SCIENTIFIC ABSTRACT KURSHEVA, A. N. - KURSHINSKIY, L. V.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000927810007-7
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: March 13, 2001
• Sequence Number: 7
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

RMSIFEVA, A. N.
it Ibe Reaction of Urine Precipitation in Brucellosis," Tn,,dy Nauchno-
issiedovatellskogo Instituta bLikrobiologii i Epidemiclogii Yugo-Vostoka SSSR, Saratov,
Vol 1, 1951, pp 2(~9, 2','c.).

't,'d ril rj,,, anfl e
j?'55. Min Pealth t')1 a 1-2~rla - 3,- ra
an'l Fr~"i'lellAo"OLV Of thp sojt"jr-31- St~l te Tnst
,wp!,t of the U.31? ",Mt rob". (Dissortatior.,3
for t~'e of "tinlida"(1 of Blolo,;?,ical
ii_21_11T.l~ ':o. 44,

Effect of the type of the nervous system on conditioned reflex
activity in experimental tumor growth Cwith vu ry in Inglish).
Biulokep.blol, i med. 45 no.l.-83-85 A 158. (WRA 11:4)
1. Iz kefedry patologicheskoy fizologil (zav. - dotsent P.Ta.Novo-
rasova) Saratovskogo meditainskogo inatituta. Predstavlena
akademikom A.D.Speranskim.
(U"LASKS. experimental,
eff. on conditioned reflex activitv, role of type of
nervous system (Rua))
REFLIM, CONDITIONUO
in exper. neoplasms, eff. of type of nervous system
(RUG)I

R~,
Fy-~'PPT't 7DIC1.
6ec 1~1 Vol 7!n ' ,tnrpr '11r', t 59
3037- Peculiarities In the development of M-i turnours in rats with a
changed functional condition of the central nervous systern (Russian text)
KI-R311FA-A A. N. Dept. of Iatliol, Physiol., Saratov 'tied. Inst., Saratov 11)01.
-Ek-iTe-r-.-HPoTTjTTr7. '95",0/1 1 (91-93) GraPhs 2
It wasshown in cxperimentson rats fliat small doses of cilkine initibit diedevel(q)-
ment or oic transplanted tumour (sarcoma Nl-t) by increasing the 11111clioll.11
mobilityOrtbe C'NS. Large doses ofcaircine accelerate fliegrowliol'ille turnoill if)
connection witli the development of the stifiralin-finil inbibition in ilic CINS.

VEUIIIIIuVA, JJ.K.; KWISIOVA, A.U.; OLLI, V.D.; XONTORINA, A.A.
Compound therapy of experimental cholera infection. Report
11o.l: Studios on the effectiveness of certain antibiotics in
the treatment of cholera septicemia in white mice. Antibiotiki
4 no.3:81-85 MY-Je 159. (MIRA 12:9)
1. Gosudarstreanyy nauchno-iseledovatel'ekiy institut mikTo-
biologii i apidemiologii Tugo-Vostoka SSSR ("Hikrob").
(AMIBIOTICS, eff.
on exper. cholera, comparison of various
drugs (Rus))
(CHOIJOh. exper.
eff. of various antibiotics, comparison (Rua))

KURSHEVAO A.N.
Change in the blood circulation apparatue in reflexogenic
hypertension in dogs. Report no. 1. Trudy Sar. gos. mad.
inst. 26:39-41 159. (MIRA 14:2)
1. Saratovskiy meditainakiy inatituts kafedra patologicheakoy
fiziologii (zav. - dotsent P.7a, Novorasova).
(BLOOD-CIRCULATION) (HYPERTENSION)

KURS.11EVA, A.N*
Reactivity of the blood circulation apparatus
hypertension in dogs with a changed functioral
central nervous system. Report No. 2, T-ivdy Sare
Wt. 26142-45 1~9,
1. Saratovskiy meditainakiy institutt kafedra
fiziologii (zav.-dotsent P.Ya. Novorasova)o
(BLOOD-CIRCULATION) (MERTENSION)
in reilexogenic
condition of the
gose made
WRA 1412)
patologichaskoy
(ITERVOUS SYSTEM)

KURSIIEVA9 A.N.; LUNTSp A.M.
------
Wluence of drinking water contaminated with oaratov petroleum
on the animal organiem. Trudy Sar. gos. med. inst. 26:89-93
159o (MIRA 14:2)
I* Saratovskiy meditsinBkiy institutp kafedra patologicbeskoy
fiziologii. (zav. - dotsent P.7a. N&iorasova)a
(BLOOD-DISEASES) (PETROIMM-PHYSIOIXICAL EFFECT)

11FDOROVP A.F.; KGROBOV, Ye.B.; KURS)TILVA, N.G.
About the so-called "a Ilystoamylase". Ferm. i spirt. prom. 30 no.1!
13-14 164. (MMA 17: 11)
1. Voronezhskiy tekhnologicheakiy institut.

KURSIMMA, V.I.
Lipogranuloma, a rare disease of the breast. 3drav. Turk. 7
now3t22-23 Mr'63. (MTRAll")
I* Iz kafedry goopitaltnou khirurgii (zav, - chlen-korTespon-
dent AMN SWR prof. I.F.Berezin) Turkmenskogo gosudaretvennoEp
meditsinskogo instituts, i Ashkhabadskoy gorodskoy klinicheskoy
bollnitsy No.1 imeni N.I.Semashko (glavnyy vrach G.T.Bondarl).
(EREAST-TUMORS)

FEDOROVP A. F.; KMHEVA, H. G.; ZHMXOTAj, T. G.
Fundamentals of the enricbment of the distil-lerts grain b7
means of ammonium lactate, hv~ viao uchebs zave; piahche
tekh. no.5:92-95 162. (KIRA 15:10)
1. Voraneshakiy takhnologicheskiy institut, kafedra. tekhnologii
brodillnykh proizvodstv.
(Fermentation) (Feeds)

ROSTOVSKIY, -
G.V. , lcand.med.nauk; KUPSIEVA.3-1-
Echinococcus of the left femur. Zdrav. TiLrk. 5 no.2:30 Vx-Ap 161.
(MIRA 14;5)
1. 1z kafadry gospitallnoY k1drurgil (zav. - chlen-korrespondent
AMII SSSR prof. I.F.Berazin) Turkmonskogo go8udarstvennogo medit-
sinakogo inatituta imeni I.V.Stalina.
I (FEMUR)

~~ r T -e 31 1 f 'e' () - ' '~)
- I - . ~ . . . . I . , I .
11',:Lnimi-m coofficierit of deep draidng."
p. 20 (Leka Promi~;hlcnost, Vol. b, no. 1, l)57, Sofiia, i3,uli-,aria)
Norithly Index of Fant European Accesz.ions 1,(,l Vol. 7, :~o.b, JIU-10- 1958.

LIPOIISKIYo V.M. t kand.tol:hn.n:~.uh; V.,~.; --ii-060j
immalu-9 1).i;.
Tho E-15-14 oxcaw-tor, Nokh. at---oi, IC ro. 2:25 F 161.
(I'MA 14:21,
Is GlavlonincrUdahoy,
(4xci-wtting riacilino---y)

YEVDOK3MVI V.i.P I
I.K., ninzh*j KEBOVp lueNsp inzhe
Semitrailer with controllable wheels for transporting long structural
elements* Strote i doro matsh# 7 no#7t2l-22 31 162. (MM& 15:7)
- (Truck trailers) (Pr"ast concrete-Transportation)

nigmA zhener; RAUTKLN, Tu., inzhener.
-WOO-Wll-
Suspended roofs for mechanized operations in open pits. Stroi.
mat. 2 no.12:26 D 156. (KLR& 10:2)
(Clay) (Roofs)

SOURCE: PrikJadimye mekhanika, vo. 1, no. 1, 1965, 22-31
TOPIC TAGS. periodic function, haratonic function, elaaticity theory, potential
function, complex variable, elliptic function
ABS-T-ULCT: Pundartental relationships are obtained in the solution of the biharmonio
problem in theory of elasticity where the region tuider. consideration forms U con- T,
~p-uont asystera of identical circular holes (Gee Fie. 1. on the Enclostae). nomple~
potentials j> (z) and (z) are introduced which are expreased by Weierstrass
.e~IiDtic functions (D 11, Wl - 00
(2h, T 51
(Z)
- - -- ---- -----
(2k + F)r Im 0 (k 0, 1,.). Tho solution is ahovm to be
1.,Cc.rd 1/3

L 3315 35-65
LCCESSIOIN MR-
applicable to both the homogeneousi and nonhomogeneour. biliarmonic doubly-periocUo
nr ob 1 eras .INto c-ases are mmlyzeds the cane vrith a doub4-periodic distribution of
-Q' ,-,,id the case with doubly-periodic distribution in stress as well as displace-
Mr-mt. To the firct case corresponds the lattice bending under a aelf-balancing,
periph~3ral stress applied to the hole boundaries. To the Beccrad, the problem of
ber-dinG of latt:Lco holea fixed or hinSed at.their boundexies under a bi-periodio
transverae stress. For alreLmlar triangular lattice Ithis last case gives the closed
24-
form ealution w(x, Aoit(z) -Act. (4), Stress concentration
curves are givon togethex with curves of elasticity modulus for regulax lattice
structuares. Orig. art. hass 35 equations and 9 figuroo.
ASSOCICHON t SibiraUy naualmo-issled. Inatitut (Siberien institute of Scientific
Re!3ea_r2I1L_
SMBPEITTIZI-i-t 21Feb64 ENCLi 01 SUB CODE.- 12
NO ?";:,r SOY: 012 MIM t 003
Carc! 2/3

SOVI'124-58-8-9067 D
)'rai-islation from: Referativnyy zhurnal, MeRhanika, 1958, Nr 8, p 109 (USSR)
AUTHOR~, Kurshin, L.M.
TITLE: Some Aspects of the Flexure and Stability of Cylindrical Three-
layered Sandwich Shells (Nekotoryye voprosy izgiba i ustoychi-
vosti trekhsloynykh tsilindricheskikh obolochek)
ABSTRACT: Bibliographic entry on the author's dissertation for the de-
gree of Candidate of Technical Sciences, presented to the In-t
mckhan. AN SSSR (Institute of Mechanics, Acaderny of
Sciences, USSR), Moscow, 1958
ASSOCIATION: In-t mckhan. AN SSSR (Institute of Mechanics, Academy of
Sk' 64W r1iA, USS It), K I ~ 10 C% I\V
Card 1/1

AUT9OR: Kurshin, L.M. SOY/55-58-1-8/33
TITLE: On the Paper of V.I.Korolev "Symmetric Forms of the Loss of
Stability of Plates and Shells of Three Layers" (0 rabote V.I.
Koroleva "Simmetricheskaya forma poteri ustoychivosti trekhsloy-
nykh plastin i obolochek")
PERIODIGALs VeBtnik Moskovskogo universiteta, Seriya fiziko-matematicheakikh i
yestestvennykh nauk, 1958, Hr 1, pp 73-77 (USSR)
.LBSTRACT: This is an adverse criticism of the above paper of Koroley [Ref 1].
the author proves that in the paper of Korolev there are incorrect
assumptions and results and he accunes him implicitly of a
plagiarism.
There are 15 references, 2 of which are Soviet, 6 English, and
7 Imerican.
SUBMITTED: July 17, 1957
Card 1/1

22,-58-3-24/38
AUTHOR: Kurshin.,. L. M. (Moscow)
TITLE- Equations for Viree-Layer Q11indrical (Uravneniya
-t-.rekhsloynylch tsilindricheskik-h obclochck)
PERIODICAL. Izvestiya Akademii Naul~ 33-H Otdelenilye Teklm.cheskikh
Nauk P)53, Nr 3. pp (USSR)
ABSTUICT: In calculationq on thrco fa-fer -zhells one urJually neglects
the transverse deformation of the middle IaZ~e-,.. or filler,
and also the bending, StiffTW-:,!:k of the outside layers; this
work presents equatiom~ obtainod ,-,-ithout these -Issumptions.
It is assumed that Pach layor has rurvilinear isotropy. The
o I Ir 171 'y 0. 1, am!
El I " E22 Gj'- 0 (1)
E and G are i:ioduli of elaoti---ity cLnd Ehear. indic-e-S 1
and 2 are for axes alon.- .-encrators and alonrr ar,~s while
3 is, for aIl axis perpendicular tc 1 a n, 1 2 . Eq -(l) is
L
tl(juivaleriL to assiming that a '22 and ~ 12
ar(- absent. For the outer lajers
E33 Gl~ G2~ (2)
Card 1/5 Thes,,, allow one f-c- wriV,. down the intt-,--Irals for

,Z4- 558 -.3-24/38
Equations, for Three-Layer Cyiindrical
the nonlinear elasticity of each layer- These 3ontain 18
product functions of x and y the curvilinear cc.-
ordinates of t-he mean surface., (RefS.2,4)z Uzi-n-S certain
simplifications a system of ncnlinear eauations is obtained
(Equations (3) (4) and (4'),, pp 1,41,2-1110, In tiieoe:
UB I VB WB vH . w 11 (1 e a o t-, i'- Uiiplacoment of moan oturface
of top and bot-tom layersi T 1B - T2B .4 S B T1H .- T2H -, SH
stresses in these layers, R mean radius of three layer shell;
6 thi-lkness of cut,er layers-, 2h thicImess of filler.
E_
modulus of e1astirAty and Poissop!,:; ratio for outer
layers, G13 G 2-, modulli of rigid!ty fc- fillerl~ E 33 modulus
of elastiGity of fil."Ler in radial direction; distributed
radial load, For an ISOtrODiC filler
E,
E33 = E G2 GI 3 =_ G~..~ = 'V(*IrO_=4 1-5-
C I C -
B and 11 ccr;respond ~c- 14pper and 1cwer layers-
Lap', ~,PeT Eq,:,. ant ar- i,, --'ra -.~qu.atione
Card P/5

Equations for Three-Layer Cylindrical Sli~lls
for the outer layers, These equaticvo may br! compared with
those of Wang (Rr-f.,5) and the differen,--~-.: bc~ween them may be
explained by the ns~-.jrlcct by Wang of the bt~ndjn- rigidity of
the outer plate, Ne:~-'eztin- defoo-L)ation of filler
E cA-,) and thcref,-.-, s~r,~E~s flir-C~ion2 ~ and
33
are introduced,
W T L) + V
yy loc Xx 1 R ex Py
to give the equationz for the thLree layer --hr-lls, aith a light
isotropic filler.
2 2
AA(P (1 - -4 )B(\.W VI V; + IV
R
Bh +
G W
(h
Djjw + (p VI (P q) B(h + 'P'T = qa
R Y-X YY Ti "'X X'% X~
Th,:-f?e agree with work of G:,q-~-Iyuk (R;-I-f.~-.) and f,-'-- R =
Card 3/5 EqJ6) Gives f:,.ric -.~quaticns f~-jr threr- -J-ayer Zht,"Is sheets

24.- --)('j'--3-24/3Pj
Equations for Three-Layer Cyii-ndri(_,ai Shello,
comparable with 41-ho_':!:e obf-ained by ReissLer (Ref,l), If the
nonlinear members of En.0) are rie-lectc.-I'l vie have a linear
system of equations fci- the ),.Lnding of a three
layer z-h.211, and tht, '_t-abilil-y equations may be
obtained (Eqs,7, Ii in Zqs,(-) 11 = 00
T0 T0 ~. SC. ~~ 0 th(,n thr! (,cju~il.-J__)n!~ ar;~ 1-omparablc with
IP ~ 20 P
those of Prlasakov (Ref,,,'~), Th-j':~z work -hows that
the equations develc.ped intc~ the. (.wo 3yst.:-ms of bucIrling of
three layer sheets, i.,c. the F;ymmotric and obliquely symmetric
Eqs,(7) above arle r'Iot developed. t(; the, end, The stability
equations also require boundary conditions, but this point is
not pursued, Theoe equatLon~ fcr or~ability may be comparod
with those of R(:issner.) E_' Teit:hia-m t_1 a1ii and St(~in. and
Mayers (Refs,7 B., 9); diff,~.rerico.', are duF, to the taking
account of the bending rig r
~,idity -,f th-~, cuter .1aye s (D / 0
and of the transverse deformal'itjn of 1-1ir fillor (E
Card 4/5

24- 53.- 3-24/38
Equations for Three-Layer Cylindrical Shells,
There are 9 references, 4 of which are. Soviet and 1~ English,
.1
SUBMITTED: November 30, 195?,
Ca.r-d 5/5 1. Cylindrical shalls-Kathematical Analys.15
I

AUITHOR: Kurshin L M. (Mosc StjV/24-58-8-17/37
R~ee-layered
TITlLL,;: On the Stability of/Curved Cylindrical Shells in
Compression (Ob ustoychivosti trelchslo7noy pologoy
tsilindricheskoy obolochki pri szhatii)
PERIODICAL: Jzvostiya Akademil Nauk SSSR, Otdoloniye Tekl-Micheolcil-.1i
Nauk, 1958, Nr 8, PP 97-100 (USSR)
ABSTRACT: The stability proble;.i for sandwich plates and shells is
usually solved in linearized form. By this means
sufficiently simple equations for plates (Ref 1) and
shells (Ref 2) can be written. But it is known that
for simple shells the solution according to normal
linear theory can lead to siEnificant reductions in
the load after loss of stability. Equations for large
displacements have been obtained for sandVich plates
(Ref 3) and shells (Ref 4). In these equations the
bending stranSth of the exterior layers and the normal
stresses in the filler are neGlucted. In the present
paper the equations foi- larL~e displacew,~nt for sandwich
shells are obtained -ahich are free from th-ase omissions.
In deducing the equations it is asF;u:.-,ed that the
Kirchhoff-Love hypothesis is valid for the exterior
Card 1/3 layers of the slriell. It is usual to ne6leeb the normal

Three-layered --30V/24-58-8-17/37
On the Stal)ility of/durved Cylin,~Irical 3110112 in Col:.prossion
stres,.-.-es in the- interior layer (Refs 1, 3, 4) but
stifficiantly simple ;2quation-, can be obtained .,.,ithout
doinj~ Sol D.,-~Lijjiiiit~ only LhaG the (J.isplacements in the
filler ohan~3(,- linearly depth. This assumption for
s&-ndwich shells wa,.-, first intro~!ucel, by Legl,et and
Llopkins (Ref 6) and Yan der NeuL (Ref 7). The
linearized equation2 for bvn"!in, z_uid stability of
sandvii(,.h Shells basLA on this asl~;umption v.;-ere obtoined
by Bi-inGzen (Rof 5). It is asswned L-li(at, in th(~ transverre
direction t-he fillp)- i.-; unjefor-jied. Poisson's
co(,fficientE; for :tll thi-ee layers of the ,--,bell are
assmied equal. It is further asoumed that t'le shell.
is curved and knol.-.,n oi~.,iplified foi.;iiulae a.-r-,e used for
the deformations i,-,rL,,e deflocGions. Tide Uhickness,
of the shell. is ne,,jecLed in compl-trison wish the radius
of curvature. It is Shown that the non-linear behaviour
of the sandwich shell cm be more or less ci-mificant
than for a simple shell. of the thicimes:3, dept;ndirltll
on the tensile strenLth and the dis-place"ient of the
T11 iddle layei,. For swidwich. shells ith a filler of
Card 2/3 avera,e rigidity, Lhe reauction c,,-Lp the sUien th after
L3

Three-layered ';OV/24-58-3-17/37
on the Stability of/Ourved Cylindrical Shells in ComT)ression
loss of stability ii; lesn than, that for simple ohells
of the same thiclaiess. DiscussinG the same problem
on the basis of a model of a compressed sandwich column
with a number of supports having non-linear properties,
Wang Chi-Thq.- and Rao (Ref 10) arrive at the incorrect
conclusion thut Lho tendency to lozro in streri6th of
sandwich shells in comparison with simple shells is
explained by the reduced resistance to displacement
of the middle layer. In fact this comes about due to
the weakened responce of the raiddle layer to normal
stresses. There are 10 references, 3 of which are
Soviet? 6 English and 1 German,
SUBMITTED; kpril 25, 1957
1, Cylindrical shells--Stability 2. Cylindrical sheels--Stresses
3. Mathematics
Card 3/3

j 1A

t,~ ~)_ -s (4 , N)L.,/M -
10); 14(10) PHASE I BOOK EXPLOITATION SOV/2606
VoproBy rascheta elementov aviatsionnykh konstruktsiy; raschet
trekhaloynykh paneley i obolochek. Sbornik statey, No. 1
(Problems in Calculating kircraft Structural Elements; Cal-
culating of Sandwich Panels and Shells. Collection of
Articles, Mb, 1) Moscow, Oborongiz, 1959. 169 p. Errata
slip inserted. 2,600 copies printed.
Ed.: A.Ya. Aleksandrov, Doctor of Technical Sciences, Professor;
Ed. of Publishing House; T.A. Valedinskaya; Tech. Ed.:
V.P. Rozhin.
PURPOSE: This collection of articles i6.intended for engineers
and scientific workers concerned with stress analysis of
aircraft structural elements.
COVERAGE: The articles in this collection discuss problems in
the structural analysis of sandwich panels with light cores,
such as problems of the stability of curved panels, design
of corei> with consideration of transversal tension (tear-off)
and the results of panel-strength tests. In addition, pro-
blems in the calculation of torsion and bending of a

Problems in CalculatIng Aircraft (Cont.) SOV/2606
cylindrical shell reinforced by bulkheads are covered and
the calculation.of unsteady temperatures In an I-beam
element is considered.
TABLE OF CONTENTS:
1. Aleksandrov, A.Ya.j and L.E. Bryukker. Strength Testing
of Sandwich Panels With Foamed Plastic Cores 3
In order to check the methods of analysis worked out,
the strength of sandwich panels with light cores of
foamed plastics In long~tudlnal compression was
Investigated experimentally. Results of the experiments
are compared with the calculated data. Flat and
cylindrical panels with nonreinforced and reinforced
foamed plastics of the FK-type were tested.
2. Aleksandrov, A.Ya. Calculation of the Core of Sandwich
Panels With Consideration of Transversal Tension (Tear-
off) 14
This paper is concerned with systematic methods of
stress analysis of the light core of sandwich panelg
Card 2/7

Problems in Calculating Aircraft (Cont.) sov/26o6
with consideration of shear and transversal stresses
(tear-off) which arise along the surface of the junction
between the outer layers and the core. Calculation
formulas were obtained for plates operating under
longitudinal compression and longitudinal and transverse
bending.
3. Kuxzhin,-L,,M. Large Deflections of a Cylindrical Sandwich
Shell 39
A system of nonlinear equations for ultimate buckling
of cylindrical sandwich shells is obtained by the
variational method. The problem of longitudinal
compression of a cylindrical sandwich panel simply
supported along its four edges is solved according to
the nonlinear theory. The results permit the conclusion
that load reduction following loss of stability is
smaller for sandwich shells with a light core than for
single-layer shells of the same thickness.
4. Kurshin, L.M. Stability Under Compression of a Simply
Supported Cylindrical Sandwich Panel and of a Cylinder
With a Corrugated Core 51
Card 3/7

Problems in Calculating Aircraft (Cont.)
sov/26o6
Stability equations are obtained for a cylindrical
sandwich shell consisting of two thin outer layers and
a corrugated middle layer. The problems of stability
of a curved sandwich panel simply supported along
its four edges and of a cylinder under compression are
solved.
5: Kurshin, L.M. Stability Under Compression of a Curved
Cylindrical Sandwich Panel the Transverse Edges of Which
Are Fastened Vqiile the Longitudinal Edges Are Simply
Supported
This paper analyzes the stability of a cylindrical
sandwich panel with a light isotxIopic core under
uniform longitudinal compression for a case where
the transverse edges are fastened and the longitudinal
edges are simply supported.
6. Kurshin, L.M. On the Calculation of Bending Stiffness of
the Outer Layer of a Curved Sandwich Panel Under Longi-
tudinal Compression
Card 4/7
69
8o

Problems in Calculating Aircraft (Cont.)
sov/26oo'
A formula is obtained for calculating curved sand-
wich panels under longitudinal compression with
consideration of the natural bending stiffness of
the outer layers. The domain Is established in which
the assemption of this btiffness being equal to zero
is applicable.
7. Galkin, S.I. Torsion of an Open Cylindrical Shell Rein-
forbed by Buikheads 85
Torsion of an open cylindrical shell reinforced by
bulkheads is considered in this paper. The solution
is obtained without introduction of additional hypotheses
aside from the general assumptions associated with
representing the operation of an open shell as moment-
less. On the basis of the solution the limits of
applicability are shown of the hypothesis of warping
which has been widely used in problems of calculating
open shells under torsion.
8. Galkin, S.I. Torsion and Bending of a Circular Cylindrical
Shell. Reinforced by Elastic Bulkheads 102
Card 5/7

Problems in Calculating Aircraft (Cont.) SOV/2606
This paper investigated the state of stress of a circular
cylindrical shell which is reinforced by elastic bu2k-
heads and loaded along the edges by an arbitrary system
of axial and tangential forces. Calculation formulas
are obtained which permit calculating all elastic-defor-
mation components for various boundary conditions at
the edges of the shell. The effect of self-balancing
forces on the state of stress of the shell as a function
of the stiffness of the bulkheads was investigated. It
Is shown that the self-balancing stresses do not decay
very rapidly; the zone of their propagation into the
depth of the shell is practically equal to the length of
the contour of the transverse cross section of the shell.
A calculation example is given for a shell under torsion
allowing for elasticity of the bulkheads.
9. Nazarov, N.I., M.S. Povarnitsyn, and Ye. V. Yurlova.
Calculation of Unsteady Temperatures in an I-beam Element 142
This paper presents two methods of calculating the
temperature fields in an I-beam element (representing,
In this particular case, a typical part of a multilongeron
Card 6/7

Problems in Calculating Al:.~craf t (Cont. ) sov/26o6
wing); 1) the method of direct Integration of the
heat-conduction equations, and 2) the method of
elementary equilibrium. Cases of symmetrical and.
unsymmetrical heating of such elements through the
outer flange surfaces are consIdered as well as the
case of different thicknesses of flanges. Solution
of the problem Is given under the assumption that
physical characteristics of the material and the
heat-transfer coefficients do not depend on temperature
variation.
AVAILABLE: Library of Congress
I SIM- 9--
Card 7/7 11-24-59

ALSKSANDROV, A.Ta., prof., doktor tekhn.nauk, red.;. Kjg=TV T..JL_,--
kand.takhn.nauk. red.; MOROZOVA, F.B., izdat.rod.; ORE.'MINA,
V.I., takhn.red.
[Dosigning elements of aircraft structures; analyeia of sandwich
panels and shells) Voprosy rascheta elementov aviatsionnykh
konstruktaii; raschat trekholoinykh panelei i obolochek. Sbornik
statei. Pod red. A.U. Aleksandrova i L.M.1urshina. Moskva#
Gos.izd-vo obor.promyshl. No.2. 1959. 134 p. WRA 14:2)
(Blastic plates and shells)
(Airplanes--Doeign and construction)

S/124/62/000/009/022/026
A0571,A101
AUTHOR: Kurshin, L. M.
TITLE: Greater deflections of a triple-layer cylindrical shell
PSUODI.CAL: Referativnyy zhurnal, Mekhanika, no. 9. 1962, 8, abstract 9V46
(In coilection: "Vopr. rascheta elementov.aviats. konstruktsiy.
no. I", Moscow, Oborongiz, 1959, 39 50)
TEXT: A system of non-linear differential equations was obtained for the
final deflections of triple-layer cylindrical shells with rigid filler and car-
rier layers of the same thickness by means of the variation method. The validity
of the hypothesis by Kirchhoff-Loew was assumed in the deduction of equations for
carrier layers, and the linear law of change of displacement 'In vertical direction
assumed for the filler. The transversal compression of the filler was not cdn-
sidered. The shell was considered to ~6e slanting, and for the deformation at the
final deflections are used the known simplified equations. The material of the
outer layers is uniform and isotropic, the filler transversally isotropic.
Poisson's'ratios of all the three layers were taken as equal. The variation
Card 1/2

S/124/62/000/009/022/026
Greater deflections of a triple-layer cylindrical shell A057/A101
equation of the triple layer shell is written in the form: (3(vl+v2+V
3) + SA +
+ ~QSwdxdy = 0 where V1, V2 = the potential energy of deformation of the upper
and ottom layer respectively, V = potential energy of deformation of the filler,
A = work of outer forces, appli2 to the contour of the triple layer panel, q
= outer pressure, w = deflection. From the variation equation is obtained a
system of five differential equations of equilibrium in displacements and boundary
conditions. Introducing the function rP of stresses and function Y of displace-
ments the author reduces the mentioned system to three differential equations in
variables i,Y, and w. The problem of longitudinal compression of a triple-
layer square cylindric panel, free resting along the found edges was solved ac-
cording to the non-linear theory, and the function of deflection was selected
in the form w = f sin IIX sin An equation was obtained which connects the
a b
value of the compression load and the magnitude of deflection in the middle of
the panel. The conclusion is drawn that the decrease of the load after the loss
of stability is smaller in triple-layer shells with light fillers, than in single-
layer shells of the same thickness.
Abstracter's note: Complete translation] T. 11. Vafsitsyna
Card 2/2

KURSHIN, L. ~L
Compressive strength of a freely supported cylindrical sand-
wich panel and a cylinder with a corrugated filler. Top,rasch.
alemoaviatsokonstr. no.1:51-68 159- (MIRA 13:6)
4 (Elastic plates and shells)

KURSHIN, L.M.
Compressive atrength of a curvilinear cylind-rical sandwich
panel having fastened lateral edggs and freely supported
longitudinal edges* Voperasch.elemeaviatsokonstr. no.1-:69-79
'59- (MIRA 13:6)
(Blastic plates and shells)

MMSHIN, L. M.
Stability of cylindrical sandwich shells beyond the elastic limit.
Voperascheelemeaviats.konstr. no.2:43-51 159-
(KIU 13:6)
(Elastic plates and shells)

AT.RXSANMOV, A.Ye.,; XURSHIN. L.M.
Compression of a roinforced plate# Vop.rasch.elemeaviato.konstr.
no.2:114-124 159- (MIRA 13:6)
(Elastic plates and shells)

SOVII 79-59-3-29/4 5
AUTHORS: Bryukker, L. E. and Kurshin, L. M. (Novosibirsk)
TITLE: The Static Derivation of the Equations of Bending of a
Three-Layered Plate with Rigid Filling (0 vyvode
staticheskim putem uravneniy izgiba trekhsloynykh
plastin s zhestkim zapolnitelem)
PERIODICAL: Izvestiya Akademii nauk SSSR, Otdeleniye telchnicheskikh
nauk, Mekhanika i mashinostroyeniye, 1959, Nr 3,
pp 167-168 (USSR)
ABSTRACT: The outer layers of the plate are assuitted to be isotropic,
and the middle layer orthotropic. Consideration of the
bending moments, shearing forces and shear stresses in
the three layers leads t6 the system of equations
governing the bending of the plate previously derived by
Grigolyuk (Ref 1).
There are 1 figure and 1 Soviet reference
SUBMITTED: February 13, 1959
Card 1/1

PHASE I BOCK EXPLOWTION SOV/4733
Alekeandrov, Avraam Yakovlevich, Leonid Eduardovich Bryukker, Lev Moiseyevich
~unhin, and Aleksandr Favlovich Prusakov
Raschet trekholoynykh paneley (Calculations for Sandwich Panels). Moscow,
Oborongiz, 1960. 270 p. Errata slip inserted. 1,600 copies printed.
General Edo.: A. Ya. Aleksandrov, Doctor of Technical Sciences., Professor,
and L,M. Kurshin, Candidate of Technical Sciences; Ed.: A.A. Goryainov,
Candidate of Technical Sciences; Managing Ed.: A.S. Zaymovskaya, Engineer;
Ed. of Publishing House i P.B. Mrozova; Tech. Ed. i N.A. I)ikhlikova.
PUBPOSE: This book is intended for designers, scientific personnel, and students
in related fields.
COVERACIE: The book contains fo=ulas and diagrams for strength calculation of flat
and curved sandwich panels with various cores (homogeneous foam-plastic type,
ribbed, etc.) under various support conditions, and subjected to various combin-
ations of loads. Data on selecting optimum parameters of panels and on strength
testing of panels are included. The introduction and Chapters 3.1, 12, 13, 15,
27, and 28 were written by A. Ya. Aleksandrov; Chs. 6, 16, 17, 18, 19, 21, 23,
24.0 25, and 26 by L.E. Bryukker; Chs. 2, 3, 5, 8, 9, 10, 14, 20, part of Ch. 4
carj~V6

Calculations for Sandwich Panels SOV/4733
and part of Ch. 1 (Sections 1.5, 1.7, 1.8.2, 1.10, 1.11,and 1.12) by L.M. Kurshin;
and Chs- 7, 22 of Ch. 4, and part of Ch. 1 (Sects. 1.1, 1.2., 1-3, 1.4o 1.6.*
1.8.1, 1.9, 1.13~ baby A.P. Prusakov. Materials supplied by N.I. Hazarov are used
in Beet. 16.2 of Ch. 16, The authors thank S.F. Trof1move for her assistance.
There are 136 references: 32 Soviet, 101 English, and 3 Ge
TABLE OF CONTEMS:
Conventional Symbols 3
Introduction 7
PAIRT I. STABIL3!rY OF SANDWICH PANELS
Ch. 1. Stability of Sandwich Plates With a Light [Low-Rigidy)
TAotropic Core 13
Ch. 2. Stability of Sandwich Plates With a Light Orthotropic Core 30
Ch. 3. Stability of Sandwich Plates With Rigid Isotropic Core 36
Ch. 4. Stability of Sandwich Plates With Rigid Orthotropic Core
and Orthotropic External Layers 44
Card~:l

KUZNETSOV, A,,P,, Olovasiblrsk),- KURSHIII) L.M. (Novosibirsk)
Solutiono bei;4d an the theory of strengthening to certain
problma-c&,~,the ~stdbility of plates and shells in conditions
of creep. ', "-,-n'O'.4/A449 N-D '60. (MIRA 14-7)
(t,..Iastio plates and shells)
(Creep of materials)

t t~_,Jhj 4,i (4-
BOROVSKIY, P. V. PHASE I BOOK EXPLOITATION SO V16 206
Konferentsiya po teorli plastin I obolochek. Kazan', ig6o.
Trudy Konforontaii po teorii plastin i'oboloch6k.' 24-2b okty'abrva
1960. (Transa6tions of,the Conference.on the Theory of;Plates
and Sholls Hold In Kazan', 24 to 29 October 1960 Kazan'. P'l
[Izd-vo Kazanskogo gosizdarstvennogo univorsitetai-1961. 4
1000 copies printed.
Sponsoring Agency: Akademiya nauk SSSR Kazanskiy filial. Kazanakiy
gosudarstvonnyy univeraitatlim. V. 1: Ullyanova-Lenina.
Editorial Board: Kh. .M. Mushtarl, Editor; F. S. Isianbayeva, Secretary;
N. A. Alumyao, V. V. Bolotin, A. S. Vollmir, N.iS. Clanlyev,
A. L. Golidonveyzen N. A. Kilichavskiy, M.~ S. Kornlchin~ .
A I Luxilyq, 0. N. Savin, A. V. Sachonkov,' 7 V. SvirBkiy,
R: G: Surkin, and A. P. Filippov. Ed.: V. 1: Aleksagi3a;*
Tech. Ed.-:- Yu. P. Semenov.
PURPOSE: The collection of artl6lee Is Intended'for edientlata'and
engineers ~ho are Interested in the analysis of strength and
stability of-aholla.
Card 1/14

Transactions of the Conference Nont.) SOv/6206
COVERAGE: The book is a collection of articles delivered at the
Conference on Plates and Shella hold in Kazanl from 24 to 29
October 1960. The articles deal with the mathcmatfoal theory
of platos and shells and its application to the solution, in
both linear and nonlinear formulations, of. problpma ct bending,
static and dynamic stability, aad vil;ration of rogulf-r!.and
sandwich plates and shellb 6f Virious shapoa under varioui
loadings in-the elastic and plastic regions. Andlya5z,io made
of the behavior of plates and shells in fluids,# and the effect
of croep of the material'is considereO. A:humbo~ of papers
discuss problems associated.with the devolopmont of effective
mathematical.-mothods-for..solving problems In the theory of-shelli.
Some of the reports propose algorithms for-the solution of problems
with'the aid of'olectronia computers. A total of,one hundredi
reports and notes were presented and discussed during the con-
ference. The reports are arranged alphabetically (Russian) by
the author's name.
Card 2/14

2,
Traneac,vions of (Cont.) SOVA20�
Kordauhznko, A, B. SYLation o,, Dy
Problem for
Soctor-Shapod avid Tapttval Plat*3 186
Kox-iishin, M. S,, V,-Id 13. A. KarIImbv4. M6thbd for"
Solution Of SYgtons of floallii.mr Finite -Difference
Equations of Banding of Flnta3 191
Korniahin, M. S., and E. N. Saflullina. Applioailon of
tho Method of Succassiva Approximations to tho
Invostigation of Large Deflections of a Circular
Plate and an Extremely ShIllow Spherical Segment, 199
Kosukhin, A. K. On the Problem of Analysis of Thin-
Walled Thrae-DImensiora.1 Structures as Systems
of Joined Plates 2o.4
Kurshin, L. ~. Stability of Wing Panels Under
Unsteady Aerodynamic Heating 209
Lepiks Yu. R. Large Deflections of Circular Rigid-
Plastic Plates Clamped by Their Circumference 215
Card 8/14

S/124/62/ooo/oo9/o26/o26
A057/A101
AUTHOR: Kurshin, L. M.
TITLE: Stability of the panel of a wing at non-stationary aerodynamic
heating
PERIODICAL: Referativnyy zhurnal, Mekhanika, no. 9, 1962, 49, abstract 9V371
("Tr. Konferentsii po teorii plastin I obolochek, 1960", Kazan',
1961, 209 - 214)
TEYT: It is assumed that the initial temperature is equal in all points.
The heating occurs because of the heat exchange with the external me2cx/k,
it will 1-..e accelerated. A rod will be in a critical atate whell tile
disturbance applied gives rise to a non-retarded, disturbed motion, whereas
any disturbance applied somewhat earlier will cause a retarded, disturbed
motion. This critical creep deformation is giver, by
1 61
Pk = 2o( En . This definition differs from that by Yu. N. Rabotnov et
al. (Prikl. matem. i mekh. no. ~ (1957); The Theory of Creep and its
Applications, Plasticity, 1960) in the character of forced motion and in the
formulation of the criterion of stability. The value of pk calculated here
is twice as high as that calculated by Rabotnov. The appl i3ation of the
foregoing to the stability problem of a plate is discussed in detail.
Card 2/3

1 28726
9/020/61/140/003/005/020
Stability of rods and plates ... B104/B125
There are 2 referenoesi I Soviet and i non-Soviet.
PRESENTEDi May 15, 1961, by Yu. N. Rabotnov, Academician
SUBMITTED% May 10, 1961
Card 3/3

ALPMANDROV, Avraam Yakovlevich., prof.; BORODINI Mikhail Yakavlevich;
PAVLOV, Viktor Vasillyevich; KURSM14j L & -kand. tekhn.nauk,
_, t
red.; GORTSUYEVAp N.A... red.*Izd a; NOVIK, A.Ya., tekhn. red.
(Elements with foamed plastic filters] Konstruktsii s zapolnite-
liami iz penoplastov. Pod obshchei red. A.IA.Aleksandrova.
Moskva, Oborongiz, 1962. 186 p. NRA 15:7)
(Plastic foams) (Sandwich construction)

7 3
3/207/62/000/001/014/018
B104/B108
AUTHOR: Kurshin,_E. 1.
_L__C~qvosibirsk)
TITLE: The stability of plates in creep conditions
PERIODICAL: Zhurnal prikladnoy mekhaniki i tekhnicheskoy fiziki, no. 1,
1962, 93 - 101
TEXT: The deflections caused by perturbations occurring at different
moments are examined on a plate subjected to uniform stress. The equation
of state for the plate in creep conditions is i g(pi,cri)ai (1.1). The
relations
3
PiJ=Yg(P,'d,)a1J*' pu = P-1i - ~G- 01) (1.2)
are presumed between the components bij of the tensor of creep deformation
rate and the stress deviator a* . Presuming that in small deflections
ij
stress and deformation across the plate change only little, Eqs. (1.1) and
Card 1/3

The Btability of plates ...
(1.2) are linearized:
S/207/62/000/001/014/018
B104/BIOB
6pi a6pi + g(b + 1) &;j
. tj
E 2g6cj* + -152 (abpj -1 gb6cj)
2 ai
a = a (ci, pi) c, A b = b (c., p,)
OP, g d3i
The equation of the perturbed motion is derived in the form
E).-jt-v-L [L' (AA--!AA)(w-w-)-Lj(-Aw]-
) Zi 1, 4h' (3.8), where
3 E it + -%, 2-) AA (w 0
T ( J1.
d2 2 a2 8 0
2bL --2:- 1 , D Eh w - deflection, w -
11 ax2 12 ax ay 22 a 2 �
perturbation (initial deflections- The initial conditionjor this equation
is
Card 2/3 2ho, Aw* 0 (3-0).

S/207/62/000/001/014/018
The stability of plates ... B104/B108
Wis.= w when t - t*, Othe instant of time at which the perturbation is
applied. From these equations three more can be derived for ww, 0*, and
V*~of the perturbed motion at time t - t*. In order to determine the limit
of stability of the plate, the condition Vt. 0 which satisfies the perturbed
motion must be included in these equations. There are 2 figures and 2
Soviet references.
SUBMITTED: August, 1961
Card 3/3

S/207/62/000/003/01 1/0 16
1028/1228
AUTHOR: Kuznetzov, A. P. and Kurshin, L. M. (Novosibirsk)
TITLE: Stability of circular cylindrical shells undcr.conditions of creep
PERIODICAL: Zhurnal prikladnoy mcklianiki i tekhnicheskoy fiziki, no. 3, 1962, 66-72
TEXT: The problem or stability under conditions of creep is treated on the basis of an analysis of the acccle-
rations of disturbed motions. Ths state of the cylindrical shell is considered as unstable if the velocity of (he
disturbcd motion produced at a given moment under the influctlec ofa disturbance increaic~; %kith, tittle. The
equations determining the velocity and acceleration at the initial moment of thedisturbed motion arctsta-
blished. and the equations of stability obtained from them. These equations are solved for the case of longi-
tudinal compression. There are 2 figures.
SUBMITTED: November 28, 1961
Card 1/1

I 7~ 9
S 20Y62~000/005/009/012
B125 B10
A - Kurshin.,_.L. M. (Novosibirsk)
AIMOR:
TITLE: Solution to stability problems of plates in the presence of
creep according to the quasistationary theory
PERIODICAL: Zhurnal prikladnoy mekhaniki i tokhnicheskoy fizikil no- 51
1962, 154-158
TEXT: The initial oonditione for the disturbed motion of a rod if r - 0
(x is the deflection of the rod) are generalized for plates. From the
linearized equation of state
formula Hn
p* Y (p) dp
..P-. V. (1.6)
Card 1/4

Solution to stability problems ...
s/2o7/62/000/005/009/012
B125/B102
follows for a small hinged rod. This corresponds to a disturbed motion
under quasistationary conditions. The stability limits (kp - a)
correspond to the minimum of the function
ek(P-1") k-
(P) P-EI ) -
a is the stress, p is the creep deformation, E is the total deformationt
6p and 6a are small increments of p and 6 added to the thickness of the
rod; I is the moment of inertia of the cross section. At the initial
instant of time t w t*1 p = p and (6p) P-p 6p he creep deformation
is 6p bE %'*IF. with 6:-: ZW W is the initial deflection. For
a xx*
plates the equation of state with allowance for creep is Si - 9(piv Ci)ai-
The relations (3/2)g(p,, a,)doo and p,j - Eij - 600/2G ~'old between
ij
the components (1 00 of the stress deviator and the components of the tensor
ij
of the rates of creep deformation. When such a plate is subject to a
certain disturbance the creep deformation bp ace 6p* arises. After
i ij ii
Card 2/4

5/207j62/000/005/009/012
Solution to stability problems B125/BI02
h
integration over the thickness (S 6p 4( zdz) the equation p, - -(2/3)OAL~*M"/E
-h 3
(2.12) follows with M* --(3/4)DPAcd.' D (8/9)Eh
a11a2/ax2 + 2a 12a2/dxay + a22a2/a/ h is ~he thickness of the plate.
is its deflection for p P** These conditions together with
Cis 3D (w.0 +
2 (2.
G,* OD (w,,V* + -1 w= 0) 13)
D
and
Gjxxs + + 211,1= - 5DAAtv*
(2.15~
determine the motion at which the time derivative of the deflection
vanishes for a certain value of pi. The relaxation caused by the initial
creep is taken into account by the factor P. Where cylindrical stability
Card 3/4

3/207/62/000/005/009/012
Solution to stability problems ... B125/B102
is lost by the compression of a hinged plate, p* - (I - 6o)aOi/o.En. For
a hinged square plate (compressed in two directions by equal forces)
P" 0 - 00)3aa,/do(i + 17,n):-:. For a long hinged plate homogeneously
i
loaded in a longitudinal direction,
S~ 3OL::i
Pt (i-31 -3.)1;.
0
- ai/(,e where ae is the intensity of stress associated with loss of
elastic stabil ity.
SUBMITTED:
May 26, 1962
Card 4/4

KURSHIN, L.M., kand.takhn.nauk (Novosibirsk)
Survey of works on the design of sandwich plates and shells.
RaBoh.prostr.konstr. no.7:163-192 162. (MIRA 15W
(Sandwich construction)

1111-a
AID Nr. 967-17 15 May
DERIVATION OF VARIATIONAL EQUATIONS FOR SHALLOW CYLINDRICAL
SHELL WITH REGARD TO THERMAL STRESSES (USSR;
Kurshin, I, M. Izvestiya vysshikh uchebnykh zavedeniy. Aviatsionnaya
le'khnika,no. 1, 1063, 151-156. S/147/63/000/001/018/020
The derivation of variational equations fo~ the relation between the force and
deflection of a heated thin shallow cylindrical shell in the range of finite de-
flections is presented. The initial equations are comprised of 1) expressions
in the finite- deflection theory of shallow shells describing the basic relation-
ships between the normal forces (acting In the middle surface of the shell)
and moments on one hand and displacement components on the other hand,
and 2) the equilibrium equation. The thermal stresses are taken into account
in accordance with Neumann's ~ypothesie and with the assumption of preserva-
tion of the straightness of normals to the middle surface. Stability equations
are obtained by.in,vestigating the instant of occurrence of a nonunique solution
of the problem, J. e. , when the difference between two successive stateB of
Card 1/2

AID Nr 967-1T 15 may
DERIVATION OF VARIATIONAL EQUATIONS [Cont,d) B/147/63/000/001/018/020
e~u'__1libr1'u_m is infinitely small, -The variational equations are.derived by ap-
plying the principle of virtual displacements and by introducing two potential-
energy functions, one in terms of forces and the other in terms of displace-
ments. These equations are reduced to a sipgle equation in which the varia-
tions in deflections and forces satisfy the geometric and static boundary con-
ditions, respectively. Formulation of the conoitions for buckling is discussed
from the energy point of view, "d a c.orresponding equation of stability is
given. JVK)
Card 2/2

VOLIMIR, Arnolld Stiteyevich. Prinimall uchastiye: TRAPEZIN, I.I.; -
AUKHIN -M,; SNITKO, I.K., red.; BRUDNO, K.F., tekhn. red.
,__4,
(Stability of 61astic systems] Ustoichivost' prugikh sistem.
Moskva, Fizmatdis, 1963. 879 p. (MIRA 16:7)
(Elastic bolids)

V(4) JD/E9
ACCESSION NR-. AR4045241 S/0124/64/000/007/VO35/VO36
SOURCE: Ref. zh. Mckhanika, Alw. 7V268
AUTHOR. KurshinLM
TITLE. OAC possible approach to the problem of the stability of rods under creep
conditions
CITED SOURCE: Sb. Polzuchest'IdUtetn.' prochaost'. Novosibirsk, Sib. old. AN SSSRI
TOPIC TAGS:- rod, stability, rod creep, bending strength, compressed rod, hinge supported
rod
TRANSLATIOW As the source of perturbation causing the bending of a centrally compressed
rod, the author considers a spread In the values of the creep constant of. the material
throughout the rod. It is assumed that at each point In the rod the following equation
describing the state Is valid:
TIE
wherefts, the stress, 6 is the complete deformation; p is the creep deforniatton; and A,Oke.,
1/2

L 17654-65
ACCESSION NR-.--AR4045241
nare variable parameters. "Assurning,that the values p,d, A, n differ only to a. small
degree along the rod section the author linearizes Eq. I by variation and, after sub-
stituting the varible p for the variable t (time), he accepts the initial condition Wp)p 0
- 0 and obtains the Integral of the linear equation in the form
at-da/5-P-'f 1(44q) 6a + 6AIA
Here p, ~', A, n, andKare the mean values of the corresponding magnitudes;S pl-,,are
small increments; andCA, Sn, S -, are random co-ordf nate functions. At this point the
author applies the hypothesis of plane sections, and the buckling of a hinge-supported rod
is sought In the form 4j.;21 V(p) sin (r(xll-) , where /Js the length of the rod. After Ultegratiol-L
fol. 'x by the Gaterkin mcthod,'l,(p) is found by quadratura formulae. The random functions
A, n, i:A , found in the expression for 1r (p), must be obtained through the statistical
processing of a large number of tensile strength tests under creep conditions. Attention
is callcd to the importance of studying the creep parameter spread as a function of the
c.lmensions of the samples tested. As a stability criterion, it is suggested that a buckting
%alue be given, at, which the serviceability of a rod may be considered to be practically
o.N1--austed, and that the critical time be determined by using, the expression found forlclp).
B. M. Broude.
'*UB CODE; ME; AS
i ENCL: 00
Cord2/2

ACCESSION NR: AT4010249 S/3052/63/000/003/0211/0219
AUTHOR; Kurshin, L. M. (Novosibir6k)
TITLE: i,h"e-,rm'~a"l,-s,t"a"b,illty of cylindrical shells equipped with cooled didphragms
SOURCE: AN Mu'SSR Institut mekhaniki. Teployy*ye napryazhentya v elementakh
konstruktsiy; nauchnoye soveshchanlye. Doklady*, no. 3, 1963, 211-219
TOPIC TAGS; shell, cylindrical shell, thermal stability, shell thermal stability,
cylindrical shell thermal stability, diaphragm. cooled diaphragm, shell thermal
stability diaphragm dependence, shell elastic limit
ABSTRACT: Several Investigations dealing with the question of the thermal stabi-
lity of cylindrical shells equipped with cooling diaphragms have appeared In the
literature during recent years. it Is known that heating of a cylindrical shell.
with a frame restraining its thermal expansion produces circumferential compres-
sion stresses which may result In the loss of Its stability. The thermal stabil-
ity of clamped cylindrical shells was investigated by W. Zuk. but the results ob-
tained by W. Zuk cannot be accepted for long shells, because of the rough approxi-
mation of circumferential and bending stresses; his value for the coefficient K
differs substantially from the value of 6.41 obtained in the present paper. The
attempt by Jones to improve the results of Zuk's analysis was not successful,
Card 1/3

ACCESSION NR: AT4oiO249
since his value for K was 12-7. The present paper presents a solution for the
problem of the thermal stability of circular cylindrical shells with tubular
diaphragms (for circulation of the cooling liquid.) The author analyzes a semi-
Infinite Sihell, since the tensions resulting In the loss of shell stability at-
tenuate with distance from the diaphragm, including cases In which the shell
either is clamped or rests freely on the diaphragm. In the solution of the prob-
lem, use is made of stability equations which take into consideration the state
of the shell preceding the loss of stability. The critical temperature during
heating of a shell with a diaphragm Is given by:
k h
(i _V)
where R is the radius of curvature, -(- the coefficient of linear expansion,
T - temperature, and K - 6.41 for a clamped shell and 12.2 for a shell resting on
the hinge. The critical value of the temperature as found by formula (1) is
sufficiently large so that the solution of problems Involving performance of the
material beyond the elastic limit has no particular meaning. The reason for this
is that in the performance of a shell material in the area of maximum stress, as
encountered beyond the elastic limit, the rigidity of the frame itself Is de-
creasing and the shell becomes more pliable. To prove the above statemento a
Card 2/3

ACCESSION NR: ATW0249
special experiment was conducted to determine the actual behavior of material
under conditions beyond the elastic limit. For a clamped shell, the calculated
value of the critical temperature (according to formula 1) was 440C. Actually,
no loss of stability was observed at 620C. "The author would like to thank
Engineers N. G. Chet-ny*shev and V. N. Nikonova for helping with the calculations.
and Engineer A. G. Zagorskly for doing the experimental work." Orig. art. has: 26
formulas.
ASSOCIATION: Institut mekhaniki AN UkrSSR (Institute of Mechanics, AN UkrSSR)
SUBMITTED: 00 DATE ACQ: 17Jun63 ENCL: 00
SUB CODE: AP NO REF SOV: 000 OTHER: 003
Cord 313

11MIMMOV, A.P.; MIIIN, L.M.; LIPOVTSLV, YU.V. (Novosibirsk)
"On the solution of the problem of creep buckling of shell on the basis of
geometrically non-linear theory".
report presented at the 2nd All-Union Congress on Theoretical and AD lied
Mechanics, Moscow) 29 Jan - 5 Feb 64.

GRIGOLYTK, E.I.1 XURSKIIII, L. M. ;FILISKINSKY, L.A.(I'Ovosibirsk)
ON a method of solving biperiodical prcIblems of e-lastic-4ty".
report prescnted at the 2nd All-Union- Congroso on Theoretical and Applied
1~
lechanics, Moscow, 29 Jan - 5 Feb 6h.

ACCESSION NRs AP4026955 S/0256/64/004/001/0060/0068
AUTHORSt Oalkinat A. P. (Novosibirek); Kurshin, Le H, (Nmaibirsk)j Styftsyuks
V. 1. (Novosibirsk)
TITLE: Stability of a heated fasbened plate under displacement
SOUXE: Inzhonerny*y zhurnal, ve h. no* 1, 1964, 60-68
TOPIC TAGS: stability,, heated platej, fastened plate, square plate, plane fora of
equilibrium, curved form of equilibrium, temperature stress, bifurcation deflection!
ABSTWiCT.- The authors consider the case of instability of a curved form'of
equilibrium (caused by preliminary heating) in contrast to the usual f oz-Vadation
of plate stability problems involving instability of the plane form of equilibrium
for a heated square plate with fastened contours under displacement# Graphical
comparisons are made between experimental data and tho numerical results derived
in the paper. Orig. art-* hass 6 figures and 33. forailan,
ASMIATION t now
Card 1/2

ACC=:roN M 2 AP40.2695.5
SuBxr~-
'tat 19Aug62 . . DATE AcQ, uApr64
SUB CODBI AP - . . NOR& WVS 0044
d
.-.- .
EXCL 1 0()
OTMRI boo li
Card 2/2

GRIGOLYIP., MOM, L.M. ; PRISPKIN, V.I,.
Peffincirant or the hypothesIs of plane reflection. Dokl. All SSSR
L
155 no.l-.65-66 Mr 164. (MIRA 17:4)
1. Irctitut gidromeRhaniki Sibirskogo otdelliniya AN MO.
I
~. Chlon-korrespoildent All SSSR (for GrIgolywk).

GRIGOLYUK, E.I. (Novosibirsk); 'YTIRSHIN) L.1'.1. (Novosibirsk);
FILISHTINSKIY, L.A. (Novosibirsk)
Method for solving doubly periodic problfms in the theory
of elasticity. Prikl. mekh. 1 no.1:22-31 10.
(KIRA 18: 5)
1. Sibirskiy nauclino-issledo-, tel'skiy Institut.

L 6481q_6,~
ACOEMON NR. AT5017588 EWA(h)/ET9(m) IJP(c) UR/(Qik~ /%280/0267
HtIW
O~IJDAIWIEMIGS Imovosibirilk)
AUMORSt Kuznatacv A. ffovoeibirak)l Kurshint L, M,
TITLEI On calculating the stability of ahelle in conditions of creak ~LOOOTding to
:the theory-of aging
Vseaoyurz"a konferentsiya, pa problomam untoychivasti Y atroitellnOY
mekhamikep Koacowj 1963. Problemy ustayohivosti Y stroitellnoy mekhani!ce (Problem J.
of stability in atruotural mechanics)i trudy konferentsii. Roacoir, Str~Vizdat, 1965,1
260-267
'Topic TAM creep c1taraoteristic, cylindrical shall, shall structure stabilityt
'ehell theoryo shall structure buckling,/ D16T pllo:r
1-6
'ABSTRAM The-authore conducted experimental atudiae- an the stability of thin
cylindrical shells under longitudinal, compression and under creejP-~(mditiona. The
'pxperiments were performed -on specimens cut from tubea of Juminum alloy D16T.
Brief commnts:on the test ~hs
observations includet on I Fur j4 durin6 loadinK11
no appreciable dents appeared~for a long period of time. ortly bdrorethe failure
of the ohall a dent appeared on its eurfacel the dent developed until % "snap"
9cm-redl signifying the virtual destruction of the shall.. The time lapse-between
Initial loading and the failure snapping is from 10 to 19% greater than the time
I Card 1/3-.

L 6481o-6,5
ACCEaSIO11 Mt: AT5017588
C7
'lapse to the moment of dent appearance. The loss of stability by- this type of
Tailure occurafor both subcri~icai and,suparoritica'I. loadingl, hence the ensuing
OMP t for geometric nonlinearity. Some
,treatment of ahell stability att to to accoun
:recent approaches to the problem are revieved. The authors' own treaimenl~ involves
ithe hypothecis of aging. Solutioa.ia,achieved on the basis of equations.deacribing
,the behavior of the shell under, creep. conditions. L dual-layered shell model, used
Tor simylicity, has an oute.- layer of thickness and an interlayer of length 2h.
War displacements are givan*by the'equationa
U U (h
2 T_
_Ii6 the -addle 6urface of the shell, and ir
where ul v, and w are referred Ldices "B"
iand 1111 refer to the upper and lower.bwing layers, Deformation of ahell. layers ici
given by 1.. I- - - -- . ..4 .
~6 Ili's ell + (tr +.: I -) I
1,2.
ere
12 Wl
2
+ -U*;
2
+ W2 -
2
Card R___

L 6481o-65,
;ACCESSION NRg LT50IT588
CM
U + v
____2 ~uy r
.Other equations describe creep deformations and streaa componentaf rorces, and.
and a solution i's demonstrated for a particular parameter setting. Con-
oluaions obtained from the. calculations are in agreement with experimental data and
with earlier work*' Orig. art, hast 21 equations and I figure.
AS-SOCIATIONt Taesoyummy& hnfarentgiya po problemam ustoychivooti v stroiteltnoy
mekhanike scow (All-Union Conferenoe on Problems of Stability in StruGtural
:Vechan
ics
.7TBMM7n: 42FOO M
MCM 00 BUB Co 10
NO M SOVI 001 OTHMt 001
. .........

t 60-02-3~65
rf XM b
~R/6026/65/163/00* 1/0046'/004-q"--------
iACCESSIO-N, INR: AP5018070
AUTHOR- Kurshin, L.M. J3
i TITLE: Formulatioa of the problem of~~slf'bulging during creep
;:SOURCE.- AN SSSIR. Doklady, v. 163, no, 1, 1965, 46-49
TOPIC TAGS; shQ11 bulging, shen creep,.creep theory, elasticity theo
ABSTRACT: One of ft previous formulations for determining stabill uring c
_Kqep~deals
writh the bulging of a rod, plate, or shell under, a load in the presence n N-atialir
regularities (see, e. g, , r. K. Odq'u1st, J. Appl. Mechr, 23, no. 3, 1956; V. L Rozenblrum
illnzh, sbm". , 18, 1954 - for the case of rods; N. J. 11off, %V. E. Jahsman, W. Nachbarj
J. Aero Space Sat. , 26,* no. 10,, 1959; A. S. VoUrnir'. Ustoychivostl upruglidi sintem, M.
1963 - for the case of sheLia). The present paper investigates hvo new formulations of shell
bulging daring creap by developing the initial Irregularities by means of equations which
talw into account geometrical nonlinear relationships. The equations are derived under the
assumpUon that Ube stresses and deformations within. the sholl during creep differ only
littlo from the stresses and deformationsof the basic momentleas atate. ThIspermitathe
'linearization of the pbysica.1- -ralaticinshipi relative to the basic state; in both alternatives
i the determination of the sag and. stresses In the flat shell Is carried out via a system of two
Card

L 37128-66 alT (d.11ANT (w) /ETqP ?) LJ !, I G')
ACC NR: AT6011753 SOURCE CODE: UR/0000/65/000/000/0106/0157
AUTHOR: Kursliln, L. Al. (Doctor of technical sciences)
ORG! None
TITLE- Equations for sloping and non-sloping sandwIch-tvpc sl!elk
SOURCE: Raschety elernentov aviatsionnykit konstr.iktiiy, vyl). 3: Treldisloynyye pancli I
obolocliki (Calculation of aircraft construction cleniuntri, no. 3-. 'Sandvich panels and
shells). Moscow, Izd-vo Mashinostroyeniye, .1965, 106-157
TOPIC TAGS: shell structure, shell theory, sandwich structure
ABSTRACT: This paper reviews (love lopinents in saidw(ch -,diell 0wory. Riii;hvich shelk
with light filler are considered. A chiracteristi6*1eaturk, of Is, the pwisibilft~y
of disregarding the rigidity of Uic filler In a direction parallel to the external layer,,3. The
longitudinal forces and moments in a structure with Pght fillcr are cornpensated by the
outer layers which act as carrying or support layers. This lei it possible to bar-oduce
,;; iurallel to the ceritor surt- r-i
an assumption concerning Uic absence In the filler of 8treysq,9?1'~
of the sholl. The Introduction of this aRsuniption makc-13 ff-p-ossiblf- to ol)L-iln integrals of
a three-dimensional problem of elasticity for the center layer. By skibordinating these
Card 1/ 2 UDC 629.13.011. 1:62-41. 539.4

L 37128-66
ACC NR: AT6011753
integrals to the conditions of coupling to t titer lavers (which are regarded iu; thin
elastic shells), two-dimensional equationsVor the sandwich shell are obtained. Li these
equations allowance is made foiT-tfic ;~-ro-Trk-of the filler on deflection and transverse deform-
ations. The obtitined equations are Integrated as a function of houndiry and load conditiona
A generalization is then made of certain equations, derived earlier by the sanic author,
to include the more general situations of sloping sandwich shells with rigid filler of Sym-
metrical and unsymmetrical structure. Within the filler a linear law for the change of the
tangential displacements is assigned. Through the Introduction of functions of the same
type as in the equations for light-filled shells, the number of equations Is reduced. An
analysis of special boundary conditions Is provided. Shells of unsymmetrical structure are
considered. The equations are transformed without the Introduction of the assumption of
the equaRty of the Poisson factors of the layers. Some estimations of this assumption: are
presented. Orig. art. has; 201 formulas,
SUB CODE: 13 SU13M DATE- 25Oct65 / ORIG REF: 032 / OTH REF: 012
Card 2/2 af

L 37 0-66 EWT(d)/EWT(m)/WF(v)/8U(V)/Ee(k) IJP(c) V&/NqJT/C[D/Rjj
ACC NR: AT6011754 SOURCE CODE: UR/0000/65/000/000/0168/0169
AUTHOR: Kurshin, L. Al. (Doctor of technical sciences)
ORG: None /_31
I/ ~ t4 .I
TITLE: Stability of cylindrical sandwich shells under compression, pressure and thV
combined effect of pressure and-657m-pression
SOURCE: Raschety elementov aviatsionnykh konstruktsiy, vyp. 3: Trekhslo e panell I
ynyy
obolochki (Calculating of aircraft construction elements, no. 3: Sandwich panels and
shells). Moscow, lzd-vo Mashinostroyeniye, 1965, 158-169
TOPIC TAGS: shell structure, sandwich structure, shell structure stability, shell
deformation, cylindric shell
ABSTRACT: In this paper the solutions of the stability problems are based on the equations
of the theory of both curved and uncurved shells. The solutions are obtained with consider-
ation of the moment work of the outer layers. Also used Is a case of lost shell stability
under compression with the formation of long waves. A solution Is derived which resem:-
bles Southwell's solutiop '.)r single-layer shells. The author also obtaint3 solutions for
shells under external pressure and under the joint effect of pressure and compression.
Card 1/2 UDC 629. 13. 011. 1:62-43:539. 4

L 3MO-M
ACC NR: AT6011754
3
Taking part in the computational part of this work were Engineer L. P. Dentsova and pro-
grammers . L. F. Ivannikova and V. P. Karyakin. Orig. art. has: 16 figures iR IS form-
ulas.
SUB CODE: 13 / SUBM DATE: 250ct66 /,,ORIG REF: 002 OTH REF: 003
Card 2/2

37126-66
ACC NR: AT6011755 SOURCE CODE: IJR/0000/(35/000/000/0170/0168
AUTHOR. Kurshin, L. M. (Doctor of technical Heiences); Lamper,--R.. Yo.; lJpovtsev,
Yu. V.
ORG: None
V +
TITLE: Calculating the stability of sandwich panels beyond the limit of proportionaWy
SOURCE: Raschety elementov aviatsiorutykh konstruh-'65iy, vyp. 3- Trekhsloynyye panell I
obolocliki (Calculation of aircraft construction elements, no. 3-. Stn(i'A0h pftreli and
shells). Moscow, Izd-vo Mashinostroyeniye, 1965, 170-188
TOPIC TAGS: shell structure stability, shell structure, sandwich structiire, shell
deformation
ABSTRACT, The authors study the possibility of an approxhivite ml-ulation ol*,~iqndivieh
layers for stability beyond the limit of proportionality by Ineans of silllp~e forlnul~'s in
a manny
al as to reduce the problem of the calculation it) the determination of a oroical
stress,1 stuning elastic working of the material and to a certain of thi8 vafli;p
to Troke st-11 ilify CL
Into a rated stress. With this kind of approach It becomes possible '')1 11.
culations for sandwich structures beyond the limit of proportionality even In those ra(,es
for which solutions are available only within the liniltn of proportionality. Jri order
Card 1/ 2 - UDC629.13.011.1:62-41:539.4

L 37126-66
ACC NR: AT6011755
the problem of the selectimi rf qn approximate formula, a soltition Is ,ften to two prohler.,,s
of sandwich panels beyond the limit of proportionality- for a hinge-fastened panel 1~,!Ider
~T2TpEesslqn and for a long panel with deflection, The eqwttlons employed werp obtatio,d
elsewhere Gy- the authors, on the assumption that plastic deformation takes pl"I ce only
.in the support layers, whereas the fillerworks within the limits of elasticity. Atthesarne ti-me,
~on the basis of the conception of a continuing load It is postulated that the stalAlity loss L-I-
not accompanied by unloading and that the plastic deformation Is everywhere active. Thl,
external layers of the panel are considered to be non-moment, w16 the filler working only
on the deflection and not taking on normal stresses. Certain variations of the approxtmata
formulas for the determinatJon of the critical stresses are also considered. A comparison.
Is made between experimental data and the results of a calculation of critical stresses ac-
cording to an approximate method outlined In the paper. Fquations are presented for cal-
culating the stability of sandwich panels in the event that the stresses in the filler are out-
side the limit of proportionality. Orig. art. luis; 20 figures and 26 formulas.
SUB CODE: 13 SU13M DATE: 2SOct65 ORIG REP: 006 OT11 REP: 001
Card 2/2 af

,
L 04110-67 E74P(k)/174T(d)/FWT(M)/EgP(W)/"-;WPkv) IJP(c)
ACC N" AR6032361 SOURCE CODE., . VR/0264/66/000/007/AO08/AO09
AUTHOR: Kurshin,,_L. _ML;',Denisova, L. P.
TITLE: Stability of triple-layer cylindrical shells -tinder torsion
4-k
SOURCE: Ref. zh. Vozdushnyy transport, Abs. 7A59
RE F SOURCE: Sb. Raschety elementov aviats, konstruktsii, Vyp. 4. M.
Mashinostroyeniye, 1965, 152-156
TOPIC TAGS: shell structure, cylindric shell structure, asymmetric shell
structtire, shell structure stability, cylindrical shell, torsion stress, cylindrical
shell stability
ABSTRACT: A study was made of the stability of a closed cylindrical sandwich
shell under torsion. A solution which is based on equations for steep shells and
which takes into account the work moment of the outside layers is obtained. The
stability of hinged shells of finite length under torsion is examined. It is demon-
strated that a transition to a rigid filler and a shell of asymmetrical structure is
achieved in the same way as in the case of a long shell. [Translation of abstract'j
SUB CODV,_,- 13/
Card 1 / 1 K11

T
1p
p
i:es

M, SONS11T, L.V.
"w~,_-
Extrapolation reflexes in birds. Uch. zap. Mosk. un. no.197:IL5-159
158, (MIRA 11:9)
(Birds--Habits and behavior) (Reflexes)