SCIENTIFIC ABSTRACT KAN, K - KAN, S.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000620320009-9
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: August 31, 2001
• Sequence Number: 9
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

KANI,K.tp s,,,jWm.tekhn.nauk; 14AKO L I., inzb.; MISHAK, A.M., lairA.khim.muk).
YEVSE-YEVA, L.S., inzh.
Investigating the refrigeration compres;Bor operlLted with Freon-143.
Khol.tekh., .1+0 no-3:5-9, *-Je 163. (DUM 16:9)
Mentrallnoyo kopetruktorskoye byuro kholodi'Llnogo iiashinostro-
yeidya (for Kan, yAk), 2, Gosudarstvenn~7 institut prikladnoy khim-
ii (for Marshak,,~,jo~rtsa~b%).
(Re.frigerants)'i'(Refrigeration and refrigerating, machinery)
,I..

BOBROV, B.S.;,,-KA14,, KIA~r -.-
Automatic recording of stroes relaxation curves for polymers.
Zav.lab. 31 no.lOtl265 165. (MIRA 19-1)
1. Leningradskiy inBtitut aviatsionnego priborontroy-onlya,

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00 z!. van; tor OuWb" iuppotts, (A poor quality. by kwination of
0. IN(mlocts 44 Wood In the, anueollux fur. ~06
3: 1-Y in. sent annegling and, canwiturally. imum- .00
:!~'i I I emnhumims ul the lubricant, toy using too bilk pirk- .00
1. i timps.. by inadmiame wa%hing after pkkhng and
ij! (I OKA.'
rying fformotiin; tif b&* Cu and Zn salts by res"ims of
i Cth with the vinkm shert murface). Lubricants of the =09
highm ity ith a hitilt pemotage of plan. aili) Nov
Un"itaMOOM ali"Ylainion clean Furfam. Ance, at a fule.
o0 0! flat lubricatinIC propt-my 6 lwoportional to the cukiiij; =Of
P city and Inkt-traly ProWtional to the combustibility
06 a- ,am# & lubrk-wo. This obstivation Is explained by the ZOO
fact that m%plndrA-ntN wid'unsatti. Isydrombons, intinm- 000
the lubricating prink"Its and that. the caking capacity .00
of thru Cotnte"uts Is high it c=PwW with satd. by.
drocartams. Thatreforr Pmeminmaloils with slow ow- 400
l: I W Plant oi'i and tat atid. are pleferal4c " lag as the
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CA ng&b in pbp* Doformadon. A. K. CbefUvAilth ani K. N. Kan Whom
nkhoo. Fitiki. 1944. 24. (0), B30-3"I.- -111, Itumtoul-I V-flo- "O"Ottlelit a
Imn aml limm iomr"drientitfuNI. mand flu, VA1101A
00 1 of tho coriTs. for mialm-r. sinit, AM Aluminium wvtv wM6,1. The ctic,110.
or frivunc -we "nulmd by 0* same wMilai Me coillorr &,ad falutill I
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KAN, N. 14.
KAV, K. N. (F'i- t'I -- "Lrrtc;-r or THC tIA7UNL or Lu;!rz i c,m u. 1, ~.J~ ~"'X I f,,- r., I I I c Ct.;t:ffri c i orr cr
rRICTION IN Tiir H-ASTIC UFFORMATION OF 1-:ETAt .ts Svo r Jim ",P, No.co~; AvtA-itoi4
I I
Tvcim,~Loatc.tL In:-. T FOP TIIE Dr,~"F.F OF (-Atli, IVI-TV M TECHNICAL ISCIEla"En)
5C~: JAmuAny-DicctmOfit il'r,2
- VECHEQ1JAYA M-~$KVA,

ACCESSION NR: AP009837 s/ol91/64/boo/bOl/0059/0062
AUTHOR: Shannikov., V. Me; Kan., K. N,~
TITLE: Investigatio,n'of the static strength of rigid plastics in
the horizontal stressed state
SOURCE: Plastioheskiye massy*, no. 1, 1964, 59-62
TOPIC TAGS: plastics, rigid plastics,t,phenoplast, strength calcula-
tion of plastics, rigid plastics static strength, horizontal stressed
state
ABSTRACT: For the investigation of rigid plastics in the horizontal
stressed state, two kinds of phenoplasts, such as K-18-2 and Monolith-
1 were usede The preparation of samples and the teating apparatus
are described. The criterion of strength exprDssed In a formula
gives a good approximation of theoretical data of miud= stresses
with the experitnental data and m be used for the calculation of
strength of plastic parts. The formulas derived from the strength
Card 1/?

ACCESSION NR-. 'AP4605837
criteria of rigid plastics are used for the calculation of threaded
plastic products, Data of maximum stresi3es forfive loadings and
values of constant parameters for the two types of phenoplasts are
tabulated.
ASSOCIATION: none
SUBMITTED: 00
DATE ACQ: iweb64 ENCL: 00
SUB CODE: MA,CH NO MW SOV: 000 OTHER: 000
Card 2/2

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R UR/0032/65jI031/01 /1262/1263
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AUM RI I Vdoviki~,.Yim n K& N
ki
TITL 3; 1 rin' 11~ ok4on'vume~ tests of ri astics
devi gid p1
-Z odsk al-labo, htofiyao vt~.:31 l965, 1262-1263,
-T,
SOUR~ #av J.
TOPIC! TAG�: olvie ein :116 test-o::static load test
t
etermina
AB MA 1:: kp6rt4l..... 6 n device has: beem developed to. simplify d
0
5T sp~
ti6n' of ithe-rqptui i6tra th of, 'he device is intended for loading
gid plastics. . 1.
.spelAme~!sj on a !uy Ifet lark, liciane cg., the TsOM-1160 machl .he, for 1-0 to 15 min, with
ubstique4 ho Ondei 0a. 0 to! e the machine., The device is described in the
1 d i
isourpe;~ bits ding r1%, 'I: Figi;j of the EncIosure. .' The new device is. being,
s g eri in
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Bpbrovj.I~ Ka KI N.,.:,
AUTHM
TITLI i..::A e*v- io f6r~l 001 t
a' ica4ly rkording stress relaxation curves in pol3rme s
r
SOU OEI d k,
Z*vo s ayio Ub ra, Oriya, vi, 31, no. 10, 1965, 12C
j;,
TO S polymtr~: rel.Oxtitioin process, stress relaxation,
The * J,
art cli dd;6ribes an~ittachment for a GagarO preso which can be use,
ASSWLACT. d
for xiec,61 Ing qtresjrexi~ation curvesi ..The device is shoRn in fig. 1 of tho Enclo4
sure I I din 41ad d~to~~the crossbeam of tb pess 1 Ior deforqnation.of'
0a. is; 4i~~Cho e
a e 21: to a pr;, value The loading head is i~ diffevential screw with
p c1pon
differen threads 4. 'fhe
:pt e,housing 3,and on the body of the loading rod
t0ea ~~:th
-thrvad~ itches'(0.25 mm)makeo manual loading possible,:
small 1: ferenoe~Wi4eeni*he
I . . . .
. I .. . . p
by rco~tat on oVhutl;: P!~~O~pr&snts reverse motion of rod 4. The specimen is
7 placcid, t4een the ~;eid 'of A e 7 which.:is mDunted on press table
the loading rod arid bas
bd
tors 9:g~Ve;,thO:,46formati6n readin Stress rele' ation is studied.at con.4 A:
~Tiftdt a. 9 Ix
stant. a6b olute 4007,mhatio~j Of the specimen, There is a coti inuous reductionin the;--,
t

ACMISGI X, RR
ENCOSURt
01

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am of the attacbment 'to the Gagarin ;,preiss
D
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umdumw~l~v - - . - - - j mffi~
SHANNIKOV, Vladlar Mikhaylovich; MOSKAIDT, Ilikolay DmItriyevicl;
KAN, Kliment Nikolaycvich; BRAMNSMY, V.A,., red.
[Strength calculatioris for parts nade o!' thermosetting
plastics with thread and mO.-` reinforcement] Rasclu,~ty rui
prochnost' detalei. iz tem~,realcti-mykh plastmas3 s 1,ezlboi
i metalliabaskol anzturol. Leningrad., 19 p. (Leningradi-Ali
dom nauckwo-tekhnicheskoi propapandy. Obmen pere'd,)vy-m opytom.
Seriia-. Primenenie plastmass, sinteticheskikii kau.~hukov 'L
krenadiorganicheskikh soedinenii v moshinos-troenii i priboro-
stroeni~~, no.3) (1-.IRA 17.7)

ADTHORs Xan~ K.V., Engineer SOIF-91-58--4-4/29
TITLEA On the Article of S.S. GadZI14yeV "On 'he Increaso of the
Number of Consumer Lines Connected with One, Common Switch
of 6 and 10 kv" (Po povodu stat'i S.S. GadzhiyeV6L "0b
uvelichenii chisla potrebitellskiEn liniy, podklyvichayemykh
pod odin vyklyuchatelt 6 1 10 kv)
I
PERIODICALs Energetikq 19%kNr 4, p 6 (USSR)
ABSTRACTs The number of 6 and 10 kv outgoing lines frDM substations
must be increased with the load increase of certain town
districts. Because of the lack of reserve units, addition-
al installations and even new distribution Btations must be
built. In this case, it ia more advisable -to increase the
number of lines connected with a common switch. The prob-
lems approached by Engineer S.S. Gadzhiyev mainly concern
the distribution systems of stations and substations having
a power reserve of electric equipment, and also stations and
substations which supply towns. In thi3 case, small loads
should be supplied through individual lines. The author out-
lines the cases in which common swit--h circLdts arp more ad-
visable and conditions required for utilizing these circuits.
Card 112

SOV-91-58-4-4/29
On the Article of B.S. Gadzhiyev "On the Increase of the Number of Con-
sumer Lines Connected with One Common Switch of 6 and 10 kv
He states that common switch circuits comprising, more than
2 lines will certainly be utilized in praotice, but he men-
tions also the difficulties caused by their utilization.
1. Electrical networks--Design 2. Transmisziion lines--Design
Card 2/2

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KANT, K. Z.
"The Present State of the Problem of Endocrine Gland Transplantati -,III' (p. 219) by Kan. K. Z.
(Mlo-szor'.1)
SO: Advances in Moderp- Diol (Uspekhi Sovremennoi Dioloc-ii) Vol. M, Vla.. 2, 1945.

A
1110
COMPRI'11111 SIhJdY Of thib effects. of thloutitell and
methyttkilmrocil on Ziritiheral b1clod. K.

21. No. .5, 111 t(Illim. R"I, "f
14yult.
NAI wt. were fell 411 tug. thiouracil per d-kY in Ilivit
ft"ll. A ft-d grmp of rats were fell 441 ing. methylthio-
unicil, and a third "sp Itut tmxl for vact ( rol. Thcrith,r
Late dow WU-k givitt, to living out tile Risk artioll of thew
With tile vilmiltioll til .,light Allculi'l in a fell fill
ill the
Tile lotid no.of fmill 13,110%) its 111.1kit).
Wit the lierevnilage of urtilrophil% drolped Ittim 21 1,, U..
After '-~l tUri off tilt- tals tirat,rd %vilb muthylilti-,
ufacyl Atowvtl thew cluitigm After. Ill Ul day, tile Im I
Crillage of milltudgi ihowillig thv~. vil'inge, %%.1, 111.6 %ild
-NIScr*v'- rvt41- Thk is 1101 a "I'MULttivy 01-t hot %ht-
111.11 rearliou mly bet lit x-fl-ru .1fler ~, I'mig IN-rmj, The -
cflvvt on tilt lieripberid Mimml imis sitidit,11 hy fi%jt-,,tmK
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irmille diii not miller file .4
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allitlitm patt of tile hyptylly'li, 411"1 liol ditIvy flotil 111,1111A
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KANI K. Z.
UM/M040ina, - Thyrold Transplantation May 197f-
, MMicine - Chemotherapy
"Ibe Reaction of the Transplanted 7byroid Gland
to Mothylthiouracil," X. Z. Kan, 3 PP
"Byul Mcep Biol i Med" Vol XXIIIp No 6
Detailed discussion of data, with micro-
photographs had a table.
14T12

PA 11/4~9`759
A
PM one
Men
nlbyr6id Glands Dae, to
~1 NO
i0ivc i
It ethylthioutalp,11.9, -and the Relation
i ty In-the cha
thi6- Do
on ages.,"
U6 ',Ai
al Madcarinol,
~U.
:Nlt aEO lrioi,lxi No 2'
U.
Iiii 0 Afppr, 7A. thyltUparaoile
to.
I sea
aid, I it/day: o
Tabulatee re.
:41qd4i-, thige, nd,brophotographs. Sub..

NAN, X. Z.
29917
Vzaimodyoystviye myezhdy koroy nadpochyschnika I shchitovidnoy zhyalyezoy na
fonye blokady, funktsii ahchitovidboy zhyelyezy ryetiltiouratsilom. Doklady akad.
Nauk soar, novpyp eyeriya, T. LXVIIII No 3, 1949, a. 6~13-36. - Bibliogr: 8 Nazv.
SO: LETOPIS' NO. 40

LW, K.Z.
&feet of mothylthiournoil-inhibition of thyroid function on regenoration
of islots of Langerhans In elloxan diabotes. CA. Acad. Soi. U.R.S.S.,
149, 69, 877-880. (URA 2312)
(BA - A III Kr 053003)

A A-C-1 A-1 i
ISO Shb
PAIM1111 AND 01APPISTRI *011
; ~1'; , ~ - , ... V.
/4) and L Kan Aw. N TtOfd, Filiki, 19", 14,(10111),439-417),-Iln
RUWAn`,1-Tbv usual Methods of obtaining b%h presoures Rm not applicabit. OGG
~
to,
for work at vrty low tempo., ol to - changes that tAke ontv in the
Gas liquid or guivous medium whlch*U=t'U& ti See
be pressure. L Lnd K. utilized
"I
th
the pvp"ty of exponsion an solidificatiott of water, bimmuth. &ntimmy. or
bed Y gallfam, to obtain a hkqb pressure inside a ap=Wly de i d ci-lioder, sihich
P
9 6: 1.= .*G
contained the spedmen to be investW" The main v 6f tho alinder
:00 W" made of bvc~llluw btow. and this pressure wait measuruil'by the &I ension
,01_rfl
0013 of a mimr opersted Not Um cylinder and procalibrated by means of a standsixi see
P-- pup. After obtWnWg the wesimm requirod.'tho whole apparatus
'he W,
Hap ihintermM in illecooling rpreptacIr. Byupinguaterfor ~in4
-as obtaint, _P. see
m(4110m. it preourn of 171WI kg.Isq.mm, (4 j 3%) % 11, at I e IS
the p17' diakpin, waWr icv Plime IN111,
4 hipild lifli"in, end by Clottin
phan weir cwWrAned wit a hWt Fireuracy. K I
flu
use
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-- - - - - - - - -
i0 too* 0
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A
POPCISM AND P001411ti M091
VA
[
"OhNuft a ft AM hNSIS lkb*W to AUMW P"Waft d 17M ki./aLl.
11. Laurev and L IZA-- Xk#Prr- TrOrCL FL-iki, 1944,14, j 12), 40-473
dk-%
i
i
R
00 n
uav
in); an
(
YwJ WAX). 1944.9.(6).361-M (in
A(
A
040
.
n 0"minatiOn Of thO suPeLCOnductMiyof tin and indJum at a pmum of
17,
17"10 'g'1#+QM- W" Made-, tht Offlefiffitnts bring carried out in
Wl

00 8 a sw
y
de4gurd 6imb, inside which the requisite pressure was cleeploprd b
fnv4n

4 C y
g
al
*aler. Pleoults for indiam wen of& preliminary nature; fortin,aprilration
of 1'r-sure W to a decrease 617'
) of a
rox
&P i
th

0
j .
n
.
pp
e supramriductivity
k"p., and a deman (W[,) of 13-5 S&,w in the critical field. AT
an'd
.
AR, both ine lkmWy with presture up to AW kg./sq.cm. Tho results
arti dkmood In fim the point of view ofoupravondut-tivit
tb
d
V
e4u, an
it Is *MwW thAt the phenotitens might be u" fur measurrintnt high
-jj- V. B.
, ME
516
A $;IALLuISKAL LiTimATURI CLAsWKATtC0
A M- L.
.,_ i_. ~ _i
plot# 411W 001 Ov all
14146,3 Ole a%; of
11
U 0 AV
'
to 0 0 0 0 0 0 0
60 ~ IM1,11 I
A 0
too.
to*
so*

Sep 48
Superc~nAuctlvlty
12dium
lAbavarements Mae Ubdar Conditions o# High Pres-
ZZ x4res and lav Temperatures. 11. The Supercon- i'
dmtlvlty c,-0 ThAI- and Tin at Preemwei- of 137QIand
3.730 Irg/co Acting Equally Fram An Sides 19 " L. A.
]Oz., :8. G. Inzarev'J.- A.'I. SuAcrtsov,, Phys-21ech
M26t, Acad Sol Ukralmlam SM,, -0 pp
"Mur Eksper I Tooret FIz" Vol XV=., No 9
Stv&lee in detail effect of given press-are an
superconductivity of polycr7stallic indium and
9A9749
r 191 AR/Jaectriolty (Contd) Sep 48
3mocryoUnic; tin. ZeUbUsbers displacement at
PrItical temperature Tk a1pprowlate for kITM
temperatures- fcw Indim. 0.063.aUdO.O&PT&n&'I:rQr
0.080 j(h tble ranv 6f pme6saim- a
0,
ITk and' L are propmwtimal to pressure. Displaft-
&-iticea xOgmetic field discreases vith re-
4AWtiOn of ture. Camoldwe reasons for
dMarent c4mverblon Intemaltlee of tbase iw"-
O&M. ior -pr"sure - Azd- *hen subjected td'#-"-
mu". ocinsidard-ble Improvements In ammWing
9A9T49

PA 157T79
KATI, L S
Opsqpwjsicsl~ L-W Teperature 11 Nov 49
8%~)erconjuctivity
Iliariation in the Superconducting Properties of Thal-
lium Under Pressure)" L. S. Kan, B. B. Lazarev, A. 1.
Shadovtsov, Physicotecb Inst, Ukrainian Aff ilate ,
Acad Sci USSR, KharIkov, 2 pp
~jok A Na;uk- SSSR" Vol LXIX) No 2
Oressure of 1,730 kg/qq ci (on all sides) displaced
~pvard critical tempe-gature of thallium 0.021 C, as
qpposed to lowering of. critical temperature in the
~tase of Sn, Ini Pb, HS, Ta. Submitted 10 Sep 49 by
Aicad L. D. DmMau.
157T79

54IL733
411M AlOwlempammex lycellam KAN
Am IL 0. LaAm. Zk *arAh. ft. Ns
(No. 12, 1"l) h AnAwL
A ma POWN 1 wu ocadnwW for t= at
the mopumm of Hipid IN or H. IU rmW caumm
coapkime wM dft arA wkb tM Sm hdd to the out-
sW qhhdrkmi mufts by a meW bud wo Iltivendod
in" a mwW Dwa fluk aM wu nWJnWMd at the
towntwo of die 14Wd by coadsacti- throuO a
Cm to& Few lk wimlom pwmkud the X-MY bol-
LS
to P" ONOWO gm No ploobim wu
waft lbr mming tw A- L 14ACKA~

'KAN 1. S.
W!"os"Ol! 'vest a~t iaw, Tempera- 21.Dec 51
tures
OlProblen Coneerning the Minimum Resistance of Mag-
nesiumAt Low Temperatures," L. S. Kan, B. G.
Lazarev, Phys-Tech Inst, Aced Sci Ukrainian SSR
"Dok Ak Hauk'S SSR" Vol L=, No 6, PP 1027-1029
The results of expts by the authors on magnesium
and gol(I indicate the absence of subject min in the
temp behavior of resistance at low temps in the case
of pvcmetals. The phengmenon of such a min re-
mains incopivehensible in the case vhore there are
yery insignificant amts of admixts in the metal.
Slibmtted by Aced M. A. Leontovich 3 Oct 51.
215T68

I.Af, A, ~,
AUTHORP
-TITLEs
Kant Ls So 1 Lazarev, Be 0.
The Influence of Universal Compression V on the Electric Con.
duativity of Metals at Low Temperatures Miyaniye vesetoron.
nego szhatiya na elektroproyodnoatt metallov pri nizkikh temp
peraturakh)
56-1-53/56
FMIDDICAU Zburnal Rkeperimentallnoy i Teoretioheskoy Fiziki, 1958, V0144
Hr It ppo 258 - 259 (USSR)
ABSTAACT# At first reference is made to papers dealing with the same sube
jeoto The wesent paper gives some results of the inveatiga.
tion of the influence mentioned in the title. Measuremente were
made with zinc, tins gold and bismuth* All samples (with the
exception of gold) were produced in the form of monocrystals,
The metals, used here were highly pure. Bismuth was only inves.
tigated# in order to compare the results obtained here with
the results obtained by Re Yee Alsksoyevskiy and collaborators
(reference 4), According to the authors' measurements, too,
pressure in bismuth causes an increase in rsaittanoe in the on.
tire temperature range investigated, But the other-metals exar
Card mined here behaved differently. The increase in resietance un.

56-1-53/56
The 10flufnes of Universal Compression Upon the Electric Conductivity of )(so
We at Low Temperatures
der pressure at sufficiently low temperatures is common to
them* Or a tsm~sraturs increase this increase of the resistance
becomes st*llor and at a o~34tain temperature (characteristic
of every metal) the increase becomes equal to zero, Upon fur.
thor rise in temperature the effect changes its sign. Numerl.
oal data on thin effoot for zinc, tin and gold are given. In
all metals Investigated here the authors observed art inotease
in resistance under ths influence of universal compression.
This.phenominon is reversible@ No explanation for the effect
observed could hitherto be given# But the mechanism of this
effect In probably different from the mechanism of the influm
once exerted by pkesoure upon the electric resistance at high
temperatures* Under the influence of pressure similar oondi-~,
tions as In semiconductors are supposed to occur for part of
the elsotronve There are 7 references, 6 of which aro Slavic,
ASSOCIATIONs Ph7sloal-Tschnical Institute AN Mcrainian SSR (Fiziko-tekh-
nicheskiy institut Akadsmii nauk Ukrainskoy SSR)
DVMTBDI Ootobier 31, 1957
ATUXUBLEe Library of Congress
Card 2/2

an the Physics of I-
T"Y0rA4Ur*8 (5-,e T-*NoyuzAojre rowahch"iya po flzike nilkikh
t..peratur)
P2210VICALs UspokhL flSlCb*.kikh "uk, 1155, yet 67. Ir 4. Rp 745-150
(USSR)
AMRAC?i 'Mi,COuforaneo !I--h ;.,am from October 27 10 Xovqmber I at
Till tali it -.. orgual-4 by the fix- -matocuti-

1k
IL mock Lk*4*.Il auk 533R (Doy.rts-t of Physic-
:0
1:
1.
.
t1C4I Sciences of the Academy Of SelacCes. USSA),
th. Akadonlya bank CruslAskay 558 (Academy of Science*.
Gra.ln*%.V. MR), and the Thillookly 90-4~st.-yy "I-
marmitat is. $tali" (Tbili.i St.%. University Imonl Stalin).
The Conforsone was attended by about 300 specialist# from
2%11121. Some-, Khar4kov, Xlyew. Loningra4, Sverdlovsk, sed

bar cities && ..12 .. by . number of young cl-tiffits,
:
:
proxwat
;orktag In th. USSR. About 50 locturas war. d.11"r-
o
ad which .0 JJT14.d ..!!a rdt.6 to research fi.ll.-

*C*U- 1. ". Elfoh.... and I. D.
k., xh~'X-w
.04 the% tCe most Important ;art in Connection Lth th-

,, to pr,porll.. of metal. is played by the CO.
en 11 moms a
be F.mj ..rfa-. Of c-ni~c%1111Y 1- J-
.
luko.y ... kiy (IPF) spoke sbut he Carried Out

vLr.
T "tIon
ro I tA ors.1 mmen-tic fl- -I
temperatures of An, Co. Pb, To. C&, 'T-A MZ4 wish
1. XO.tl.A&) Of To, S. 3cro,lk 414 1 T I %
N"i
-- ,- ":
cu."ll Inwe$%
tasperstures of chroAltic 4Z~li 2~4-~Oulu~, ~14 to=;! -ho- the
rggl.t"ce of chronlum 9"12 *W: field Otrszl%h w',%n*ut at-
5/1 11
a. Mm.r., (rh7.1)
I. r a meturatian value. L. a. r..
1 B
~, ~
j;
IVU.4 the r.-Ixtacc- QIA=- B.
fou.4 thAt If tht -43;"- 1- heated- lh* 'ic"'
elos,"Ars. yu. P-. Gayduk" (177) sold Ia this -QmM-Ct'-u
Im, Ibe course or the dlac".1on %.hot the =in-AC,C= ff..t do..
01 mock in Cold In the ease of very pure saz;141; tk;* 118-
%h4 staimum, I. xplaj.od by Sh. 91-Ontle Is.for--
pgrature*. X. Yo, Arb6l'
th
1
1: in -atnootlan -ilh the
.. =
'
gasussna theory of the hlsh-f"quoncy r*olstanco of =.to, In
6 eanes"t magnetic field at low %4m?orAtur*R--Z--1-VA~ -=0v
IA V. K. ?..kq"jk (Xhpyj3 s;ok* about . theoretical In'*.-
-
.flb* lnfluenco, porclood by thor=ooloctrIc fOrCOA
.Van the skim aff.*$ IA various Conductor.. B. I, work z and
9. W. jLlakdondrow (KbIP71) spoke about =,eA3urwZaAT# Of the
-T;--r-- par
,1.0, of thin jr.m calo from hlr-ly- -
M 1.=gth of
Iin, lading and cadmium, -4 computed the fr
:
p,t% at 4.2*K in these *4 -Oucti-,l a 113 1- 2/) ne-
_gr~E.41 (j!GV) and 2. 1. Vrki, a-- I. T1. D=trwzwJCO
17,dr-
leated the *xe=I#ad ly Z~
L
.!&tic pro r* (of JOW atconph*rex shea r.) Pa.
Cord 6/is 1-0 behavior of "%%1s -I Ia. lom;,.r.turaa _d jz..jtjg.%.d
4azz,ton 4#4iltoisax of a.. -c-tte susceptibility of
=
=- CC&--
Ih at 1.6 - 4.2 F. 0. To. Z1212-n and A.
-
'ich MY-11) saws - the*" sical *XVIA" ion Or sho, f-7-1-IS-Z
relatively .2.11 d.rco.z.ti..M exercise coemid-ohl.
1-flasnoco upon "Cillat Ion
off.0 %
in net
l
jl-
:r
:
;
_pgrMtt-A0,eLAOv (Irp 4.11, 1. r P: *- Lm-tig--
)
Ia to cazri*d out of the -1004"Pr Of the -0-k f-mc-
--snatiou to monacrystal sanplos of the 4n1Iforr.:Ca-gaotlc
%MI(th%offect of anisotropy was predicted by the It re*-
cal, bsory developed ty zzyaloshi-okly). In %h* COVX&-
of the dIanumaton R
A. Llikh"Ov (TFP) a;Ok. ah"I A.utr-no-
;I
grophiont 'in- Jjr, Ono be ..",ad ou, or v%. a-zuotic
struo ja,ne of V-C03 an, p*, a
&t low j.c-'Sr toss.
-
.1re
s
d the I
l b
sed u
on
r
it
f U
th

0o,
. .
o
.. .0
a
a
r
s
4p
p
p
DayalohLusku's lb.or7.
Imataro ..* read by A. S. Bara, k-?O=LA-v, r.p4rt-4 am. mn-gur4-
oax-rl.3 *.I by big (in In) of the "Cc-417 aa'-O-
of S ", am Sl f.rroaacto t a cusoc and COS0,.OQaOCry.t.I..
Card 7/ft j.. &. TIrow (In Aj 5332. Sverdlovsk) .1p.k. bO-1 his tb*or.-

IT -Z~So
26 4
S~l 1
076/61/035/0071/011/019
B127/B102
AUTHORS: Krasovitskaya, R. M., Kantor, P. B., Kan, L. 8,1
Kandyba I V. V. p Kutsyna p L. M. , and f-om`ic ~Ie-,-qe. b'.
TITLE: Determination of enthalpy and specific heat of boron oxide
in the range 1000-22000K
PERIODICALt Zhurnal fizicheskoy khimii, v, 35, no. 7, 1961,
TEXT: The authors studied a sample prepared by the Vsesoyuznyy nauchno-
iseledovatellskiy institut metrologii im. D. I. Mende3eyeva (All-Union
Scientific Research Institute of Metrology imeni D. i. Mendeleyev). In
order to dry the preparation which contained 0.01-0.02% Mg and water, it
was slowly heated within 7-6 hr to 600-7000C at a pressure of 10- 2 am Hg.
It was kept for about 5 hr at this temperature. A formation of bubbles was
initially observed which ceased during heating. The sample was then heated
up to 10000C, durifig one hour, and looked then 'Like colorless transparent
glass. Investigation was carried out by means of a massive calorimeter
Card 1/4

26341
S/076/61/035/007/01 1 /019
Determination of enthalpy and specific ... B1r-7/B102
wh,ioh consisted of an aluminum block 30 kg with lateral Pt-resistance thermo-
meter. The aluminum block was hermetically enclosed in a vessel which was
connected with a vacuum system. Cooling was performed by a double water
Jacket kept at 25 :t 0-050C. A vacuum furnace was used for heating, consist-
ing of an electric heater (a graphite tube of 600 mm length and 45 mm
diameter), which was surrounded by coaxially arranged cylindric 3creen5 of
graphite, tantalum, molybdenum and steel. The temperature was iLLasured by
means of a Pt-Rh-Pt thermocouple and an optical 90n-51 i'EOP-51) pyrometer.
Visual readings were made through a window in the furnace. The error of tem-
perature measurement did not exceed 0.1~ up to 170001C and 0-3~ up to 23000K.
The apparatus was evacuated to 0-4 mm Hg and then filled with argon
(15-20 mm Hg) during the experiment. The ampule were made from platinum
which does not react with B20 3 up to 1650OK- Molybdenum was also suitable.
At temperatures above 16000K the argon pressure was increased to 600-700 mm
Rg. The results of measurement are summarized in the Table. The following
interpolation formula was used: HT - H - 30-54T - 11920 cal/mole
298.16
and Cp 30-54 cal/mole-degree (1000-21500K). There are 1 table and
Card 2/4

26341
S/07 61/035/007/011/011
Do ttrmina tion of enthalpy and specific ... B 12 7Y131 02
9 references: 6 Soviet-bloc and 3 non-Boviet-bloo. The most recent
references to English-language publioations.read'as follows: Ref- 4:
X. Keller, Contributions to the data of theor. Metallurgy, X, 1949-
Ref. 2: 1. C. Southardi J. Amer. Chem. Soc., 63, 3147, 1941.
A850CIATION: Institut mer i izmeriteltnykh priborov (institute of
-11,easures and Measuring Instruments)
8UBMITTEDt Octobe~ 17, 1959

ZM (14,7 2, 11do, 13 ~.T) 20456
/
Irw I S/0-56/61/040/002/010/Cr47
24-1100 s- B102/B202
AUTHORS: Kang Le S., Lazarev, B~ G., Mukarovv Ve I*
TITLE: Superecnductivity of tin -and indium under pressure
PERIODICAL: Zhurnal eksperimental~noy i teoreticheakoy fiziki,
V. 40, no. 2, 1961, 457 - 455
TEXT: In previous papers (ZhETF, '49 46,3~, 944 and 18, 825, 1948), the
authors described studies of the efTent of pressure on the critical tem-
perature of titi and indium at 1740 ard 5`0 kg/nm2. They observed shifts
JT of less than' o.10. -, t- d T, ed to prooeed linaarly, the
'_./ d a f, s u m
following shift rates are obtainfd: -i 0.~)_10-5
deghttm for tin,
and (-4.6 410-5 deg/atm for jnd-.m. In recent times, the correct-
+ 0.2)1
ness of th~.ie values has been doubted. For thi-s reason, t1113 measurements
were reyQftted ir, the range of fror, 0 tc, 1 -!50 k6i./om-2. For indium, To(p)
was linear also in this range, and j+. wa.,~ fourid t)iat dT0/dp -- (-4-4 4 0,,3)
?10-5deg/alim "see solid line in Fig.."). Tzri, h-,wever, showed a linear
Card 1/#_;

SupercondvactAvIty of 'Din
20456
S/O~ 61/04011002/010,104?
B102YB202
course of ItC(p) with dT. /dp -(-4.4 -!- 0.2),$4O-%og/atm in the range of
from 0 - 100 atm. At higher temperatures, a amviation from linearity was
observed (see Pig.2, dashed ourve,,, obtained from two tin speelmens A and
o-, the dashed line correspancis to &T Orl dr, -k--5-7 + 0.2 )'%j 10_~'deg/atm.
The meaourements vere made by the different-q! and the ice method ( t he
latter in the range 500 - 1200 atm). In tho range of from 800 to 1730
dTC/dp viaz (4.6 + 0.2)'~10-5deg/atm. Since this curve runs in Daralell
Ivith the, Indium. curve, it, can be assumed that between 100 amd 800 atm a
transition takes place from one straigh* line to the other. The effect
of pressure on superconductivity has hitherto not been fully explained.
The new theory of superconductivity gives the relation '_T0w 9 exp(-2/gv)g
where 0 Is tho Debj*&~temperature, g ,he electron-phonon interaction con-
atant, and %, the electron density. Compression on all sides of the me-
tals leads to an increase of 0 and, thus., to a linear increase of T 0 . To
explain the course of T O(p), the pressure-dependent change of the electro.-
iC.ard 2/4

YM#.LoVa
.Some species of the genus Hypericum L, to be introduced
in Uzbekistan. Vop. biol. i kraev. mad. no.0210-214 163.
(MIRA 17t2')

3nTANSXIY, I.M., inzhener; XAJI, H.I., inzhener.
Unixg smooth measuring wires in checkrow planting an& Bolting.
Sellkhozmashina No.4:9-11 AP '56. Mn 9 -4 7)
1.Zavod Belinakeellmash.
(Panters (Agricultural machinery))

XANp N.I., inshener.
Oaloulation of kinematic factors and establishing an efficient system
.-for the, working parts of potato planters. SellkhosmeAkins no.,W-8-li
AP
1.,Zayod 3*4nakeellwash.
(Plantere(Agricultural machinery))

KkNq M*I,, inzh,
Parameters and calculations for the rotary plowBhares of
potato planters. Trakt. i sellkhozmash. no.10328-30 0 1644
(MIRA 17%12)
1. Gosuderetvennoys spetsialinoys konstruktorskoye byiiro po
mashinam dlya vozdelyvaniya i uborki kartofelya.

LI!FT";,KAY9 S.S.; KANP MA.'! GOLOVLP-~V!,
I f ~
The IMIG-1 hydraullo markers. Trakt. 11 sellkhozmash. n0.10-,
35-36 0 164. 0 JUM A "A. 7 -. 12
1. Gosudaretvennoye spetsiallnoye konstruktorskoye hyuro
po inashinwr dlya vozdelyvaniya i uborki. kartc-felye,

KM, M.1w inzh.
Use of the synohrcmized power take-off of a tractor for the
drive of the mechanisms of potato plante-ra. Tral,.t,, i aellkhozmash.
no.12:17-18 D 164 (MIRA 18:2)
1. Gosudarstvernoye spetsialinoye konstruk-torokoye byi=o po
mashinam dlya vozdelyvuniya i uborki kartofelyao

GOLOVITSYN, S.K.v lnzh.L.!!I&.UAIA#,Inzh.
La
Mathode for comparing the parametere of potato p" r4ters, Trakt,
i sellkhozaash, no,1209 D 165. (MIRA 1&.12)
L. Gosuderstvannoye spetsiallnoye konstruktorskoye byuro po
wAshinam dlya vozdalyvmniya i ubarki kar-tofelya.

KANp M.S. , _
Thermal waterB of the Ili Depression. Izv.AN Kazakh.SSR.
Ser.geol. 22 no-5156-64 S-0 165.
(19RA 18:12)
1. Yazakhskiy institut minerallnogo syr1ya, g. Alma-Ata.

.> to IV It
IWAROT, Uvilly Stratonikovich; MUROWSV, Alekvey KMsqlovioh; MUl-
KIN, A.G., redaktor; US. P.M.. redektor; EWILTA, L.K., tektmi-
chaskly redaktor.
[Ooeimograptwl Okesnograf lia. Kooky&, Izd-vo mMorekoi transport,*
1954. i65 p. (HM 7:12)
(Oaemnograpby)

t'ICHRIN, 11.1ya 111ftch; K.4.:'ENIGH, V.Ye.j ret---en..en'-; L.ILI.J,
retsenzent; KAN,-, G.F., doktor tek~m. nauk, .,ed.; F2J.'I
~A~tp red.
[Transducers in marine remote control ~;:!stemsl Datchiki su-
yk' sistem distantsionnogo kontro21la. 1-. L;I-va Tzd-vo
dov 0 xl~ I -
"Tram-port, 19(4. 209 p. Ik.AIRA 17:F)

AYZENVARG, Rhaim Vollfovich; POSTNIKOVp S.A.v inzh.9 retsenzentg
YASIKOVI A.A.p inzh.t retoenzentj RZHECHITSKIYI B*D.p -
inzh.j red red.
(Textbook for electric harbor crane operators] Uchabnik
kranovshchiku portal0nogo elaktrichaskogo krana,, lzd.2.,
ispr, i dop. Moskvap Transport, 1964. 241 p.
(MIRA 17:12)

POLONSKIY, Vladimir Ivanovich; KHOIffAKOV, N.M., doktor tekhn. nauk
prof,, retsenzent; GRITSMO, P.I., kand. takhn. nauk, dots.
retsenzent; FRIK, A.O.p insh., vauchn. red.y.W. P,M,, red.
[Electric equipient and electric propulsion of.ships)
Eloktrooborudovhnie i elektrodrIihe'a-e sudov, Moskvaq
Transports 1965. 321 p. (MIRA l8t12)

NIKITIN) Gennadly Mikhaylovich; MOKIMOV, G.P.p retsenzentj
ROZEDESTUNISKlY, A.P.p retsenzent; CRITSMVIKO, F.I.,
red.; KAN
[Organizing the operation of the electric equipment of
sbios] OrganizatsHa ekspluatatsii elektrooborudovaniia
sudav. Moskvaf Transport. 1965. 109 P. (11111A IW)

TIKHOMIROV, Nikolay Alekseyevich. Prinimal ucbastiye VITSINSM t
1. V,V,p dotes) YJ11O P,14., ted.
-
(Theory and equipment of a ship for inland navigation)
Teoriia i uatroistvo evAna,vnutrennego plavaniia, Moskva,
Trahoportp 1965o 273 ps (MIRA 18:5)

NORNEVSKlY, Bor-.r, Tvanovich; TARATYPOV, Ivan Afanaslyevich
[deceased]; MORDOVIN, B.M.0 prof.p retserizent; PAIN, B-S-P
dot.s., retsenzent; MURATOV, I.I., kand. tehhn. nauk,
re-tserizent; FAIK, A.O., illzh,, red.; KAI), P.M.0 red.
-1.11 ..... 111-I.-
[Electrital equipment of shin and short, stations and sub-
stations] Elektricheskoe oborudovaT-Ae beregovykh A sudo-
-vykb stantsil i podstantsii. Moskva., Transport, -.1965. 334 p.
(MIRA IS - 5)

DUBOVOY, Anatoliy Alsksandrovich; POPOV~ Al.eksandr Vasil*yevich;
NIKITIN, G.M.., doktor tekhn. nauk, red. - NAN tt. red.
L.:=A-
(Electric propelling machinery; servicing and maintenance)
Elektrogrebnye ustanov1d; obslu2bivanie i ukhod. Pod red.
G.M.Nikitina. Moskva) Transport, 1965. 63 P.
(MIRA 18:12)

UN, R.A.; UUMA, N.A.
Oriented conduction of excitation in the atrioventricular region of
the heart. Rauch. dokl. vys. shkoly; biol. nau)d no.1:51-55 160.
(MIRA 13:2)
l.Rekomendovana kafedroy fisiologii shivotnykh Moskovelmgo
gosudargtvannogo universiteta im, M.V. Isomonosovat
(HPART-IMMUTION)

KDZIOV, A.I.: UN, S.A.
Resoui~ces and means of lowering the production costs at the lansk
Hydrolysis Plant. Gidroliz.i lesolchim.prom. 12 no.,9:23-24 '59.
(MIRA 13:4)
1. Nauchno-iseledovatel'skly institut gidroliznoy sullfitno-
spirtavoy promyshlennosti (for Kozlov). 2. Xanskiy gidrolisny7
savod (for Kan).
(Thusk-Wood-Using tuduatriee-Oosto) (IVdrolyele)

IVANCHENKOP G.Ye,; TIKHONOV, V.Ya.; 8YRIKA, V.F.; KAN, Sh.U.
Determining the transient process in a stepped-relay svstem
of automatic control with it multiple series operatim of the
regulator. Nauch. trudy KNIIJI no.15:196-221 164. OAIRA 18-.8')

M .1 94. 1. tand. Tech. Sci- Forcnotine of R I-Ovel in -the North P"r* of the
Dissertatio'n: iq4ethod for Short-Range 6) 17 Jun 47.
Caspian Sea." Cent-ral Inst of Weather Foreastin
SO: Vec ernva . Jun, 1947 (project #17836)

I(Ai: I 1 1.
for Pred',-et-lon of thc~ Dvel `.n Ue *,'-,I,tl- rn :,).n of th,-- ^,fi-7- *
1, i . "' -,. I ::JI I
1
T --iv Tsll, no 3 (:;0), 1948 (%rro)
t Z~~
SO: 11-YO', 11 '*"- r 1953

W, m.
, 1, r~: :I',
Non.periodic currents in the etraito of Kuril Islands and
p6esibilitles for tbeir-prediation. Trudy TSIF no.57.-132-143
1570 (mm 10t-9)
(Kuril Islands region--Ocean currents)

fn 4 A
Aw
it
so
it
UK
r 1i
-Ilk
41

-KA.zw"s. I.
"A Modified Methfxl for Speedy L--vcl and Curm:i.~it Ff--~vccasts."
report. to be submitted for the IntlvC(,,,n.-r. New Yorlt "itY, 31 Aug - 11 Sup lg'--l)..
> I
-
(Central Weather Forecast Institute)

W, 2. 1.
Improving the method for current prediction in the Kerch Strait.
Meteor. i gidrol. no.12:25-27 1) 160. ' (141RA 13'.11)
(Kerch Strait--Ocean currelats)

ISTOSHIN, Yu.T., kand.tekhn.nau!5s kanfl.tekhn.nauk
Calculating and prodictiDg physical phenomena in the sea.
Vest-AN SSSR 30 W-7s95-96 JI ~60. (14M 13 : 7)
(ocean)

W, S.I'
C03-culating and forecaoting c=Tento in the Kerch Strait, TrIldy
Okean.kom. 3.ltl3O-Ul 161. (MM 14:7)
(lorch Str+-Ocean OWT*ntB)

AC
AT16026 49 SOURCE CODE: UR/2546/1)%6/600/156/010510120.-
"ORJ SI
A:
ORO Cenirinnstifiate of Weather Forgeast pg (Tsentrallnyy institut, ozov)
iL progn
T17 LE: Foriedastinit and balculation of AgA ice in the- Sea of Okhotsk
SOIAICE, ltsentrallnyy tristitut prognozov. Trudy, no. 156, 1968
Ra6chet i'plvgi,loz'~~6inentov rezhima-morya (Obseiving and forecasting
chef ~acterisiticiof 60 en m en
o a~, 105-120
I-TOPIC TAGS pressure, Tschebyshev
-s alo.e' oc erty, atmospheric
:; e ean prop
povirlomial
A
IL
TRACT:!i Metbddb ofJorecasting and calculating sea ice in the Sea of Okhotsk.
iarO.,aisc 4;: Thp. keferenbe,potnts in prognosis equations are the fiel& of L
usso
atz~i)spheric, Pressure- over. a.broad region presented as analytical series expan-
_QiTschebyshev pokynomial. Orjig. art. has: 4 figures and
si6ns accordill.9 to,
5 tablesi~' [Da0ed on author' s abstract)
INT]
SUB CODE: 6,6 StJJ3M DATE: none/ ORIG REF: 019/
Vir'
C 11

Y-4140
Raschet kryla na sdvig. (Tekhnika vozdushnogo flota, 1941, v. lh, no.b. p.5-20, diagrs.)
Title tr.: Calculation of shear in the stress analysis of the wing.
TL5oh. T4 1~41
QO: Aeronautical sciences and Aviation in the Sodet Unionj Library of Congress3
1955

KATI) S. N.
Ruschet kx7la na Bdvig. (Tekhnika vozdushnogo flota, 19h1, v. 15t no. 4,
P. 5-20, diagrs.)
Title tr.: Calculation of shear in the stress analysis of the wing.
TL504.T4 1941
SO: Aeronautical Sciences and Aviation in the Soviet Union, Library of
Congress, 1955.

ml So N. I SVERDLOVI 1. A.
ion of the Strenglh of Aircxv~Lt, Moiscow 1945

PHASE II TRFASURE ISLAND BIBLIOGRAPHICAL REPORT AID 46 - 11
Call No.: T1671.2.K33
Author -. W, S. N.~
Fl.,,11 Title: AIRCRAFT STRENGTH
Transliterated Titlet Prochnost' samoleta
Publishing Data
ChIginating 4ency.- None
n 'tblishing 11ouset State Publishing House of the Defense Industry (Oborongiz)'
Date: 1946 No. pp.: 292 No. of copiest 15,000
Mitorial Staff
Rditar: None Tech. Ed.: None
Editor-in-Chieft None Appraisers: Cheremukhin,, A. bl.,
Professor, Doctor Technical
Sciences
Rostov'tsav, G. G., Professor,
Doctor Technical Sciemea
Text Data
Coverage: This is an enlarged synopsis of leatirres given in advanced courses
for USSR.Air Force praoticing engineers by the author in the
Military Air Academy imeni Zhukovskly. The book might be used by
readere without special technical education to help them understand
problew of aircraft design. (Diagrams, graphs, tables).
Prefaces None
1/8

Proahnost' samoleta
AID 46 - U
Introductioni A comparatively long introduction (23 pp.) gives a review of
fundamental laws of machanieB (Newton, D'Alembert),, with
simple examples illustrating their application. The air-load
d1stribution and its effect on the aircraft are briefly
described. Traction, compression, shear, bond, torsion, and
flexure are shown in their simple form, and fundamental
formulas are given.
Abstract: In Chapter 1 (25 pages), the author gives the basic formulae for
the calculation of the external load of aircraft in various kinds
of flight, and in landing. In each case numerical examples of the
appli"tion of formulae are given. In dection 6 (P. 45-471, the
definition of the safety coefficient is given., and,in section 7
(p. 47-51), aircraft strength standards are analyzed. All aircraft
are divided into three classes: 1) Maneuverable aircraft, with
which all acrobatic flights are permitted without restriction,
2) Aixeraft of limited maneuverabilit , with which rastricted
acrobatic flights are permitted and 3~ Non-manouverable aircraft.
Six cases illustrating the distribution of stresses and their
intensity and direction are given.
Wings and empennages are discussed in Chapters II-VII (110 pages).
2/8

Prochnost' samoleta
AID 46 - 1I
The author describes the choice of an airfoil, the dihedral of the
wing, the spanwise air-load distribution, the determination of
Inertia forces due to the mass of the wings, the direction of the
force resulting from the air-load, the distribution of loads of
,rarioug components, the direction of the resulting force from the
wing's inertia and the mass of the components, the position of
these various forces, bending moments, torsion, etc. Section 11
describes braced wings, wings with corrugated skin, double spar
wings, and box-structure wings. Normal tensions in monospar wings,
in two-spar wings, and In box-strueture wings are described.
Section 13 describes the shear due to diagonal forces and to torsion.
Section 15 describes flanges, webs, reinforcing webs, birch-veneer
opars, etc. Section 16 describes flange stiffeners, truss spars, ato,,
Section 17 describes the approximate calculation of_rjbB, external
foraes and bending moments, and the determination-of-stressen.
Section 18 describes wooden and metal ribs. Seetion.20.describes
aerodynamic compensations, balancing loads, flettners, tArmrs, etc.
Sections 21 and 22 describe the e3lternal load of the eilerons,
their attachment and their work. 'Sections 25-27 describe slate and
flaps, split flaps, simple flaps, zap flaps, flower flaps, etc.
Sections 38-31 describe empennages, their surfaces, airfoil, shape
and Don1tion, and balancing methods, external loads, and reaction
determination. 3/8

Prochnostf samoleta
AID 46 - Il
Chapters VIII-XII (102 pages) deal with fuselages and landing
gears. Sections 33 and 34 describe the design of truss and
monocoque fuselages and the determination of norval and diagonal
atxesaes. Sections 41-46 describe basic defects of conventional
and tricycle landing gear, wheel types, shock struts, and various
cases of Irregular functioning of oleo-pneumatic struts.
Sections 47 and 48 desoribe a-8 give diagrams of shock-absorbing
struts of tho following types; IL-2~ Pe-2 and Yakovlev, and of
-the landinp pear of the MTG-1~ TA_~. Ypk-71" IL-2 or Te-2 typeo.
* J"~ ~,rul 50 derscribe ir-Aln stresser, in landing geare.
Sectiw T
Chaptor X111 (20 pages) starts with a brief explanation of the
phenomena of vibration,.',and then describes vibration in various
parto-of the airoraft.
At the end of the book, 4 tables give spocificatione of j4dieal
and mechanical eharacteristic3 of )-raterials used In aircraft
construction. The following materials are describedt low-carbon
ateel, medium-carbon steel, Chromansil, duralumInftMp'iffVFd%d
wood and Improved veneer (referred to In the text, page i3
"Delta-drevesina") and plywood. 7he last table enumerates eleven
4/8

Frochnost' samoleta
AID 46 - II
kinds of nc.Tmal grade woods used in aircraft production, the regions
~of their growth, and their specifications.
Evaluationt It im a well written and well-presented popular textbook. The
table giviDg specifications of different kinds of Soviet wood
% might be interestingl but otherwise the book does riot contain any
original information.
Purposes This is a textbook for aviation techniciants, and evrNmual for
practicAng engineers and technicians of the USSR Air Force.
TABLE OF CONIMS Pages
Introduction 5
Ch. I INternal Loads on the Aircraft 24
1. Horizontal Flight 2-5+
2# Curved Plight '26
3. Flight in Turbulent Air 35
4. Strosees in Acrobatic Flight 41
5. Landing Loads 44
6. Safety Coefficient 45
7. Strength Standards 47
Ch. 11 The Design and Perforrance o~ the 'k-Ang, 51
8. The Design of-the Wing 51
5/8

Prochnost' sarmleta
9. External Londo on the Wing
1.0. The hirtoravinco of the Wing
11. The Nni(m 1~qyout of the Wing
Ch, III CalclOation of the Pattern of Forces o:V the Wing
12. Normal Forces
13. Tangential Forces
Ch. IV - Bani,(, 11.1ing Gwnponenti
14. Tho ;:a),' W,)rk of Spars
15. Woodlen
Motiil &rqir~
17. Thel lltwpotw tind Approximate Calculation of Ribs
:18, The'DesiRn of, Ribs
011. Aij~rons
.;19. The ht~poae,:'of Ailerons
.20. Aileron Cot4*nsation
21. A116r6n, Lo'ad and Performance
22. Aileron Da~~jrn
P3. R6vdiiijbid Aflerobs
Ch. V! ble~*haniz':d'tioh of the Wing
24. The!Purpaaa of Mechanization
,25. Aspocts of1flechanization
6/8
33. Fuselage Naign
34. Jbnocoque.,ruselage Calculation
35. Truss.-fuselage Calculation
Ch. IX Engine Mounts
36. F,%:ternal loads
37. Engine Hownt Design
38. Engine Mount Calculation
Ch. X Landing Glear -
39- Bxtervlal lxwls on the Landing Gear
40. Baoic 1/indlng Gver Requiremants
41. Thwee-uh&el Landing, Gear
42. Lwiding G-ivx Whet3ls
V8
AID 46 - II
Pages
55
62
73
85
85
90
95
95
97
102
109
114
118
118
121
.12r)
-129
13..
134
134
136
167
177
186
190
191
196
200
205
205
209
212
217

Proohnost' samolets, AID 46 11
Pages
Chi XI Shook-absorbing Struts 221
43. The Purpose of Shook-absorbing Struts 221
44. Principles of Operation of Oleo-pneumatic Struts 223
45. Influence of Bushing and Washer Friction on the
Work of Shook Absorbers 229
46. Irregu3.ar Load on the Shook Absorber 232
47. Shook Absorber Design 237
Ch. XII The~Performanoe of the lending Gear and of its Parts 243
48. Cantilever landing Gear 253
49. Braced Landing Gear 254
50. Double-strut Landing Gear 257
Ch. XIII Air6rgft 'Vibrations 265
51. Baele,Paramoters Characterising Vibration 265
52. Aircraft Vibrations 267
53. Bending and Torsion Flutter 272
54.- Bending Flutter Due to Ailerons 286
Tables of Physical and Mechanical Properties of Aviation
Materials 287
Blbliograpbyt None
Facilities: None
Availables Library of Congress
8/8

KAN, S-N -
ELI, S. A., and ~1- 0. PANOVKO.
Blemanty stroitellnoi mekhaniki tonkostennykh konstrul-tsii. Pod red.
A. M. Cheremulchina. Dopushcheno v kachest-ve ucheb. posobiia (ilia
aviats. vuzov. Moskva, Gla-v. red. aviats. lit-ry, 1949, 126 p., diagrs.
Title tr.: Elements of mechanics if thin-walled structures. Approved
as a textbook for schools of advanced aeronautical studies.
TM71,2. K3
SO; Aeronautical Sciences and Aviation in the Soviet Union, Library of
Congress, ip,55.

Ran, S.- - .11.
Elerenty Stroitellnoy Nekhaniki Tonkostennykh Konstruktsiy (.Zlemnts of
St,ructure Rechanics in Thin-Walled Construction) Jzd~ 2&j Perer, 1 Dopo,
By S. N. Kan and Ya. G. Panovkoe Hoskva, Oborongiz, 1952. -
161 P. Magma, Graphs, Tadles.
SO: 1415
666.2
IKI
1952

PHASE I Treasure.'
lslai~ 1,Bibliographic Report
Authoirt RAN S;,N.
mi iiti!7 J*w? sTRENGTH... 3rd edition.
,TrawliteraW Title't Proobnost' sawlete,
I~ibjia~ing Data,~
Originating~ Agencys None.
Publishing Ho~~-. $6te Publishing House of
Dat6 t 1953. No.. pp. : 302
4, 6
Can No. TL 671.,2.133
the Defense Industry(Oborongia).
No. copiest None.
'Edit*rW Staff
Editors iffono* Technical Rlit-ort Mone
Witor-in-4h1aft None. Appraisers None.
Otherst The~authcir'expreosea,thanks for valuable help to :kykovjV.T*#
and-Iota,, N.M.
Y.N.* Um~~Iiyp D.E., larnoshitskiy,
Text:Data
Caveraget The.'stresses acting on aircraft and the strength of construction
req:6irea,~to*me6t these stresses are discussed. FAcent changes in
airbrafti,construction and outside form walls are outlined. Methods
tion are explained
008ternining the strength of aircraft construct
by~qpec Iitio examples. To evaluate -correctly the strength of con-
St?"Uet,oIft following factors are studieds the purpose of that
construction, external atresses acting on the aircraft,, Vie, stability
of-the-constructionF end., finally., its strength, This is the third
edition,,revived and expanded to include considerations important
for jet propulsion and sonic speeds, Discussion of maintenance
1/2

Card 2/2
Gall Moo TL 671.2433f, 0046
Full Tit,191 AIRMAFTSTRENGTH. 3rd edition.
Text D&U
coveftget (coutinued)
problems giyen.in earlier editions is not reprinted. Instead the
reader is Warred tothe 1951 Oborongiz publication ftiMblep. 2t
which should be oqnsidered as the first
part of th'a books N=erous charts, tables, and diagrams appear
in the, textil
Purpoe; A textbook feir a course of aircraft strength for stidents of Technical
Schoolip and for' students of Technical Aviation Schools. It may also
be used,as &~Vftjqnuql for the aviation auxiliary technical staffs
Facilities: ShisbkinZN " Goryainov, A*Aop Kuzimin, Gol., amd Makarevskiyf AsHop
arm-catecifor their achievenent. in formulating normo of 1. s-trength.
No& Russian and Slavic Warences,: Only one reference is mentimed in a footaote.
(Sutugin., L.I. ProyDktirovardya chastey
samoleta. 1947).
Availablet Library of Congress.

I NNI 11m
KAN P f, .it.
11
"Pressurized Cabins ;, represents a translation of the Sub-Chapter 43 (Gemeti-
cheakiye Kabiny) of the book "Stress Analysis of Airplane" (Pr,,)chxnost1--SWPoleta),
published by the State nibLishing House of Defense Industry in Moscow, 1.953.
Report D-102898, 12 Oct 54

KAN, S - N.
"Catapult Pilot Chair," a slightly condensed translation
of the rmnograph, "Airplane Stress Analysis," published by the
of the Defeme Industry, Moscow, 1953.
of Chapter 44 (pp. 202-210)
State lublishing House
Report D-102897, 1-2 Oct 54

KANp,S.N.
f. Vibratsii samoleta. (In his Prochnost'samolete. Vloskva, Oboron,-iz, 1953.
p. 278-294., diagra.)
Title tr.: Aircraft vibration.
TL671.2.K33 1953
SO: Aeronautical Sciences and Aviation in the Soviet Union~ Library of
.Congress.. 1955.

KoN)
PL4SR I BOOK EMNATION
Kan., Saveliy Nakhimovich
------------
Frochnost' sawlets. (Structural Strength of Aircraft) 4th Rd. Moscow, Obororgz*
1955. 2`85 P-
RevIeverss Rostovtsev.. G. G.., Doctor of Technical Sciences, Professor; Scientific
Ed.- Gimellfarb, A. L., Candidate of Technical Scienceso Docent; Ed, of
Publishing House: Suvorova, I. A.; Tech. Ed.- Zudekin, I.M.; Managing Ed.:
Sokolov, A* 1.
ItMWE: The present book is a textbook on the subjeet of "Structural Strength of
Aircraft" for students of aviation tekhniktos., technical schools and
readers,with a secondary school preparation.
COVMACE: The boolr deals chiefly with the ,aialysis of vircraLft design coraidering
purpose, layout, and the character of external loads. The atatment of
problems Is given in an elementary form. The fourth edition hae a mmbet
of significant changes. It contains new sections on aileron efficlencq$
brake flaps and hydroboosters.
Card 1/8

Structural Strength of Aircraft
In the new edition each chapter is based on the analysis of citroctural stresses
and deformations Of bigh-Byeed. jet aircraft. SPP-Cipl attention has been 1;L-mn I;o
bydroboosters, aileron efficiency, tricycle lending gears and otlier modern struntural
devices. The author at-Ftes that, in structu--.1 comInitatiore not only strength problms
but rigidity problems must be considered. Yne rigUlty of a structure govarne t4t;
extent of deformation. The rigidity nffects the sta:bility and controllabilit-,,
characteristics. Insufficient rigidity may vibrations of the separete parts
of an edreraft. The problems of autovibrations of the ving., the empennage., -And the
landing-gear nose vheel were investigated fliLly by Soviet scientists 14. V, 'Celdyshj,
S.I. Krichevskly., E.P. Grossr-on, rind others. The bcok eontains one table and 295
figures. The author expresses gratitude for valuable assistance to A.L. Ginmellfarbi,
Candidate of Technical Sciences.. Docent, and V.14. Koto.
TABLE OF
C 0 hM'T S>
Preface to the 4th Eclition 3
Introduction 3
Card 2/8

:L62
Structural Strength of Aircraft
Ch. I. External loads of the Aircraft
7
I.. Horizontal flight. 7
2
2
. ftmd Mgbt 11
3. Flight in turbulent air 20
4. Stresses in acrobatic flight 25
5. Landine loads 213
6* Safety coefficient 29
7o Strength standards 30
Ch. II. Desiga and Performance of the Wing
35
8. Design of the ving 35
9. External loads on the ving 43
10. Perforzance.of the ving 49
11. Ifiug design lay%mts 59
Card 3/8

Structural Strength of Aircraft
Ch. TEE. Calmlation of the Pattern of Forces on'the Wing 72
.12. Vormal. forces 72
13. Tangential forces 76
lit. Distribution of forces on a mrept-back ving 82
Ch. IV. Basic Wing CcmToneuts 93
15. Purpose, work, and design of spars 93
16. Purpose.. vork, and design of ribs 99
Ch, V. Allerons 106
17. Purpose of ailerons 106
18. Aileron ccapensation 108
19. Aileron load and performance 113
20. Aileron design U6
21. FMciency of ailerons 119
cm,a It, 8

Struetural StremgLh of Urcraft
Ch. 1:X. Paselage 172
34- Rctemial Io9A on the fuselage 1T3
35. Fuelage design 17T
,1,6. Honocoque-fuselage calculution 184
'U. Tnws-fuselage calculation 190
';8. Airtight cabins 191

.J9.
Ejector a=angements for the crey 199
Ch. X. Engine Mounts 209
4~. External lop& 210
41. Engine-munt design 213
42. Engine-mmmt ealmantion 213
Ch. %'I. Landing Gear 217
43. Basic landing gear requirements 220
44. Three-vheel landing gear 222
45, Landing gear vheels 223
cari 618

& ~;truclhwrl .1trmigth of Aircraft
!i& BeudJ.ng flutter due to :ilerona
16 L-
L11-j,
Table of Phyuierl and Mechexical Properties of Avitktion Steel
A.
cmd Duralumin M~
AVA3VJU- Librery of CoiWeas
Card IS /ncw

KANy I;. N. (Engx.-Col)
...... -.,
"Tempezuture Stresses in the Framework of a Casing (v korgase obolochki) Partially
Filled with Liquid," report presented at the Ninth Scientif ic -Technical Conference,,
helC~ at the Khar-kov Higher Aviation -Engineering Military School, Dee 1958-

PHAO I BDOK EVWITATION 786
-Nan, Saveliy NakhImovich and Sverdlov, Josif fairamovich
--------------
Baschet samolets, na prochnost' (Analysis of Aircraft for structural strength)
4tb ed.,, rev. Moscow,, Oborongiz,, 1958. 291 p. 3.1.,000 copies printed.
&viewerst Odinokovp !M.G., Doctor of PhyolW. and Mathematical Sciences, Profes-
qcjr, and Che,remukhin, A.M., Doctozo of Teclutical Sciences,, Profemr; Ed.:
Ydralaia,, A.R. Rw#werj Ed. of Palishing House: Sheynfapj L.I.; Tech. Ed.:
anhim, V..P. Y"asing Ed.:* 06,kolov, A.L., Engineer.
PURPOSS: This book Is approved by the Ministry of Higher Education of the USSR as
'a textbook for aviation YwAs. It my aloo serve as a drafting manual in design
offices ofaircraft factories, and as an idd in improving the qualifications of
designers.
COVRIVZ-. The 1945 edition of this book has been radically revised and greatly
mWplemented. Probleap in determining aircraft loads and calculation methods
fox; the separate aircOaft components an considered. Completely new sections
have been added*cm aerodynamic heating and thermal stresses, calculation of
swqtback and delta wings and tail assed.)lies., calculation of fftmes with con-
sideration of their elasticity, ~ibratiaas of aircrdft components, etc. Fbr
Card V 7
7
3
5

SOV/86-58-7-23/38
AUTHORt Kan,,,,.S N Engr Col. Profeseor., Doctor of
TITLE: one Heat Barriar Problem (Odna iz problem teplovogo.
barlyora)
PERIODICAM Vostplik vozdu6hnogo flota, Nr 7, 1958, PP 56-61 wsw
ABSTRAM The author states that the heating up of modern high
speed aircraft or rockets can be defined as the rise in
temperature in the boundary layer. The law governing
.the distribution of heat in the aircraft depends essen-
tial~y on Ithe.duration of flight. He gives some heat
temperatures which an aircraft may reach at certain
speeds.,altitudes and during certain flight durations.
Analizing the diagrams which represent the variation of
the temporary resistance and the modulus of elasticity
of some materials depending on the temperature, he points
out that one way whioh may solve the problem of heating-
up it; the use of heat-resistant materials. The effoot
Card 1/2

KAN, S.No. -. -
I--# ~!Jj ~
Analyzing oylindrical shells with large cutouts.,Izvi.vys;
uoheb, sav.-,'av.tokh. 2 nool$32-37 t59, (MIRA 12:3~
lolharl1mvekoys vyisheye avintsionnoys inshenernors voyenuoye
uchilishchs.
(Mmtic plates a-ad shells)

I~Iu
,,XhN, Beg. (Iluirlkov); SHKOL'Nffo P.A. (Rhar"kov)
Strength of open prismatic shone. Pr;rkl, mekh. 5 no*353-370 159.
0(!iZk 13:3)
(Ilastio plates and shells)

III li'llfiHirl limp INIII I q M I
=wmu Aw qj 11 g-up HIIII,
. ............... ....... ........................................... ........
if
2.m
J1
A, Ila
j avi
A

rAY. qaval1v Vakhtmovich
Nai gning an aircraft for stran th, by '5. 1% Kan and T. A. svemlov.
7-H-O'ht-Patterson AirForce PaRs, Ohio. 1040.
?04 1, MW-4-, MaRIM, vrapbs ( r-"-qQO5jV)
I'rannlateA 'Prtym the orivinal %iilan: Paschet samoleta na
rrm.I~nmqt'.. YOSCOW, Ip9q
'Tarlier Pusslan lanpuapv 6ditionrhave title: Prochnost' 9-3moleta.
'IbRoprraphy: 1. 4-5

VINOEUDV, Lev doktor,tekhn.nauk,
retsenuent; RMCK, VoY., doteenC:vGnd;- MeG'.-n '
I - auk, retsenzent;
DAVIM, I.V*, doteent, kand.takhn.nauk, otv.red.; KURILOVA,
T.M., red.; TROFIMENKO, A.$., takhn.redi,
(structural mechanics of rod systems; theory of the deformation
of rod systems] Stroitallneia mekhanika stershnevyk:h sistem;
teoriia deformiroveniia starzhrievykh sistem. KharIkov, Izd-vo
lbarikovskogo gos.univ.$A.A.X.Gor'kogo. Pt.l. [Statics]
Stetw. 1960, 387 P. (MIRA 13:10AI
(Structural frames)

VINOKEIROVp Lev Pbikhmoviob; KOLESVIROV, L.A.# kand. tokhn. nauko reteen-
zent; CHEWSOV, A.P*) kand, tekbn, naukiretsenzent; ALUMEV,
Yu.N.p kando takhn. nattk,, retoenzert~--XMi.,5,Pp
., -, profop doktor
tekbn. naukp otv. red.1 MIWVA., T.M., red.; %IILYANSWA~ T.M.,,
tAbn. red.
[Structural imoobanice of rod systeria-, tbeory of tbe deformation of
rod oys4w] 3troitellnaia mekbanilta oterzhnevykh sistem; tooriia
deforriirovaniis otersbnevykh Biotoin. Kharikov, Izd-vo Khar1kovokogo
goo. univ. im. A.M.Gor1kogo. Pts. 2-3. 1961. 198 p. (MIRA i4in)
(Beams and.girderil)

tigi Mile ROF111 [sill fifiJUL-.1 Ul"Lia
20597
s/l47/61/000/Ool/Oo6/Oi6
E03VE1135
AUTHORS: Kan, S.N., and Silantlyevv A.V. (Khar,kov)
TITLE- Fuselage Bending Calculations in the Region of a
Mid-wing Junction
PERIODICALt Izvestiya vysshikh uchebn3,kh zavedeniy,
Aviatsionnaya tekhnika, 1516l, No. 1, pp~ 46-60
TEXr: It appears from strain gauge data that neither iti the
region of the Junction of a mid-wing isrith a fuselage nor beyond
the boundaries of the region do the -normal stresses obey the plane
law of distribution,. There is therefore a need to find a more
ace-urate method of calculating this distribution. The present
paper -describes some of the results of investigations made at the
Nalitchno-issledovatellskiy laboratorii Kharlkovskiy vysshego
aviatsionno-inzhenernogo uchilishcha (Scientifi~~ Laboratory of
the Kharlkov Higher Aviation Engineering College) with that end in
view. It was assumed that the fuselage and wing were held rigid
along their contours The fuselage is regarded as a multiply
statically indeterminate structure. only axial forces on the
transverse sections of the fuselage, bending moments on the ribs
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Fuselage Bending Calculations in the Region of a Mid-wing Junction
and the bending of the side wing ribs will be considered in the
deformation equations. Consider the problem of determining the
fundamental stresses o and q when the fuselage and wing are
joined along their common contour, so that the fuselage can be
considered a shaft with a cantilever in'the elastic state, Only
the central part of the fuselage need be discussed and this is
assumed loaded by a bending moment from either the front or rear
part of the system. To determine the distribution of normal
strosset; along the length of the wing, a is written as the
product ast, y(x)9 where oef. represents the normal stresses at
a section of the fuselage coinciding with the reinforced frame,
and x Is weasured along the axis of the fuselage, Substituting
this value for a in the equation for the equilibrium of an
elenent. of the fuselage we obtain a differential equation for q.
Initially it is assumed that the twisting moment of the wing is
taken out through the reinforced frame, The fundamental stresses
can easily be found after solving a irery simple variational
problem for ~p(x). By setting up the expression for the potential
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E031JE135
Fuselage Bending Calculations in the Region of a Mid-wing Junction
energy of the systsm and fulfilling the conditions for its
extremum an inhomoganeous differential equation with constant
coefficients in obtained for y(x). In solving this equation it
is., assumed that the moment of inertia of a section of a side rib
Is inf inite. The boundary conditions are determined by the rigidity
of 'Lhe reinforced frames of the fuselage, which analysis of the
solution shows to have a significant effect on the fundamental
stresses at the central section. Calculations show that even if
the reinforced frames are elastic, the assumption of their absolute
rigidity gives sufficient accuracy irk practice. The determination
of the supplementary stresses is considered next. These stresses
may be found from the condition that the deformations of the
central section are shared with the front and rear sections. They
can be written in the form Air.~(q) 1pj.(x), where the Aj are
amplitudes, 1~ gives the variation of the supplementary stresses
at cross-sections of the section, and fpj gives their variation
along the length of the so--tion. The coefficients Ai are found
from the deformation condition giver. above. The determination of
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