SCIENTIFIC ABSTRACT AMBARTSUMYAN, S. A. - AMBARTSUMYAN, S. G.

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• Collection: Scientific Abstracts
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• Release Decision: RIF
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• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: March 20, 2001
• Sequence Number: 7
• Publication Date: December 31, 1967
• Content Type: SCIENCEAB

.111111~-~'v

MBARTSUMYAH , S.A. ,,
Calculation of lamizAted shells of revolution. Dokl.AN Arm.VSR 11
me.2:59-66 149. (MLRA 9-10)
I.Institut stroltel'afth materialov i sooruzheaiy Akademil nauk
Armynnskey SSR, Yerevan. Prodstaylems, A.G.Nazarevymo
. f. (R~Rstlc shells aid plates)

AMBARTSUMUN, S.A.
Calculating slanting cylindrical shells assembled from anisotrople
layers. 1xv.AN Arm.SSR.Ser.FW nauk 4-no-5:373-391 151,(KM 9:8)
1. Institut stroymaterialov i toorusheniy kkademii nauk Arayanskoy
SSR.
(311astic plates and shells) (Anisotropy)

"URTSUMUN, S.A.
Long anisotrople rotary shells. Izv.AN Am.SM.Ser.70? nauk 4 no.6;
423-431 '51. (NLRL 9:8)
1. Institut stroltellnykh m&terialov I sooruzhenly AWenji nauk
Armyanskoy SSR.
(Anisotropy) (Blastic plate@ and shells)

4 .,U"y t, I .
'17 T, 5. A. -- "Ardsotropic Coatinps.11
.- -.B.ART6Uly Sub 26 Jun 52, Inst
of 1,',echanics, Acad Sci USSF, (Dissertation for the Derree of
D,:~ctor in Technical Scie!~ces)
SO: Vechcrnava Moskya, January December 1952

IMBARTSURYAN, S.A.. doktor tekhnioheskikh, nyuk.
0.A. Ambartsumian's dissertation Unisotropic laminated shells.* Zzy.
AN SSSR, Otd.takh.nauk no.3--489-490 Xr 153. (XLRA 6:5)
(Ilastic plates and shells)

AXMBTMMN, B.A.
-41fte"
Computation of laminar anisotrople shells. Isr.AN Arm.SSR.Ser.
FM nauk 6 no.3:15-35 My-Je #53. (K6RA 9; 8)
1. Institut stroitellnykh materialov i soorushenty AN Armiyanskoir
SSR.
(Elastic plates and shells)

'Ambarcutrivan. S. it. On the computation of long shells of
Nauk ArmN%m..SSR. fzvestI5
Fiz.-Mat. Ntiiil: 6, no. 5-6,65-68 (1953). ([ZuB-
sian. At
The author c nsiders a vcry slopim, shell (a sloping Shell
ni all opell shell (,( Small curvaturos) which in made up of
orthotropic layers, Solutions for Such a diell are obtaillw
flom :1 symcn) (if two diflert'!ltia! equatio-lir giv-mi by tile
author in his pievious (unav:iilahlvl publications. In rasc of
a long shell (tht exact definition of it long, must be also
in the mithor's previous publications) the 6y,,tem of diOcr-
4.-ntial equations simpliflu!i cowiderably and reduces to the
icine given by V. Z. Vlasov [Gencral theory of shells,
Guswhizdat, Mosr-ow-Leningrad, 1949; MR 11, 627]. The
author makes one more ritnplifving assumption that the
Poisson ration are zero iwtl F.dvo~ the systern for a long
cylindrir' al Flopill", shell curved ill tile longitudinal diiection.
1.:or a isolTopu 0~01 the Fo4ttioll reduced to
tile on~- ~ivvtl h, V, Nov""dov F'Fheory of thin shells
19,-! ~ and the dutlt~r
C.011CILICIC.3 thilL NO%O~110~ lik:W', ffJ VI: SOV'fr I,"Wo1% are.
coincident. T. L.-scr INW.".

fjmr_tjr~ I ovt-i I !-)!V. __ - - --- __
USSR/Engineering - Mechanics
card 1/1 Pub. 41-4/13
Author AmbartsunWan, S. A., Yerevan
Title on the limits of applicability of certain hypotheses of the theory of
thin cylindrical shells
Periodical : Izv. AN SSSR. Otd. tekh. nauk 5, 57-72, MY -.954
Abstract : Establishes the'limits of applicability of certain hypotheses of the
theory of thin cylindrical shells of arbitrary slope. Sixteen refer-
ences. Graphs, tables.
Institution : Institute of Construction Materials and Structures of the Acadeny of
Sciences of the Armenian SSR.
Submitted : May 21, 1954

An, To, h
AGARTSUNYAN, S.A.
Problem of computing the stability of thiu.-walled rods. DokI.
A Arm. BSR 17 no.1:9-14 154. (MMA 7:6)
1. Inatitut stroltellufth materialov i soorusheniy Akademii
nauk Armyanekey SER. Predstavleno A.G.Nazarovym.
(Stability) (Mastic rods and wires)

t, '/Nysics S~ell theory
Card 1/1 nib. 85 - 4/12
FD-637
Author Ambartsumyan, S. A. (Yerevan)
,A
Title Problem of constructing apprcximate theories of calculating a
sloping cylindrical shell
Periodical : Prikl. mat. i mekh., 18, 303-312, MaYliun 1954
Abstract : Notes that in thL theory of cylindrical shells approximate methods
of calculating are based on simplifying assumptions vhose selection
depends mainly upon the ratio and dimensions of the mean shell sur-
face (according to V. Z. Vlasov and V. V. novozhilov, 1951). Con-
siders here the various hypotheses.
Institution : Institute of Structures, Academy of Sciences of the Armenian SSR
Submitted : January 27, 1954

T, j
T
r-iO37fi/j____'____'624.1Q74.4 .531.259.2
On the-, Calculation of k-dsotrapio IYv..Kkw1.14a*,Otd.tek4N&uk
with Transversal Ribs i 95JS
SLA. AmbartrmLyan U. S. S. R.,
A - M_- rloa~ily st~"Saaa Win cylindrical rotary shell
consisting -of. -hmopnsous orth-Aro~ic_ layors tW=43trical
toymds the central surface cif the shall, is "rwidared.
It is asEurmd that the cnatoria-1 of each lavar of the shei!
follows Houkln expandea Ism. The )Vpotha;iS of lion-
deforming normis is &ssumei to be hcolding good. RO~-vant
ftlmulae are obtained for very ver7 long or infinitely
long shells. qever,-l practical cases are considared, in
which the manner of loading ar.A th~~ ntnber and distri"tioil
(if ribs vary. (Pibl.10)

A"ARTSUKYAN, S.A.
-
Calculations on a symmetrically loaded circular cylindrical shell
reinforced by longitudinal ribbing. Dokl. AN Arm. SSR 21 no.4;
157-162 155 (KM 9..3)
1. Institut stroitollzWkh materialov t soorushenly Akademii nauk
ArmWanskoy SSR. Predstavleno A.G. Nazarovym.
(21astio plates and shells)

AUTHOR: AmbLrtsumyan, S.A. (Yerevan). 24-7-8/28
TITLE:__Un__Ehe 'calculation of two-layer orthotropic shells.
(K raschetu dvukhsloynykh ortotropnykh obolochek).
PERIODICAL:"Izvestiya Akademii Nauk,Otdeleniye Tekhnicheskikh Nauk"
(Bulletin of the Ac.Sc., Technical Sciences SectionTl-
1957, No.7, pp.57-64 (U.S.S.R.)
ABSTRACT: A thin two-layer shell is considered which consists of
two orthotropic layers. It is assumed that the planes of
elastic symmetry of the materials of each layer are mutually
perpendicular and that one of the planes of the elastic
symmetry is,iri each point of the layer,parallel to the
external parallel surfaces of the shell, whilst the other
two are perpendicular to the coordinate lines a = constant,
P = constant. It is assumed that a and 0 are curvilinear,
orthogonal coordinates which coincide with the lines of the
main curvature of the coordinate surface, y is a distance
along the normal from the point of the coordinate surface
to the point of the shell. The surface of adhesion of the
layers which is parallel to the external surfaces of the
shell is taken as the coordinate surface and it is also
1/3 assumed that the coefficients of the first quadratic form
A = A(m,P) and B = B(a,P) and also the main curvatures of

On the calculation of two-layer orthotropic shells.(Cont.)
8/28
247
range of applicability of the here present tHeory is
considerably wider than that of the theory constructed on
the basis of the hypothesis of non-deformable normals;
since the here made assumptions on the deformations
correspond more closely to reality.
There are 2 figures and 12 references, all of which are
3/3 Slavic.
SUBMITTED: June 25, 1956.
ASSOCIATION: Institute of Mathematics and Mechanics, Ac.Sc. Armenia.
(Institut Matematiki i Mekhaniki Akademii Nauk Armyanskoy
SSR).
AVAILABLE:

1~ I I
A.-MAhTrI5VVYj,II, USA.
a - ropow"m
Two --- c.,thcdn for calculati,,u- tw-.!-Iayer orthotropic shells.
I%v.,-N 10 r-10-2:17-38 157. (M-:.RA 10: 8)
I-Imtltvt matemati~d i mekhnniki Ak-,Ildemii naW- Arriyanslz-oy Ss"'.
(Mlastic platen and shells)

AUTHOR: 4iQM111ijj1j6,jAQXevan) SOV/24-58-5-12/31
TITLE: On the Theory of Bending of Anisotropic Plates
(K teorii izgiba anizotropnykh plastinok)
PERIODICAL: Izvestiya Akademii Nauk SSSR, Otdeleniye Tekhnicheskikh
Nauk, 1958, Nr 59 PP 69-77 (USSR)
ABSTRACT: The first attempts to evolve a theory of bending of
isotropic plates taking into consideration displace-
ments in the transverse direction were made by
Reissner (Refs 3 and 4) who dispensed with the hypothesis
of non-deforming normals and assumed that the basic
calculation stresses a., and a P and Tup along the
thickness of the plate change in accordance with a
linear law. The author of this paper considers that
in evolving a theory of bending of plates, particularly
of anisotropic plates, it is inadvisable to assume a
law of the change of the basic calculation stresses or
of the respective displacements. Therefore, the
hypothesis of non-deforming normals and the assumption
of the linear law of distribution of the calculated
Card 1/5 stresses along the thickness of the plate are substituted

SOV/24-58-5-12/31
On the Theory of Bending of Anisotropic Plates
by the hypothesis that secondary non-calculated
tangential stresses x U-0 and -ry change along the
plate thickness in accc-rdance with the law f(y),
particularly in accordance with the law of a quadratic
parabola. The possible inaccuracies which may be due
to the selection of the function f(y) do not affect
greatly the final results. This hypothesis was
confirmed in solved problems of the transverse bending
of beams and plates. The problem is investigated of
a plate of a constant thickness h, the material of
which possesses in each point one plane of elastic
symmetry which is parallel to the centre plane of the
plate. It is assumed that for such a plate the
generalised Hook law is valid. The plate is in such
a position relative to the triorthogonal system of
rectilinear coordinates that the coordinate plane oto
coincides with the centre of the plane of the plate and
the gamma coordinate is directed towards the load-free
external plane. The following assumptions are made:
Card 2/5 a) the normal stresses cr Y on the planes which are

SOV/24-58-5-12/31
On the Theory of Bending of Anisotropic Plates
parallel to the centre plane can be disregarded?(?Ompared
to other stresses;
b) the distance along the normal (y) between two points
of the plate remains unaffected by the deformation:
c) the tangential stresses T OLY and T PY along t~e
thickness of the plate vary in accordance with a given
law, f(y); since it is known from the work of other
authors (Refs 19 29 5-8) that the tangential stresses
Tay and T0Y change along the thickness of a beam or
a plate almost according to the parabolic law with zero
values at the initial and at the end points (-h/2 and
+h/2). This function can best be expressed by the
relation:
f(Y) = 1 (Y 2 _ 1h2 (5-1)
7 V
The results obtained by means of this theory are
compared for the case of bending of a square isotropic
plate which is freely supported along its contour with
Card 3/5 results obtained by other methods, namely, by means of

SOV/24-58-5-12/31
On the Theory of Bending of Anisotropic Platec
the accurate theory of Vlasov (Ref 8 ., and by the
classical theory of Timoshenko (Ref �). The comparison
shows that even for a very thick plate (h/a = 1/3),
the error in the values of bending does not exceed 5.8%
compared with the-results obtained by the accurate
theory, whilst the errors of the results calculated by
means of the classical theory of Timoshenko amount to
UP to 35%. In his manuscript devoted to the Reissner
theory of bending of plates, A. L. Golldenveyzer (Ref 10)
shows that in evolving the theory of plates without
taking into consideration the phenomenon of transverse
shear it is not advisable to apply a linear law of
variation of a and a and T~pisalong the thickness
of the plate, p9rticularqy when i necessary to
solve the problem of satisfying vi-th sufficient accuracy
the boundary conditions, The bending of the plates can
be effected by applying to the faces of the plate forces
which change in a way greatly differentftom that assumed
Card 4/5 by Reissner and in this case serious errors may arise.

SOV/24-58-5-12/31
On the Theory of Bending of Anisotropic Plates
Acknowledaments are made to A. L. Golldenveyzer for
his comments on this work.
There are 1 table and 10 referencest 8 of which are
Soviet, 2 English.
ASSOCIATION: Institut matematiki i mekhaniki AN Arm SSR
(Institute of Mathematics and Mechanics, Ac.Sc.,
Armenian SSR)
SUBMITTED: January 16, 1958
Card 5/5

SOIV24-58-10-24/34
AUTHORS:Ambartsumyan, S. A, Zadoyan, 1A, A. (Yerevan)
TITLE: On the Problem of Elasto-Plastic Bending of Beams (K zadache
uprugo-plasticheskogo izgiba balok)
PERIODICAL: Izvestiya Akademii nauk SSSR. Otdeleniye tekhnicheskikh
nauk, 1958, Nr 10, PP 130-132 (USSR)
ABSTRACT: The theory of bending of beams is based on the hypothethis
of plane cross-sections and does not take into account the
effect of tengential stresses on the form of the bent axis of
the beam. This restriction is removed in the present paper
and an attempt is made to determine the role of tangential
stresses in elasto-plastic bending of beams, Explicit ex-
pressions are derived and these can be used to estimate the
effect. The present work is a development of the treatment
given by 11r'ager and Khodzh (Ref.1) and the first of the
present authors (Refs.2 and 3). There is 1 figure and there
are 3 Soviet references.
ASSOCIATZON:~~.Institut.matematiki I mekhaniki AN Armyarsskoy SSR
(institute of Mathematics and--Mechanics AS
Armyanskaya SSR)
SUBMITTED: June 23, 1958
Card 1/1

AMURTSUKW. SA*j TJvHTAW, D.V.
""" I
Nonlinear theory of slanting orthotropic shells. Izv. Al Am. SSR.
Ser. fize'-mt. nmk 11 noiltI546 158* (NM 11W
1*' ItLetitut matematiki i makhanin AN ArnVbzekoy M
(Ilastio plates and shells)

AUTHORs Ambarlaumyan. -56A* (Yerevan) 40-22-2-10/21
TITLEz On the General Theory of Anisotropic Shells (K obshohey teorii
anizotropnykh oboloohek)
PERIODICALs Prikladnaya matematika i mekhanika, 1956,Vol 22,Nr 2,
pp 226-237 (USSR)
ABSTRACTs The author considers thin anisotropic shells of constant
thickness* It is assumed that the material of the shells satis-
fies the law of Hooke, and that in each point of the shell an
elastic plane of symmetry exists which runs in parallel with
the central plans of the shell.
The author introdubes curvilinear orthogonal coordinates which
coincide with the main directions of curvature of the shell.
It is-presupposed that an element lying nozoally to the shell
"urfaoe does-not change its length during the deformation.
Furthermore the normal stresses are assumed to be small
compared with the tangential stresses. Furthermore it is sup-
posed that the tangential stresses are distributed cirer the
thickness of the disks according to a quadratic law.
Under these assumptions now a system of differential equations
for the calculation of anisotropic shells can be set up which
Card 1/2 covers several pages in the representation of the author. Be-

On the General Thgory of Anisotropic Shells 40-22-2-10/21
sides of this system of differential equations the boundary
conditions must be also consideredi the author investigates
four different kinds of them s
I* The freely resting boundary,
2. the freely pivoted boundary,
3o the rotarily fastened boundary and
4- the fixed boundary.
For the case'of a oiroular~cylindric shell,the pysteiss of
formulae are simplified, but they are still very complioated.
They are essentially simplifiad for the case that the shells
are isotropic in the tangential direction. For this case the
problem of a horizontMy supported tube'is considered which
is freely supported at the ends and which is completely filled
with a liquid, The numerical oalculation of this cast shows
that the error of the classical theory in this case can rise
up to 15% compared wi:bh the improved theory by the author.
There are I table p and 13 Soviet references.
SUBMITTEDt January 13, 1958
I. Cylindrical shells--Theory
Card 2/2

16(l)
AUTHORSs
TITLEs
PERIODICALt
ABSTRACTs
Card 112
A,.j and
Peshtm&ldzhyan, D.V.
SOV/22-12-1-3/8
On the Theory of Orthotropic Shells and Plates (K teorii
ortotropnykh abolochek i plaatinok)
Izvestiya Akademii nauk Armyanskoy SSR,Seriya fiziko-matemati-
cheakikh ( nw-Ak, 1959, Vol 12, Nr 1, p-p 43-60 (USSR)
The author considers a thin orthotropic shell. In the c-arvi-
linear coordinate-system o(, S, j-the medium surface is
assumed to have ihe equation 3- - 0 ; let the directions of
o(-, 8 be identical with the directions of the principal cur-
vatures. Le.t the planes of elastic symmetry of the mate:rial be
parallel with the coordinate surfaces in every point. The dis-
placement along the normal w io assumed to be independent
of r . The normal stress 0ri- is assumed to influence only
unessentially the deformations edr.0 , e a I ecl-B , The
tangential stresses T at 8 1 'Var change according to the law
fo) so that eba- - a 55 f (0 q I (d-, B) , 013 a, ~ a44f (S-) Y2('_~ 16)

4
On the Theory of Orthotropic Shells and Plates 0V/22-12-1-3/8
where a 55 ' a44 are elastic constants, f(2-) is the given
function-and PI '%P2 arbitrary sought functions. Under
these assumptions the author calculates the moments and
stresses, substitutes them into conditions of equilibrium and
obtains a system of five differential equations (not presented
because of its complicatedness) for the calculation of the
five unknowns u,v,w..%f1 lf(P2
An explicit calculation is carried out in the following special
cases 1. Shells rectangular in plan form of positive Gauss
curvature ; 2. Spherical shells ; 3- Round plates with free-
ly resting boundary and fixed boundary.
There are 12 references$ 10 of which are Soviet% 1 English,
and I American.
ASSOCIATIONs Institut matematiki i mekhaniki AN Armyansko SSR (Institute
of Mathematics and Mechanics IAS Armenian SSR~
SUBMITTEDi October 15, 1958
Card

AKBLRTSUKYAN, SAq MCIATRTAX9 LA,
Stability a3A vibrations of anisotrople plates. DokI AN Arms
MR 29 no.4:3~59-166 '399 (MIU 13:4)
1
I* Institut matematiki i mekbaniki AN AmSM. P. Chlen-
korrespondent Al *ATuSSR (for Xwwhatryan).
(31a'stic plates and shells)

(Acad. Scl. USSR)
*On a general theory of anisotrople shells and platea."
ftport presented at the 10the International Congress of Applied Mechanical (ICSU)
Stress, Italyl 31 August - 7 SOP 1960.
The system of governing equations is of tenth order for shells and of
sixth order for plates, Only one plansof elastic symmeta7 parallel to the middle
surface is a53umed to exist. It turns out that a certain relative reduced thickness,
which depends both on the square of relatives thickness of the abell and on the
relatives values of physical and mechanical properties, is of great importance.
The author shows that the results of problems of equilibrim, static stability,
vibrational and dynamic stability of plates and shells obtained on the babis
of the classical theory may be very different as compared to those obtained on the
basisof the anisotropic theory, In the case of static stability, for example,
as the relatives redaced thickness increasess the value of the critical force
thnda to decrease in comparison with the critical force obtained according to
the classical theory,

69297
S/179/60/ooo/oVoi4/034
E081/E535
AUTHORS: Ambartsumyan, S.A and Khachatryan, A*A. ~Yerevan)
I
TITLE: The Stability and Vibrationsloof Anisotropic jlated'~A
PERIODICAL: Izvestiya Akademii nauk SSSR, Otdeleniye tekhnicheskikh
nauk, Mekhanika i mashinostroyeniye, 1960, Nr 1,
PP 113-122 (USSR)
ABSTRACT: The paper is a continuation of previous work (Ref 1).
It is assumed (1) that the plate is orthotropic,
rectangular and of constant thickness h, with one plane
of elastic symmetry parallel to the middle surface and
the other two planes parallel to the sides; (2) the
rectangular coordinate system (a,p,y) is such that the
ap plane is parallel to the middle surface with the a and
P axes parallel to the sides; (3) the normal stress a
on planes parallel to the middle surface can be
neglected in comparison with the remaining stresses;
(4) the distance along the normal (y) between two points
on the piate after deformation remains unchanged; (5) th
Card 1/7 tangential shear stresses T., and -r,y are given by

69297
S/179/60/000/01/014/034
Eo8l/E535
The Stability and Vibrations of Anisotropic Plates
Eq (1.1), where 9(a,p) and q,) (a,p) are arbitrary
initial functions. The bending of the plate is governed
by the three differential equations (1.2) containing the
normal deflection of the plate w, the functions V and
41 and the elantic constants of the plate B and a ij.
ii and the
In stability problems Z is given by Eq (2.1
equations become (2.2). For a simply supported plate
subjected to bi-ax1al compression (Fig 1), the solution
of the equations can be written in the form (2.4) which
on substitution in (2.2) gives (2.5). The critical
stress P a is then found as (2.6) with Pm;, the
mn
critical stress, assuming the validity of the Kirchhof
hypothesis, given by Eq (2.7), and d given by Egs (2.8)
If the plate is compressed in one direction only, Eq (2-7i
is replaced by Eq (2.9). If the plate is made of a
transversely isotropic material with the isotropic planes
parallel to the middle surface of the plate, the equation
for critical stress becomes (2.10) with D, c and k given
Card 2/7 by (2.11) and E, p elasticity modulus and Poisson's 7

69297
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E081/E535
The Stability and Vibrations of Anisotropic Plates
ratio in the isotropic planes, G' is the shear modulus
characterizing the change in angle between directions
in the isotropic planes and directions perpendicular to
them. The minimum value of the critical stress occurs
when there is one half wave in the direction perpendicular
to the stress; in thiscase (n = 1) Eq (2.11) becomes
(2.12). Table I gives values of k and coordinates of
s e2chVT acteristic points of the curves ~f) = ~ (c)
P'mb /1, D11 for ji = 0.25. In the upper part of the
table h/b = 0.1 and in the lower part h/b = 0.2. Values
of 11 are plotted against c = a/b in Fig 2; the curve for
k = 0 corresponds to the classical solution. Values of
J,(c) for orthotropic plate (obtained on the electronic
calculating machine M-3 of the Calculating Centre, Ac.Sc.,
ArmSSR) and for various values of k and c are given
in Table 2. It is assumed that m and
1 1 51 k = a E = a E h 1 0.3
E '~W 1 55 1 44 21 '9 = To- 1
Card 3/7 2 2

69297
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E081/E535
The Stability and VibrAtions of Anisotropic Plates
where E., p, and E., p. are the elasticity moduli and
Poisson's ratios in the directions corresponding to a and
For free vibrations, Z (eq 1.2) is replaced by
yoh
Z a"w
~t2
which leads to Eq (3-1), with y 0 the density of the
material and g the gravitational acceleration. Writing
the solution of (3.1) in the form (3.2) leads to the
0
equation (3.3) for the frequency w nI w :r:,,iwmR
(Eq 3A) is the frequency according To the I ca
solution. For a transversely isotropic plate, the
frequency reduces to (3.5). Table 3 gives values of the
ratio W /W 0 for modes of vibration in which m,n = 1.2.
mn mn
The departure of the true frequency from the classical
frequency increases with increasing k and with
-t.ncreasing mode number. The equations of dynamic stability
Card 4/7 if an orthotropic plate are obtained by substituting the
V,

62297
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Eo8l/E535
The Stability and Vibrations of Anisotropic Plates
expression (4.1) for Z in (1.2). If the plate is
compressed in one principal direction only, the
conditions (4.2) hold; assuming that the external force
varies periodically with time((Eq 4-3) where P is
the amplitude and 0 is the frequency), Eqs (1?2) take
the form (4.4). Taking the solution in the form (4#5)9
where w(t), y(t) and M are values of the functions
w, T and at the centre of the plate, Eqs (4.4)
become (4T6). Eliminating y(t) and 0 from (4.6)
with respect to w, the Xdifferential tuation (4-7) is
obtained, where w mn , Pmn are the frequency of vibration
of the unloaded plate (3-3), and the critical stress for
uniaxial stress in the a direction. Eq (4-7) is the
known Mattieu equation; for certain relations between
its coefficients the solution increases without limit,
corresponding to regions of dynamic instability of the
plate. Rewriting (4-7) in the form (4.8), it is known
(Ref 7) that the limits of the unstable regions are
Card 5/7 given by (4.9) for the first (principal) instability

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E081/E535
The Stability and Vibrations of Anisotropic Plates
region, by (4.10) for the second region and by (4.11)
for the third region, where 0 .9 is the critical
frequency of the external forces. It will now and
subsequently be assumed that there is one half wave only
in the a and P directions (i.e. m = n = 1) and for
simplicity the subscripts 11 are omitted. Under these
conditions, the dynamic instability regions of a square
plate (a = b) of transversely isotropic material are
given by (4-13, Ist region), (4.14, 2nd region) and
(4.15, 3rd region) in which the results are presented
in a form for comparison with the classical results.
From (4.8) X 1/2 and accordingly the limiting
ko is given by (4.16). The values oi 03K/2wo as a
function of Xo calculated from (4-13) to (4.15) for
variovs values of k are presented in Table 4; Fig 3
shows the instability regions for k = 0 and k = 0.2.
Fig 3 and Table 4 show that the Instability regions
differ from the classical values (k = 0) by greater amounts
Card 6/7 as k Increases. Similar calculations for a square V\/

69297
The Stability and Vibrations of
orthotropic plate wera
are given in Table 5,
k El ILI EI
1 ~ "2 112 "12'
S/179/60/000/01/014/034
E081/E535
Anisotropic Plates
made electronically; the results
where
k = a E = a44E
2 55 1 2
where El, 1i, and.E 21 IL2 are the elasticity moduli and
Polsson's ratios in the directions corresponding with a
and p; GJL2 = B66 with a55 , a44 and B66 known
elasticity constants (top of p 114). The calculations
were carried out for IL I = 0.3, h/a = 0.1.
There are 5 tables, 3 figures and 7 Soviet references.
ASSOCIATION: Institut matematiki i mekhaniki AN ArmSSR
(Institute of Mathematics and Mechanics, Ac.Sc., ArmSSR)
SUBMITTED: June 19, 1959
Card 7/7

S/179/6o/ooo/oo6/012/036
EO81/EI35
AUTHOR: (Yerevan)
TITLE: The Bending of Non-Linearly Elastic Three-Ply Plates
PERIODICAL: Izvestiya Akademii nauk SSSR,Otdeleniye tekhnicheskikh
nauk, Mekhanika i mashinostroyeniye, ig6o, No. 6
pp. 86-9o
TEXT: A three-ply plate in considerid which consists of non-. JP
!.linearly elastic layers symmetrically located with respect to.the
middle layer of the plate (Fig-1). The plate is related to a
cartesian coordinate system a, such that the middle plans

plate coincides with the plane a 0. The followtng
of the 4
.
hypotheses and assumptions are made: , (a) the hypothesis of -0
undeformed normals for each part of the plate as a who4.e;
Cb) incompressibility of the material in each layer of the plate;
(c) coincidence of the directions of the stress and strain tenvors
in each layer of the plate; W the non-linear relat*on
Mi,
Ti ai8i biSi
Card 1/.10

88520
S/179/6CVOOO/006/012/036.
8081/E135
The Bending of Non-Linearly Elastic Threie-Ply Plates
exists between the stress (Ti) and strain (Ei), where i Im number
of the layers, &i, bi and mi are constants of the material
determined experimentally in simple compresaion-tensions The
strains in the i-th layer are given approximately by:___.
7. T
eall epI YXII 1CCIP1 5 (112)
""I
T I
;
t 11 11 U
1 L
1!',);: fill Vol'.11 'I
' 0 -3)
en
esy 0; epy
.; ~;
.
.
ai~` O2W A 11L 1111,101 .11T
X
H
2
1
ill
OPT "I
A A
where w is the normal displacements The stresses ban be
approximately calcxilated by means of the equationst

Caf-d 2/ 10

S/179/60/000/006/012/036..,,
E081/9135
The Bending of Non-Linearly Elastic Three-Ply Plates
yaj (XI + -L XI) +
lyll"ibl(VTO vni-I
sign y (XI + Lxf);~11_
yal X2 + -Lxl)'+
y -P.) (Xi + f9i)
+ sign T PLO
-rd -Lyaji + sign y ()rp.) (1.10)
Yi.
These stresses determine the bending moments Mcz, Mp, and ~he
twisting moment H, which are expressed in terms of the linear
-(D and non-11near (D cylindrical rigidities by:
e p
Card 3/ 10

S/l79/6o/ooo/oo6/0l2/o36
E081/E135
The Bending of Non-Linearly Elastic Three-Ply Plates
- --------------
-(D. - D3,)

Alp- - (D.-Dp) -F X1
+

Using the equilibrium equation
82M 02 82M
H
a p
+ 2- + Z 0
2 2
6a aa ap 8p
the non-linear differential equation
OD OD opw

p
-
-
2
Vw - DVVw 2 :i
D.V
a
) T
.
a,
5
v
DsD /0310 1 O1W\ OID, OR D 0110
p
p + p z (ta)
,
.. I I
1
) 1

.
.
,
00
01 .
Card 4/10

S/179/60/ooo/oo6/ol2/036
~9081/U35
The Banding of Non-Linear2y Elastic Three-Ply Plat*x
(V . 82/ja2 + 82/8p2). F-
C
is obtained or a circularly
symmetrical problem, the equation when transformed to cylindrical
coordinates becomes.,
(Ow 2 dsw i dho , t dwN 2 d1w t dkv
-F + Ir -;TI d-FT. +;F 7r-
;r;Vj _ Dp d'
D.
dD 5 d-w I d I
OD 0 +J:dtvN
P(2 dow + a -)
wr
gr 2; arrT
C
As an illustrationg the problem in considered of the cylindrical
bending of an infinite 3-ply strip formed from non-linearly
elastic materials, and subjected to the action of a uniformly
distributed load q (Fig.2). The equation to be so2ved is thont
Id'w d' d, 1-1 (d%o mi-!
101+2 d%v d d1w d' to \ .,
t D. -dar -r. + =d,. 7.TD + D$ (2. 1)
dctT
_3 ITQT
Card 5/ 10

-88520 3!
S/179/60/000/066/012/036 -
E081/El'35

The Bending of Non-Linearly Elastic Three-Ply Plates
Particularly, taking
1 '20
0
1
0
.
.
,
al as 100, as 04, bi mw bi m iOl, b, iOl
MI M MS M mo am 2,

For the rigidities and the rigidity coefficients we obtain:

e 3-031:10 5
D 5 kg.CM2; D2 7.698,io5 kg.CM2; D, 0,35727 .109
kgiCM2.
In this case, Eq. (2.1) simplifies to

F
d4w dho ddt~ d%o do

_
_
--
D. __ 2 (DI + Do) j-,
T + -d
r
l (2.2~
d
a
a
d
.
.
de

which is solved by the method of disturbanced (Refs 3-5).'.-: For.:.
'
a strip with built-in ends, the boundary conditions-are:
w 01 dw/da 0, where a
Card 6AO

6/179/6o/ooo/oo6/012/036 A

E081/9135 ~
Th a Banding of Non-Linearly Elastic Three-Ply Plates

The deflection and load are taken as the power functions 1 1.c
+wX + 0., +
+ q2t, +
of the deflection at the centre of the strips, The straight
line in Fig-3 gives the relationship between q and � when

term of the series (2-5) in taken, the curve in this f gure
one i
represents the relationship when the first two terms of the
series (2.5) are taken. The normal stress at a 0 is
calculated from 2C
4 anw
-
-
T'
-f +
bty,
-1 X
a f aiy
'
'
U
d
O
)(O

which gives 1.164-10-2 for q 0.5 kg/cm2, and t =-2.49~ x
10-2 for q = 1.0 kg/cm2a By means of these values the
corresponding values of w are obtained.which, when insekted!in
Card 7/10
;
_.._
------

88520-
S/179/60/000/006/012/036.,
ROBI/El.35
The Banding of Non-Linearly Elastic Three-Ply Platen

(2.15), give the following e
quations for the atressest 1-4(
1 -4
= 1.424-10 a
c, -8
1.756-10 b
2

~ iW
for q Oa
5t
iW
4
i
2.7373o!0-4
a
'r

.489-10-8 b
2 for q 100.
i~
a ir
The values of oQi (kg/cm2) for the external layer 1.1) and 3-,
the internal layer.(w 1o0) are as followat
Non-line ar theory Linear theory
5(

q = 0.5 0
100 0.5 q =.I*

External layer 135-4 zz2.6 161.3 322.6
Internal layer 1.41
1-47 2'.941,
2.67

These results, and those of Fig.3, show that appreciable error&,
arise in determining the str eases and displacements if the non-;
linear properties are not taken into account#
Card 8/10

S/179/60/ooo/006/012/036-
EOBJL/El35
The Bending of Non-Linearly Elastic Three-Ply Plates
The purely illustrative character of the examples is emphasined,
V/z
Our. 2
A
Wxr. 8
Card 9/10

6025 h
S/046/60/024/02/20/032
AUTHOR: Ambartsumyan, S, A.,_(Yeqvan)
'~ .. i
TIM""" ;'~n~ nd Flat Shellsi~
Es On th.' ~~~Tnd"'!i lates
e ~ heory of Anisotropic.P s a
PERIODICALs Prikladnaya matematika i mekhani.ka, 1960, Vola 24, No. 2,
Pp. 3.50-360
TEXT: The author considers a thin orthotroptLc shell with the constant
tM'ckness h. He assumes that the material obeys to the generalized
Hooke law and that in every point there are three planes of elastic
symmetry whose normals coincide with the direction of the coordinate
lines of-, ~ I e . The W , ~ -lines are. identical with the main curvature
lines of the central surface; the central surface is the ot,11 coordi-
nate surface. The coordinate line e is the normal of the central sur-
face, instead of the assumption that the normals are transformed again
into normals by the deformation the author assumes: a.) The distance
between two points of the shell (on the normal e ) remains constant
under the deformation, b ) the tangential stresses twd and T-Ay
change in dependence on ;he e -coordinate according to a prescribed
I; .he shell is particularly subjec-t to a normal lcad Z only,
then it is chlosen according to (Ref-3,4):
Card 1/2

AMR&RTSUMUN, S.A.; KH&CHATRYAN. A.A.
Stability and vibrations of a shallow, orthotropic
cylindrical panel. DDkl#AN Arm,SSR 30 n0-10-39-45
16o. (MIRA 13:7)
1. Institut mtematiki i mekbaniki AkAdemil nauk ArmyanskoV
SSR i Terevanskiy gosudarstvennyy univereitet. 2. Oblen-
korrespondent AN ArrVanskoy SSR (for Ambartsurqan).
(Xaatio plates and shells)

h0776
s/i24/62/000/009/023/026
A05-1/A101
AUMOR3 Ambartsumyan, S. A.
TITIE: Theory of anisotropic shells
PIMIODICAL: Referativnyy zhurnal, Mekhanika, no. 9, 1962, 14 - 15, abstract
9v89 K (Moscow, Fizmatgiz~ 1961, 384 pages, illustrated)
TEXT: In the book are collectee and systematically presented the results.
of the investigation upon the problem of elastic equilibrium of anisotropic
shells and partially anisotropic plane plates'(special questions). First is
presented In the monography the accumulated wide material upon the theory of
anisotropic shells, published in numerous articles In periodicals. As basis, in-
vestigations of the author are laid down, but also works carried out by other
scientists are indicated. The main part of the book is dedicated to problems of
the stressed and deformed state of various shells, which are composed of series
of anisotropic layers glued or soldered along the contact surface, and studied
from the standpoint of the linear theory of elasticity and classical theory of
shells, bbLsed on the hypothesis of straight normals and other assumptions. Si-
Card 1/5

S/124/62/ooo/oo9/o23/o26
Theory of anisotropic shells A057/A1O1
multaneously with the presentation of general aspects of the basic problems of
the theory of shells, the book contains a great number of particular questions
and numerical examples with tables and diagrams. The book is divided into seven
chapters. Chapter I has an introductional character; in it are reported the
necessary data upon curvilinear coordinates, presented terms for the components
of deformation, equations for the equilibrium of the element of the shell, and
equations which express the generalized Hooke's law for the basic forms of ani-
sotropy. Formulas are given for the transformation of elastic constants at the
transition to a new system of coordinates and numerical values of elastic con-
stants for a series of anisotropic materials. In chapter II are reported general
equations of the theory of shells, composed of anisotropic layers. First is dis-
cussed a general case of a shell, when the layers have an arbitrary thickness md
their number is arbitrary, and anisotropy is characterized by the presence of
only oneplane of elastic symmetry, parallel to the coordinate surface of the
shell. Based on the hypothesis of straight normals and other assumptions, ex-
pressions are.deduced for stresses, inner forces and moments, equations for
equilibrium, elasticity relations and indicated basic cases of boundary conditLons.
Furthermore are discussed special cases: shells ccmposed of an arbitrary number
Card Z/5

S/lL,4/62/OW/009/023/026
Theory of Anisotropic shells A057/A101
of orthotropic, isotropic, or transversally isotropic layers and of-an odd number
of layers, located symmetrically in relation to the middle surface. The case of
a monolayer shell is discussed, and compared to the case of a multilayer shell
in order to determine the relation between them. It.is demonstrated that in a
general case the calculation of a mUltilayer shell should not be identified un-
conditionally with some monolayer shell (� 15). The chapter III is dedicated to
the membrane theory of anisotropic shell. First is discussed the monolayer shell,
for which are deduced the basic equations*of the7membrane theory and presented
their integration for a symmetrically loaded shell of revolution of an arbitrary
form. Furthermore are discussed shells'of special shape: 1) cylindrical, 2)
conical, 3) spherical, and 4) formed by revolution of circle are, studying the
general case, as well as special cases.' The results are geheralized without con-
siderable changes for the case of a symmetrically constructed laminated shell and
demonstrated on the example of a triple-layer cylindrical shell. In the presenta-
tion of the following three chapters IV - VI the author keeps the following
sequence. First is discussed the multi-layer shell of a general form with layers
having only one plane of elastic symmetry each, and all formulas and equatiors
are presehted for it. Then are discussed basic special cases, when the layers
Card 3/5

S/124/62/W3/009/023/026
Theory of anisotropic shells A05VAIOI
are orthotropic, isotropic, or transversally isotropic, but oriented arbitrarily
and when the layers are oriented symmetrically in relation to the middle layer;
in the last case, specially in the presence of orthotropic layers, considerable
simplifications of all equations and the corresponding solutions are obtained.
In chapter 1V is discussed the theory of axisyminetric deformation of shells of
revolution. General equations, solving equations, and formulas for all mechanical
quantities are derived. The method of asymptotic integration of the solving
equation is described. The problem of the boundavy effect and long shells of re-
volution is discussed and several examples given for the calculation of cylin-
drical, conical, and spherical shells. In 5 12 are investigated cylindrical
shells with transversal (circular) reinforcing ribs. Chapter V is dedicated to
the problem of equilibrium of a cylindrical shell with circular cross section,
loaded arbitrarily. After deriving the general equations, tho technical theory
is presented by using additional assumptions. Two general methods for the forma-
tion of solutions based on the technical theory are discussed. A method for the
solution of a shell with open profile by means of double-series (applied also to
the particular case of a shell with closed profile) is given, as well as a method
based on the use of single-series. The methods are illustrated on several ex-
Card 4/5

Theory of hnisotropic shells
3/124/62/ooo/oo9/o23/o26
A057/A1O1
amples. In chapter VI is presented the theory of slanting shells. -General
equations, solution equations and formulas for -all mechanical quantities-are de-
rived. By means of double series the solution Is found for a very slanting shell,
rectangular in the plan. Several numerical examples.are discussed. 'In chapter
VII are discussed more rigorous theories of anisotropic plates and shells, not
using the hypothesis of straight normas. Three different theories are presented,
which are applied to mono-layer plates and shells, as well as to multi-layer slant,
ing shell and triple-layer cylindrical shell. A comparison of the results, ob-
tained on the basis of different theories Is made on particular examples. .
S. G. Lekbn:Ltskiy.
[Abstracter's note: Complete translation]
Card 5/5

28970
10-~000 OW 5/179/61/000/003/012/016
E081/E435
AUTHORS: Ambartsumyan. S.A. and Gnuni, V.Ts. (Yerevan)
TITLE: Forced vibrations and dynamic stability of 3-ply
orthotropic plates
PERIODICAL; Akademiya nauk SSSR. Izvestiya. Otdeleniye
tekhnichebkikh nauk. Mekhanika i mashinostroyeniye,
1961, No-3, PP-117--123
TEXT: The paper is a continuation of previous work (Ref.6:
Ambartsumyan S.A. Pmm, 1,96o, voi,xxiv, No.2-, Ref.11: Gnuni V.Ts,
Izv. AN Arm.SSR, ser. fiz.-mat. nauk, ig6o, voi.xiii, No.1; Ref.14t
Ambartsumyan, S.A., Khachatryan X.A. Izv. AN SSSR, OTN,
Mekhanika i mashinostroyeniye, 1960, No.l: Ref.16: AmbartsumyanS.A.
Theory of anisotropic shells. Fizmatgiz 1961). The material in
eeLh layer of the plate obeys the generalized Hooke's law and'has
three orthogonal planes of elastic symmetry at each point, with
printipal directions a, P, y, the y direction coinciding with
the thickness of the plate. The following assumptions are made:
1. The hypothesis of undeformed normals applies to the external
(bearing) layers. 2. For the internal layer- a) the shear
streisses T., and ipy have the form
Caz d 1/3

2P~970
S/179/61/000/003/012/oi6
For~:ed vIbratione and dynamiz ... E081/E435
It Ct Y. f (.()y 6 , 0) .TPy ~ f` (-() 4) ta , P)
wheit ~p(3,p) Lind ~(aj) are functions to be determined and
f(y) is a funclion rhara-c-terizing the law of change of shear
stresses through tht, thi,:kness, subject to the condition f (+'h/2) = 0;
b) the normai stress ay on planes parallel to the middle ;iurface
can be neglected in comparis= with the other stresses;
c) the normal displa:ement is intrariant. svith thickness.
3. The normal displazements are comparable with the thickness, and
ortly tho5e, non-linear term* arising from the normal displacements are
refained in the e.-pressions for the deformation of the middle surface.
On the bazts of these assumptions, the differential equations
gcverning the deflection and stress functions of the plate are
stated. The deflecti--,n and stress fun:-ti3ns for a plate simply
supported at the edges and subjezted to compressive stresses Pl,
P2 in its plane are assumed to be double Anfinite trigonometric
series and expressions are obtained for the frequen:~y of vibration
and the critical values of the stremses Pl and P2. The dynamic
Card 2/3

28970
S/179/61/000/003/012/Oi6
For,~i:d vibi-atIOnS dnd dynami.. ... E081/E435
stability of the system and the shape of the resonance curve are
also diszussed. Special zases of the equations are discussed and
the equati:ins are illustrated by numeri~.al examples. There are
6 figures, I table and 18 references-, 17 Soviet and I non-Soviet.
The reference to an English language publication reads as follows:
Reissner E. Sm&411 Bending and Strbt.-.hing of Sandwich-Type Shells.
NACA Rtport, 1950, 975.
ASSOCIATION- Inatitut matematiki i mekhaniki AN ArmSSR
(Instl Lute of Matherndtics and Mechanics AS ArmSSR)
SUBMITTEDi Febiuaty 28, 1961
Caxd 3/3

29067
S/179/61/000/004/011/019
E081/E335
AUTHORS. Ambartsumyan.. S.A. and Bagdasaryan, Zh. Ye. (Yerevan)
. ..............
TITLE- The stability of orthotropic plates in a supersonic
gas current
PERIODICAL: Akademiya nauk SSSR. Izvestiya. Otdeleniye
tekhnicheskikh nauk. Mekhanika i masinostroyeniye.
no. 4, 1961, pp. 91 - of
TEXT: The paper is a continuation of previous work
(Ref. 1 -, Izv.AN SSSR. OTN, 1958, no. 5; Ref. 2 - n1H, 1960,
v. 24, no. 2; Ref. 8'.- Izv. AN SSSR, OTN, 1960, no. 1). The
problem is formulated in rectangular coordinates a, 0 and
y , such that the a and P directions coincide with the sides
of the plate. The thickness of the plate h is constant. One
plane of elastic symmetry is parallel to the middle surface of
the plate and the other two planes of symmetry are parallel
with the sides. A super-sonic gas current of velocity u flows
over one side of the plate in the a direction. It is assumed
that, 1) the normal displacements in the direction of the plate
thickness are invariable; 2) the shear stresses et; and -[~
Card 1/3 ay y

9/9067
S/17 261/000/004/011/019
The stability of .... E081/'E335
have the forms
IV ay = f(Y)Y(a'P)' 'rPY = f(Y)y (aP,)
where 9(a9p) and LF(a,P) are initial functions, and
f(y) is a function characterising the law of change of shear
stress in the thickness direction, subject to the condition
f(+h/2) = 0 3) that the normal stress cy is negligibly
Y
small compared with the remaining stresses-, the excess
pressure due to the flowing gas is given by the piston theory;
5) only those nonlinear terms are retained which are connected
with the normal displacement w ~ On the above basis, the
nonlinear differential equations for the motion of the plate
are established in terms of the elastic constants, the deflection
w , the stress function and the functions charaterising transverse
shear. These equations are solved appr,.#ximately by a
variational method for a plate having all its edges simply
supported and subjected to normal forces p p, acting in
Card 2/3

10 U10
31076
S/179/61/ooo/oO5/013/022'
toBi/s477
AUTHORS: Ambartwumyan, S.A., Bagd6saryan, Zh.Ye. (Yerevan)
TITLE: The stability of nonlinearly elastic three-ply plates
in a supersonic gas stream
PERIODICAL: Akademiy& nauk SSSR. Izvestiya. Otdoleniye
takhnichoskikh nauk. Makhanika i mashinostroyeniye.
no.5, 1961, 96-99
TEXT8 The paper is a continuation of previous examinationo of
the subjett (Ref.4i Ambartsumyan, S.A. Izv. AN SSSR, OTH, 1960,
no.6) and deals with the stability of rectangular thr*e-ply plates
which are subject to a supersonic gas stream at zero angle of
attack. Surplus gas pressure is catered'for approximately by the
"piston theory" (Ref.3: Ch&rnyy G.G. Flow of gas with a high
*Upersonic speed'. Fizmatgiz, 1959). The plates are symmetrical.
The following are assumedi
1. The hypothesis of undeformed normals applies to the complete
specimen of layers as a whole.
2. The material of each layer of the plate-is incompressible.
3. The tensor stress and strain components in each layer coincide.
Card 1/3

31076
S/179/61/000/005/013/022
The stability of' nonlin6Arly ... 9081/Z477
4. The nonlinear relation between the stress components Ti and:
the strain tomponants Ri is
Ti sr. ai1i - bigimi
where i is the number of layeral ai, bi and mi are constants
determined from simple tests of the material of the layere in
tension and zompression.
On the basis of theme assumptions, the bank: differential equation
for the movement of the platwis quoted and reduced to a system of
ordinary differential equations by applying the Bubnov- Galerkin
method. As an example, a hinge supported endless strip is
examined and it is shown that the amplitude of steady flutter
vibrations may be determined by a velocity parameter V , and a
parameter Q , which depends on the properties and construction of
the plate. It is shown that there in a crittcal value of V
below which, when Q is larger than zero, the amplitude decreases
with an increase of I. Above this value, when Q in smaller
than zero, the amplitude increases with increasing There are
Card 2/3

31076
S/179/61/000/005/013/022
The stability of nonlinearly ... 9081/2477
4 figures and,6 referencest 5 Soviet-blot and 1 non-Sovist-bloc.
The reference to an English language publication reads as follows:
Ref.6: Prager W. On ideal locking materials. Trans. Soc.
Rheology, 1957, 1.
ASSOCXATION: Institut matematiki i mekhaniki AN ArmSSR
(Institute of YAthematics aiad*Machanics
AS Armenian SSR)
SUBMITTED: April 24, 1961
Card'3/3

AUTHOR:
TITLE:
PERIODICAL:
89489
S/022/61/014/001/009/010
B112[B202
Ambartsumvan, S. A.
Axisymmetrical probiem of a thr--in-red cylindrical shell
consisting of nonlinearly elastic materials
Izvestiya Akademii nauk Armyariskoy SSR. Seriya fiziko-
matematicheskikh nauk, v. 14, no. 1, 1961, 105-109
TEXT: The author studies circular'ly cylindrical shells consisting of three
nonlinearly elastic layers. The layers are symmetrically arranged with re-
spect to the central surface of the shell. The system of lines of curvature
and normals of the central surface is a very appropriate system of coordi-
nates of the cup. Therefore, it is used as reference system. The author
assumes that the shell as a whole is not sub3ect to normal deformation and
that no axial stress component occurs. The following is assumed for the
individual layers: they are incompressible, the main axes of the stress
tensor and the deformation tensor coincide, and the relation between stress
intensity Ti and deformation intensity Ei is nonlinear:
Card 1/2

89489
Axisymmetrical problem of ...
S/022J61/014/001/009/010
B112/B202
T E b Emi
i i i i i
a; b; m are constants of the i-th layer which were determined by material
experiments. A nonlinear fourth-order differential equation is obtained for
the normal displacement w of the central surface of the shall. In the spe-
oial case of a shell with linearly elastic boundary layers and nonlinearly
elastic central layer this differential equation can be solved by the method
of Rndnnv-r..Q1Prkin in first approximation by w a C sin(na/1). I is the
length of ine sneil, a the circular coordinate, the constant C is the root
of a cubic equation. Finally, the method is illustrated by a numerical
example. There are 2 figures, 1 table, and 4 Soviet-bloc references.
ASSOCIATION: Institut matematiki i mckhaniki AN Armyanskoy SSR (Institute
of Mathematics and Mechanics AS Armyanskaya SSR)
SUBMITTED: November 16, 1960
Card 2/2

2E 11 33
S/040/61/025/004/014/021
1k,0 0 D274/D306
_~U~JT;10~s Ambartaumyan, S.A. and Gnuni, V. Ts. (Ycrcvan)
TITLE: On the dynamic stability of nonlinear-elastic sand-
wich plates
PM10DIC.&L: Prikladnaya matematika i meldianika, v. 25, no. 4,
1961, 746-750
TEXT: The plate is referred to an orthogonal coordinate-system
0( A, Y so that the middla surf ace coincides with the L'XO -plane.
Certain assumptions are made with regard to stress and strain ten-
sors. The equations for the normal displacement w are set up. Pur
ther, the dynanic stability equation is obtained. The solution of
this equation is sought in the form
W - fit) x (CO Y (2.3)
where f is the sought-for function and X and Y are chosen so as to
satisfy the boundary conditions. Using the Bubiiov-Galerkin method,
a nonlinear differential equation for f is obtained. Under certain
assumptions and taking into account linear darVing, this equation
Card 1/4

261 3.~
S/040/61/025/004/014/021
On the dynamic stability... D274/D306
reduces to f + 2e*f I + Q*2 (1 211 cos GO f + V (f , f I t) = 0
(3.4)
where
W (3.5)
V(f,fl,t) 2(E - E*) V + Q2 - Q*2) (1 - 2p cos Ot) f -
-Ofllflm'-l f -0(21fl Mx-lf '
The critical frequency Q* is determined by the assumption that the
initial unperturbed state is not deformed. Thus, e.g., at the
boundaries of the principal region of instability:
92 -,,49,2 1 TF a 462 N
0", (3.6)
rTI
E . T.4~ allows periodic solutions,
For 9 a O*t the linear part of q
which are given by the following estimates
4?i.(t) P., Cos (Y -CI), T2(t) -, sin (19t - a' cr are sin I
T
3.7)
Card 2/4

2filM
S10,4 0/61/025/0.01;/ 0 14/021:
O.,h the dynamic stability... D274/D306
By me=slof L.I. Mandellahtam's mathod, the ampliiude C of the
teady-state oscillations at the boundarieu, of the principal instab-.
ility-region can bo determined in the zeroth approamation' from
V [C (t), tj Pi (t) dt 0 3,
6
Hhence the nonlinear algebraic equation
m + A2Cm = Cq 2 2) U T 1-k cD s 2 or
AIC
2T
_i9 Mi4*1 dt, or A, +1 Ot
Cos t sinni 2. -~Idt
2ar (IF ( . . I ) Y
(3.10
It is shown that the-negative sign in the right-hand side of (3.9)
refers to the lower-i and the positive sign to the upper boundary
of the region of instability. It is also shoi-m that the coefficients
A. vanish if the corresponding layer of the plate is'made of linear-
Card 3/4

S/b4 61/023/004/014/021
On the dynamic stability... D274%506
clastic material. Fig. 5 shows an amplitude vs. frcqiiency pl6t of
steady-state oscillations in. the principal instability region, viincil
i~i >, 0. Fig. 4 shows Such a graph f or j~i ~r- 0. If the two cocf:gi-
cients ~3. and !h2 are of opposite sign, the correspondii-ig two terris
of (3.9) will have oppoqite effects on'the frequency of oscillations.
2 e-.-tamples are given -for illustration of Eq. (5.9). There are, 7
figures and 5 references: 4 Soviet-bloc and 1 noi-i-'Sovict-bl6c. The
reference to the Engtlish-language publicat.`,'on reads an follows: W.
Pra-er, On ideal locking materinls. Transac"Cions of the Society of
11heolbgy. 1957, 1.
iMUMITION: Institut inateriatihi i r.-telthanihi AM ASSR (Ifts'titute
of- 11athematics and Irleclianics kS AniSSIZ)
SUBUITTED: April 22, 1961
cL
ois:~ ~6_ -.0 0 9 6
819 Rb 0 b
Card 4/4 Fig. 4 Fig. 5

I
AMBARTSUMYAN Ae, DURGAR'YAN, S.M.
Nonsteady temperature problems of an orthotropic plate. bokl. AN
Arm. SSR 33 no.4:145-149 161. (14IRA 15:1)
1. Institut matematiki i meW;niki Akademii nauk ArVanskoy SSR.
2. Chlen-korrespondent AN Armyanskoy SSR (for knbartsumyan).
(Elastic plates and shells)

SAVIN p G.P.) otv,,red,; ADADUROV, R.A.,, red.; ALTUIXAB , N.A., red.;
.-AYMARTSUIffAN, S.A., red.; AMIRO, I.Yu., red.; 13GLOTI14, V.V., red.;
VOLIMIR, A.S., red.; GOLIDRIVEMM, A.L., red.; MIGOLYUK, E.I.,
red.; KAN, S.N.,, rod.j KAFVISIIIV, A.V., rod.; KILICEEVSKIT, V.A.p
red.; KISELEV, V.A.p red.; KOVALELIKO, A.D., red.; MUSIITARI, KhX.p
red.; NOVOZHILOV, V.V., red.; UIWSKIY,A.A., red.; FILIPFOV, A.P..,
re4.; LISOVETS, A.M... tekhn. red.
(Proceedings of the Second All-Union Conference on the Theory of
Plates and Shello)Trudy Vsasoiuznoi konferentoli po teorii plustin i
oboIochek*2djLvovj 1961.Kiev, Izd-vo Akad.nauk USSR, 1962. 581 p.
(Min 15!12)
1. Vsesoyuznava konforentsiya po toorii plastin i obolochek. 2.
Lvov, 1961.
(Elastic plates and shells)

3/879/62/000/000/039/088
D234/1)308
kU.THORS:, ~.AMbAr~tpqMyanu_S,_A. 9Bagdaearyan, Zh. Ye. and Gnuni,
To# (Yerevan)
TITLE;
Some dyn amioal problems of aniaotropio three-layer shells
SOURCES Tooriya plaeltin i~obolochek; trudy II Vaeooyuznoy konfe-
rentsii, LIvov, 15-21 sentyabrya 1961 g. Kiev, Izd-vo
.'AN UPRv 1962, 25.4-259.
TEXT; The.authors consider.Ia thin shell whose layers are uniform,
orthotropio and symmetplical, with respect to the middle surface.
The.'material of each layer.' obeys the generalized Hooke Is law.
Normal displaoements are assumed to be comparable with the thick-
ness and not to vary along the thickness. The complete system of
differential equations- in tome -of 5 unknown functions is formu-
lated; it is essentially simplified if the effect of norma3 stress
I-e-ne-g-1 "oe40 Thi'd-Watem7oan-be ap~plied to problome of nonlinear
dynamical stability or aeroolaoticity if appropriate substitutions
are made..
L-Card

39809
s/179/62/000/003/009/015
E191/E435
AUTHORS.: -Ambartsumyan. S.A., Durgarlyan, S'.M. (Yore ,van)
for-the
TITLE: Some nonstationary temperature problems
orthotropic.plate
PERIODICAL: Akademiya nauk SSSR. Izvestiya. Otdoleniye
tokhnicheskikh nauk. Makhanika'i mashinostroyeniye,
no.3, 19621 120-127
TEXT: A homogeneous orthotropic rectangular plate is considered
wherein the principai directions of stiffness are parallel to the
edges of the plate. The*first problem treated is that of a
plate, initially at zero temperature, which is subject to heating
by maintaining a given constant temperature of the boundary planes
constituting the four edge faces. In the analysis, use is made
of a hypothesis attributed to Franz Neumann which leads to a
generalized Hooke's law for the temperature problem. The analysis
leads to the derivation of the field of the stress function.
A numerical example describes a square plate (.40 cm per side) made
of moul:ded fibreglass laminations. The thickness of the plate
does not enter into the problem. The principal stresses after
Card l/ 2
41 J-961 --- ""a i'10chanic
AS Armenian

L i~A 7 1 ;;JI ( W 'I, i~WT i f-.
A UTB&P i AmbartaurWan, S. A. (Yerevan~
71F: IN the r"blem of orthetroz-Or r1fita onralintiant) Dlaced in a 11iAh-
Y
TOPIC TA(;Sv Hooke system) plate oscillation, elastio medium, elastic moduluB,
partial differetntial equation
,kBSTRACT, An orthotropic plate of constant th:ickni--mi h in EL .axtesian coordinate
system obeyirig the gene-ral Hooke's 1-i-w vnp- 7-1 t.~~-rp iixipt th-f-pe planen
of el"-tic uy etr-v is oonsidered. Tli t- t piate is def ine-d by
7 - T (z,t), It io furthec asuumv~-'~ ti nyTotheapa hild.
Tn" stress equations then yield j, - n.,r~ 4 v,,X,) - a, r
of, - But, , - ~67-
T.1 BA*bo + 2.IFSOT
Vr, VIR
where B, D" - - --L . Des off
VIV,
Cord 1/2 Aj -
L)

L 26053-65
AOMSSION M AP30048DB
The Vii are 11ne&r coefficients of expansion. The equations of motion of the plate
element are then written t-)gether wif-N thp cxDressions for internal moments and
foroes, azn-' a set of three partial ~rt ! ~ -- r. 4'~ S't tP I ned f.-Jr d i spl
mentB u, Y, and w. In these equations the U i): --unk K, ar V !' LM Cor. El
1k, k I 11C
on],,. The temperature dependence of the elaetinity moduli is g-iren by
:-B, ~ Bi'- BIO'T, ' G1, Gn'T or E,-rj,'-j:,--T"3. r,- G'31-7~
It .4B assumed that tho plate undorgoea trarsvqrse onaillations with mean temperature
variations .7- At.: A. T M32,11-1 (D T-I'M,,X-.4.1, y>j,). The resulting equations
arp them integrated with bounda7 conidi tional w-D. 81w1azi-O at x=O and a-mi
and initial oonditioribi wmq(z), at t - 0. The solution, obtained by
f-~-a I-nnt, increasing the UzE t ialnes
whic azp,; tuae se
P-r-.. has: 47 equations.
I A ~N materztl~ii i --khaniki JUT ~~,:Uannkoy SSR (Institute of
Mathematioa and Mechanics, AW Armon:Laa cn>~"
EN C ,, I CC SUB C=E! MF, tS
SUAGI-IM. 2C)Feb63
NO REF SOV WS OTIE-vi., X,
CCrd 2/2

AMBILRTSUMrAN S.A.9 BUHMUANI S.H.
Some problems of tanperaturs aM creep of anisotropic sarxlwieb
plates and sbells.
Report to be submitted for the Sball Structures,, International
Association for (IASS) Symposium on Non-Claosical Shell Problems
Warsaw, Pol " , 2-5 Sept 63

A,,jBAR,fSTR4YANp S.A. (Yerevan)
Stability of inelastic plates allowing for deformations due to
transverse shear. Prikl. mat. i mekh. 27 no.4:753-757 Jl-Ag 163.
(KIRA 16:9)
1. Institut matematiki i mokhaniki AN Armyaziskoy SSR.
(Shear (Mechanics)) (Plasticity)

AMMTS121YAN, S.A. (Yerevan)
"The development of the theory of anisotropic sandwich shells"
report presented at the 2nd All-Union Congress on Theoretical and Applied
Mechaniesp Moscowp 29 Janu&ry - 5 February 1964

DURGARIYAN~ B. M.; AHaART~SUMWYAN2 S. A.
"Some problems of vibrations and stability of elastic orthotropic shells and
plates in an alternating temperature field."
report submitted for llth Intl Cong of Applied Mechanics, Minich) W. Genrany,
30 Aug-5 Sep 64.

S r 0 N P A F 0 v 1 5 y 3
a , rr, a
P I o ( a c v T f v
tiyao MekhanIX8 J,
SOURCEI AN SSSR* 1XV65
1964, 77-82
7 0 P 1 C T A C S : C y I i n d r i c a I a h c i I c v I L n d r i c a I s h e 11 f I u t t e r h a I I
flutter speed, infiaLts plate, flutter speed, plate flutter. plate
f 1 u t c 6 r a p a c d
u t t e r o A
11

r c b o f o v e hypothes i b o n p r e s a r v It
rn -i n n r n o r~ rOQ e Ii o n n f t n i e I y sma I a 1143 1 1
0 tr Lim 0 Q v A r c
r v of a o w L t t- r v q,c
a ik p, T c a a a r) f o r d a t a T m n I n
no mm m

1 211l4-65
ACCESSION NRi AP500259i
of a given time interval is derived for tne case when the els3ticity
modulus varies linearly with temperature ac%d the temperature linearly
witb time. The procedure of extending tho results obtained to an
infinite plate is indicated and foymulas for toe flutter speed
r m u
deduced. Orig. art. heat 39 i,
socr"Iox I -b -0-"
SJ BM I T TE D i14Apr64 E N C L 100
NO REF SOVt 010 OTHE R 001
SUB CODEi As, ME
ATD PRESSi 1116.11

- "; ..l. 1. , I V LIE, L . fa .. -tt . . , i~* - . I -.. . I - - I I . I 1 1,
TG -'~- :' -. AGS : sh c. I 1 6 tX-u c t ure
~ h rl"Vie-V A I - - I .. -.1 ~ . I . ~ k~' *

1
4.1 52597-65
ACCESSI-T? ;11R: A~P'5015?21 11o
S; ~~-,Iestions on the StabilitYl &Ld

67-1J. art. has 3 riguros and 16 formulas
.

AO,
64 ZNCL: 33 S*,P- c3D-.
R7-.- ---V: 1&3

U? SIAN

ACCESSION NRt APhO33061
5/0252/6h/038/002/0087/0092-
.AUTHORSs Ambartsumyan,, So A* (Corresponding member); Dargarlyanp So He
TITLEt Oscillations of an orthotropic slanting shell in a variable temperature
field
SOURCRI AN AroSSRe Doklady*# T. A noe 2# 1964p 87-92
'TOPIC TAGSt variable temperature fleldp orthotropic shell, slanting shell., free
osciLLationp positive Gaussian curvature, generalized Hook law, heat equation,@
olasticitjr modulus, shear modulus, linear expansion coefficient,
ABsTRACTt The authors study a very slanted# orthotropic shell,, whose material Is
subject to a generalized Hook's lawp referred to an orthogonal curvilinear
coordinate systomiX.* At each point them are three planes of elastic
symmetry parallel to the cooramte surfaces* The authors am concerned with free
oscillations of the shell which has positive Gauspian curvature and constant
thickness h., in the field of inl2uence of high tennaratures, The following
:assumptions am mades the shell temperature T a Tjjt) satisfia an initial
,condition (t.= to) surface conditions and the heat equation; in the first
Card 1/2

A
TITLE: Flutter in a plate i:, a temperature field
SOURCE: AN ArmSSR. Doklady, v. 31), no. 3, 141-147
TOPIC TAGS: x lut ter, f I at ;A at
ABSTRACT- The article deals wit-~i ar
P '~!)e n'. I S 77-
t;tperturbed 'velo~-:iLv 6.Lre,7teo o axis, -is assumed
Card 1/3

L 26335-65
ACCESSION NR: AP5002648
'SUBMITTED; 02Apr64 ENCL: 00
NR REF SOV; 008 OTHER: 001
SUB CODE: AS, HE

WWI
.7,7~`-L- 2C ---- EWAJ ~F N-4 ------ -
611110119--
0/0179/64/0*660
7.
J
~v~; anuni
-77
A6 di Wit-
---- ------- -
I lX7;,-n
SWRGEt AN SM. .17MOStiYa, hdr-W) kti
TOJ11G TAGS: flexible plate Ugh frequeney vibration., te"rature fieldo varlaw
)I
resonant state
tional calculus
ABSTIMCT: Consider a flexiblo isotropic plate of t1dickness h in a Cartesian
i courdlinat-a syelem. The rectangular plano of the i)L-,t,3 is hinged around Its perim-
eter and is subjected to a Nagh-f requercy 11on-itu Jinal load
:A
and temperature 7' T(z, t) T(-2) t't. The ola-aticity modulus 9 is assumed to be
a function of the tegpuraturo. t i f lynawn, i c stability are obtalnPA on
the bases of the hypotheses that nomial dispiAceiiarts arg uoiTV-arablq to t!i-
.thickness$ that the plate normal dooz n~A def orm, and tl~wt to.--perattrre ctiwgos ill
g d-4ferwAial al--mnt do not induce iisplacomeniz, For an appraximate solution

L 29541-65
AGCSSSION NR: AP5005179
it is assumed tha, during a prjuu;-Ipa~ ,araffnitric reso--,%noe period, the hent ,-A
-where
,Using the Galerk.Ui-Bubnov variational piInciple, thn rei;nlt obtained !B
Cill -3- T (Id f-'
where tne uhar,,;Q5 are v,) rv ar-q. 7~1q.
uxv ourwas A solution for 04 iv
jk
aiso given for the conditions
E - E, - 67, 7 - B(:Itl E - F, -
Orig. art, haq: 2L- equatIons.
jLSDCJP.TTCNi none
SUBMITTEDi 12Jun6h Om COD92 AS 4
OC7 OJQ
A

;soimu: AN SSSR- Izvestiva. Wkhanika, no. 4, if-;
-elastIcity mod u1i *mate ri (a:) -un-equal
st rt~i I ti-tty thec~ry, shell strera, vh~ll df:fnrmntinn~i~
~ARSTRACT: Before starting to discuss the problem, the !,Lsti-ity relationships are
LCard I/J-

L 65ozo-65
and
F; rs t h P !-,I r~ul WIS ;V
L
7,at-i,,)n or Tne vr7,niuir ill
TT,
Card.

.,~. . : !T~,: ." V.4 2
1
, 1. 1
-!, :~ 6'~

NAZAROV, Armen Georgiyevich; AMBARTSWYAN, S.A., akaderik, otv.red.;
ZAIT11YET, K.S., akademikp retsenzent; NAITTVA]RIDZE, Sh.G.,
prof., retsenzent
(Mechanical similitude of solid deformable bodies; the theory
of simulation) 0 mekhanicheskom pcdobil tverdykh deforml-
ruemykh tel; k teorii modelirovaniia. Erevan, Izd-vo A.N Arm.
SSRp 1965. 217 p. (MIRA 18:10)
1. AN Gruzinskoy SSR (for Zavriyev). 2. AN Arnyanskoy SSR
(for Ambartsumyan).

L 06223-67 EA-f(d)/- (m)/h-WP(w)/E'V7P(t)/E 1----1JP(0- JPAM-
ACC NR. - ------ ------
AP6024189 SOURCE CODE: UR/0424/66/000/002/0044/0053
AUTWRS: -Ambartsw-au S.,.A, _(Yerevan); Khachatryan, A. A. (Yerevan)
~~ C 161,
ORG: Insillute of xathemgtico and Mechanics
,-Ali Armenian SSR (Institut matematiki i
mokhaniki AN ArrQranskoy SSR)
TITLEi Basic equations of the theory of elasticity for materials rosistine both
extension and compression
SOURCE:- Inzhonernyy zhurnal. Mekhanika tverdogo tela, no. 2, 1966p 44-53
TOPIC TAGS: elastic theory, Hookes Law, stress analysis, matorial doformtJon,
material strength
ABSTRACT: An attempt is made to derive the basic equations and relationships of the
theory of elasticity for materials resisting both extension and comprussion. It III
noted that the modulus of elasticity may differ for tho samo M terial In comproqsJon
and in tension and that -the Poisson coefficients for each castf may also dIffor, A
Cartesian coordinate system is used to state the problem. For e".nirle, the fitroos
equilibrium condition is given as
aX.X .1-'l -X T~V TIM
XV"' ~- Ti:,, +0.
1r.... + ami. + TV, 9 + T'X
+ + 0'.' + Z 0,
Card

ACC NRt
AP6024189
Cri , ~1' k
whore %.1 are normal and tangential stresses, and X, Y, Zare global force
components. Cyclic permutation of these equilibrium conditions allows the remaining
conditions to be written in xyz. Additional equations are given in definition of
deformation and geometric relationships. Hooko's Law is applied to the analysis of
a volume element, and the deformation of the element is studied for the case of com-
pressive principixI stresses and for tensile tertiary stress. Deflections are analyzed
in reference to a rotated coordinate system. The Lamg equations are derived, and the
solution for those equations stems from consideration of the strain continuity leading
to the Beltram relationships. An analytic expression for the shear modulus is found.
The analysis is also extended to the case of a hollow cylinder in torsion, Orig, art,
has: 65 equations and 2 figures.
SUB COLE: 3.19 12, 20/ SUBM DATE: 09Deo65/ ORIG REFi 004
Card 2/2

ACC NRi AP7002693 SOURCE CODE: uR/oh24/66/ooo/oo6/0O64/OO6T
AUTHOR: Ambartsumyan, S. A. (Yerevan); Khachatryan, A. A. (Yerevan)
!ORG: none
:TITLE: On the "bi-modular" elasticity theory
,SOURCE: Inzhenernyy zhurnal. Mekhanika tverdogo tela, no. 6, 1966, 6h-6T
I
;TOPIC TAGS:
!ABSTRACT:
elasticity theory, elastic modulus
Certain-problem-9 'of elasticity theory, applied to "bi-modular" materials
which possess different moduli (strengths) in tension and compression are
discussed, and the validity of some formulas and theorems of this theory
for "bi-modular" materials is proved. The generalized law of elasticity
in the "bi-modular" theory is examined in a case when one of principal
stresses has a sign different from the signs of the other principal
stresses, and the directions of principal stresses do not coincide with
the orthogonal co6rdinate axes. Expressions for the specific pctential
strain energy of a body made of a "bi-modular" material are derived ia~
terms of stresses and in terms of strains, thus proving that the Clap Fon
formula is valid for these materials. It is also proved that the
Castigliano formulas are valid for "bi-modular" materials. The.Clapeyron
formula for the potential strain energy in stresses and strains in also
IUDC* none

ACC NRs AP7002693
given in another form'by using the Green and Castigliano formulas. It
is also indicated how it is possible to prove the validity of the i
Clapeyron theorem. the Lagrange and Castigliano equations in variations
for the discussed "bi-modular" materials.
Orig. art. has: 29 formu-
las.
SUB CODE: 20/ SUBM DATE: 27jun66/ ORIG PXF: 004/

PAPOYAN, S.A.., starshly nauahnyy sotrudnik; X\IBAPITSMAN, S.G.
Osteogenic sarcomas induced I*r radioactive strontium-90
aild the possibility of their utilization for exporim3ntal
chemotherapy. Vop. radiobiol. [Ali Ann. SSR] 1:137-139 160.
WIRA 15:3)
1. Iz Institute. tontgenologii. i oWcologii i Sektora
radiobiologii AN Armyanskoy SSR.
(CHEMOTIERAPY) (STRO11TIM-4SOTOFES)
(BOOS.-GANGER)

PAPOYARP S.A., starshiy nauchnyy sotrudnik:~ KI'MRODYAN, F.A.,
starshiy nauchnyy aotnidnik; AIABAfiTSUMWI, S.G.
X-ray characteristics of the osteogenic sarcomas caused by
radioactive strontium-90 in rats. Vop. radiobiol. [AN Arm.
SSR) 1:141-]J~7 160. KRA 15:3)
1. Iz Instituts. rentgonologii i onkologii i Sektora radio-
biologii AV Aimyanskoy SSR. -
(STRONTI%I- JS OTOFES)
(BONZS-CANCER)

ARRYUMN, R.K. 0 kand. biolog. nauk; AMBAWMMIAN, b.G. p m1adshly nauchnrj
sotrudnik
N.E. Vvedenakii1s optimum and possimam phenomena in the cerebral
cortex of rabbits following radiation injLry, Vop. raaiobiol, [AN
Arm. SSHI 3/4:173-lits 'b3o ktIIL4 I'llb)

AFCI*l]JNYANI R.K.0 kanue bloi, nauk; GAMIELIAN, la.fj., ojtulally nuu(innyy
sotrudnik; AlibAlfrSUMUN, "I.G.p ffdauskuy naun%nyy voLrurinik
- -.- - .... -- -
I=ect of direct ctirrent on the blood catalase activity in
irradiated rats. Yop. radiobioi. [AN Am. SSHJ 3/4t2b9-291
'0. L/:b)