armature deflected from the gyro axle due to
the aircraft angular speed, the grid of valve 315 reoeives 1.0.
voltage whose phase depends on the angular speed veotorq and
? ~ 1
the amplitude - on its value. The ripple current flowing
through valve 11 and the winding of transformer Tp2-I
induces A.C. voltage in the windings of transformers Tp2-II
and Tp2-III. If during the first half-cycle points H of the
windings of transformers Tp2-II and Tp2-III and point K
of the winding of transformer Tpl-II have positive potentials,
valve )L, will pass tho current and valve 712 will not, an t:u
anode of valve J12 receives negative potential. The current
will flow from point K (Tpl-II) to point H (Tpl-II) through
transformer Tp4--I, resistor H69 wire 69 and valve 711.
During the second half cycle, points H of the windings
of transformers Tp2-II and Tp2-III will have negative
potentials delivered to the grids of valves 111 and J12
to improve their nutting-off. In this case there is no
current in the correction circuit despite the positive
potential is fed to the anodes of valve '2? During the next
half-cycle, the current flows in the same order as during
the first half-cycle.
Thus, flowing through valve ;11 are separate pulses
smoothed by capacitor C 10 of great oapaoitanoe. In this
instance, the direct component of the rectified current
flows from wire 61 through resistor H6 and the 'correction
circuit to wire 69.
The angular speed vector changes to change the phase of
the voltage supplied to the amplifier input. The positive
potentials match on the anodes and the grid of valve 312
which delivers the current through the load in the - opposite
direction, i.e. from wire 69 to wire 61.
In both cases, the value of the current across the outpat
is proportional to the input voltage amplitude.
Pilament circuits of each valve of the zero gyro
amplifier are made independent to prevent intereleotrode
punotare'of the valves (cathode filament) during operation.
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To make the zero gyro operation at able under` the a a 50X1-HUM
vibrations and to damp its notation oscillations zero
'gyro amplifier employs the negative feedback in acceleration.
If aooeleration.is present, the value of the output our..
rent in
changes proportion with the aooeleration. When the
changed current flown via the primary winding of the feed-.
back transformer Tp4..l, the seoondary windings of trans-
formers Tp4-II and Tp4-III induce voltages proportional t(D
the acceleration. These voltages' are fed to the
valves 1~ and grids-of
in opposition to the input pulse to
decrease the voltages acting on the valve
decelerating thereby
the output current increase and making the Jgrrs'',
functioning steady.
The other channel of the amplifier funotiona in the came
way*
4. ELECTRON RELAX P3
The electrical computing circuits of the sight (range
follow-up circuit, time, reticle circle and' lano-s
plate angles of turn follow-up circuits) consume plat
D.C. voltage. D.C. delivered to the electron relay input serves as a
mismatch signal.
The value and direction of this current
depend upon the mismatch between the receiving and trans-
mitting branches of the bridge. The output of the electron
relay delivers 27 V to a winding of the electromagnetic
reversible clutch so that the mean value of the current in
Proportional to the signal
at the electron relay input.
The amplification of the D.C. s r )~
i&nal fed dire
tl
c
y to the
electron relay input involves a number of technical diffi-. 41
culties. Therefore, the electron relay of
i
h
s
g
t ACfl- Q
employs the circuit where the D.C. mismatch signal in gnat fed to
put is amplified by the magnetic amplifier and
converted to the A,C, signal whose amplitude is proportional
to the mismatch signal value, the
phase depending on the. mismatch direction (direction of the current in the oontro:1
winding of the magnetic amplifier). Then,.this signal is
amplified by the A.C. amplifier and fed to the
phase..sensi?.
tine rectifier that governs the functioning of the vibration
iEl
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relay) outs in the appropriate winding of the oleo tronw4paeti,
reversible clutch 2PT-200 (P-200) ensuring the follow-up
required. Every unit of the electron relay comprises-tiro
independent channels that in no way differ from each other.
The electron relay unit arranged in the computer ensures tho
follow-up of the range and time. The electron relay assembled
amplifier. The vibration amplifier (polarized three-position
as a separate unit (Assy 8) ensures follow-up of the reticle
size and of the vertical component of the airqraft slip
oorreotion.
In Fig.26 the letters stand to indicate:
lAy - magnetic amplifier intended to amplify D.C.
signal and convert it into A.C. signal;
YHq - A.C. amplifier;
diB - phase-sensitive rectifier;
BY - vibration amplifier.
The relay has three negative feedbacks:
I - inner feedback of the vibration amplifier intended
to create vibration conditions for functioning of
the polarized relay and to uniformly change the
output signal due to change of the signal across
vibration amplifier input.
II - inner feedback between the vibration amplifier output
and the magnetic amplifier intended to decrease the
time constant of the electron relay P3.
III - outer feedback for speed between the tachogenerator
of the electromagnetic reversible clutch 2PT-200 and
the input of valve ]j1 of the A.C. amplifier intended
to improve operation stability of the follow-up driv4
and to remove self-oscillations (Fig.28).
I1E netio Amplifier. The magnetic amplifier (MY) serves
to amplify D.C. (mismatch signal of the automatic follow-up
system) and to convert it into A.C. whose phase depends upO
the direction of the current in the control winding, and ho
value, upon the intensity of the current across the latter.
The magnetic amplifier utilizes a bridge circuit. The
magnetio conductor of the amplifier is assembled of four
packages of go-permalloy discs (I, II, III, Iv) with the
following windings: SECRET
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of these windings change correspondingly, and the current is
'adjustable to obtain equality Ll?L3 ^ L2?L4, i.e, bridge
balance.
,Control winding 7 of the magnetic amplifier is connected
between the receiving and transmitting branches of the
computing oirouit. When current flows through winding 7,
zag-
netic fluxes induced by this winding will increase one pair pi
fluxes Oil 03 and decrease the other pair of fluxes 1129 141
or vice versa, depending on the direction of the current in
winding 7.
The magnetic fluxes are changed to change the inductances
of windings 1, 2, 3, 4 (they are decreased in windings 2, q,
and increased in windings*l, 3, or vine versa depending on
the direction of the current in winding 7), thus interfering
with the bridge balance, and the magnetic amplifier output
produces A.C. signal whose phase depends on the direction
of the current in winding 7, and the value, on the current
'intensity across this winding.
Negative feedback winding 9 of the magnetic. amplifier is,
arranged to decrease the electron relay time, constant.
This winding is fed with current through the contacts of the
vibration amplifier.
Transformer Tp-l mounted inside the housing together with
the magnetic amplifier serves to match the magnetic amplifier
output resistance with the A.C. amplifier input resistance.
A.C._Amplifier. The A.C. amplifier is a voltage amplifi-
cation stage based on valve 11i (6111[1) (Pig.29). The magnetic
amplifier output sends voltage to potentiometer R2 intended
to adjust the relay sensitivity.
Capacitor C1 compensates for the phase shifts of the
magnetic amplifier output voltage and suppresses the higher
harmonics. The Slider of Potentiometer R2 delivers voltage
to one of the grids of valve JIi for amplification of the
the A.C. One triode of valve ni is used in each channel of
the electron relay to amplify A.C.
Resistor R4 is the anode load of valve .4.
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Resistor R3
voltage to the
functioning of
oharaoteri8tic.
Both triodes
and capacitor C2 deliver the automatic Mae
grid of valve n1. This voltage ensures
the valve along the straight portion of its
711 are 'fed with voltage from the
full-wave reotifier based on valve J!, (6u4n),
.When A.C. voltage is delivered to the grid of valve f
the valve anode current dhangee bringing about a respective
change of voltage aoross the anode. From the valve angde,
the amplified voltage is fed to the grids of phase--sensitive
reotifier 712 through capacitor C3.
Phase-Sensitive Rectifier is a twin triode, type 6H9.R;
the grids of its both halves receive the signal from the
preoeding stogy (valve JI1). The anodes of valve 7I2 are feid
with A.C. vo.uage from the step-up winding of the power
transformer 'p-3 the sough the differential windings of
relay P1.
When th!,-e is no signal across the valve grids, every
triode of alve J12 passes current pulses of the'same value.
Flowing ' -.ong the windings of polarized relay P1, these
pulses :.,e smoothed by capacitors C4 and C5, every winding
induoL.ig equal opposite directed magnetic fluxes. In this
-lie armature of relay P1 stands in the middle posi-
tiono he phase of A.C. voltage applied to the grids of the
phas sensitive rectifier coincides with the phase of the
voltage across one of the anodes of the valve and opposes
the phase of the voltage across the other anode, depending
on the direction of the current flowing along control wind-
ing 7. The current aoross the triode with the same phases
of the anode and grid voltages increases, and that across
the other triode, decreases. Relay P1 functions due to the
difference in magnetic. fluxes.
Yikration Amplifier is three-position polarized relay Pl
(P3 - Assy 41) with four windings. Two of them (control
windings) are connected to the anode oirouits of valve J12
as described above, the other two (feedback windings) sup-
plying current by the contacts of the relay in question.
The feedback windings create vibration conditions for
relay P1. The vibration conditions are created in the
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generator (IT)yielde the negative feedback si
This
signal oppose& the phase of the signal passing from the
magnetio amplifier to the A.C.. amplifier grid to reduce the.
latter signal by the value proportional to the follow-up
speed so that'the current across the electron relay output
decreases enough to disconnect clutch 2PT-200 before the
mismatch has been followed up. The shaft of clutch 2PT-200
decelerates, and the negative feedback signal decreases.
The total signal on the grid of valve AI increases to' cause
clutch 2PT-200 to operate again. As soon as the follow-up
speed slightly increases, clutch 2PT-200 is disconnected
again. The intermittent follow-up process will continue
until the mismatch has been followed up, the follow-up
speed gradually coming down.
This is the way to obtain the smooth follow-up of the
drive maintaining the system highly sensitive and without
self-oscillations.
Fig.28 show the diagram of one channel of the electron
relay together with clutch 2PT-200.
A number of circuit components is not shown in the
diagram (e.g. rectifier, filament oirouits, etc.). The
detailed diagram of the electron relay is shown in Pig.29.
The electron relay circuit is fed with the followirgg
voltages:
27V+10%ofD.C.;
22 V of stabilized D.C.;
115 V ?5%, 400 o.p.s. =596 of one-phase A'.C.
The A.C. voltage is fed to power transformer Tp-3. Conneot.
ed to one of the transformer secondary windings are diagonals
of the magnetic amplifier bridges. The power transformer Tp-3
supplies voltage to the voltage amplifier valve 11i thzb;;3a,
the rectifier using valve J14. The transformer supplies
voltage to valves 7Ii and JI3 and to the filament circuits of
valves JIi, 1X29 n3, n4'
22 V of stabilized D.C. are fed to magnetizing windings
5, 6 and correction winding 8 of the magnetic amplifiers.
The circuit of feedback winding 9 of the magnetic ampli-
fier is fed with 27 V D.C. through the contacts of relays P
a.
and P2 (vibration amplifier).
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Connected in parallel with the control windings are
selenium rectifiers CB1 and CB2 which pass a part of the our..
rent when the ourrent exceeds 20 to (the mismatching sign,
being too great) to avoid the saturation of the magnetlo
amplifier.
The sight automatically computes the altitude by means
of the aneroid oap3Ues of unit BA-28 (BA-20).
The travel of tho aneroid capsules driven by the potentio-
meter follow-up system is converted into an angle of turn of I
, t
the sliders of potentiometers 12 and 113 introducing the value
of the altitude function into the ballistic bridge (Figs 30
and 127).
Electric motor MA-0.5 of the follow-up system is linked
with the contact disc, altitude scale and brushes of the I 1i
altitude transmitting potentiometers by means of the reduction
unit. The oontaot disc has two slip half-rings insulated from
each other.
The control winding of eleotrio motor )WA-0-5 is fed
from the winding of transformer TP-1111 through contacts KBD
(moving off the aneroid capsules), one of the slip half..rings
and limit switch KB,j (KB 22)' Capacitor 07 shifts the voltage
phase in the excitation winding through 900 relative to the
voltage in the oontrol winding. This shift is necessary for
operation of the induction motor. Capacitor C8 improves the
operation of the induction motor when changing over
oontaots KBH.
Contacts KBD, and I{BB2 disconnect the motor when the
altitude roaches its extreme values thus protecting the
meohanism from damage.
.The altitude,ohanging, contact KB, clears the insulated
portion to energize the winding of transformer TP-1111
and the oleotrio motor control winding via the slip half-ring
and ose of the oontaots KB BI (KtB2). The eleotrio motor
a-:.rts rotating to set in motion disc 6 with slip half-rings,
,ogle 1 and the brushes of altitude transmitting potentioa
meters 4 through the reduction unit.
1 SECRET
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flotation speed under 3 gr-om. load
moment ............................ > 1500 r.p.m.
Starting voltage:
at t - ?50?C not exceeding 0.4 V
at t - -60?C 000*00*0000000**0000* 0.8 V
Transformer Tp-1 is connected to 115 V, 400 o.p.s.
The electric motor excitation winding is connected to the
winding of transformer Tp-l1z produoing 35 V; the control
winding - to one of the half-windings of the transform-
er Tp-1III yielding 14 V each. The voltages in these half
windings are phase--shifted through 180?.
Unit BA-28 is rated for operation up to 30-km. altitude.
All the above components are arranged in the altitude
init.
The eleotrio motor supply circuit is assembled so that
the diso rotates in the direotion required for bringing its
insulated portion opposite oontaot KB Once the insulated
portion of the disc has oome opposite the oontaot xB He
the diso stops rotating, the electric motor supply o1rouit
opens, and the system comes to standstill.
Thus, the transmitting potentiometers keep following up
the altitude sent by the aneroid capsules.
Data of eleotrio motor, type AM-0.5: rotation upped
under no-load conditions:
at T within +2000 to +5?C eo*voeoes at least 13,OOO'r.p.m.
6. VOLTAGE REGULATOR CH-4
Note: Change of the output voltage up to 1:0.5 V in
(d) aooeleration vibration reaches 3 g.
(o) air temperature changes from -60?C to +50?C;
(b) the load ourrent changes within 1 - 3 A;
(a) input voltage changes within 27 V ?10%;
The voltage regulation keeps accurate when:
directly aoross the load with an accuracy of ?0.3 V.
voltage applied to eight ACll-5HJ. It stabilizes 22 V
Voltage regulator CH-4 is intended to regulate the D.C.
admissible under t - '-600C.
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 {tawyi- 1... 0
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---- 64
ing resistor R 136 receives the stabilized voltage brought
by wires 183 and 184. This voltage is also fed to frame p20
Movable frame P20 of the sensing unit compares the
stabilised voltage (transformed by electromagnet K 3 into
magnetomotive force of permanent magnet M which serves as
a reference.
The system is designed so that when the voltage stabilised
has its rated value, the magnetomotive forces of permanent'
magnet M and electromagnet B3 are equal but rurn in the
opposite direotions, henoe,the frame does not pass the
magnetic flux. In vase the voltage stabilized differs frog
the rated value, the difference of the magnetomotive
forces of the permanent magnet and of the electromagnet
creates the different magnetic flux which flows through the
frame to affect its magnetic field and to turn the frame.
In this event, contact IHP20 mounted on the frame closes with
one of the fixed contacts.
Cut into the circuits of the three contacts KHP20 are
limiter resistors 8133, "134' 8135 mounted inside the sens-
ing units.
These resistors limit the oharge-diocharge current of
capacitor 031 and determine the change speed of its oharge.
Resistor 8133 in also a protective resistor designed to
keep the frame springs against blowing out when they
accidentally contact each other upon sharp perks.
Capacitor C31 is connected to the circuit between the
plus of the voltage stabilized (wire 183) and the control
grids of the electron valves. This connection of the
oapaoitorp when the voltage across the control grids depends
directly upon the value of the current stabilized acoelerat-
es the stabilization process and prevents the automatic
osoillations 8ppearing in the regulation circuit due to
introduction of the negative feedback.
The main coil 11 of the oarbon-pile regulator eleotro-
mapet oonsumes the stabilized voltage via wires 183 and
and 184 and damping. resistor 8130.
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 MEN
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- 66 --~
50X1-HUM
I
leak resistor and then charged through the'sensing wait.
This phenomenon is also observed when gradually charging
capacitor C31 by the valve grid current and discharging it
to the sensing unit.
7. PARAMETER AUTOMATIC FOLLOW-Up SySIEH
The electrical computing systems of the sight are D.C.
potentiometrio bridge circuits, with electron relays used
as sensitive units, and reversible electromagnetic o:lutohe?,
a4 follow-up unite.
Prior to proceeding to the description of oleotrioal
computing bridge circuits of the sight, the prinoiplo of tlu
automatic follow-up must he explained.
The automatic follow-up system includes: transmitting
potentiometer HA (Fig-32), receiving potentiometer IIII,
sensitive unit amplifying mismatch signals of the electron
relay r3, and slave mechanism (electromagnetic reversible
olutoh 2PT-200).
Potentiometers (voltage dividers) are units comprised
of ar. ohmic resistor made of wire having high resistivity.
Any portion of the voltage delivered to the ends of this
re?istor may be taken off the potentiometer by means of the
mi,ing brush (slider).
Potentiometers I1A and IM are similar in design, the
only difference being limit switches of potentiometer II11
which deg-energize the electrical circuit of the electro-
Magnetic reversible clutch when the potentiometer brttmh
Moves to its extreme positions. Adjusting resistors are
employed to adjust the electrical circuits to the desirable
parameter setting.
Slave mechanisms of the -follow-up drives are reversible
eleotromagnetio Olutohes 22T.200 (Fig-33). The clutch
is provided with two coils 6 whose magnetic fluxes not
on armature 11 with the diao. Arranged to the left and
right of the diso are gears 5 driven by the electric motor.
,The gears rotate towards each other, the butt surface of
each gear facing the armature being used to engage the
latter. Two cork rings are glued to the diso.to ensure
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liable eng ement The rot ti 50X1-HUM
re ag
a on 18 imparted to the clutch
axle by the armature only provided it has enga6ed one of the
gears. The armature can slide-along the olutoh shaft in the
spline IvZo. When the eleotromagnetio coils are de-energized,
the clutch armature and the gears are disengaged.
. The current flowing through one of the coils presses. the
armature to the respeotive gear rotating the axle. The
sense of rotation depends on the coil passing the current.
The axle transmits motion to the slider of the receiving
potentiometer.
The duraluminium sleeve secured to axle 1 serves as an
armature of the tachogenerator. The armature rotates in -the
magnetic field created by the tachogenerator excitation
winding.
The latter consumes 400 o.p.so voltage regulated within 0
to 6.3 V.
The secondary winding of the taohogenerator yields this
voltage with the phase dependent upon the sense of the
electromagnetic reversible clutch axle rotation, and the
amplitude, upon its speed. This voltage is used as negative
feedback of the follow-up drive.
Both windings of the generator are arranged on the stator.
When the system operates, the transmitting potentiometer WI
feeds voltage UA proportional to a certain value and
compared with the voltage taken off the receiving
potentiometer flf.Voltage difference appearing when the
above voltages have different values is indicative of
mismatch signal. In this instance, the electron relay winding
will pass the current whose direction and value are
determined by the difference of voltages UA and Un.
The amplified mismatch signal governs the polarized relay
accommodated in the elpotron relay P3. The 'polarized relay
closes the circuit of one coil of electromagnetic
clutch 2PT-200, the armature being attracted to the.
corresponding gear. The axle of the reversible clutch receives
rotation and the slider of the receiving potentiometer 1111
moves to equalize UA of the transmitting potentiometer
and Un, of the receiving potentiometer.
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68
50X1-HUM
8. AUTOMATIC INTRODUCTION OP RASGS
When. the range is introduced automatically, the radar'
ranging unit sends voltage UA proportional to the range to
the target.
The ranges yielded by the radar ranging unit and by tie
outer base optical range finder are followed up by the sa
receiving potentiometer X11 included into the bridge
circuit (Pig.34).
The brush of potentiometer 1111 travels through an ju2gle
proportional to ,
AQ Sliding together with the brush of
potentiometer 11 11 are brushes of transmitting potentio.
meters 114 and 115 included into the ballistic bridge, the
brush of potentiometer U16 included into the eight reticle
circle bridge, and the brush of potentiometer II17 inoluded
into the circuit of the range indicator.
When taking the range by the radar ranging unit, the
receiving branch of the range bridge uses the reference
voltage U0 fed from the radar ranging unit through relay
contacts P8-5. The circuit of the bridge makes it possible
to use radar ranging unite, type CPA-5 or CPA-554A
(KBAHT).
The radar ranging units have different initial voltages
of the range and different gradients - changes of the
voltage per 1-m. range. The bridge resistors are changed
over to obtain different voltages of the initial
range (Ap . 200 m.) and different gradients corresponding
.to the type of radar ranging unit employed.
In so doing, the output voltage of the
CPA-5 (base-6)
and CPA-5I[J( (XIMM) ? radar range finders is in a reverse
proportion to the target range. When the sight i? operating
in Con junction with the CPA.-5 and CPA.-5M M) radar
range tinders, the elements of its recei
connected in the wv~8 branch are
ay different from that of the sight
operating together with other
with radar ~8e tinders, a$ in sere
range finders CPA-5 and CP
range voltage outpufi is a diminish CPA-591[ the law of
i.~. with increase of ~ (subsiding) one,
range, voltage UU deofeases.
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69
50X1-HUM
when ranging unit seleotor iIxp-1 is set to the CPA-5
or CPA -59K (XHAHT) positions the polarity of the refer,Uoe
voltage in the range receiving branch changes ft>~_ over?
p 2'ensures voltage polrrity change at ?e
input of P91_29 thus maintainhg the direction of the follow
up. The position of selector licp..2 should correspond to the
position of selector IItcp_1.
When the eight operates in conjunotion With the CPA-5
or CPA-511K (MUM) radar range finders, the initial voltage
at ,~ 200 m. is ensured by connecting resistors R95 and g
96
to IIgl circuit.
Resistors R91, R92, R93, and B97 set the required
gradient of the voltage, the middle portion of the bridge
comprised of resistors 811. 8098, R98 having regiired rated
volta
ge
.
Designations in Fig,34 mean:
1911
R91 to R9?,
R99
R
093
R98
P Pap-2
8-l' 8-2
P8-39 p8-4,
p8-5
- receiving potentiometer;
- fixed resistors;
- resistor for matching the sighs;
input and the radar ranging unit
output;
- adjusting resistor;
- electron relay;
- contacts of 'slay P8 (look-on
relay);
IIgp-1, f zcp-2 - radar ranging unit type selectors.
? The radar ranging wait is connected to the sight by
means of the RADAR -OPTICS (PAMO -- OfITNKA)ewitoh mounted
on the eight head bracket.
When the switch is set to RADAR (PAAdO)g
the radar ranging unit receives the high voltage. In this
Lnntanoe, neon lamp A7 on the eight head bracket goes on
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70 ----~
to indicate the high voltage available in the radar ranging
unit.
When the radar ranging unit has looked on the target
,
{ - wire 170 og the eight connected to the look-on circuit of
the radar ranging unit receives the voltage of -.27 V. The
application of voltage is indicated by green ~warning lamp
(mounted on the eight head) which In this instance
goes one
and relay P8 Is energized.
The contacts of relay P8 change the range pridge over for
reception of the range supplied by the radar ranging unit.
Contacts P8-3 send the voltage UA proportional to the range
to the target to electron relay P31-2, Then, contacts p8-
apply reference voltage U0 to the receiving branch of the
bridge, the voltage ooming from the radar ranging unit along
wires 152 and 158.
If the range, the sight follows up, differs from the
range measured by the radar ranging unit, the voltage aoroes
slider of potentiometer Il11 differs from voltage UAe
Electron relay p31-2 receives the mismatch signal trans-
mitted as a difference of the two voltages. By means of the
polarized relay oontaota, ekeotron relay P31-2 energizes
the appropri$te winding of the reversible clutch 2PT-?00
(PTA) whose axle shifts the brush of potentiometer 11j
till the voltage across this brush comes to equal the
voltage delivered by the radar ranging unit. In this event,
potentiometer. Nil yields the followed-up range correspond-
ing to the range measured by the radar ra
i
i
ng
ng un
te
Potentiometer n11 follows up all changes of the range.
Resist
R
or
093 is connected in series with the winding of
the electron relay. It improves the smoothness of the
bridge operation and increases the input resistance for the
radar ranging, unit.
Potentiometer 1111' resistors R97, R98, R098
, R99 are
mounted In the computer; resistors R91
selector 11Rp, relays P and r - R93, R9S~ R96?
? 11 are arranged its the,
control box.
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Electron relay P31-29 reversible clutch PTA,
selector IIxp-2 and electric motor MB are mounted in the
computer. The eleotrio motor used is of AP-3.511 type, azd
relay P8 of PC-13-10 type.
9. MANUAL INTRODUCTION OF RANGE
Receiving potentiometer 011 changed over according to the
Diagram in Fig-34 follows up the range introduced into the
sight manually in the same way as in the case of autowatio
introduction.
When there is no voltage across relay P8 (which happens
when the radar ranging unit fails to look on the target or
when the sight is changed over to receive the range from the
optical range finder), contacts P805 of relay P8 change the
range bridge circuit over for 27 V supply, contacts F8-3
connect' relay P31-2 to the slider of transmitting potentio-
meter 1112 intended for manual Introduction of the range,
and contacts P8-41 P8_1, P8`2 short the circuit of
resistors B911 R92, R93.
The brush of potentiometer II12 is linked up with.the
handle of the throttle control. The latter is turned to move
the brush of potentiometer U12 and to produce the mismatch
signal (voltage difference between the brushes of potentio-
me;ers fl and 1112)sent to electron relay P31-2
Electron relay P3 outs in the appropriate Winding of
c'.utoh 2PT-200 (PTA) 1 via the contacts of the polarized
relay. The axle of the electromagnetic reversible clutch
moves the brush of potentiometer H11 until the difference
between the brushes of potentiometers n11 and II12 is nil.
The slider of transmitting potentiometer H,6 of the
? retiole circle bridge is rigidly connected with the slider
of potentiometer 31i and also turns in proportion with the
range, changing the diameter of the reticle circle. Reoeiv--
ing potentiometer f11 follows up the range correctly when
the target is properly framed by the retiole circle. The
pilot keeps the target framed rotating the handle of the
throttle control. SECRET
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When framing the target by the reticle oirole, tue
circle diameter (in angular units) is determined by the
formulas
B . base (target wingspan);
AO - Initial range to target;
0.966 - coefficient oorreaponding to aspeot angle 1/4,
The sight has a device which computes "d" value using
relation (27) and transmits it to the mechanism forming the
retiole circle.
Relation (27) is solved by means of the electrical
bridge shown in Fig.35. The bridge is supplied with eta.
bilized 22 V.
H16 - transmitting potentiometer introducing range AAi
U14 - transmitting potentiometer introducing base B;
fl,5 - receiving potentiometer following up the retiole
circle diameter "d";
8160,
$201' fixed and adjusting resistors.
8310'
R311
The bridge comprises a transmittingbranch including
potentiometers R14 and U16 and a receiving branch including
potentiometer fl and resistor R310? The resistance of
potentiometer II14 included into the bridge circuit is
proportional to the target wingspan to be set. The total
resietanoe of potentiometer H16 and resistor 8310 is
proportional to the range introduced.
The retiole circle diameter is followed up by receiving
potentiometer 1115, the angle of its brush turn being
proportional to the diameter of the oirole corresponding
to the base not and to the range introduced. The adjusting
resistor 8311 ensures total resistance of potentiometer k5
and resistor 8311 proportional to the oirole diameter.
Adjusting resistor 8160 matches the coefficients of
resistances and voltages of the bridge branches.
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--- 73
It the reticle circle diameter does not meet the B
and A0 values introduced, relay P92-1 passes the voltage
to out in one of the windings of eleotromagnetio reversible
clutch 2PT-200 (PTx). The clutch axle shifts the light tube
of the range mechanism; in this events the reticle circle
diameter changes and the brush of receiving potentiometer II15
turns proportionally to the circle diameter. The circle is
followed up until the winding of relay P91_2 is do-energised'
i.e. until the diameter of the circle meets values B
and A0 introduced.
Turning the handle of the throttle control (the slider of
potentiometer H12) and keeping the target framed by the
retiole circle, the pilot introduces the range into the
eight.
Resistor R201 and potentiometer H14 form the transmitting
branch of the bridge when following up the circle in posi-
tion FIXED (HEl0A.) The circle is changed by potentio-
meter I114. This branch is oonnected by contact P9-50 with
the gyro caged.
Potentiometers 1114 and 1115,resietors R311 and 8160 are
mounted in the sight head; potentiometer 1116 is mounted in
the computer; electron relay P32_1 - in the relay with the
base plate; resistor R201 - in the control box; electro-
magnetic reversible clutch PTx - in the eight head.
The clutch is actuated by the electric motor M4,
type Aj'-6, arranged in the eight head.
The bracket of the sight head mounts an indicator of
range Ao (voltmeter of M-63 type) showing the pilot the
range to the target introduced by the radar ranging unit or
manually by the range handle on the throttle control.
The voltmeter scale is graduated in hundreds of metres
from 0 to 2000 m.
Fed from the slider of potentiometer 111? to the volt-
meter is voltage proportional to the range. The slider of
this potentiometer moves simultaneously with the slider of
the range bridge receiving potentiometer II 11.
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Resistor r16 connected in series with potentiometer Ill?
is intended for oreating on the slider of potentiometer II
the voltages proportional to the ranges the computer rolioj0
up. Potentiometer II17 and reeistor rl6 are arranged in the
sight computer.
Resistor r19 mounted in the voltmeter housing is intended
to ensure the operation of the voltmeter within 0 - 22 V'
measurement range.
11. INDICATED TIME FOLLOW-UP SYSTEM
50X1-HUM
Sight ACII-5HA employs the same formula of time T for
all types of rockets and shells:
T A + T (Ao)?f(H)
where:
(p ( ) function of initial range;
N)- H)- function of height;
A - coefficient;
T - indicated time computed by the sight
of design in question - function of
time Tp.
oeftioient A and values 9 (Ao) and f(H) are different
for every shell/rocket.
Refer to Section 2 of Chapter 3 of the present Manual
for fo;.uulas of time T for different rockets and shells.
The :4llistic bridge is intended for determining T by
fo?.'aula (26).
To simplify the electrical circuit computing the expres-
sion for time T, the functions of the range and height are
expressed for cannon by. linear relations dependent upon
mean functions kpap(A0) and fc~H). Due to this simplifios.-
tion the electrical bridge may be provided with common
potentiometers -for these cannon to introduce funa-
tions Apo (A ) and t (H) the o
p to , 2aUSe-over to the linear
iuuotlocs p 50) and ffH) dependent upon them being done
by means of change-aver resistors. Rockets require special
mean tuno;ions fop(H) and `pop (Ao) and common potentiometers
introduoing them. The required funotions of every
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7 5 .`....
50X1-HUM
shell/rooket are changed by means of change-over resistors,
arranged In the ballistic unit.
Described below In the circuit of the time follow-up
ballistioal bridge (Fig.36).
The ballistical bridge circuit has two channels to fol-
low up time T: one channel - for cannon, the other channel
for rocket launchers. The channels are changed over by
operating contacts P P
2-41 3-5' P3-2' P3-1' P2-6" P2-5' p3-6?
belonging to relays P2 and P3, which are out in by the
sight function switches.
See, how time T is followed up for rocket launchers. It
is evident that relay P3 should be energized to actuate the
appropriate circuits. The bridge in question is comprised of
several branches. The transmitting branch (branch of the
range) includes transmitting potentiometer its connected
according to the rcciator diagram. Its slider is mechanically
connected to potentiometer f11 following up the range.
The slide * o:t' potentiometer 115 moves proportionally to
range A~ Functional potentiometer 15 computes . (Pep (A0)
for rocl r top change-over to y (AO) for projectiles being
done by conneoting the proper ballistic resistor into the
voltage .-ivider circuit.
T'.' voltage divider branch includes changeable
rA., .utors R33 and R26. The bridge diagonal (branch of
a: itude) comprises transmitting potentiometer Iii whose
n;ider moves in proportion with the flight altitude.
functional potentiometer 113 computes f~j(11) for rockets,
change-over to f(H) for each projectile being done by
connecting changeable ballistic resistors to the circuit
of potentiometer I131
The receiving branch of the bridge is made up of reoeiv-
iug potentiometer Ill whose slider moves in proportion with,
time T. Coefficient A for various types of projectiles Is
computed by using changeable resistors in the circuit of
potentiometer 111.
Thus, the slider of potentiometer 11,5 moves proportional-
1Y to range A0 and the slider of potentiometer 113.. propor-
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tionally to altitude H. The slider of potentiometer 113
moves to change the value and direction of the current in
the bridge diagonal (branch of altitude) proportionally tc)
funotion cp(A ).At the same time, the slider of potentio-
meter 113 yields voltage U3 which is a product of the ourrenj
flowing along the bridge diagonal multiplied by the
resistance between the slider of potentiometer 113 and the
voltage divider which is proportional to function f(H).
Hence, voltage U3 amounts tot
U3 . c.q (J ).f(11)
Potentiometer Hi is a follow-up potentiometer of the
ballistic bridge. Its slider moves proportionally to T, an',l
voltage U1 across the slider changes proportionally to 1
value T - At
U1-C (T-A).
The wires running from the sliders of potentiometers II1
and 113 are connected to the input of the electron
relay P31_1. If the indicated time differs from values 1J.o
and H introduced, voltage U1 is not equal to voltage U3. The
voltage difference is sent to the electron relay P31.1, which
functions to close one of the windings of the reversible
clutch 2PT-200 (PTT), whose axle is mechanically linked with
the slider of potentiometer' II1. The slider of potentio-
meter 1i turns until U1 s U3 covering angle proportional to
time T. The axle of the slider of potentiometerlll carries
the sliders of the time transmitting potentiometers, H WAS 7 potentiometer of the prediction oirouit, 118 and 119 - those Of
the oirouit computing additional angles.
Sight AC1I-MA employs two potentiometers for introduc-
ing y (A0) relations: potentiometer 114 serving for cannon,
and potentiometer 115 - for rocket launchers. Their sliders
are mechanically linked with slider 1111 following up the
range, and move proportionally to the range.
Function t(H) is also reproduced by two potentiometers H2
and 83 whose sliders are moving proportionally to the flight
altitude.
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W.W. 78 --~
50X1-HUM I
Sight ACII-5HA may operate in conjunction with AYAC-133-8
and. AYAC-8u transmitters which are capable of measuring tht
attack and slip angles within the following limits:
5o>a 0,< +4.5?
13. CONSTRUCTION OP AI&CRAPT SLIP CORRECTIONS
Sight ACII-5HA computes correction for aircraft slipping
only when firing rockets. The correction is donstruoted by
two components: horizontal component (in the wing plane) atd
vertical component (in the plane of aircraft symmetry),
The relationship between the components of the aircraft
slipping correction is as follows: pa ^ A?a; 0 ? - Aop;
where a - angle of attack; a - slip angle in the wing plans.
A. Construction of Aircraft S11p Correction
angle. The horizontal poles of the zero gyro magnetic oor-
reotion unit are furnished with special coils KHre Whose
key diagram is shown in Plg.37. These coils are fed by the
computing system with the current proportional to some
apparent angular speed of slipping:
the same way as the vertical component of the elevation I '?
Horizontal Component
The horizontal component of the aircraft slip correction
is computed in the sight by.means of the zero gyro and in
the zero gyro. This current is transformed by the horizontal
additional coils of the main gyro into the ampere-tuxss
of the aircraft slip correction horizontal component oausi
the defleotion of the gyro and line of sight in the
horizontal plane through angle Poe slip angle p is
Introduced Into-the circuit by potentiometer II2i arrvaged
proportional to wa is induced in the correction ooile of
OPT
Coils Karo being energized, a correction ourreut,
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in the transmitter. Time Tp is Introduced into the oirouii;
by potentiometer U26 meohanioally linked with time follotti
up potentiometer QV
When angle PO is ooatputed at time Tp < 105 Sao., errors
may arise (angle ac is less'than the rated angle, and the
error increases with decrease-of time). Aotuatly the errors
are not high, as, when firing rockets, time Tp can not
be lees 1.5 sec.
The allowance for'Aop is made by changeable resistors
mounted in the ballistic units. The computing circuit is
energized via contacts P .1, P2-3, and P3-39 which allows it
to out off the circuit of the airora,t slip correction
horizontal component, with the eight In the pix. (HElIOo.)
position, when firing cannons and during bombing. Adjusting
resistor $216 Is arranged in the zero gyro unit.
B. Gonetruotion of Aircraft Slip Correction
Vertioal Component
The vertical component of the aircraft slip correction is
computed by the eight through turning the piano--parallel
plate (11I111), which Is included into the sight optical system
and provided with a system of automatic follow-up of the
required angles in the vertical plane. as is constructed
together with the constant portion of the elevation angle
vertical component by the formulas 0o.= Acp as + 3'
where B' - constant portion of the elevation angle vertical
component.
In eight ACII-5HA the vertical component of the air-
craft slip correction is computed by two ways:
(1) by introducing the value of the angle of attaok from
the B transmitter;
(2) by introducing the value of the angle of attack from
the altitude unit as a function of altitude H, average speod
at a giveh altitude VC .H and average value of overload
at a given altitude .P
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The key olootrioal diagram for oomputing the v foal
component of the aircraft slip correction is given
in pig.38.
When firing rockets, with the night operating in oonjyxW.
tion with the MAC transmitter, transmitting potent-io.
meter 1120 of the angles of attack is oonneoted to the
transmitting branoh of the potentiometrio bridge. 4,0,, Ill
followed up by potentiometer Hg) kinematioally,connected
with the piano-parallel plate which receives through eleoi;ro.
magnetio clutch P-200 the pulse from the mismatohing
amplifier of P32-2 (electron relay) connected to the
diagonal of the potentiometrio bridge. The allowance for
'coefficient Acp for various projectiles is made by changeable
ballistic resistors, oonneoted to the circuit of potentioa?
meter 1118 and arranged it the ballistic units.
Connected to the MAC - SIGHT (AYAC - M IM) EJI) oirouii; bet.
wean trani:iitting potentiometer 1120 and receiving potsntio.'
meter IIj8 is an aleotr:.oal filter (damper) presented by
link RC. the filter is .'ntended to smooth the retiole sharp
fluotuat:.'ns and in t', s way to taoilitate sighting. In
this '.r f.anoe the fr.' iow-up of angle ~a is slowed down bar the
van, _ e filter V. ,,a constant i a 4.8 coo.
The filter oc. 3iste of capacitors C17, C189 type 3T0,
resistors R2(-r R212, type &TP and adjusting resistor Romp
type C11. E. these elements are arranged in the oontrol
box.
When '.unotion switch H (YAC is set to the H position,
altitude unit potentiometer 1119 beoomes a transmitting
branch of the potentiometrio bridge. The centre point of
potentiometer IIj9 yields voltage as a funotion of altitude,
fighter average speed and average overload at a given altittudes
when the altitude changes, the eight continuously follows
up the vertical component of the aircraft slip correction.
The allowance for various functions of f(YopR; 0g)
for different types of aircraft is Made by resistors a208,
$209' 8210' 8211' $10' a010' arranged in the control box
and? ohanged over by means of selector' fp..3.
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n~i ;IS,kcR.c N~: wnt: ~~ y:}mw q +;'% "Flew
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81 ---.
magnetic clutch, type r-200.
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. The piano-parallel plate is operated by the eleotro-
50X1-HUM
When firing rookets at ground targets, the voltage
divider of resistors 8152 and 8154 beoomes a transmitting
branch of the potentiometrio bridge.
The ,voltage dividaV
Is connected by a Jumper mounted in the baliistio unit
(wires 994 and 099a are oonneoted).
When the sight is changed over to fire connon,
contacts P3_4 energize the voltage divider, whose
resistors 1154 and R52 yield voltage corresponding to'+ 00
and contacts P2-1 and P2-2 connect additional resistors 02
R40
and R50 to potentiometer 1118. The Plano-parallel
plate (HRR) returns to the zero position. Thus, when firing
cannon, the vertioal oomponent of the aircraft slip oorreo-
tion is not computed.
The sensitivity of the masmatching amplifier is adjusted
when the sight operates in conjunction with AYAC trans-
mitter, whose n20 potentiometer circuit includes an
eleotrioal filter, comprising some resistors.
When the AYAC transmitter is switched off, the filter is
do-energized and the mismatching amplifier sensitivity
inoreares. To prevent the piano-parallel plate against
auto-,tbrations, the oircuit includes ballast resistors 11204,
11206, 5207 of MAT type, which deorease the sensitivity of
the 1:11ow-up system. The potentiometrio bridge, which fol-
lows ip the vertical component of the aircraft slip oorroo-
ttior is energized through contacts P2-3 and P3-3. When the
sig) operates in the bombing mode of operation,
re' ye P2 and P3 are de-energized and the circuit, which
fds voltage to the bridge, is oft. In so doing, the piano-
frallel plate may be manually sat to the given angle.
Resistors R40, R50, 1138' 11207 11212, x205 , R152, 111549
R54, capacitors C170 C181 tuned resistors R52, 1120, 8101,
866, 80205, R58' R55 are arranged in the control box.
Potentiometer H18 of IM-400 type is mounted in the sight
head. Resistor 11206 is incorporated in the sight head
braoket.
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This clutch is-not provided with the tachogenerator,
otherwise the construction being similar to that of eleotte,.
magnetic clutch 2PT.-200. Clutch-P-200 is arranged in the
Adjusting resistors Rte,, 8619 8599 R65 and fixed
resistors 8629 R689 R60 of the Dig potentiometer circuit
are accommodated in the altitude unit.
eight head.
50X1-HUM
14..INTRODUCTION OF BALLISTIC CHARACTERISTICS
OF EMP'.LOYED WEAPON
The values of the angular corrections (lead, elevation and
slip corrections) depend on the ballistic characteristics
of the weapon for which these values are computed,
Sight ACfl-5HA takes allowance for the weapon ballistic
characteristics by setting in the computing circuits change
able resistors, whose value varies in accordance with the type
of the weapon employed.
The changeable resistors, which are included into different
circuits of the sight computing system to ensure the operation
of these circu'ts for certain types of rockets, comprise a
changeable ba]'.ictic unit. It is evident that the number.of
such ballistic, units should correspond to the number of rocket
types.
Fig. 39 r:presents the electric circuit of the ballietioal
units for tt,, rockets, the'sight was designed to operate with.
Resistors, .ncluded into the computing circuits for cannon
(type V-3,), are fixed and arranged in the control box.
15. SETTING OF SIGRT OPERATION MODES
Sight operation modes are changed over by selectors accommO
dated on the sight head bracket.
1. Selector IC has positions HR.3p..F0 and provides for
changing over the sight operation modes to fire cannon or
rockets. The allowance for the type of rocket is made by set-
+1109 the proper changeable ballistic unit into the control box.
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The sight computing circuits are changed over. for firing
shells or rockets by relay contacts p2 and P3. The relays
are energized by 27 V D.C. and are switched by selectors flag
and IIicp.
Relays P29 P3 are of PO-13-10 type. They are arranged in,
the control box.
2, Selector IIxp has positions C -~ 5 and provides for the
sight operation in the mode of firing or bombing."
omb
fig. In the
bombing mode of operation selector Rxp disconnects the minus
circuit of the P-200 clutch windings to exclude the opportuni.
ty of the piano-parallel plate operation
from the signal of .the zero drift currents induced in the mismatching. amplifier.
Selectors lie and IliP energize wires 501p,
546r 542r 541,
running to the aircraft fire control system.
3. Se1'ctor Itxu is intended to change over the circuits,
wbic'. _:omputo the vertical component of the aircraft slip
co;.r ' on, for operation from the AYAC transmitter or from ~yr
~.~ ut;itude unit. The main mode of sight operation is in f t
.,onJunction with the AYAC transmitter. The method of comput-
ing the vertical component of the aircraft slip correction
from the altitude unit is used only in case of AYAC failure,
In this case selector D-AYAC should be set to the H
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84
Chapter V
DESCRIPTION OF SIGHT-M-11 DI.AgRAM
?
apeoial generator.
the interference filter, and 115 V, 400 c.p.e. from the
A key diagram of the eight is shown in Fig.127.
The eight uses 27 V A.C. from the aircraft maim, through-,;
to the other oirouits of the sight.
The eight heater and the illumination lamp are connected
t, wires 01-02 and controlled by switch ~HIIi ( heater ). i
Spitoh BKII1 applies +27 V to switch BK112. The oontaota
,f switch BKH2 ( eight ) deliver +27 V and 115 V, 40Q o.p.a.1
Computing' oirouits of the sight (circuits of the lead
and elevation, ballietio bridge, reticle circle follow-up
circuit) are connected to wires 3 - 4 and fed with stabilized;
voltage (22 V) coming from the voltage regulator CH-4.
Wires 2, 02, 002 of the oirouit are grounded to the eight
housing.
Wires 125, 129, 130, 131, 152, 158, 166, 166a, 1.709 295,
296, 317, 35]. are screened, the screens being connected to
the eight housing.
Switches BKIIi and BKH2, damping button KH,A, AYAC'.
and throttle control handle refer to the aircraft equipment.
1. ILLUMINATION AND WARNING LAMPS
Lamp ni (27 V, 18 W) is intended to illuminate the
eight reticle (pip and circle); it is connected to the mains
through illumination rheostat RU. The latter regulates the
intensity of illumination of the circle and pip of the
eight retiole.'All members of the oirouit in question are
aooommodated in the rear cover of the eight head.
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50X1-HUM
0 11!
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Lamp 33 (rod) Is Intended to indicate the time of oomia,S
out from attaok.
Lamp JI4 (green) indicates' that the radar ranging unit
has looked on the target. The minus conductor of lamp
receives the voltage from the radar ranging unit.
Lamps 13 and 314 are mounted in the eight head housing.
2. SIGHT HTATERS
The sight head and the zero gyro are provided with,heatere.
intended to eliminate temperature errors and to create normal
conditions for operation of the eight components.
The eight heaters are out in by means of switch BKII1
(heater).
A. Sight Head Heater
Heaters 081 09, 010 maintain the constant temperature
in the gyro head housing which is necessary for keeping
reeis',lnces of the coils (copper) and diamagnetic materials
(alu'-inium) characteristics constant.
:isater Oil is wound over main coil Ky placed in the pole
r+. he gyro cover, heater 010 over the coil attached to the
gyro housing bottom, heater 00 over the brass former of
coil Ky2,and heater 09 over coils 1C 2 and Ky3.
These heaters are switched on by contacts of relay P119
the coil of relay P11 being oonneoted to the circuit by the
thermoregulator T4 adjusted for the out-off temperature
of +60? ?2?C.
Relay P11 is the relay of the ACII-4H sight heater.
Capacitor Cu4 and resistor ru4 are connected in parallel with
the thermoregulator T4 for quenching the sparks.
Relay P11, thermoregulator T49 capacitor Cu4 and
resistor ru4 are mounted on the front cover of the sight head.
Heaters 0129 and 013 are intended to protect the semi-
silvered 'Mirror and the objective lens of the eight head
against fogging.
The objective heater 012 is a transparent ourrent--oonduot-
ing film applied to the objective inner surface. Heater 013
is a circular current-conducting film applied to the mirror
surface facing the mounting.
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-86
?
B. Zero ro Ifenter
The beater of the zero gyro includes a number of heat]
elements arranged in and out of the gyrrosoope houaiig (ic*
the heat-insulated jacket)* The.heaters are ocntrolled by
means of two thermoregulators, one being arranged in the
gyroscope housing, and the other - in the Jacket.
Heaters 01 and 02 accommodated inside the gyro housing 44
bitilar windings wound over the former of the main.eoil,of
the gyro. The heaters, are controlled by relay 'P12'ot
thermoregulator Ti. The heaters are disconnected
,under +7000 +2?C.
On'the outside, the gyroscope is heated by heaters 04,
0S0 06, 07 controlled by relay P1'7. Heaters 04 . 07 are
mounted on the gyroscope housing.
Thermoregulator T2 arranged inside the heat-insulated
Jacket controls relay P1?, disconnecting the heater
under +30?C +2?C.
gyro to break the circuit of the coil of relay P9 and to
out out electric motors wt, end M8 of the gyro and of the
computer.
Unlocked (operating) position of the gyro'requires that
Relays 212 and P1? are the heater relays of sight A.CII-Q,
Spark;quenohing capacitors Cul, Cu2 and resistors rul,
rut are connected in parallel with the thermoregulators
3. LOCK SYIITCH
Look switch KBap,' mounted on the sight head, looks the
the.oirouite?of the coil of relay P99 and of electric
motors and 93 be closed (the look lever ie in
GnO (PAPO) position).
4. ELECTROMAI TIC LIUITER CIRCUIT
When the
gyro has deflected through an angle approximat-
ing that at which the gyro reaches the mechanical limiter,
the spring contact KI80 on the Gyro frame touches the
plate seoured to the sight head housing. The sight head
body receives the minus of the mains, therefore relay P 80
in energised the moment the contact touches the plate. ;[n.
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87
thl?s instance, the contacts of relay Pso and resistor r3
in the circuit of the gyro main 0011 pass additional our-
rent,.the magnetic flux in the main 0011 increases and the
deflootion angle of the gyro spin axis decreases. The circuit
of the electromagnetic limiter breaks, If later on the
deflection angle of the gyro spin axis exceeds the maximum
value (130), the above process is repeated, and the sight
reticle forms an oscillating pattern during operation.
Relay Pao used is of PQ-7 type. Capacitor C3 is
intended to smooth the current pulsar; sent to relay P' when
the spring contact touches bus KN80. Relay P80 and
capacitor C3 are mounted in the control box.
5. DAMPING CIRCUIT
During sharp turns, the electromagnetic limiter may fail
to eliminate blurring of the reticle. In such oases the damp-
ing button will be pressed.
When the button is depressed, relay P15 operates to close
oontaots P5_1. Resistor r7 and the prediction coil pass an
additional current, the magnetic flux increases and the
deflection angle of the gyro spin axis sharply decreases.
6. ELECTRIC MOTORS OF SIGHT HEAD AND ZERO GYRO
Sight head gyro electric motor Mr, type AP-4M and
electric motor MA, type U4. of the reticle circle and
piano-parallel plate mechanism follow-up, are controlled by
switch BKQ2 SIGHT ( IIPPI'.',EJI) which delivers 27 V D.C.
to them.
Gyro electric motor Mr r9oeives voltage by means of
lock switch Rap (with the g;rro looked, the oirouit?of the
elnctrio motor Mr is open).
The radio interferences oc.used by operating electric
motors Yr and M are rectoed by shields that screen A the supply cables and by duct oapaoitor, type KIM-0.025DF
used as filters.
The zero gyro electric motor U8r is an induction motor
with shorted rotor. Capacitor C4 and resistor r4 are
intended to shift the phases in the rotor windings. The
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normally closed - de-onergize the oirouit
following up the aircraft slip correction
horizontal oomponent, when the mode selector 1s
%set to the HP-30 position.
- normally oloced - change over the of?otrioal
circuits of the ballistic bridge to follow up
time T for cannon or rocket launchers.
normally opened 4 change over resistors in the
circuit of Knrn sighting coils with respect
to the type of the weapon employed (cannon
or launcher)*
with the operation mode selector in the PC
position, energise the circuit computing air-
craft slip correction vertical oomponentf
with the selector in the HP-30 position,
disconnect the circuit mentioned above and 0=-
aeot the transmitting branch of the baridg.?to
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50X1-HUM
_7~
electric motor is out in by contacts P 14 and P6, with
the gyro unlocked.
?. PUBPOSS OF CONTACTS OF SIGHT OPICiATION MODES
CHANGE-qVIM RELAYS
Relays P2, P3 control the circuit operation in firing,
The contacts of relay P2, P3 servo the following purposes:
P2_l9 P2-2 obange over ballistic resistors in the reoei,
branch of the bridge, which follows up the
vertical component of the aircraft slip oorrso..
tion, to follow up the angle by the piano-
parallel plate, when the operational mode
selector is set to the PC position, and to
drive the piano-parallel plate back to the zero
position, when the mode selector is set to
the IIP-30 position.
p2-3' P3-3 normally opened - energize the bridge following
up the vertical component of the aircraft slip
correction.
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the middle point of the constant voltage
divider. As a result, the plan
o?garallel, plate,
takes the zero position.
Bombing with the employment of eight ACQ-5HA should be
performed with the looked eight head gyro,'To ensure'
automatlo Operation of the sight in firing, unlock the main
gyro by setting the look lever on the eight..hoad to the GYRO
position. In so doing, relay P9 operates whose contacts
connect the following circuits:
P9-1 -? with the gyro in the FIXip (HEIIOA.) position,
de-energize the circuit following-up the
aircraft slip correction horizontal component.
P9-49P9-6 - feed alternating voltage to the zero gyro
P9-5 connect the transmitting branch of the reticle
circle bridge with the bane 'and range potentio.
mete'u-at GYRO (MO); connect the transmitting
branch with the base potentiometer and
resistor R201 - at FIXED (HEHOA.) position.
P9-2 - energize the sight computing circuits with .22'Y
stabilized voltage.
When the target is looked on by the.radar range finder,
relay P8 operates whose contacts make the following
switohings:
p8-5 - change over the receiving branch of the range
follow-up bridge to 27 V voltage or to the
reference voltage from the range finder.
P8-3 -change over the range follow-up circuit to the
range voltage from the radar range finder or
from the range manual introduction potentiometer.
P8-11P8-2 - short resistors R92, R91, R 3 when sight is
P8-A functioning in the OPTICAL (OIIT- ) mode of
operation.
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Olson" 90 -
8. OPERATION OF SIGHT WILT N FIRING SHELLS AMD
ROCKETS
When firing shells* and rockets, the eight should perfo
the following tasks:
(1) compute in the eight field of vision the necessary
angular corrections for prediction, sighting and slip of the
aircraft;
(2) follow up the range to the target, flight altitude
and rated indicated time of the shellrooket flight neoee-
eary for computing the angular corrections specified above;
(3) send necessary signals about the mode of the sight
operation and the operating conditions. During firing, the
sight is controlled by relays P2, P30 P , P9 and.switohe?
BKU1, BKII2, IIKe, KK 1' for AK 2' AKe. c' i C 3 ubp' ago.
To the s a p
prepare p ,proceed as follows:
1. Mount into the control box a changeable ballistic unit
corresponding to the type of the employed rocket.
2. Set switches 1 and IKp_2 to the positions
corresponding to the radar range finder mounted on the
aircraft.
3. Set switch Iltca to the J YAC position corresponding
to the main way of computing the aircraft slip angle
vertical component. ,
4. 3 - 14 min. prior to take-off (depending on the
ambient temperature) out in switoheo $KIII, and BKf2.In efl
doing the following circuits are energized: sight head and
zero gyro heater, reticle circle illumination lamp, filament
circuits of valves of the CH-4 voltage regulator, zero gyro
,amplifier and electron relays; sight head electric motor i(~
and altitude unit electric motor Yg.
5. For sighting, unlock the sight head gyro (close
contacts IC$ap> after.the take-off to start the electric
motor V. of the sight head gyro (the sight retiole moves),
eleotrio motor IVIN of the computer, and relay pg, whose
contacts energize the computing oirouits.
6. Set switches lllto-Up to position corresponding
to the type of.the weapon fired. In this instance, the
voltage is fed to one of the ballistic change-over relays 22
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50X1-HUM
or P3. The contacts of these relays change over the ba]._
listio bridge resistor groups and the sighting oirouitei,
.adjusting the circuits for oomputing the
angular oorrealticnd
for appropriate weapons. When rockets are 'fired with the
switch u1CC set to PC, relay P3 operates connecting by its
contacts the follow-up system of the aircraft slip oorreo-
tions.
The fYAC transmitter introduces into the sight the
values of the fighter attack and Blip angles. The sight
reticle moves down through the angle produced by the
vertical component of the angle of attack oorreotion and by
the constant component of the elevation angle (oorceeponding
to the type of rocket).
When cannon are fired and switch fixo is set to the AP-30
position, the oomputing circuit of the hccizontal oomponent
of the aircraft slip correction is disconnected, while the
vertical component bridge is oonneoted to the middle point
of the voltage divider. The divider yields.voltaze correspond.
ing to the Z] RO position of the piano-parallel p1.-to (TIiif).
The follow-up system returns the piano-parallel plE%o to
the ZIRO position with the help of electromagnetic o:.?itoh
P-200.
7. In case the sight functions together with the radax
ranging unit, set switch IIKBO to RADAR (PATIO) thus feec-
ing the high voltage to the radar ranging unit. In 1 - :3 mi-
nutes lamp A7 must f;o on indicating that the high voltage
is available in the radar ranging unit oirouit.
Before the radar rangiug unit hag looked on the target,
the sight operates reoeivirg data from the outer-base range
finder. The diameter of the retiole oirole and the mobility
of the retiole depend on the range introduced by the range-
manual introduction potentiometer Q12 and on the base set
on the base scale by turning the brush of potentiometer 1114.
When the target Domes within the radar ranging unit
operation range, green indioating lamp A4 LOC&?ON
(3AXBAT) goes on and relay P8 is energized. The contacts
of relay P 8 disconnect the range manual introduction oirouit
and change the sight over for reception and follow-up of
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50X1-HUM
the range (transmitted by the radar ranging unit) by po?tentio,
meter Tl1i.
The slider of potentiometer fl17eende to the voltmeter a
voltage proportional to the range to the target. The 'slider
of this potentiometer moves together with the slider of the
follow-up potentiometer nil of the range bridge.
The slidore of potentiometers A4 (when tiring the
cannon or AS (when firing the rocket weapons) connected
according to the resistor diagram and arranged ,on the oomaon
axle with the slider of potentiometer fill feed the current
(proportional to the range) to the diagonal of the ballistic
bridge. The resistance of potentiometer A2 (when firing
the cannon) or of potentiometer 113 (when firing the rocket
weapons) is adjusted in proportion with the altitude.
The indicated time of the shell/rocket flight is followed
up on ballistic bridge potentiometer A1.
The slider of potentiometer fl.l fixed on the same ax].e
with the slider of potentiometer Al feeds the current
whose intensity depends upon the changed indicated time of the
shell/rocket flight, to the oirouit of eight head gyro main
coils K 1 and Ky2'
Additional ooilo KKr and KKH of the sight head gyro
connected to the circuit of the horizontal and vertical
channels of the zero gyro correction, pass the current,
proportional to the product of the aircraft angular speed in
the horizontal plane (the sum of the aircraft angular
speed and of the apparent speed proportional to fraotor at
in the vertical plane) and the indicated time taken off the
sliders of potentiometers 08 and
canto axle with the slider of ~ arranged on the
potentiometer A1.
then the central pip of the retiole follows the, target,
the sight head gyro deflects thr
to the target relative ~6h an angle proportioruel
the Betio flux of the angular
and additional coils and
deflects the reticle within the s oils and
t~O?' the lend ~t field of vision
horizontal the and the elbrgtion. angle in the
the elevatipl (the lead angle and Variable o
angle in the vertical o~aia~t of
Diane).
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93
50X1-HUM
When sighting, the pilot should-keep the oentra.l pip of.
the sight reticle matched with the centre of the target,o
Before opening fire, 3 - 5 eeaonde must elapse, wbd.oh ill
enough to match the movement of the sight retiole central pip
and of the target.
When the eight head gyro computes the total angular oor.,-
reotion exceeding 13?9 spring contact KH8O on the gyro
mounting touohes the bulbar attaohed to the sight head house
ing?
The oontaot touohes the bulbar to feed voltage to the coil
of relay Pao. The oontaots of relay P80 out resistor ril
in the circuit of the gyro main coil to energize this oirouit
with 27 V. In this instance, the current in the main coil'
increases to decrease the angle of, the gyro defleotion. If
the total angular correction keeps exceeding 13?, the sight
retiole oscillates.
The sharp turn of the aircraft requires that the damping
button KHA be, preened to considerably decrease the angles
of lead. This is achieved due to increase of the current in
the prediction circuit paused by small resistor r7 oonneoted
to it.
If no encounter with the enemy is anticipated in flight,
the pilot must out off switch ICBap keeping the sight ready
for operation as the valves of the voltage regulator, zero
gyro amplifier and electron relay are energized and the
heaters are on.
For turning the eight off, first look the eight head gyro
by bringing the looking lever of the eight head to PILO
MUM). Then turn off the switch SIGHT (flPHRU) and the
switch HKATI t (OBOI?PEB).
Notes Never take off and 11~~ith the gy~co.unlocked
0)?
(knob against GYRO
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____ 94 ---
Chapter VI
SIGHTD83, ;
The sight is comprised of separate units oonneoted
electrically, therefore every unit is described in this
manual separately.
1. SIGHT HRAD
The eight head (Pig.41) is intended to form an image of
the retiole in the eight field of view and to d.efleot this
image through required angles.
The image may be formed as an unbroken circle of variable
diameter with a central pip both at GYRO (PBPO) and at
PX. i D (HEHOA.) positions.
'A detailed description of the formation of the retiolo
image in the sight head is contained in Sections A (Optical
System) and B (Gear Train) of the present Paragraph.
A. Slight-Rea Optical System
The eight head is furnished with an optical system of the
collimator type.
The optical system includes (Pig.42): diffusling glass
light filter 7; refleoting prism 6; two-lens objeotive 8;
gyro mirror 9; piano-parallel plate (semi-silvered'mirror)..
IN plan-ap4ra11el plate 11 with reflecting surface and
small right-angle prism glued to .piano-parallel plate 11;
mirror cone 12; glass plate 4.with transparent pip; light
tube 13; plauorocmves condenser lenses 3 and 115; light
sowroe 2 (27 Yo,18 N lamp, type C$-46); metal z~eflsotor l;
miner 14.
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Ir l
~rC
it
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WW, 95
Gyro' mirror 9 plaoed at the point where the.,light' rare .
converSe,'between objective 8. and its food -plane, Serves to
plot angular corrections both -in the, horizontal, and .vertical
planes.
Lamp 2 sends the light rays ' ough' 'oondenaer. l4me 15.0
mirror 14 to light-tube 13 whe3ioe they get through the
oiroular groove'to the refleoting.portion of cone :12. The
focal plane of objective. 8,
light tube in shifted along the mirrror',oone1axio'to change
the diameter of the image of luminous ring looatod in the
.,coated all along its surface except for'the end.faoing the
illumination lamp. Made on the other and of the .light tube
i8 a, circular groove that passes the light beam forming the '
luminous circle. Aluminium ooating of the light. tube is
painted black. The end of the light tube with the circular
groove is made spherical inside with a small lens and metal
cap glued to it.
Other condenser lens 3 passes the light rays of lamp.2 to,.
glass disc 4 with transparent pip arranged in.the ;local plans?
of objective 8. Then small prism 5 and piano-parallel plate ,
.11 (with semi-translucent layer in the cemented optical
block) direct the rays to the centre of the luminous ring,
Plano-parallel glass plate 11 is made of two pasta glued
together and chamfered at 450. One part of the plate has a
semi-transparent spot on the ohamfer intended-to project the
luminous pip to the centre of the circle. The other half
of the plate carries a small right-angle prism cemented. to
The light tube is an elongated glass cylinder aluminium..
it.
Condenser lens 15 is made of yellow-stained glass to
improve the contrast of the sight reticle circle image
against brightly lit background. Therefore, the retiole is
Projected in the eight field of view bright yellow.
Thus, the images of luminous ring and pip pass. 'through
clear glass refleotor plate 10 and reach gyro mirror 9 which:
refieots them to the reflecting surface of Plano-prrallel
plate 10 and finally to objeotive 8. Emerging from the
objective, the Imageg 'pass to refleotiag prism 6 and finally
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50X1-HUM
11
reach the observer's eye. The observer pees the images of
the luminous circle and the pip projected to infinity.
Light filter 7 made-of diffusing gasp may be placed in
front of reflecting prism 6 for dimming the background
against which the target appears.
The images of the central pip and of the luminous retiols
circle designed for framing the target may ohange their
position in apace by changing the position of gyro mirror,g?
and by turning piano-parallel plate (semi-silvered mirror)
Lxtreme positions'of the movable components of the
optical system intended to shift the eight line are shown
by dashes in Pig.42.
The maximum deflection angle of the gyro mirror (and t1a
gyro axis) is 140, that of the oemi-translucent plate is-
8030,.
B. Sight Head Gear Train
A gear train of the sight head is shown in Fig.43.
Bleotric, motor 27 (type AI'-4M) is designed to rot-Ate
gyroscope 1. Rotation from the electric motor is trans.uitied
to the gyroscope by means of spring belt 26. Another 6eotrio
motor 2 (type AT'-6) rotates the reticle circle follow-up
mechanism and the tilting mechanism of piano-paralle].
plate 24. Electric motor 2 is coupled with the gears of
electromagnetic reversible clutch 20 by means of two sore e
pairs and four spur gear pairs. From axle 16 of electro-
magnetic reversible olutoh 20 motion is imparted to the
brush of receiving potentiometer 22 (1j5) through the gear
pair, screw pair 21, worm gear 15 and worm-and-wheel pair 23-
Besides, motion is transmitted through screw pair.21 to
motion screw 12 along which nut 14 bearing glass light
tube 11 moves.
Bleotromagnetio reversible olutoh 5 is driven by eleotrio
motor 2 through spur pair 3 and reduction unit 4.
Mounted on the axle of electromagnetic reversible olut0h
is coupling 6. Notion is further transmitted through tho
spur gear pair and worm-end-wheel pair to friction olutoh
We 10. Prom the friction clutch axle motion is imparted
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objective 2 is placed in the threaded mounting and look..
pinned. To protect the objective from cranking when the
temperature is changed, it-is pressed with a spring adjuat,~gg
ring and clamped with a threaded ring. The amounting with the
objective screwed into the housing is fixed with look eore1re
focusing.
The objective is protected against getting dial by a
heater (a olroular current-oarrying film on the lower portion
of the objeotive lens).
The ourrent-oarrying layer receives positive voltage vi4A
a spring oontaot seoured to the piano-parallel plate and
oontaoting the ourrent-oarrying bulbar on the objective
mounting. The bulbar delivers the voltage to the current-
oarrying layer by means of a special oontaot insulated fron
the qbjeotive mounting. The other oontaot oonneoted with the
eight head body through the objeotive mounting feedmi the
negative voltage to the ourrent--oarrying layer.
The housing is furnished with two lugs with bearing
siLrtacee whioh mount two brackets 3 for fixing reflector 4.
Two slots made in the side surfaces of the reflector receive
the lookpins when the reflector is mounted in the brackotee
The reflector is looked with retaining strips, the screws
being looked with wire. The housing lugs aooommodate two
indioating lamps, lamp 3 (Pig.44) going on when the radar
ranging unit looks on the target, and lamp 5, when it is ties
to come out from attack.
Fixed to the left bottom portion of the housing are two
bearings with shaft whose ends carry :Corked levers for
operating the l00ke The shaft is protected by a apeoial
jacket. The sight head is eleotrioally connected with other
sight units by a cable and connector III'-2.
(2) i, QoyaX Bjjh ;Vj Fit
bout oover 2 (71g.45, 46) is a rectangular plate with
gyro unit 3 and two elootrio motors 1 and 4 secured 'to AU
The shaft of electric Motor 4 designed for rotating the,g ro
is provided with pulley 5 and spring belt 6. attaohi to
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belt 6, and block ? securing the wires running to the eleotrio..
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motors. Bolt bendjng 1s precluded by.washers placed under the''
rollers
the rrum-6 wvvnr aww rva,anr o Zniienaea ;o guide and to tighten
...... 99 .-,
Bleotrio motor 1 actuates the mirror tilting moo h4 i and
the ratio's circle rollow-up mechanism, Mounted on tho ^ame
side, where the electric motor and the gyro (Fig' 46) are scoured,
are relay 9 (P11) of the gyro heating system; angle
bar 13 with one adjusting resistor 14 (B ), two fizc4
resistors 12 (8030 and R77) and nine-terminal block 15 for
unsoldering the wires; resistor 8139; four duct oapaoitors 10
for suppressing the noises generated by electric motors 1 a:na 4;
six..terminal block mounting three thermistors'(RT,, B , RT ).
temperatures.
Front oovgr 2 is screwed to the sight head housing aiul
protected by a jacket with heat-insulating lining glued to Its
i
inner aide.
The main part of the front cover is the gyro unit (Fig, 47)-
The gyro incorporates: rotating mirror 3 with mounting l3
and spherical dome 6 secured on the axle. The axle is fixed in
the gimbal so that it can rotate together with the latter, it
the ball bearing screwed to gyro cover 5. The cover in made )f
permalloy and is provided with a specially shaped polo) which
oarries a part of gyro main coil Ky1 and heater winding 0116
The gyro cover is screwed to gyro housing 8. The latter is made
of permalloy forming a sleeve ending in cone.
Cores 11 mount four correction coils 10 (Kxrand {B)' heater
soil 010 being screwed to the flat portion of the houi3ing bottom.
Terminal block 11 is fixed to the outer flat surface Of the
howling bottom. it serves to connect the wires running froil the
inner coils of the gyro.
Four holes in the cone portion or the bottom of housing 8 ao-
oocnnodate our bushings 9 with flanges. The openings of the
bushings receive four cores 11 which are looked by screws upon
setting the core-to-dome air' gap.
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The thermistors increase stability of angles oomp%ttatio4 at, plus
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i l attached to bracket 1, The latter oarries adjuwti r~w o ,
!! ng screw 2
with c
t
t
en~ 100 ?....
brass former that is screwed to the gyro houatng.Therno?
regulator 7 is secured to the guiding slots inside the
ea ng system are wound Over the aurae
wound over brass former 12 are fitted inside the Qyll.nao
portion of the gyro housing. Two windings 08 1W Og (imier
and outer) of the h ti
50X1-HUM',
The other part of main ooil Ky2 and negative ooi-~l
former. The external view of the thermoregulator is-ahox
a
'tl in Fia.48. The
on
ac
,. ourrent.oarrying wires being sol.dored to
plates 4.
The gyro look design is as follows. Hinged four-bar
mechanism 1 is fixed to ring 4 (Fig,47) screwed on gyro
cover 5, The mechanism carries lever 2 with three stops
secured to. it for looking the gyro mirror. Axle 14 of the
rubber paddings (Fig,49).
The plate is prat eoted
a8ainat dimmi
b
s
a
ts with ball bearings.
The plate is fastened to the mounting by means of four mull
bare 4 with
g
ever rotates to turn axle 14 (Pig947) which
shifts the four-bar mechanism. The stops of moving lever 2
look the wirror.
The gyro unit In eleotrioally connected with the sight
set by a -.cable and connector III'-1.
(3)1po ?P,pat_Ui
The unit (Pigs 49, 50, 51) inoorporates parts of the
tilting mechanism and reticle circle follow-up mechanism.
The parts of the unit are fixed to ..
housing ll. Mounting ~ shaped oast
4 (Z1g?50) of the piano-parallel plate
Is.eeoured to housing 11 on axle
h
f
four-bar mechanism is connected to looking lever 13 (p;1g.43)~
The lookin
l
ng
y a circular
ourrent.?as
rryi~g film
a,Ppl$ed to the mirror non-operatirg
surface. The mt,.,.e.,,l. _--
contacts ;vafJlves DLit].vent from
~ 5 (pig.50).
Ply-parallel plate mo
unting
(119e49) serving for bal 4 is provided irith weight 14
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NO, !'OREiGN. DISRE
carries sector 3 p anoiug Plate., The plate mounting
(
ig?50) '"60604 with the redwoitiott unit
trwAsittift rotition of elec OO
010416200 to the p.+. - do reversible
`K
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in case of plate gear train Jamming and, seoond, to enable
the sight operator to adjust the plate angle manually
(motion of the worm gear cannot be transmitted to the worm).
Electromagnetic clutch 5 (2PT-200) follows up the diameter
of the reticle circle (Fig.49).
The electric motor rotates clutch 5 via input gear 13,
worm gears 9, 8, spur gear 10 and reversible drive 6.
The output shaft of clutch 5 transmits its rotation are far
as the rear cover to the reticle circle follow-up meohaniem
and to the slider of potentiometer 1115 through gear 15,-
Mounted under reversible drive 6 (Fig.49) is reticle ofrole
feedback transformer 7.. Spring contact 6 (Pig.50) delivering
the voltage to the objective heater is arranged on the side
wall of housing 11.
C.'hen the eleotromagnetio reversible olutohea funotion as
brush through a friction olutoh. The friction olutoh
is used first, to decrease the load on electric motor ,1Q'.$
The rotation of the worm gear is imparted to the potentiometer
The rotation of the output shaft of the eleotromagus,bio
reversible olutoh is transmitted to the shaft with gears 2
and 1.(Pig.50) through cam coupling 4, spur gears 5 and 6,
and a worm-and-wheel pair. Gear 2 is meshed with toothed
sector 3 of the plate mounting. Gear 1 engages the toothed
sector of the rear cover linked with the knob of the plate
tilting mechanism. Mounted on the same axle with gears ].,
2 is a worm gear, which imparts motion to the brush of
potentiometer U18 (7) through spur gear pair 25 (P4;.43)9
us
o s
the sight retiole in the 'vertical plans.
-Motion is imparted to clutch 2 through input gear 13
engaged with the gear on the electric motor shaft, ,and
through the reduction unit made up of spur gears 1 and 2
and reversible drive 3
(Pig.51).
-40 o ollow up the plate tilting eagle and .
U4.04.
t
th
hi
vi t r s of housing 11 (pig@49)r
olutoh 2 e
Electromagnetic reversible clutches 2 (P-200) are attaohed to the side wl and 5 (-20D).
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101
for the purpose (Fig.49).
drives, the automatio follow-up systems require that the clutch
run-out time is reduced to minimum by special brakes '1 provided
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' iii
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102 -~--
box with flange accommodating parts of the retio]s carols
follow-up moohaniam, plate tilting mechani?m, bate setting,
The, rear cover unit (Figs 52, 53) 1s a oast rootatiguZ.,.
(4) je Cover.wiith igh Retiole Circle Fallow- p
e
ras
h of potentiometer 14 (1115) and of the light
tube,
Arranged inside the housing of the roar cover 1Ei an
electric lamp, type CM-46p illuminating the retiole, circle
and its central pip. The holder of leap 15 (Fig.53)- is
which is in turn fixed to mirror cone mounting 1, Besides#
mounting 1 bears: special spring-loaded mounting 2 with
glass plane-parallel plate 15 Demented of two portions
ohamfered at 45?; motion screw 5 on ball bearings with a
special nut which mounts light tube 12; a key. The light
tube securing nut travels along motion screw 5 and along
the key,
Mounting 1 with the mirror none forming the luminous
retiole circle of variable diameter is attached to the
flange, Gear 4 has a out-.out hub rigidly screwed to the mo?,
tion, screw for turning the gear when matching the positione
of th
b
. The worm and potentiometer A15 are secured to-bracket 16
meter 14 (III, following up the variable diameter retiole
circle.
bear 8 is rigidly fixed to worm gear 9 mounted om. common
axle 7. The axle rotates on two bearings pressed into
bracket 6.
The latter is screwed to the front cover on the outer
side of the flange. The axle also mounts a gear with 1, ,t.,
ing pin which engages another gear having a limiting pin,
too, thus meohanioafly limiting the travel of the light
tube.
Gear 9 is meshed with gear 4 rigidly fixed to motion
screw 5. Via gear l0, gear 4 transmits motion to worm 17
meshed with gear 13 fitted on the axle of reoeiving potentiio-
clutch 5 is imparted to gear 8 0ig.52) by gear 15 (P4.49),
mechanism and gyro looking lever.
The rotation of the output shaft of eleotroniq do
SECRET
NO PAWN DISSEM
50X1-HUM
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connected to bracket 8 which is in turn attached to throw-
out bracket 9 by two adjusting oorewo 12. When the hinged
cover is olosed, two springs 10 rigidly attached to the
cover, press bracket 8 'with the lamp to ad3usting screw 5
(Fig.41) and the lamp-holder contacts close the ourrent-
carrying oontaots cin terminal block 4 (Fig.53).
,The lamp rays run through: (a) condenser lens 3 (Pig.42)
in the Done mounting; opaque (aluminium..plated) disci 4 with
transparent, pip secured to mounting 1 (Fig.52); emal.l right
angle prism 5 (Fig.42); plate 11 to the .centre of the
luminous oirole; (b) condenser lens 15 in the mounting;
miror 14 to light tube 13,
Condenser lens 15 (Fig.42) in beaded in mounting 23
(Fig.53). The out of mounting 23 houses mirror 20 pressed up
by rubber-padded bracket 21 seoured by two sorewa'to
mounting 23.
Refleoting plate 11 painted with white enamel is mount-d
on the hinged cover to improve the illumination of't,he
circle and the pip.
The proper setting of the lamp filament is obtaired by
shifting bracket 8 relative to throw-out bracket.9 in two
perpendicular directions, eorews 12 being driven out.
The lamp is brought strictly vertical by means of sorew 5
(Fig.41). Prior to this, the looknut should be loosened.
For obtaining the required brightness of the reti.ole
illumination, when replacing lamp 15, use spare parts, tools
and accessories of the given set only.
The right wall of the cover body oarries rheostat 19
whose handle is rotated to change the eleotrio lamp glow
thereby changing the brightness of the eight retiole oirole
with the central pip.?The wall is also provided with knob -3.6
for tilting the piano-parallel plate by hand. This knob is
fitted on the oommon axle with the gear engaged with
sector 18 (Fig.52).
The axle mounts scale 14 (i?ig.53) graduated from 0
to 120. The knob axle with the scale rotates in ball. bearings
inserted into bracket 13 that is attached to the rear cover
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NO 'OREIGN DISSEM
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 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
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SECRET
- - NO FOREIGN DISSEM
-w
50X1-HUM
and three selector switches, 13 to change over thq followy4
modes of operation:
(1) firing "HP-30
(2) firing and bombing "C -b""
(3) operation with the JYAC transmitter or tom the
altitude unit "H-AYAC".
Attaohed to two contacts of selector switch "H-AYAC"
is resistor 8206, type HAT, intended to maintain the
sensitivity of the follow-up system when operates in
mode "H" with the disconnected filter.
The right side wall of bracket 8 mounts housing 15 with
signal lamp 16 which indicates the high voltage supplied to
the sight when the radar ranging,unit is oonneoteC. The see
housing aooomodates selector switch "Hadar-optical" ohm
over the eight for receiving range frcm the radar ranging
unit or from the outer-base optical range finder.
Inside housing 15 there is a block mounting absorbing
resistor r1, type IUIT, connected to the signal lamp oirouit,
The electrical circuits are connected to the bracket by
cables 14, 17 with connectors "C" and ."P-j". In attiwh-
meat points the cables are protected against mechanical dema
by wire bindings 18.
2. COMPUTER
The sight computer (Fig-58) comprises the main .potexttio-
metrio oomponento of the eight computing circuits.
The computer Is made up of two independent unitin: a
computer proper and an electron relay.
The construction of the electron relay will be desoribed
in the section dealing with theoonstruotion of tho relay
on the base-plate.
At. Cotuputor Unit. Gear Train
The computer unit gear train is shown in Pig.59.
Motion from electric motor 6 (J P-3.5ii) is transmitted t
electromagnetic reversible clutches (2PT-200) 7 W19 by va
pair 5. The rotation of eleotrommgnetio reversible olutoh 7
is transmitted to?the reduction unit (gears 8 - 13) which
turns slider 17 of range potentiometer unit 15(0.
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 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
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Unit 15 follows up the range and introduces it into the
computing circuits of the eight. Brushes 16 secured to
slider 17 slide along the potentiometer windings When
slider was 14 is being turned. Axle 14 mounts range goals is.
potentiometer unit 3 follows up indicated time-Tv the
gear train being identical. Slider 2 with the br=ibes is
actuated from electromagnetio reversible olutoh 19) via
redui-
tion unit 4.
Be CQmnuter Desoriotion
The computer is shown in Pigs 60, 61.
Angle barn 7 secure range follow-up potentiometer unit 2
and indicated time follow-up potentiometer unit 6 to base
plate 8 (Pig.60). Plate 5 (Pig.61) with eleotromqnetio
reversible clutches (2PT-200) 3 and 4 is secured to the above
angle bars by screws.
Gear pairs 7 and 8 of the electromagnetic reversible
clutches are screwed to plate 5, eleotrio motor 9 being
ceoured to it by metal yoke 10. Bracket 13 attached to the.
plate mounts high resistor R98 out into the oiroui.t of range
receiving potentiometer.
The inner surface of plate 5 carries bracket 1 with four
screws 2 bearing the following adjusting resistors:
R37p, R39p. - adjusting resistors of range potentio-
meter 11 for rockets in the ballistic bridge; 5 R . A - adjusting resistors of range potontio-
3711 3911 meter 114 for rifled weapons in the ballistic
bridge;
R7, R8, R9 - adjusting resistors of time reoelving
potentiometer Qj in the ballistio bridge
R53' R63 - adjusting resistors of the time receiving
potentiometer in the additional winding
circuits for the vertioal and horizontal
channels (118, 119);
R31, R32 - taohogenerator adjusting feedback resistors
of olutohes 2PT-200 in the range (A) and.
time'(T) follow-up circuits.
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- - -- NO FOREIGN DISSEM
108 -----
Negative feedback transformers Tp-2, Tp..3 are arranged
the plate.
. On the opposite side of braokot 1, the 0justing resiete2
are, held by strut 3 (Fig.60) mounting a group of fixed
reeistoro 14. These fixed 'resistore are coimected to 'aribtl
circuits of 'the eight electrical systems
$173 - to the oirouit of ballistio bridge time reoeiyN
potentiometer 111;
R073 - to the prediction circuit;
R310 - to the circuit of sight reticle circle
potentiometer 11 16;
r17 - to the oirouit of range indicator potentiometer
'1098 - to range follow-up bridge (to the circuit of potentiometer 1111).
Connector plugs 12 and 1? are meant for delivering poorer
supply and for connection to other units of the sight. The
computing mechanism and the electron relay ,are connected
by means of flat connector 11 (Fig.61). The latter is rigidi1
secured to the base plate by sorews. The corresponding
socket of the connector is made floating. It is secured
to the electron relay plate via intermediate discs thereby
ensuring centering of the socket with the terminal block'
when the two parts of the computer are joined together., The
base plate also mounts two duct oapaoitors Cm5 and CQ6
for suppressing noises produced by operating electric
motor AP-3.5u. The lower portion of the plate mounts
seleotor switch Axp'2 intended to switch the control winds
of the electron relay magnetic amplifier depending on the
type of the radar ranging unit used, The switch in olooed
? by a protective 4aoket, its lever being held against
spontaneous obange-over by sleeve 15 (?1g.60;',
Riveted to base plate 8 are angle bare 9 and 13 (;Vig.60)
that receive screws fastening the computer Jacket.
The unit protecting Jacket is riveted
Its oentral portion is provided with inspeotioof thrae n holeap ee
oovered by organic glass plates. The base plate mounts
resistors R97 and R99 oonneot.d to the oirouit of the range
reosiving potentiometer II1i.
SEW -
FMM DI55iM
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 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
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109
The base plate is provided with four threaded bushings 12
(pig.61) which receive the electron relay fastening siorews.
The computer mechanism is'secured to the aircraft by
means of four holes in the base plate edged with rubber
eyelets 10 (Pig.60) and metal bushings 11. Attached i;o bass
plate 8 is a braiding with lugs serving as a bonding wire
when the computer unit is mounted on the aircraft.
The potentiometer units are shown in Pigs 62 and (3.
The circular recesses (Fig.62) of oylirdrioal.housipg 18
receive holders 17 with potentiometer formers 15 pressed into
them. There are five potentiometers altogether:
Ujj - range receiving potentiometer;
as and p5 - range transmitting potentiometers In the
ballistic bridge;
Q17 - range transmitting potentiometer for the range
indicator'
II~ - range transmitting potentiometer in the reticle
circle follow-up bridge;
The ends of the potentiometer windings are brought to
terminal block 19 secured to unit housing 18.
Potentiometer brushes 6 are secured to textolite slider 7
which is, in turn, fixed to bushing 10 connected to axle 20.
The latter is mounted in the unit housing on'the ball bearings..
Pitted on the other end of the axle, opposite the sliders
is bushing 21 with a lugged flange, Driven gear 23 is rigidly
fixed to bushing 21.
Driven gear 23 meshes double gear 1 whose axle its flanged
strut 2 secured to the unit housing. Double gear l is
engaged with gear 3 of bracket 4 attached to oylindriocl
housing 18. Gear 24 is engaged with driving gear 8 (Pig.59)
of electromagnetic reversible clutch 7.
The unit driven gear carries limiting pin 22 (Pig.62) 'with
insulating sleeve slipped over it. Driven gear 23 U ng,
the limiting pin comes Clear of the stop and bream oontaot
plates 5. Then the lug of bushing 21 bears against the Stop
rubber pad keeping gear 23 against further rotation., The
contact plates mounted on the part secured to the hc-usiag
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50X1-HUM
are intended to break the circuit of the winding of ele0tra.
magnetic reversible clutch 2PT-200.
The current is fed to brushes 6 of slider 7 in the
following way.
The slider has strut 8 with terminals 9 soldered, to the
brushes. The terminals are pressed into the strut hole.
Spiral springs 13 are welded to the ends of the terminals
protruding above strut 8. These springs are assembled on the
bushing and insulated by washers 14. Every sprung has a lead
(terminal) welded to the spring. The whole assembly is
screwed to bracket 11 mounted on the cylindrical housing Mg
looked by nut 12.
flange scale 16 is screwed to the unit axle flange. The
index for taking off the readings is marked on the oylindriag
housing.
The indicated flight time potentiometer unit (Pig-63)
and the range potentiometer unit are identical in design.
Listed below are potentiometers mounted into cylindrical
housing 28 similar to that of tbe'range unit!
potentiometer receiving indicated flight
time T;
117 potentiometer transmitting indicated flight
time for the prediction circuit;
118 and 119 - indicated flight time potentiometers in the
additional winding circuits for the vertical
and horizontal channels;
1126 potentiometer introducing the indicated time
into the computing circuit of the aircraft
slip correction horizontal oomponent,o
Unit slider 30 is turned through r,duotion unit.26 as-
sembled of the parts specified above for the range unit.
The reduction wait is driven by. electromagnetic reversible
clutch 19 (I'ig.59).
Indicated flight time aoale 27 (Fig.63) is attached to
the s13der We flange by screws. The readings are taken
off the index marked on the oylindrioal housing.
The wiring diagram of the computer is presented in Pj1.6 '
SECRET
NO FOREIGN D
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038RO01 700230001 -9
 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA -RDP82-00038R001700230001-9
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---- 112 --
cover 5 has four poles bored along the sphere concentric
with the sphere of the aluminium dome.
Rotor 4 is a shorted rotor of an A.C. single-phuise
asynchronous electric motor comprised of segments tuad?
of 0.35-mm thick steel 944? They are plaoed between the copper
flanges and riveted to. them by copper rivgts. This riveted
assembly is beaded in bushing 2 that rotates in the ball
bearing relative to bushing 6.
Stbtor 20 of the asynchronous motor is also assembled of
segments made of 005-mm think steel 8448 The ee1;ments ojri
pressed to base plate 21 by ring 3.
The grooves of the stator assembly house two windings of
the electric motor.
The asynchronous motor has an excitation winding and a
control winding. The voltage phases in these windings should
be shifted relative to each other, which is necessary for
creating the rotating magnetic field that rotates the eleotrio
r. .
motor rotor.
The phases in the windings are shifted by planing a
capacitor in the control winding circuit.
Squal resistances of the zero gyro electric motor stator
windings run into 118 ohms, each winding being composed of
two series-connected windings of 59-ohm rusistaaoe each.
The stator windings are fed with 115 V, 400 o.p1,s., one-
phase current and have a common point connected to one of
the supply wires. The ins of the windings are oonneoted to
the other wire, the control winding being connected through
the capacitor.
Soreen 22 is fixed to ring 3. Cover 5 carrying the gyro
and the rotor is attached to base plate 21.
? The gyro look is a device based on the centrifugal forces
effect. hook bushing 19 is screwed into holder 28 and
provided with a cylindrical lug. Milled in the lug are three
recesses for three rods 7 with weights 13 soldered to them.
Rods 7 are inserted into these recesses and fixed tc them by
means of tubular axles relative to which they can notate.
hollers 12 are eorewea to weights 13 to ? arrest the gyro
axis when-it must be looked. Sbery weight 13 with r1oller 12 SECRET
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
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`50X1-HUM
P17 gyro external heating relay disoonneoted
under +3000;
P12 - gyro internal heating relay disconnected
under +7000;
R49 - main coil circuit adjusting resistor;
8203- fixed resistor;
8216'" adjusting resistor of the K11 0 0011 circuit.
Besides, bracket 8 mounts thermoregulator T2 (disoonne0tfA
at T s +3000) to govern the external heaters, and termi"l
block 14 to secure the wiring.
Capacitors Ci; C2; 05 and 06 (10) of the induotive -trans.
mitter and eleotrio motor oapaoitor 04 are.seoured to
bracket 8 together with resistor r4 of the electric motor
control winding, spark-quenohing capacitors Cul and Cut ad
resistors rui, ru2.
Outside, the zero gyro with the brackets is proteotid
by a jacket with heat-insulating rubber gaskets. Screw"
attach the Jacket to the adapter, and the latter is secured
to base plate 4.
The zero gyro planes are aligned with the sight,heMl
planes and with the aircraft axes by means of a opeolel,
matching'devios oomprised of the ball support and two
bushings with springs.
Level 13 is mounted on the bass plate to check: whether
the zero gyro is oorreotlj arranged on the airoraft.
The mechanism described is connected to the control box
and to the zero gyro amplifier by a cable terminating in
connectors YH1 (for the zero gyro amplifier) and HI'
(for the control box).
The wiring diagram of the zero gyro is presented in
Pig.69.
4. ZERO GTRO AMPLIpIR
The zero gyro amplifier is made as a separate unit
(lig.7o).
Horizontal plate.15 (Pig.70) mounts:
? - bias *trout* oapaoitors 060 071 0?t 091
Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
 Declassified in Part - Sanitized Copy Approved for Release 2011/11/28: CIA-RDP82-00038R001700230001-9
p-4, Tp-S of the vertical and'
horizontal channels;
12 -valve 6Hifl(A5) of the horizontal'an
t
f
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. ---- 117
2, 6 - interetage and feedback transformers Tp..4,
T 3 T
r
ve
oal channels voltage amplifier,;
l
va
ves 60120 (Al, A2, '3'1 .
4)oi