ENGLISH TRANSLATION OF MIG-21F-13 AIRCRAFT MANUAL ENTITLED AIRCRAFT YE-6T, TECHNICAL DESCRIPTION, BOOK III, CONSTRUCTION, PART I AND II

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80T00246A028600420001-8
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 288
• Document Creation Date: December 27, 2016
• Document Release Date: February 28, 2013
• Sequence Number: 1
• Publication Date: May 1, 1963
• Content Type: REPORT

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CENTRAL INTELLIGENCE AGE
This matenal contains information affecting the National Defense of the United States v
18, U.S.C. Seca. 793 and 794, the transmission or revelation of which in any manner to an unauthorized person is prohibited by
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COUNTRY USSR
REPORT
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SUBJECT Eng:1.?th 'Translation of MIG-21F-13 AircraftDATE DMIL
Manual Entitled Aircraft Ye-6T, Technical
Description, Book III, Construction, PartL,NO.PAGES
land. II
REFERENCE
May 1963
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? DATE
INFO.
PLACI
DATE
THIS IS UNEVALUATED INFORMATION. SOURCE GRADINGS ARE DEFINITIVE. APPRAISAL OF CONTENT IS TENTATIVE.
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English translation of pages 1 - 222 of a
language manual on the MIG-21F-13 aircraft entitled, Aircraft Ye-ST.
Technical Description Book III Construction Parts I and
Distribution of Attachment (for Retention):
ObJ.: 2 copies
00/IIA: 1 copy
OPR: 2 copies
Army:
Navy:
DEA:
Akr:
2 copies
2 copies
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2 copies
2 copies
2 copies
bkX: 2 copies
Alr/FTD: 9 copies (Previously forwarded)
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ZCOLIJDZID FROM ADTOMATIO
DOWNGRADING AND
1MCCLAWMPIDATION
STATE
ARMY
I
I NAVY
AIR NSA
OCR I DIA
SAC
1 ' bta TITC
(Note: Washington distribution indicated by "X"; Field distribution by "*".)
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For convenience' the material is collected into two separate volutes:
First volumei :Chapter I.- General. informatics.'
. #
Chapter II Desim of the ....dass
- Chapter III Power ',lent
Second,volumai Chapter IV Take-off ani landing device.
Chapter V 'Air and hydraulic eysteme
.Chapter VI Central of the aircraft
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Chapt.er-Y-II ? Fire-fighting equipment
? Chapter Ventilation, preesuriaation,:ard
' air?temeratui's control
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CHAPTER I'
GENERAL UR/RATION
The* ..6T aircraft is a single-teat'light fighter with high nerformance
characteristics.
J
The craft ie powered brans 17F turbojet engine with an aftarburnef.
Structurally, the plane is an all-metal midwing monoplane with a delta
wing controlled by a stabiliser and nofmal wing.tiO fins. '
The fuselage is divided into the noes and tail sections.
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Structurally, the plane. iM an all-metal. atidwing monoplane wit,ha delta
.Wing controlled by a .stabiliter end 'normal wing-tip fine.
'
The Amplers is divided into the nose andtikil sections.
On the front part of the ,Nselagei.on the air-intake duct, there is a movable.:
bons which decreases the plane's resistance and creates optimum working conditions
. for .the ?itgi tie during flight.
..':TO prevent:diturbances of the air.intaloa duct, on the fuselage thire .are?
automatically. controlled vines on 'opposite sides; ahead Of the engine inlet on ?
. .
. .
. . . . . .
'the. siddei-of the fuselage ..there are: aumillark air-intake vanes (le, .(i- vanes).,
. On:the...fuselage :eim..thred brake flapp,t.two front end one Sar flip,'
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Tile cockpit enclocure canopy is streamlined, affording the pilot a good
view ahead and to the sides. The canopy is designed so that the tem forward part
. ? can be opened on the groupd, or ejected if necessary during the flight by means,
of the emergency release handle.
The canopy has a ? liquid de-icer.
The plane has a type "SK" catapult seat which allows the pilot to ejeot
himself from the plane in an emergency, at high or low flight speeds. The hinged
? part of the canopy, during ejection, is used 'to protect the pilot from the oncoming
. air stream' the canopy is not released but carers the seat, which during ejection
retains the canopy. .
To keep the pilot from being hit, the plane has armor, consisting of an armor-
1
screen forward under the canopy, .'
?
a n inecalawn a,. IL,11 fltCtfl1
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. armor plate on trans. 6 and 114 and an armor-plated head rest on the seat.
The wrings Of the plane are delta winos with a sweepback angle of 57?1 the
trailing edge of the wing forms ? W.-angle with the fuselage amis.
The wing is made of high-speed profiles. The area ii 23 ml, the span .
18.7.16 m, the chord with respect to the axis of the plane :is 5970 ma. The
setting angle is ? 0? and the lateral dihedral is -2?.
: On the wing are ailerons with axial aerodynamic compensation and "floating
-
type" wing flaps. The "floating-types design assures -a decrease in the flapping
angle of the wing flaps under the influence of impact pressure with increasing speed.
controlled '
Tho horisontal tail section consists Of a . stabiliser with ? oweepback
angle of 55?.
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'The piebilizer.loneists of two symmetrical. helves7the. right-ens:11 ' 114
.. The vertical :tail Neotioh.,. cooe'stipg...of a .vettical...401
..an ,a .rucider,
llas...
. a sweeriblok ;angle. 0,00; The rudder - hes axial aerodYnamie compeasation.
' The 31fturhojetengihe-with Controlled boost Makes.poseible?smocith regulation'
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. .. . . .
....tof the traei ih'beCat'regieeiroathe poiitiolimiiiimam blostte:thelt#oeitios,:?,
? Onal ix.piti'ta. ?
The raell?syetem consists of the system, including siven'taaba6t.ense..?
" ? ??? ? ? ? : ? .?
inside
the f'us:-Jlageseici Wing;..tank?oaite tt) divided into three imoupsiand.
. ?
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? ,oss. suspended A:Saki There'll :e)artinR eySte? for starting the engine
.:on the ..iround. sin d: 'left ?
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NA sywar Tr ATIMVII/NA IrtSRVM ARRAAD/GANTRAI LEI) DISSEII
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The Plane has a three-wheel lending gear which is retracted during flight.
The wheel base is .14810 Ns, the wheel track is 2692 sit. The front landing gear is.?
?
retracted forward and housed in the lower part ,of the front of the fbeelage... Thor
:main landing gear is housed in the wings. When. the 'main' Ilanliing gear is retractdd,
?
? ?the Kaki wheels turn. relative to the Strut and are housed in. the fuselage, while .
the struts are housed in the-wing.- The main landing gear has .KT-82 wheels .with?
tiree
660 the front landing gear Me a 'iT-38. -wheel with a 5OQx8OA (jtire. ?
To decrease the landing distance, .the plane has:a:drogue 'chute in the
.section of the fuselage.. The Parachute is designed .to:!ae .rileased the moment the main.
Wheels touch ground.
Theyneumatio'.gystee aonaista of two independent Systems: the mainsyitem
and SA 1411?0110i Ohs.
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1 serves the following purposes:
The main syste% to brake the wheels, lift and pressurise
the canopy, relsaie the canopy in an emergency, recharg2xg, closlitg the fuel shut.-
- off valve, operate the de-icer, release and ejoot the drogue chute, and feed the
anti-0 suit.. The emergency *steM'releases the landing gear and brakes the wheels
in an emergency.
ihe hydraulic system consists of two different systems. Pressure is
Created in each of them by a variable-output pump which creates a maximum pressure,
1
of 210'kg/cm2.
The first hydraulic systems serves .the contirol system (the two-ihaMber
.43U-51148 stabiliser. booster and the BU.h5A aileron booster).
The ;second hydraulic xssiem serves the
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r 12 V 'V
landine,gear, the WillA flaps, the
rake flaps, the adjustable engine nozzle, the
? cone at the air-intake duct inlet, Ithe fire-prevention vanes, and one chamber of the:
BU-51MS booster (the other chamber id served by: the first hydraulic system); it also
takes crior for the ? first system for the 'aileron boosters in case Of
. a breakdown in the first system.
In the event of a drop in pressure or a breakdown in one of the two systems,
the BU-S1 MS booster continues to operate on one chamber, fed by the system that
Still operates.
:Me hydraulic system that servo, to control the plane inoludet an emergency
pumping atation which, if the system breaks down or theengine stops, maintains the
required pressure in the hydraulic system to &Deur. e safe landing. .The pumping
station is switched in autoMaticellY.
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? The -stabiliser is controlled by ? .Control handle using a BU-$11.4 booste. r
and an 01.14V. 'aUtornetia .device.
?
'he ailerons are controlled by a control handle With the aid of BU4L5e..
booster. i Iri the ',Vent the SU-Oa sboosters are cut out and both hrJraUlie. systems .? .
'fall, the boosters perform the funetions of rigid unite of the aileron control ?
.The r.xder is controlled by pedals, i system of rigid connecting rode, And
a nonlinear mechaniem.
The pilot'. Cockpit is pressurieed,' affords a good View,. and a roomy. enough
for the. pilot to work conveniently. The cockPit is ventilated and conditions by
'hot and cold air :taken tran. the:engine oontpreasore The cockpit?hee ,autsimatio .
??taciperattire ,And'-oreseUre contra. .
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To assure normal conditions for the Pilot at great altitudes, the plane
has an oxygen feed and caspensation system for the pilot.
' Electrical and radio equipment. The d-c power source is ? OSR.8T-12000 VT
.generator-starter. As a reserve power -supply source theplane has two 1f3T'S-45
silver-sine -storage batteries. .
The plane hie provisiOne fdr etarting the engine by means of the on-board
-.storage batteries. A converter Nieves as the d-o Power source.
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The plane has the following radio equimenti
1. A composite ultrashorticave receiver-transmitter!
21, An auttmatic radiocompaisj
. A low-altitude reiliCaltimeter$ ,
A marker radio receiver;
.5. The airplane equivalent of a radar identification system)
6. An aircraft radio rangefinnet.
The aircraft hes a fighter course system 101.
Tho technical description of the plane is given in four books I I, It, II/
and Ty. In this book we describe the aircraft design.
The general views of the aircraft are given in Pigs: 1 2 and 3 in Book /
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Fig. 4. Exploded view Ofthe plans.
1. Drop tank. ? ,
- ?
2. Trim tab.
3. _Below -fuselage.wedge.
I. Valve wedge. .
.5. Right wing cantilever.
? 6. Aileron
7. Wing flap.
8. Right half of the stabiliser.'
9. Vertical fin. ?
, .10. Tip of vertical fin.
11. Rudder.
,.. 12. ,Cowling.
13i Pylon.
Flare on main 'wheal strut:
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21. Air-pressure receiver (Pitot tube).
22. . Cylinder for raising and lowering
nose landind-gear strut.
23. Nose landing-gear strut.
24. 4Flaps on nose landing-gear strut.
.25. .Air brakes.
26. Flap for main wheel housing in ?
fuselage.
27. Left wing cantilever.
15, m'afn Landing ..pear strut.
I '
16. Cylinder for raising and lowirriAg male landihg-gesr strut.
17. Canopy. ?
18; Nose section ofthe fuselage.
.19. Tail section of the fuselage.
20. Lett halt of the stabiliser. '
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CHAPTER :',It ?
DESIGN OP NE Aift1ISAMS -?
The Duielig?
Oeneral ?tnforeation..
. . .
fuselage. is a cigar-shapeci ?? elliptical cross section with:
butCavay 'nose and tail cones.
'Ili is a eentimonocoque fuselage made mainly of D06 'and D95 material using
joints.
? For mounting, removing, and examining the 'engine for regulation operations,
? .,-.the iUselage can be 'split into two parte--thenotie and tail sections.
? assembly ?
?
The transverse . ? " of the. nose of the fuselage cons1 st sof
. .
28 ? frames '? of whitil Nos. 2. 6, 11, 13 16 16A 20 22, 25 and 28 are
i the main ones.
' .The len tudinal assembly consists Of longerons and 'trusses With :a? few
tringere Whin is -compensated for by using a relatively thick
-covering,'
? Such a ajein?makes possible maximum use of the inside of the. framework.
The nose section-et:the Plane is asserted in xatsab panels. ?
The t.rri roe .aieeteiiref the tail sectiorco.f. the fuselage ?masts of 13
'frames, of 'whit! 31),:?35k, and 36 are the 'Main ones.: Stringers make up the.longitudinal
. ?
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I. Nakt..op of the Noserof the Fuselage
(Fig. 5)
The nose section of the fuselage is made up as followsi along the forward
5
Section of the fuselage is the air-intake duct with anzaztakbe inlet section which
..canbe regulated using an adjustable three-position cone (1).
The upper section between frames 2 and 6 contains the radio and electrical
equipment (2); the lower part of this section is for access to the nose landing- ,
gear strut.
?
Pressurized cabin (4) is located between . frames 6 and 11; the storage
battery section ii beneath the cabin.
, Behind the cabin, between frames. 11 and 28, are the holders for seven light.
kerosene tanker.
from frame 11 to frame 13 - tank No. 1 (7)1
from frame 13 to frame 16 - tank Na. 2 (8), and ? second auxiliary tank tam
(i4) between frames 14 and 16;
time trims 16 to frame 20 - tank No. 3 (9)consisting of ant upper and lower
troM frame 20 to frame.22 - tank No. 4 (11)1
frail frame 22 to frame 25 - tank No. 5 (12)1
fromItrame 25 tn frame 28 - tank No. 6 c13)6 .
1
Tanks Nos. 5 tnd 6 Consist, of two parts connected together.
The air duct for the engine passes throughthe nose section of the ftselage;
ahead of the cabin it separates into two parts and circumvents the cabin. Behind the
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Pig. 5. Airframe ard mike-ap of the nose section of the fuselage.
ti?fe.lte.
a) Pitot tubs k b) oolkpit canopy, o) air duct, d) engine housing;
e) ingiAa.mixnt b6sm, f) air duct g) (illegible), h) front $ 1) cockpit floor,
j) left brake flap, k) compartas for second auxiliary tank, 1? cress seotion AsA,
m) rear brake flepiii) cross section -8, o) sarelre hatch, p) air ducts, q) non-
wheel housing* r) uppers) tank No. 2, t) air duct.
? 0i4
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a19.
? ;
-cabin both sections converge into a Common that to feed air to the engine compressor,
I ?
. Oh the .side Panel's of the . fuselage, on 'both sides between frames ?
? . Velvea
2 .and 3 are located 'adjustable anti-Surge 7 (16)s, while between -frames 9 and 10:-
-?
there are two air-duct pressure-relief valves (6).
Ih the duct ahead of the engine intake, between frames 21 end 22, is located ?
???? the ? air-Air radiator for the 'Cabin system....
? I
Between frames .16 and 20, ir..the sides. of ?the fuselage., there are housings
: for. the Main landing-gear. Wheels (10)..
.The region between frames 22 and 28, along the fuselage axis, is occupied by
the power plant..
In the lower part or the fuselage, between frames '11 and 111, are two brake
flaps (15), while. between frames 22 and 25 there is the rear brake flap (17).
The brake flips are looked With special looks if there is no pressurein?the
??hYdraulie Mixt,uria:
. ? . .? ? ?
? nose section of the ??
There are a number of hatches in the/fuselage ? for servicing Of the equipment....
Al/ the hatches are semoseatk nd require idaily Maintainenca to enure that they are
?
fast.nidL
'The pladiseni of the hatches is shown in . ?
. ? ?
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RbP80T00246A028600420001-8
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50X1-HUM
. 6. Diagram of. the location of the oysietional hatches on the airoreft.
!1).1eft nide of fuselage, Wiiew of wing frai above, Lo) tight. side of foielegea:
d) view of Wing frea
50X1-HUM
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50X1 -HUM
Fig. 6. Diagram of the location of the operational hatches on the aircraft.
install ground look on emergency
4 Radio equipment; ? 2. "Open hanopy.
, cockpit handle; 3. 79. :Electrical equipment; 14. Technological ha tt..; 5.
units
Kerosene system 6. Oxygen-feed reducer; 7. Tnepection hatch; B. Aileron'
?
actuating arm; . Wing-tank joint; 10. Tank rill; 11. Float valve and emergency
eupply signal; 2 93. Kerosene tank drain and aircraft Control; 13. Gasoline
rill; 14. Tank; Kerosene stoke- 14 5i .nci: 6; 16; 52, 86, 8t. Engine
units
I IT 72: Engine stOutitel. 18. Engine and hydraulic system
_
,
: :19. Kerobene? ta). lirain and :Control,: go , Rooster-System Pump'Conn Ctionj .21.
"11Ydraulicreretem. tank fill; "22. -Kerosene-line joint... 23; ...ARU4V,;: 21.. .ThOrrdooliplei '
. _ .
. . . .. .
. . . . .
. . .
. . . . . ? . .
'.. 25. . ARU-EV. ba ng ,Ise on144Srl 1 ?:26..: Hydraulic accumulator .. of ,the bo.ister System;
1 ' . . . ... . . .
50X1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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27. NP?27 pwsping station. 411;ekammhisestalaliiissmolmsemaser and MRP-56P; 28, 35, 36,
37. Fastenings for redo wires and elet-antenna mmeidoaragimiemeemse driver; 29, 141,
'
65. *Stabiliser control; 30, 31, 32, 33. Actuating ens for control of R.P;
ID-2 transducer (K5I)1 la, 614. nasals cylinder; la). nossle hydraulic tube;
IA; 92. Afterburner attachment{ 115. Ix: Drogue chute look; 46, 91. Rearing ,
lubrication; la. Drain for telescoping connection; 148. Drogue chute; 149, 89.
Detachable hydraulic valves; 50. Neelage butt joints; 51. Kerosene drain;
53, 71. Engine and hydraulic system units; ,514. Kerosene drain; 55. sediment i
drain; iiinallelairsialimielowommionemodkrobsiodip 56. Kerocene and hydraulic
gigtefle units; 57. Pune for third kerosene tank. Control{ 58, 74. Kerosene tank
No. 3; 59.' Kerosene system Jilts; 60. Kerosene line and line Pm cockpit ventilation;
1
1.
61, 82. Brake flap attaohment) ?
?
S-E-C-R-E-T
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S-E-C-R-E-T
-23-
62, 81. Landing-gear strut axle; 63. Rudder actuating arm; 66. Hydraulid accumulator
,
- for the basic system; 67.; Thermocouple; 68. Hydraulic tank fill; 69. Aeim-tank
L. safety valve; 70. Connection for ground pump.of the basic hydraulic system; 73:
Hydraulie units; 75. Dolts for attachment of kerosene tank No. 3; 76. ilizzioccipt ?
tax Charging of oxygen feed; 77. Wing-tank connection; 78. InspeCtion hatch;
8$3. Tow-line attachment point, in emergency; 83. Voltage regulator. )CAF-I2A
turboCoolers. Connecter withOatchl 85. Fire-prevention cylinder; 88. Duemmak Heat
warning device; 90. EK-48, MRP-56P; 94, 97, 100, 103. Attachment for special
suspension; 95. PUS-36. Electrical detachment; 966 Landing-gear strut axle;.
98. Nonlinear mechanism; 09. Air cylinders; 101. Kerosene fill; 102. Electrical
? ? Atetts
separation.of Carrier; 104. Aileron actuating are; 105. 'Ammmmaah to 8/i ....Ne);
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1076 Power-assisted control; 108. %ling-flap cylinder; 109. Place for ground
Jack; 110. Destruct button; 111. Alcohol fill; 112. Battery hatch; 113. Element
- control farad* emf of the storage batteries; 114. to MN(?) units;
115. Airfield powering; 116. 444gialt t.43 electrical units; 117. Hatch for logirisii
- to front landing-gear strut unite; 118, 119. Hatches for examining the bolts of
the control actuating arms; 120. Hatches for =ash to the bolts that hold the
booster in place; 123.. slismomMin Access to aileron axle.
a r i n V
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Diagram or technological mmtpartmento of the nose section of the fuselage.
2) forward* upper compartment; 3) compamtment from frames 6 to
?
opkommr;
111 4) side
panels frcm
10) upper
panels' .5),ccmparbsent from frames,11 to 13; 6) bottom panel; 7) aide
frames 13 to 20; 8) side panels from frames 23 to 28; 9) lmttdm panel;
panel.
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" S-E-C-R-E-T
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
S-g-C- R-E-T
50X1 -HUM
?26.,
.Design of Nods Section .of 'FUN left) (Fig. 7)
The nose section' of the fuselage, to facilitate assembly, is divided into.
the follbving compartments an d.panelei the. nodes. tyctrotex. nacelle Up to frame 2
. (1); the front Upper compartment from frames2 to 6 (a); the compartment from f.rames
6 to 11 (3) tide. pane]. ? from trims 2 to ii (Ji); compartment from frames 11 to
13 (5)i the upper panel from frames 11 to 28 (10),i, the lower panel from frames 11
to 0 (6); the dide panels from frameel 13 to 20 (7); the side panel froM frame's 20
to 28 (8); the i.c1?er 'panel from frames 210 to 28 (0); .the inner sich panel.'frai
.. ?
. frames 20 to 28; the. engine' mounting frame; the forward brake haps; the housing
for .nio right brake flop; the homing- for the lef brake flap; and the third tinier
?
flap.
:Nose Nacelle (Fig. 8) '
The. nes.e nacelle, from.the,nose -t.
oframe, 2, is ?ifl. the fon, of a
t422.WitA a sharp leading edge. ? ?
In the ? center of the air-iritakeil duct is radio-transparent cone (2) made Of
triplex glass texthlitat two .laye are .1.2 mms.thick, and one '
T4te.ione7is.att.aehed to e-positionoylinaer (5) which wibVfil along tube
?
(3),?Whisk.il ibm, the s4i of thi cone. The tuba is made. or ZOKhOSA. materialoitt-a?
O ? re rirL:r v. ?
50X1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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III 1
Declassified in Part - Sanitized Copy Approved for
' ?
Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
50X1 -HUM'
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S-E-C-R-E-T
-28-
telescoping cons. _
1. :Nose nutelle{. 2.'te1eSooping-cons'; guide tube; le diso; 5. thres-position
cylinder; 6.. adjusting slider; 7. hanger; .8. articulated cantilever; 9., support;
; 13i
.10. -spring; 11. 'self-locking bolt; 12. bushing; rod for Pitot tube intake.
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S-E-C-R-E-T
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50X1-HUN
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
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' One end of
Attadift4.14.ttlime.a.? cone-control hydraulic cylinder ( 5) is attached to
frame 3 and the other ant is a'ttaciled to adjusting slider (6).
The lower Part I the fron nacelle Contains a revolving rod for the Pitct
tube intake (13). It is .attached the front nacelle by two steel,iussenblies-.
? the front and rear--vhich are lode ed on the lower spoke.
The front rod-attachment aeltembly has a univerbal bolt joint. The rear ?
assembly is in the form of a conicel pin which is attached by the self-looking
vertical bolt to corresponding assembly on the Auselage. The rod between the
assemblies has aii opening tope condensate tran,, and fnr,?exit of the cor.vminination'
lineso
Articulating Cantilever (8) is -useif.te fix the rod. in in inclined .poeition;
?
the ? rod attachment Unit is covered on the outside with a detachable cowlipX.
?
? The lower spoke or the .?front .nacelle has a tube for passage Of the cosalUni.1
? I. . .
cation lines ani a tow unit is attaChed, made Of. ZOKhRSA steal.
'Frame 2 lie main. -.Palt,ana.. de of ' .materialj in the upper ?part .is
AIcLi,
-?
an insert, of materiel.. A.. disc, of Yft. material,is it riveted to the.
frame; the cone tuba is. attached to this disc.
Thecantilever Of frees 2 has an end witch which signals that the cone is
eXtended.
Pront.Compartment. from Frame 2 to Fripare
Tt.is ceapertment from frame . 2. bo trams. 6 contains'
50X1':HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: -CIA-RDP80T00246A028600420001-8
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S-E-C-R-E-T
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a upper'hitch for the radioequipment, and a housing for the front landing-gear strut.
? The compartment.has four Z4shaped stamped trusses made of sheet
duralumin D.16 with tubular spacers, and a horizontal bulkhead (also of D.16 dura-
lumin) which separates the equipment compartment from the nose landing-gear housing.
.The horizontal bulkhead has a small hatch for access to the RVU units.
-
? The main longitudinal assembly of the compartment consists of two upper and
two lower W-shaped longerons.
The side walls of the compartment are made of 1.2-ems sheet D-16. These serve.
as the inside walls for the air duct.
Compartment from Frame 6 to Frame 11
Frames 6 and 11 form the cockpit and the bottom equipment hatch which are
divided by the cockpit floor.
The main transverse assembly of the cockpit compartment consists of two
main wall frames 6 and 11 and 8 intermediate frames. The longitudinal assembly is
torrid by the upper and lower W-shaped longercas and the panel beteelath the canopy
with a groove for the pressurization hose. Sheet D.16 is the material for the
main elements and the covering.
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631..
The control cables which pass along the cockpit floor are covered by an
auxiliary removable subfloor.
The mein cockpit is pressurtzed by means of a U-30M pressurizer.
+le framework of the lower part of the fuselage under the cockpit is an
assembly of frames made of sheet D-16.
Tp frame 7 ie attached the hanger f=rhedtdierweatts that contains the lock
for looking the front landing gear in the retracted position.
Frame 6 is ? main front a tattcruoimexd partition of D-16 duralumin, is
attached by means of D..16 angular profiles placed along the outside contours of the
frame, by vertical molded angular profiles made of V-95 esterial, and by two
extruded trusses of V-95T material.
To this partition are attached the forward armor plating and the unit for
suspension ofthe front landing gear.
The lower part of the frame is cut out for the front landing gear and has
a support for the landing gear in the "down" position.
Frars 11 is a rain frame, a partition of V?95 material with an assembly of
profiles made of V-95 and D-16 material. To it are attached the rollers for the
ejection seat, the rear armor plating, the canopy bulkhead, them upper fuselage
panel, and the actuating area for the aircraft control stem.
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*32-
,/ Side Panels from g,Tans 2 to Frame 11
The side panels from frame 2 to triune 11 twill the outside walls of the air.
ducts. From frame 2. to frame 7.the. panels are made of 3.5-mm D-16 sheet duralumin. ?
On .the panels between frames 2 andl are attached two adjustable anti-surge valves
pratz4,11. M abruis.. .?
. ? -froa-shel-Ms-8-.64.14ton..
Thepanel frca frames 1 to 11 has two coverings (the outside one from frame
nd the inner one from frame 8 made of 1.2-mm D-16 duralumin).
The transverse assembly consists of Z-shaned frames of D-16 duralumin.
'Between framee 9 and 10 On the left and right panels are pressure-relief
valves?folm &law= MI4rVith the inner Sheet made of 'D-16 duralumin.
On the right side of the Oottca part of the panel is a groove made of
11Ch18N9T-ll steel.
Compartment frau Frame 11 to Frans 13,
The compartment from frame 11 toframe 13 is made of D..16 sheet duralumin.
4,serves as the housing form kerosene tank No.. 1 and Consists ofs panels 11 and
' 13, uppei removal:8s hatch on the right aide, and outside covering on the left side.
The air-intake duct which passes through this compartment isms made of D*16
IN? ??? 04 ? ?
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Frame 13 ii a main frame, made in the form of a gilatieV -95 material with
, an opening for the air..intake duct.' Stir tank No. 1 the partition of the frame ie '.
i
. attached by me Ms of extruded profiles; at other plates it ls attached by means of ,
I
.' angular profile made of D.6 material. To the left and right on the frame are
1
-. theunite for lttaching the wings to the fuselage. !
1
The bottm arc of the frame is a double T-aection. To it sre attached three
aileron actuatiim arms. The coupling units are Oadt of ML5 -I Eiektron.
The Upper Panel from grams 11 to Frame 28
The unper panel from frame:11 to frame 28 is in the form oi a partition
made of 211.236 sheet D-16, to which are attached two main longerons.: The longerons
are made of V-95 ani are-strength ned by angular steel profiles.
The panel at frame 11 his a flat cutout for the canopy. To it are
attached the units for coupling the aircraft-control actuating arms.
the
To/longerons frtm frame 11 to frame 14 amleattached the rear of the canopy
with its glasswork; to the longerons from frame 14 to frame 28 is attached the
ktc(-puit'
.removablet. which eoni4sta of three parts with joints along frames 20 and
butt?
25. The/two:1 is made in the form of a parabolic-cross-sectional second structure;
(Pitt ?
of sheet D-16. The
ii attached crosswise by extruded frames of D-16.
4T;iek.1
wires and also the electrical..and dio -equipment cables.
it contains .the stabilizer amialmuemmimaa_and rudder control
s-v-r T
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" The Lower Panel from Frame 11 to Prima 20
The lower panel from trams 11 to frame 20 is attached to the bottom longerons
of the side panels and to frames 11, 13, 16, 16A, and 20. The longitudeuval assembly
channel -section
from frame 11 to frame 13 consists of three/trusees on the ripht?and two on the
chanrel-section 1,
left, merle of V-95 material; from frames 13 to 16 it consists of two/cast trusees
1
'of -14L5-/44 material; from frames 16 to 20 the profiles are nude of 30kh0SA steel.
The panel has a number of intermediate half-frames 12, 11s, 15, 17, 18, and '
1
1 1 .
19, the lower parts of i'rames 16 and 16A, and ilso auxiliary transverse elements i n
1 4 I
the form of two side longerone. passing from the trusses of the brake-flap housings
'
to frame 20.
I
To the cast trusses at frame 15 . is attached the unit for coupling
the line for feeding the ? ? ' tank. To frame 16?ie attached the bracket for
forward attachment of the pylon ofther
dron. .
tank.
At frame 16, to the trusses are attached two angl ? plates made of SZOIOASA
steel; these extend to frame 20. At frame 20 they are 'joined to the bracket for
the rear attachment of the pylon of the drop tank.
?he panel covering is of sheet 0-16 duralumine
wheels of the
The housings for the/mein landing gear are between frame 14 and frame 20.
The duct from frame 13 to .trame_20 is of round cross section and is made of
S-E-C-R,-13.-T ?
50X1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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Frame 16/ a main !rime, is in the ihare of a ring formed by/V..95 partition
and angle.profiles of V-95 and SZOKhOSA materials. /n the middle ofthe frame
(
there are extruded rlates of V-95 alloy to which are attached the steel assemblies
for coupling the wing and the fdselage.
' The Side Panels frcm Frame 13 to Frame 20.
The side panels from frame 13 to frame 20 are made of sheet D-16 and v-95.
with
Longitudinally, they are attached by_thelOngerons
-
hatch framing made of 0-16 angle profiles and bulb-profiles along the contours of
the cutouts for the housinge? of the main landing-gear wheels.
Inside, between frames 13 and 14, on the riFilt is a sleeve consisting of
a Z-shaped profile and a covering.
On the left side, between frames IL and 16, there is the housing for the
second auxiliary fuel tank.
I I.
The side panels are 'fastened to frames 13, 16, and 20. The ,upper and lower
longerons of the panels are ri;noted to the upper and lower panels.
Frame 20, a main frame, is a partition of V-95 material, in the fora of a
ring, and attached by prefiles of 0-16.
On the right and. left, angle profiles are used to join the walls of the
main Wheel wells to the frees.
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.,
? he lower part attne frame contains- the bracket for, the rear attachment
i
Of the . kip-tank pylon. The bracket is drop-forked of AKb-1 material.
. ,
liie Side Panels: from Creme 20 to Frame 28
The side panels from traits 20 to frame 28 are made Of sheet V.95 and D?16..
They are attached. to frames 20,22, 25, and 28. The upper and laver panels are .
fastenedto' the longerons of the side panels.
The longitudinal assehbly of each side panel consists of the fbllovings.upper
and lover longerons at V-95 material, stringers and molded profiles of D.16 material,
and profiles laid out along the contourof the wing profile.
; air-intake- duct ends and .the .engine compartment begine.. The: frame contistsof
four sections bolted together. The upper end levet; parts of the .frame are. of
channel xmiattion cross section, extruded of V-95 material:.
'to .the bottam part ars 'attached the "units :for coupling the controiaotUating arms.'
?'
? ,
riett and lett -parts Of the frames tra forged channel-section cross-
beams, made of SZOKht1SNA steel.
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Each has four collar fittings for attachment to the upper and lower parts of the
frame, and four horieontal eyelets for junction with the virg-attachment fittings.
The Lower Panel tram Frame 20 to Frans 28
The lower panel from frame 20 tofrare 28 ie.a longitudinal J1,-shaped kmgm truss
molded of V-95 materiel.
442/44?11-4"Aip
At frame 22 to the truss is attached the fitting for
attaching the rear brake flap; at frame 25 is the fitting for attaching the brake-flap
hydraulic eylindrr made of S20KhO9NA steel.
Inner Side Panel from Frame 20 to Frame 28
The inner side panel from frame 20 to frame 28 can be divided into two parte:
the compartment from frame 20 to frame 22, and the panel from frame 22 to frame 28.
The compartment from frame 20 to frame 22 is part of the round air-inlet
duct, made of D-16 material.
. The panel from frame 22 to frame 28 is the inside plate of the housing for
kerosene tanks Nos. 5 and 6, on which are installed tracks for mounting the engine.
S-E-C-R-E-T
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The rhgine Mounting Truss
The engine-mounting trues is between frames 22 and 28.
The truss is a built-up beam of V-95 material; it is a wall with a lipped
upper flange and a lower flange made le from a molded T-profile.
At frame 8 a recess is rade in the truss for the coupling bolt of the math
engine mount.
A forked fitting it attached to the upper part of the recess. for the coupling'
bolt; a support fitting of SZOKhOSNA steel is attached to the lower part of them
recess.
Frans 25 is a main tram. It is in the term of a horseshoe with ,a lower
aro-shaped tie piece of double-T cross section, forged from SZOKhOSNA steel.
Tim main part of the trains consists of two halves joined to the engine-mounting
truss; they are made of
V?95 molded angle plates.
a V-95 partition and flanges made from
On the partition of the frame are a number of reinforcing struts, while
in the middle, from both sides, there are brace plates and profiled of V-95, to
which the steel wing junation fittino are attached.
forced
The bottom part Of the. trans consists of two/partitions, betveen which is
'attached a trues of ZOKhOSNA steel. To this trues are attached the fitting for the
cylinder of the third brake flap and the engine-moOnting fittings.
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?
Houe.ing fbr -Flight Brake Flap
..The housing for the right brake flap, between fiamel and 13, is made' in'.
channel-section ? ? ? .
? the form of three/extruded trualses of V-9 material Which are bolted to frames 11'
and 1.3 .
. At frame 13 ?the universal Joint of the brake-flap cylinder, wade of DZOKhOSNA ?
'Steel, is attached to the trusses. At frame 11; the trusses have a bulge for the ?
brake-floip. attache* nt. fittings The trusses 'are. connected by ehoet. 0-16 partitions
?Housing Lf or .Left Brake Flap ?
The housing for; the left brake flap near. frames 11-13 is similar to that for
? ?
the 'right flap except that it is made in the form Of two extruded trussei. Be-
tween frames 13 and 114 them is In additionaltruse extruded of V-9$, and* horisiontal
? partition made of D-16.
Halfstrime 16A is extruded .of Sheet D-16 with flanges of D-16 angle pieces
and with MI..5.111 fittings, for. attaching the?loWer trustee end fittings to sujport A
_special. suspensiori.
: .
Frame. 28' terminates .the flees section of the fuselage and is theoinin. Ft. frame:
? . ' ,
for the hoe, and tail .?t Ions of the fuselage.
?
?
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? The from a rim of V-95T Molded, angle iron with/S2OKhOSA reinforcing
'angle ) Plate* to which is attached a partition made. of ghee DLI6.. ?
. .
The. Arne! flange of the train. is made of molded 'angle plate .from V-95
?
material. , To the :outer rim are attached..54portso dqock washer.. made Of 0.46T,
? I
for clamp bolt... '
. To the center of the frame are attached three V-95T fittings for auxiliary
setteetinent of the engine, and also fittings for ettectment of the rear of the wing,.
.in .14., form. of telescoping :eupporta with cap; of 3201ChO5NA steel.. :
Joint Fitting* (Fig. 9)
.,The nose and ta 1 sections of the fuselage are :joined at frame 28 Of -the noes
Section and frame 28A of the. tall section. The fuselage joint is a fl
. hawing ithree guide pins and 18 joint .... (rest of paragraph illegible)
? 50X1-HUM,
. ? , - I
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IptifittrTmtlitittTtittneudwinntstsintetulartuffnultuauuhiri?
50X1 ?HUM
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Bli.tt. ;tilt Of, noes and tail beatioria Of fuselage. 1) rtaitel _28t .2) guide
pintlei 3) fkame.29f 4)1 jo4.411:bitles--#) 'cap) i) hatch; 7) nuts 8):?rabber seal
9)
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50X1 -HUM,
The -joint it ril?Tle .13 ii ? fork-type 'joint with. one vertical bolt.
? ? . .?
The joint. at from. 16 has an upper and lower fork, in the horizontal Plans,
and a middle :big in the vertical
accomplished by i vertical ? eteppe
by a horliontal. belt, fastened
plane. ? The jot. at each fork le ?
bolt. The:joint at the Middle lug. is .eccomplisbdd._
in tantilever fashion in the lug of the wing spar.
1he joint at frame .22 is of the cellar type, with two vertical clamp. bOlts,..
? ?
. .
The joint atframe 25. is Of he forked type, with One bolt and a nut..
-? ? ?
joint at?rrac*28. ii accomplished by a: ult. -?bi?A is. inserted end"
- - , ?
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:locked, at thi firs. . win g in the telascOping...Ooliar .fitting. ?
. . ? ? ?? ? ?? .. ?
S-E-C-R-E-T
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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2. Design and Maks-Up df the Tail Secticm of the Fuselage
- (Fig. 10)
?
The transverse main assembly of the tail section of the fuselage consists
of 13 frames, the longitudinal stain' assembly consists of stringers; the covering
r
I
is mad. of D_OATM. 11, 2, and D -16AT, 115.
Frames 341 35A. and 36 are main frames, Made of. SZOKhOSNA steel; joining
;/-
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/
frame 28A is made of molded D-16 profile, and the other frames are made of X-shaped
D-16 sheets..
The stringers are made of molded D-16 angle pieces. The four stringers
that frame the cutouts for the parachute and the MAN antenna are thicker.
At the bottom left between frames 30 and 32 is the well for the fuesposm drogue
k
chute.' Antenna MRN-56P is located at the bottom right between frames 30 and 31A.
?
frame 28A to the end, along the aids of sysmetry.
ventral fin passes along the bottom of the fusolagerrom
The 'front part of the tin is radiotransparent; at the rear of the fin, behind
:frame 36, i. the drogue chute lock.
The engine cowling is inside the fuselare from frame 29 to frame 34.
The stabiliser is attached to an axle
frames 31A end 36.
that rotates in bearings mounted on
,
I.,
The engine afterburner is attached to frame 36.
plating:
Thr fuselage terminates in the tail nacelle, made with no inner - 1
R. ?
There are snecial air-inlet ducts at, frame 3IA te for engine blow-off. I
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
50X1-HUM 1
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? Fig. 10,. romewer1COr till section of the tnielgge And. the -tail.
? ? . ? ? ? ? I' . .
I) ATIMOlir iluddet?''fairingi b) ruddep e back4aii!ingl:41.ti44.'
t) atabjijier .0tachnOnt irussi 'g) Joining trame
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I ? I ?.
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2. Canopy and rjection Seat
The canon, and the ejection seat form the system "SK" designed to save the
' pilot when he leaves the plane at speeds up to 1100 km/hr, by instrument.
A. Canopy
1. General Information
The canopy of the Ye-6/ is designed to cover the pressurised cockpit, pro-
toot the pilot from the air stream, and assure normal vision during flight and when
landing the craft. /n addition, the canopy in used to protect the pilot from the
incoming air dmcdmet stream during ejection. . '.
?
The canopy (Pig.11) is a streamlined transparent secondary structure on the:
upper part of the fuselage between frames 6 and 13. The rear of the canopy forms
f.
.4 Smooth junction with the back-fairing.
The canopy consists 4 the lloving.basic partst
.?
-.the hinged part,.
-.the tan rear section,
--a heat battle;
--a transparent screen.;
--aide flap..
The canopy has the following eystems to'fuifill its functional
? -.preasurisaiion and cortrol1systetto0 '
-temergenoy ejection system;
.leeat-retention system; -
?de-icing erste% ? ?
? S-E-C-R-E-T
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
50X1 -HUM
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When the cockpit is opened, the hinged ,part of the canopy lifts out and Up,
. on an axis on frame No. 6. The hinged part of the canooy, is lifted by an air
,
?? cylinder.
The canopy ie preeaurited after it is lowered and locked in place. The canopy-. .
" is depreseurised either auteMatically, when the leeks are removed, or autonomously,,','
? ..?
using.the.preaeurizatipn. thumb button'. The preesUri.sation hone ie :located- in the
fuselage.
? The sir cresaure in the preseurisition:hoee,is 1.7..2.55 kg/cM2 The pressure .
.. . .
: ? ?
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in the hose ie lees than that behind the .reiiUer due to the preieure *drop because
:
of 'reel stance n the check ?vale. : ?1
The Ca..
oy.tan be 'released, .in in emergency, by meina.of the emergency :
. ? .
? . releae? andle on. the right. aide hf:the..fueelage.. The emergency locks are released
by means of. .? yroteahnii3 aye tem. The canopy le raised hy lift. PY Indere to Which.
. I
-log lair .at a p assure of 130: kg/cm2 iil fed.
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-.- During e ection With canOpy...ehielaing, the canopy 'eeParates from the N selage
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and le sheld to he seati .the. emergency ?canopy.lecks ins:this case 4 releatied?b
. . .
',seat pins.
?Tie canopy emergency ejection system is tnterlinked with t seat firing
meohanisrtt; if nedeeeary iii..eject ',after emergercy ejection of the ci.nopy, part of
4::.HenoefOrth, in Such expreeeiona?we viii uae 'the weft "canopy'
mein its hinged
,
? :50X1?HUN
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. .1,
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49-
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. ? bled off
the gases are from the firing mechanism. This prevrnts the occurrence of great
:overloadm due to, a decrease in the mass of the 01erteesystem.
2. Design of theCanopy (Fig. 12)
Hinged fart of the Canopy
The hinged part of the canopy (I) is designed in the form of a rigid
structure, bearing the convex main glass (1) and the flat front glass (17).
The frays consists of WO longitudinal side trusses (18), attached together
in the front by a cast bracket made of magnesium alloy ilia (32) and in the back
consist of
by an aro (2). The' longitudinal trusses Elsktron profile (26),
duralumin profiles and plating (27)rivetedtogether. .Rear arc (2) is of rigid i
rivited design and has a,cutout covered by special cover (3) made of magnesium
allay. During ejection with the canopy used for protection, the cover of the hitch
is dislodged by the pyromechaniam of the seat-stabilizing ahmtem parachute.
ThJ main glass (1) is heat-resistant organic glass,
x
The-glass s affixed in the side profiles by means of/Capron tape (20) glued to;the
1 . I
,
4 I ?
glass. .0nCedge of the tape to glued to the glass, the other is inserted into a
!,
brand ST-1, 10 mm thick.
special groove in,the profile (26) and held in place by i rod (21).
50X1 -HUM
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Along the'rear arc and the frame of the forward glass the main glass is
held in place by rubber gaskets between the outside covering and the inside brew.
.plates; these are tightened by bolts.
In .the longitudinal direction, between the ends of the glass and the parts
of the frame there is a gap to prevent contact stresses in the glass.
The front glass is silicate laminated safety glass 14.5 mm
frame (16) which is bolted to the frames of the front glass. .
The moving part of the canepy at the jointe is pressurized
U-)em .2 pressurizer (19).
thick in a special
by means of an
If there is no air in the plane's hydraulic system, the canopy can be lifted
manually by means of handle (5) on left truss (10); when not in use this handle-is
in a socket in the truss,' held in place by knob (6)..
The Rear Section of the Canopy
The rear part of the canopy (II) is not preesurized and is removable. It
is attached to the fuselage by anchor nuts. It is designed in the form of a frame-
work whichoontains the glass. Olais'(30), brand CO, 5 mm thick, is fastened along
the perimeter between the outaide,eoverim of the framework and the inside brace
plata; these are drawn together with bolts.
1
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : 61A-RDP80T00246A028600420001-8
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rig: 12. .CaisOpy,deeige.. ) creme eetion at "A-A"; .b). pro section at "G-6"1
o). crime section et "B-B 0). Cross eecticei"it...:?.r-f"s ?croanseCtiOn t
t) OroSa section at "E.Eof g) cross pen:A.1mi at:"X-rs .h).0oeor. pins 1). shear: bitati ,
56X1-HUM.
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A628600420001-8
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
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Fig. 12. Canopy design.
I. Hingdd section; It. rear section of canopy; /I/. Heat baffle; IV. Transparent
screen; V. Side flap; 1. Main. glass; 2. rear arc; 3. Cover; h. frame for trans- ?
parent screen; 5. handle to manually open canopy; 6. knob; 7. rubber grommet; 8.
0.41.41..9
of
? groove for preesuri tat ton hose; 9. framework of tY4'711?. section
10. Dural (7) pressurised bulkhead sheet; 11. glass of side,flaP;
' 12. gun.sight bracket; 13. de-icer collector plate; 14. outside frame; 15. inside
brace plits; 16. front-glass franc ;?17. front glass; 18. side truss; 19. 11-304-2
pressuriser; 20. oapron .tape;
?
50X1,-HUM
'50X1 -HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
50X1-HUM
pintle for ()Orating trim; 25. operating frame's 26. Molded at rlektron ptefilei
27. oovering$ 18. Dural ptOf1.1.al 29. glass of beat bu3.1chead, 304 glaael 31. rubber'
Monett ii; "04600 I . 33., bloit-Off. tube
Declassified in Part.- Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8 .
50X1-HUM '
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i
To or?ven t acetatet. emus etressee in the..glasei between the. covering and the: glass
.?:. there is "UPL.0.t1!. pec'king. take., while the openings in :the nano for the bolte to
paes through are made larger thinAhe bolt -diameter, and rubberbushins (7) are .
'.'?putin them,
Pressure Bulkhead??
pre BUM . . . . ? ".
The b4khead (III) ienarates the preseurited'dodkpit front the unpreeeurized'..-
.:, .
Lregion behind herear'eection of the canopy*it.ie attached to the panel behea.th.
the canopy to ramez 11, :Along.the.buteide. edge it is aottuatutd b ted to the front.:
?
-end! -of the re Election of the canopy. In the center it is attached by bolts. to '
"
--the armorpla
The Ores ure bulkhead le,Ofhermeticelli.sealed..flat design made of crimped
Dural
sheets (1 ) with reinforcing ridges stamped into it, and riv ted profiles':
?
Above and to,thiaides in thapressure*lkhead are tnaU ndovs fer..
exaelinaitonlef.therear hemisphere. The Windoim eOneist of.flat,0 ass (29), brand
so.(t), 5 (671 tom thick,
. .
?
It front, in the center at the pressure bulkhead, is aahanneied...
. .
north (!) which contains the:oehopi.preteurisation:hose:(22).
?1. 'OX1-HUM
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Transparent Screen
The transparent screen, of bulletproof glass (IV)f is located directly
beneath the front glass of the movable part of the canopy. It serves
, three purpose/it 1) it protects the pilot in front from direct hits by bullets,:
; shells, and shrapnel; 2) the oanopr rolls along it during ejection with protection
. I by the canopy; and 3) it proteoia he pilot from the air stream after release of
the canopy.
- The transparent screen is
* a rigicisteel frame (h) which is bolted, with h bolts, to sight mount (12). -
I.
t ea-sheet laminated safety glass 62 mm thick in
Side Flare
To the sides ofthe transparent screen are two side flaps (V) which have
- ? I
'small windows (11) made of ,organic glass. The side flaps together with the
transparent screen form a sort of baffle plate which protects the pilot from the
'air stream in the event the canopy is released in an euverienoy.
3. .Pressurisation and Canopy Contiol System
(Fig. i3)
The canopy is attached to the fuselage suspension bracket (1) by means of
two bolts which serve as axes of rotation when the canopy is raised and lowered.
50)(1 -HUM
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Declassified in Part - Sanitized dopy Approved for Release 2013/02/28: dIA-RDP80T06246A028600420001-8
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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Canopy control conflate in the opening and.olosing of the operating locks
; ? and raising and lowering the canopy. The canopy is controlled with a special 1
I
handle (7) on the lift side of the panel beneath the canopy. The canopy is pressur-
laid with hose (h); pressurisation is accomplished by turning button (15) whic
- is on the same shaft as canopy control handle (7).. On the panel beneath the canopy .
? and an the fuselage covering, near handle (7), are instructions for the correct
use of the valve.
Canopy control and pressurisation are possible both from ins.ide and outside.
. tkeFor this, the double-arm canopy. control lev"r? has two handiest one inside (16). ? ?
and one outside (13). The outside handle is in a slot in the. fuselage and is held
.in plIce by catches and knob (11). In this position, the outside handle is kine-
matically separated from the inside handle. When knob (1h) is pressed, handle (13)
?
moves out, and when it ts turne'd'aCen it engages the inside handle, after which the
canopy can be ooitrolled from the inside,
' it must be pulled ?
: To retract handle (13) . from the inside intil the handle
disengages from the inside handle and fits into its housing such that the catches
I
f the handle drop into place and knob (1h) can be turned, looking it in place.
.Pressurisation from the outside is accomplished by turning shaft (17) by means of
. I
a sorewdriver_placed in the ? at the and of the shaft.
. ?
. slot
. ? ?
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 :.CIA-RDP80T00246A028600420001-8
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loopj d. point "6"; 0. 'gee belatill f.? arose .eaction. at l'A-A,; g. gee. beloy7;... ?
? a. diagran.of -canopy attaclunent iihen auspende4 b. view at "B"; o. Canopy'.
?
? ?? h. remboiel of Oanopyj.1..frase.6. ?
.. ? eea_ _IAA ,
. ,
. ... ,
When- lifting the canopy; let : ??-. lisiiii-ided,
the-air out of the hernallo hoses ? ?
- before -releasing. the look ? ''' - ? ? - / *
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
*Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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Fig. 13. Pressurisation and canopy control system.
1. Canopy suspension bracket; 2. canopy lift cylinder; 3. canopy operational lock;
catch
..
Is. pressurisation hose; 5. 6. push-pull rod; 7.. (anile
? fnr canopi, control; 8. check valve) 9. RV-1.5 reducer; 10. air valve; 11. actuating
arm; 12. pintle; 13.. outaide handl.; 14. knob1.15. pressurivation push battom-
.
. ? Seei-ete..?
.
' 16. inside handle; 17.4.shaft with aplibe for pressurising the he canopy from
. . .
thecutsidel 18. 'swivel lock.
vet
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420061-8
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. -
The taitsPyie affixed in the lowered position by Di* locks (3) located ii
?
the luaitat panel beneath the canopy Look 3 ie\a (mat, bracket with a groove into:
I :4 r
which the cano/py loop. fits. Pintl .(1'2)b Moved \by. actuating arm (11) oroseei
.ttrocYC?
. ?
The eCtbatirig arils Of all the loc. ke areaohheetsd by connecting rode to ,the
-Canopy-control...handle //tilde to reveht the locks from opening before the
... . -
.. ., . Catch .
canopy is .released, the - rear left . - 'lock has .a \* ' ' (5) which covers . the kreOwe '.
. ? . -; 1' ? " .. . .
. at .the point when,' pintle (121 emerges. ? ?
- .;When the ..canopy is released .the loop. compresiescatch (5) And frees ..
,..
? . i
1
..pintle (14).
.,lowered
The canopy is ? : by means of.cylindere (2) Which get their air from the,
. lowered
. hydraulic system by. means of canopy-control Valinsa the canopy is by its
?
own Weight, dleplaoing the air frm cylinders (2) into the atmosphere.
i. ?The double-ann?cannPy COnt. ro :handle (rig'. 14) is attached to 'Penal (16)? .
and housing (i). it consist1s of rod (IA) which. has on it inside handle (,)i -:
. ?
pressurisation button (11); and; guid (?). Inside rod (6)-lasheft .(3) Containing.
outside. handle ;(.2)... Shaft: (3) is pressed outward by .spring.(6)- and in this position
engages shaft (14) 'by means of two ..screws :Screws (5) and the grooves in the'.
-
?
:head of shaft ()) are positioned asymmetrically, so that the outside handle engages ,
the insidi one, only in the ?down 'position.
;
5050 -HUM :
Declassified in Part - Sanitized Copy Approved for Release 2013/02./28 : c?IA-RDP80T00246A028600420001-8
Declassified in Part Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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Declassified in Part - Sanitized 'Copy Approved for Release 2013/02/28: CIA-RDP80T00246A02860042000.1-8
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: 'rig. 14.. Two .position,canopy -control ' handle.
?
?
1. housing for outside ,handle; 2. outside handle; 3. sti,af:ti 4. rod; 5. screw;
6. sprin;,2.'puide; 8. pressurisation push button; 9. inside handle; 10. syringV
1 ,
,11. nut;
. ,
. ?
12. connectingrod; 13..braoket; 14. gears; 15. pressurization and canopy
'control vales, 16. panel.
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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The preJpnts disturbing the handle when the canopy is Closed from the outside.
Guide (7)and button (8) have clearance relative to handle (9) and rod (4)
of 300 and 15? respectively. By means of the clearance of pressurisation button
(B) the canopy can be pressurized and depressurized when handle (9) is looked in
the extreme forward position. The toothedsect'on of button (B) is connected with
canopy control'valve (15), which is also on panel (16). The Projections of shaft
(3) and the sx stem of the valve ars hermetically sealed by means of gland packing
anda rubber ring. %hen the outside han9e is operated, shaft (3), by means of
connecting rod (12), deflecti the inside handle and does not permit it to be locked
in the fIrvard position..
Canopy Air System (rig, 15) .
The canopy air system is divided into the operating and emergency systems. -
The operational air system is desired for pressurisation and raising of the canopy.
It includes canopy lift cylinders (5), pressurization hose (B), canopy control
valve (11), air valve (12), reducer RV-1.5 (13), and.cheek valve (14).
The canopy lift cylinders (5) are located on the sides of the panel beneath
the canopy hear frame No. 7(7). Canopy Control valve to (10 is attached to the
panel,of.the canopy control handle.
50X1 -HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8 ,
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. 15. Canopy system. a, from cylinders, p ? 130 atm;b. dsoignationst
System for control using canopy-lift cylinders, p ? 50 i,'/cm2; --;--
canopy nressurisation system, i ? 1.7-2.55 kr/cm2; - canopy emergency
removal system, p 0 110-130 kh/cm2.
1. check valve; 2. reducer RV-???;3. emergency valve1.4. filter; 5. air cylinders;
. 6. check valve; 7. air cylinder; 8. pressurisation hose; 9. emergency tank; 10.
pips; 11. canopy oontiol valve; 12. .air valve; 13. reducer RV-1.5; 14. check valve.
. ,
OVI,1347.
50X1-HUM
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420061-8
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
The pressurisation hose is in a.special groove In the panel beneath the
canopy. Air valve (12)) connected into a single unit with RV-1.5 reducer (13),
. and check valve (A) are on the left side of the cockpit near trainee 7 and 7b(7).
Using the emergency air system, the canopy cosonka is cast off when
it is released in an emergency. This air system coneist of:chock valve (1),
located on the right side of the cockpit,
/which separates the canopy emergency hydraulic system from the 13o -atm aircraft
emergency tank (9), in the forward equipment compartment;
pressure system; emergency.
valve (3) on the bracket that holds the ripht-hand canopy-lift cylinder; filter (1);
air cylinder (7), attached to the bracket canopy suspension bracket and used to
open the time-delay lock during, emergency canopy release; check valve (6) which
separates the emergency air system from thi?operating system; and air cylinders (5),
which during emergency release of the 4anopy serve as ejection cylinders: Pipe
I ?
(10)is used to measure the pressur0 in the emergency canopy air system, and to
bleed off the air.
50)(1-kum
50X1-HUM
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8 .
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028600420001-8
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1.1Ydrau1iC System tinits
. Par101)Y
Pressurisation and :1, Control Valve
(N. 16)
.The pressurisation and canopy central -valve haa two cavities; iihilar in
bodY. and
design,, The valve Consists of .-(3),ila?nheft with cams (.1) and valves -(6)
: And .(7) On a shah (1,).1a a gear (see turns .the .tuuthed.sactor .of ?
the pressurisation?btton
? The. gear ratio of. the :Coupling! is -1,11.e.. when the toothed sector is ?turned
7!) the gear and the valve stens turn:1.25Th; The-other end Of, the shaft passes to.
'
the 'oUtei"ii thrtingh the eifietiiig of Ow cockpit and haa:a. slit: Ito .that the cockpit ?
?(
can be ? aresenrieed.: ..fron. the outside Aiming a. sarevdriivir.
,
. ?.
remai.nder blUrred
50X1 -HUM
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
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Fg. 16. PressurisatiOn and canopy control veil'.
"16'shaft with cams; ,26 connecting pipe; 36 bodyl.h. oOniweting pipe; 5..conneeting
pipe; 6. 'valve, 7. Va1ver86 guide; 9. cap; 10. eau; 116 oonnecting pipe.
' !-
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'
46 To canopy lift o'dinlere
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b. To pressurisation hose.'
?
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,connecting 141:ei. 2. eti4ire* aorineetor; 3, hO1c1er 1i. rods cylinder support
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
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The inlet connecting pines of both cavities have throttle openings-
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0.5 mm in diameter. '
.Canopy Lift Cylinder
Figure 17 shows the de?ign of the canopy lift cylinder and the method of
attachink it to the panel beneath the canopy. Cylinder (8) is attached to support
-bracket (5) by means of connecting PiPe (1) and pin (7) in holder (3). Pipe (1)
and pin (7) are kept from shifting longitudinally by split pins (6). When the canopy
is raised or lowered, the cylinders move in the longitudinal plane, rotating on
.piPe fend pin (7). Air is fed to the cylinders, by means of swivel pressurised
? connection (2). Air is fled to the left cylinder from Ake the coring side; it
is fed to the light cylinder from within the cockpit.
.To prevent the meow raised canopy from lowering due to absence of pressure
in the planets hydraulic system, ground stoppers. Are. placed in rod (4); these are ,
removed before lowering the canopy.
1 .
(Fig. 18)
, . i , . .
I' The air valve is a. set of check and safety valley in one body. It consist.
, .Air valve
.? of body (1), two slide:di* valves (3) with rubber washers, springs (4).
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41. (5),Mnd plug (7). .;
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Who rt air is fed ta.pipe.? ? elide valve (3) Of the cheek
and the ear passee ithrough pipe NA" to the: spreesuri. sation valve. ?
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When air moves fm FApef "A" to pipe "2," spring (4). of the
seats ?
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hide valve (3) artainSt Plug (6)- and : blocks. the air -path. :.
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Ire? is opened
ehech:yalve
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valve opens and mks the air escapes intothe atmosphere through pipe ire
Ernergency Valve ?
(Fig.'. 19)
The emergency valve serves to Nisi+ air from the emergency sitmvutrmtuee hydraulic .
the safety
system to the canopy release cylinders and to the cylinder that closes the laicise
time-delay leek: It consists of body.. (6) with two pipes,. separated by membrane (7) .s
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? ?made of 0.ainlese Steel 0.1 Mm thiCk.
Membrane .(7). is" hermetically CoMpresped by'.pipe?(8) between thebodyseat
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and bushing. (9) to Which it is. attached. To change the membrane it is necessary ?
o unscretelpipe. (8). The air is fed to'. pipe "S." ?
When pip (3) is Pulled Out; .Pin .(5) Moves forward; actuated by ?? ?..
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7.(t), and begins to .rupture :membrane (7). The Weakened Membrane is ,ruptured
by The air..presSure,.,and Pin (5):is thrown backward and .seals ?the 'cavity. ni the
body?:.pressing with it' conical eekion e(gainet.the rubber washer..
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Declassified in Part- Sanitized Copy Approved for Release 2013/02/28: CIA-RDP80T00246A028800420001-8
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Fig.' 19. Itmsrge nay valve (membrane valve).
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valve completely engagied.'
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(rig. '20) .
? ?Th? filter .*e to trap the fragments from the :ruptured rembrane of the .1"'?
esurgency ealt0) it consists of body. (0, =144(2).; and cover (3). .
? . " aboard the plans,
? If; the 'imsrgenely vales is actuated ? ths filter is removed.
and the labium* 'fragments removed frets it.
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Operation of the Canopy Control Handle and Valve
(Fig. 22)
Opening the. Canopy
To open.- the canopy the canopy control handle Must be roved froli th?eatrese
forvard position to the extreme rear. If the canopy is pressurised during the
first 150 whits)* the'handle'.tUrns the. canopy becomes dePresgairised. If the
is not pressurisedi'only,.the handle :polies in the 'tint 1,5?. ?heti' the handle:begin
shaft -
":-t0.'tizrn.the,plissaurisation button anti, by rie4s of..thie'button:,*. the r: of the:.
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Declassified in Part :Sanitized 'copy Approved for Release 2013/02/28 : CIA-RDP80T00246A028600420001-8
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turns 66.63 the.pintlei Of the operatiignk looks Completely clear the canopy loops
and:oome extol the groove. in the bracketai during the next 3? obi, begins to be
admitted.tn the oanopy.lift_Oylinders.'.
? pRECAUTTCW: The At:Clop); .should imgtoliftimmoothly 3-5:eeconda after air is fed'
to the lift cylinders.: Forced retention of the canopy in the'docn'Ooeition might
result in a midden .upward snap of the canopy,:dmiegina the lift-cylinder-rod fitting's.
. .
...Closing the Canopy'
To Close the canopy the handle Mutt be mo'ved:frOm-the-extreme.rear position:'
to the extreme forward position. First only one handle melee. .After 15? the
. clearance in the preSeurisation button is takenup And it begins to turn and
rotate thestem of the canopy:control,Velvil.. When the ? handle has turned 30-400'
-.the. bleeder. Valve fOr.theOylinder- cavity:opens...air' from the canopy liftf
cylinders escapes into the .6:tome:I:here, and the canopy begin. to lover. After the..
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of the rear left look is held by.theoriesting device (450.7* 13) After the
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Declassified in Part - Sanitized Copy Approved for Release 2013/02/28 : CiA-RDP80T00246A028606420001-8
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