SCIENTIFIC ABSTRACT VAKHIDOV, V.V. - VAKHITOV, YA,SH,

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001858410010-3
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: August 31, 2001
• Sequence Number: 10
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

I,- TAKRIDOT, V.T., dotseut
Benign neoplasms and cysts of the lungs and medlastimm. Med.
shur.Usb. no.6t26-34 is 158. (KM 13:6)
1. Is kafedry obahchey khIrtirgil lechobnogo fakulftets, (say. -
Prof. Xh.G. Gafurov) Tashkentskogo gosudaretvonnogo neditsim-
skogo instituta.
(LUIG--TUNORS) (CYSTS)

VAKHIDOV,_V.Vp U.med.nauk (Tashkent, ul- Karla Markma, d.59) RTABUKHIN,
I.A., kaud.med.nauk
Reconstructive operations on the extrahapatic b1le ducts in c1cat-
rical stenosis. Vest.khir. 83 no.1008-54 0 159. (MIRA 13:2)
1. Iz kafedry obahchey khirureft (saveduyushchiy - prof. Kh.G. Gafurov)
Tashkentsk o maditainakogo instituta.
TILE DUCTS diseases)

'VAKHIDOV, V-V-, dotsent
Histogenenis and structure of the pleural adhesions; experimental
and clinical studies. Med. zhur. Uzb. no.11:40-44 11 161.
(MIRA 15:2)
1. Iz kELfedry obshchey khirurgii Moskovskogo stomatologicheskogo
instituta (zav. - prof. B.B.Linberg) i kafodry obshohey khirurgii
(zav. - prof. Kh.G.Gafurov) lechbbnogo fakullteta Tashkentskogo
gosudarstvennogo meditsinskogo instituta.
(PLEURA-DISEASIZ)

VAKHIDOV,, V.V., dotsent
Treatment of spontaneous pnewaothorax. Med. zhur. Uzb. no.12:25-27
D 161. OUSA 15;2)
1. Iz kafedry obshchey khirurgii Moskov3kogo stomatologicheskogo
instituta (zav. - prof. B.E.Linberg) i kafedry obshchey khirurgii
lechobnoeo fakullteta (zav. - prof. Kh.G.Gafurov (deceased])
Tashkentskogo gosudarstvennogo moditsinskogo inatituta.
(PNEUMOTHOW)

VAKHIDOV., V.V., dotsent
Histogenesis and strurture Of pleural adhesiM experimental
arA clinical studies. Report 11o.2. Ifed. zhur. Uzb. no.l:
54-59 Ja '62. (MIRA 15:3)
1. Iz kafedry obshchey khirurgii I/loskovskogo stomatologicheskogo
instituta (zav. - prof. B.E. Linberg) i kafedry obshchav khirurgii
lechebnogo (fakullteta Tashkentskogo gosudaretvennogo meditsin~-
skogo instituta (zav. - pwof. Xh.G. Oufurov [deeemmd]).
(ADIESIOM (AMT00))

VAKHIDOV, V.V., dotsent
...................... .,
Histotopographical structure of the blood vessels in inflamma-
tory adhesions of the pleura. Med.zhur.Uzb. no.3:49-54 Mr r62.
(KMA 15:12)
1. Iz kafedry obshchey khirurg# (zav. - prof. B.E.Linberg)
Moskovskogo stomatologicheskogo instituta i kafedry obshchey
khirurgii lechebnogo fakul'teta (zav. - prof. Kh.G.Gafurov
[deceased]) Tashkentskogo gosudarstvennogo meditsinskogo Instituta.
(PLEURA) (ADHESIONS (AMTOMY)-BLOOD SUPPLY)

VAKHIDOV, V.V.
Vascularization of pleural adhesions. Eksper- khir. i anest. 7
no.4:16-20 J1-Ag 162. (MIRA 17:5)
1. Iz kafedry obshchey khirurgii (zav. - zasluzhennyy deyatell
nnuki lattroat Laninnkoy premit B.E,.Unberg) Monkovskogo ntovito-
logichaskogo Instituta i Iz kal'edry obshchey khiriirgil 1notie--bnogo
fakiillteta (zav. - prof. Kh.G.Gaftirov) Tashkentskogo meditsinakogo
instituta.

GkSPARYAN, Iv" Gavrilovich,, prof.; VAKHIDOV, V.V..,_dots., spets.
red.; AVAKIMOVA, L.A., red.izd-va; SUKHANOV, P,P,,,
tekhn. red,
(Tuberculomas of the lungs] Tuberkulonq legkikh. Tashkent,
Medgiz UzSSR, 1963. 76 p. (MIRA 17:3)

V-i'~IiDOV V.V dotsent; AZIZOV, N.A.; IMAMOV, T.Kh.
Late results of lung resection in tubercuics-Is. Frc~.'. tub. 42
no.8:28-32 164- (MIRA 18,D)
1. Kafedra, obshchey khirurgii (ispoInyayusheldy o1rjazannosti
zaveduyushchego - dotsent V.V.Vakhidov) lechebriogo fakull-
t~--ta Tashkentskogo meditsinskogo instituta i khirurgicheskoye
ot.deleniye protivotuberkulemogo dispansera No.2 (glawiri
vrach N.A.Azizov), Tashkent.

j
ARSVO.SELY, I.Pt,;
vation .P-nt.:--r of !,hF- hf:iart al'i J:DWC-7- fr'onkoyti (Xa,-a-~a), Biul. --~sP-
biol, i joed. 57 ro,4,12-36 Ap '64, (VITIRA 18-.3)
I.. LabovsitoT ~yli I-atolcwti (Zav, - prof ~ I A
Arshwrskiy) 1notAtut.9 normalltricy
dey3tvotellnyy r--hlen AMIT SSSR Pain) A.MN SSSR) MIcnk-.-a. S-il-mdtti-d
April 28, 1963~

Analy--s of th,~-
va-riouo ages. Blul. hi,il. i ned. 59 F
0", -- I '! : 7)
z v
Laboratorlya vozra-~'Aloy i- P- t-0101- a
II.P . Arshavokly), lns~,, nor--mllnoy 1 pqtolG9lc!,e--,'l-~--,Y
-
IoV -A*-i Wir. .. doyo tv i !,l 7.. ln~li-.v AMN pro . v
AMII SSSR, Moskva.

YUKUSOV, A.Yu.; MAXHMUDOV, E.S.; VAKHIDOVA, R.T.
Effect of a predominantly protein and carbohydrate diet on
salt and water metabolism at high temperatures. Izvkff Uz.
SSR.Ser.med. no.2;35-44 '58. (HIRK 12:5)
1. Inatitut krayevoy zeditsiny AN UzSSR.
(BLOOD--ANALYSIS AND CHEMISTRY) (SALT IN THE BODY) (DIET)
(HEAT-PHYSIOLOGICAL EMCT)
I

YUNUSOV, A.Yu., akademik; VAKRIDOVA, R,T.
40.
Affect of stimulation of interoceptors of the digestive tract on the
saline composition of the blood. Izv. AN Uz.SSR. Ser.med. no.4:3-8
159. (MIRA 12-12)
1. AN UzSSR (for Yunusov). 2. Institut krayevoy meditainy AN UzSSR.
(DIGICSTIVIC ORGANS) (BLOOD--ANALYSIS AND GMISTRY) (F&JIMS)

VAKHIDOVA, R. T.
Cand Biol Sci - (dissJ "Effect of irritation of the mechano-
receptors of the gastro-intestinal tract on the water-salt
metabolism under conditiona of high temperature." Tnfihkentj
1961. 19 pp; (Academe of Sciences Uzbek SSR, Inst of Kray
Experimental Medicine ; 160 copies; price not given; (KL, 6-61
sup, 206)

VAKHIDOVA, R.T.
Influence of stinflation of the mechanoreceptors in the gastrointes-
tinal tract on some blood indexes at high temperature. Med. zhur.
Uzb. no.401-34 Ap 161. (MIRA 14:5)
1. Iz laboratorii J"iziologii (zav. - prof. A.YuJunusov) Instituta
kravevoy eksperimentallnoy meditainy AN UzS8R.
(DIGESTIVE ORGANS) (RECEPTORS (KEWROLOGY))
(BLOOD) (HEAT-PHYSIOLOGICAL EFFECT)
(SOLAR RADIATION-PHYSIOLOGICAL EFFECT)

VAMOVt A. Z,
VAKHILCIV, A. Z. - *Topographico-Analytic Interrelations of the Lumbar Triangles and
the Costo-Diaphragnatic Sinuses in Connection with Access to the Subdiaphragmatic
Spaces." Samarkand State Mad Inst Imeni Academician 1. P. Pavlov, Samarkand,, 1955.
(Dissertation For the Degree of Candidate in Medical. Sciences).
SOs Knizhnava letopis'. No. 37, 3 September 1955

NLI-1- Rr.7
- F14
1 1- - -- - 7 -, 'I'- - . .-- - It- _ - - -
-.- --- - - 0 itl.' i-k - - -- ---k - , -U119 .~t - I . -
I ',X ki ~ -, )- --I- .- ... - - .- I

V Cj/r ~j / la t~' 0 0- 124-1957-10-117990
Translation from: Referativnyy zhurnal, Mckhanika, 1957, Nr 10, p 86 (USSR)
AUTHORS: Vakhitov, G. G., Govorova, G. L.
- ----------------------
TITLE: Some Radial Problems of the Displacement of Petroleum by Water
From a Non-uniformly Permeable Layer (Nekotoryye radiallnyye
zadachi vytesneniya nefti vodoy iz neodnorodnogo po pronitsayemosti
plasta)
PERIODICAL: Tr. Vses. neftegaz. n.-i. in-ta, 1956, Nr 8, pp 250-261
ABSTRACT: The problem of the radial displacement of petroleum by water
in a layer of uniform thickness containing two annular zones of
different permeability is examined. The difference in the Vi5-
cosity of water and oil is taken into account as well as the de-
creased phase permeability relative to water in the displacement
region, which is regarded as approximately constant, The fluids
and the soil stratum are regarded as incompressible and the
seepage as laminar. Also investigated is the case of n annular
concentric zones of different permeability. An example demon-
strates the effect of non-homogeneity on the time of contraction
of the petroliferous contour toward an annular tunnel.
Card 1/1 V. L. Danilov

SOV/124-58-4-4329
Translation from: Referativnyy zhurnal, Mekhanika, 1958, Nr 4, P 91 (USSR)
AUTHOR: Vakhitov, G. G.
TITLE: Solution of Problems of Underground Hydrodynamics by Means
of the Method of Finite Differences (Resheniye zadach podzemnoy
gidrodi-,amiki metodom konechnykh raznostey)
PERIODICAL- Tr. Vses. neftegaz. n. -i. in-t, 1957, Nr 10, pp 5 1-87
ABSTRACT: The article considers application of the method of finite
differences for the solution of oroblems pertaining to the see--
page of liquids into fully or pa;tly penetrating shallow wells
within a layer having nonuniform physical parameters, when the
outline of the influence zone is arbitrary. The zone of seepage
D is approximated by a flow-net region lying either partly or
wholly within the zone D. The boundary conditions along the
influence-zone contour are transferred to the border of the
flow-net region by interpolation. The wells are considered
as points and are located in the nodes of the flow net. Methods
are developed for determination of the pressure and velocity
fields in a nonuniform layer for the producing wells and the
Card 1/2 injection wells. A correction coefficient is introduced for

SOV/1 24-58-4-4329
Solution of Problems of Underground Hydrodynamics (cont. )
determination of the yield of the wells in order to account for the effective
well diameters. The problem of the selection of an optimum spacing of the
flow net is analyzed. The accuracy of the results is illustrated with a large
number of examples suitable for theoretical solution. Bibliography: 5
references.
P. F. Fil'cbakov
1. Wells--Water supply 2. Water--Motion 3. Hydrology 4. Mathematics
Card Z/Z

YERONIN, V.A.; MALIYS37, M.V.; VAKHITOV, G.G.; SULTANOV,S.A.
,
Introducing new machinery and methods in the exploitation of
Tatar oil fields. Neft. Khoz. 35 no.10:211-31 0 157. (MIRA 11:1)
(Tatar A.S.S.R.-Petroleum engineering)

S-)Y/93-58--7-7/17
ADTHOR: Vakhit~,Y~ G.G.; lerLain, V.A.; MiailtBev, M.V.; Cholovskiy:, 1.P.
TME: S+,-atA azd DovelcPn*nt rf the R~M-qhkiz-- Oilfi~,,ld :U~
the Tat%r ASSR (Tsk-lghcheYe Sostj!~'Y&IiYe i za4achi dallz!t-YOMY rai;ral'-~~.kl
R--mashIdY:.ski,S7 meborozMeniya Tttarskc;j ASSR)
PERIODICAL: N,-.ft;jWZ -Ye khozYaYstm), 1958, Nr 7, PP- 31-37 (TJSSR)
ABSMACT: V6e allf1eld of tle War ASSR was diso-,,vered in %7,~.Iy 19119.
A', +,bLLs ff-~2A the ~41 of ci:,,anercial value ie in tbe oil-bearing smnds of the
Dill* V-~ D-r - W-,d Do (',-be- Rikhaylovskiy) Dr.--rcUsa. fca-m&ticas, as well as in
the swnis -,:f the carb,-aaceo-as fcrmation of lower cafr,=- The Dj-
f^WM*,.I'.'X. Is -'*.e and it has-been afiiitrarlly ai*divided int-)
I-Q,", fs: w.,;I e. The d aad e layers have better por.)sity and per-
--11 capack"'Y. Fig. 1 praseats the Evological pr.-,)fiel
f tlii~~ R-mashkin-~~ c1iffleld., which is bei-rg acc=d1mg t,) a VNn. acbeme
Tlilz eabeme. p=,-j-jja-. .0--r cf rezarnlr press-am by w.;&zs c,f water
a-rA this makes it pcesible t-, artificially sepamte the otifield irr~tj
9:7A t:, expL~it -,;he rivla la~~.rs -,f the D fcrmatic. J:~Lnci;34-. C:-,~--
c:~.Ly -1-f the 23 reserv~-irs arz beir-S c~nWrcial-',y expYiinl-
PtLv1-:vsksya,.
a.--1 &I'metlytv !-.il reser~r-dra
Ead R-ig-- ma z-ilfield admiz-
Fig. 2. 7
I
are 3--~ nharge .~f tbe 'i1 m-sen)".irs. Table 1 preEe-ls da;'~% ,-,a

Sov/93-58-7-7/Yl
.zx,sen-b State! amd Yatrre Development of (Cont.
well spac:LrZ &',, the oilfield. The high operating pressure on the injection
litas has made it possible to increase the volume of wa+---r injection (Pef.1).
SUfts irn -.be oil-bearing contours were determirpd by a 1957 TELtNII study asing
is.:~t'ar maps (Ref.2). The oilyield was increased by fractzing the formtion,
Wf.3). By April 1958 ab(YxI, 127 wells were being exploited either by M or
SKN-5 ymps. The 9~..,-,~hors make seven suggestions for the improvement, of the
Rcmshki:r..N oilfield exploitation. There are 2 figilms, I table, and 3 Soviet
references.
Card 2/2 1. Pet--oleum--USSR

1. VAMITOVI G.G.; SULTANOV, S.A.
Results of the development if the Romashkino oil field, Geol. nefti
i gaza 5 no. 5:12-18 My 161. (KIRA 14:4)
1. Tatarskiy nauchno-iseledovateltakiy neftyanoy institut.
(Ramashkino region-Oil fields-Production methods)
11

VAMITOV, G..G.; SULTANOV, S.A.; ONOPMENKO, V.P~; KLYA-ROVSKIY, G.V.
Additional sectionalizatlon of certain areas of th-p ',:~=ashki_no
field. Neft. khoz. 40 no.10:28-33 0 162. '~;FR~ 16:7)
(Romashkino region--Petroleum troduction)

'VAKH1TOV G 6_11
a ell Galyautdi.no Cb; LATUKRINA, Ye.l., ved. red.;
STAROSTINA, tekh-n. red,
(Effective means for solving the production problems in
nonuniform oil-and water-bearing layers fW the fi~141te
difference method] Effektivnye sposoby resheniia zadach
razrabotki neodnorodnykh neftevodonosnykh plastov meto-
dom konechnykh raznostei,, Moskva, Gpstoptekhizdat,
1963. 215 P. (MIRA 16:11)
(Petroleum engineering)

-I-
CHEMODANOV, V.S.; OSHITKO, V.M.; SULTANOT, S.A.; VAKHITOV, G.G.;
FMYANj 1.G. - , -
Conversion of reserves and the determination of thm recovery
factor (,,' a flooded section 6f reservoir Di in the Bavly
field, Nefteprom. delo no.ltl3-15163 (MIRA 17t7)
1. Tatarskly neftyanoy nauelmo-issledovatel'skiy institut,
g. Wgul"ma I Noftepromyolovoyo upravrIonJye "Bavlyneft'".

BEGISHEV, F.A.)_YAKHITOV. G.G.; SULTANOV, S.A.-, CHOLOVSKIY, I.P.
Controlling the development of horizon D of the Romashkino
oil field. Geol. nefti i gaza 7 no.lW~-26 0 163.
(MIRA 17:10)
1. Tatarskly neftyanoy nauchno-Issledovatellskiy inatitut,
go Bugullma.

47152-66 EWT(d) IJP(c
:C NR, AR6000720
SOURCE CODE;
122
AUTHORS: Vakhitov, G. G.;._Alishayev, M. G. 40
TITLE: Investigation of difference schemes for nonlinear equations in unsteady S
filtration
SOURCE: Ref. zh. Mekhanika, Abs. 9B807
REP SOURCE: Tr. Tatarsk. neft.-n.-i. in-t, vyp. 6, 1964, 195-211
TOPIC TAGS% difference eauation, nonlinear equation, filtration. JCkV to AA 7ej
PR e J-1 UR 8
ABSTRACT: Difference schemes are investigated for parabolic type nonlinear equations
describing the unsteady seepage of liquid in a bed whose permeability and-piezo-
conductivity depend on the pressure. It is shown that the nonlinear equation under
consideration leads to a linear equation for the case when a constant pressure and a
constant flow rate are maintained on the contourg if only the permeability of the
bed depends on the pressure and not the piezoeonductivity. The investigated equation
is replaced by simpler nonlinear finite difference schemes. Applying the'principle of
"freezing" of coefficients and nonlinearities, the authors have obtained a practical,
satisfactory criterion of stability in the explicit finite difference schemes. The
applied implicit schemes are always stable. To consider stability and converge-ace
problems under,stricter formulation, the properties of the solutions of the applied
finite difference scheme are considered. Bibliography of 11 citations. G. R.
Gurevich Oranslation of abstract7
SUB CODE: 20
r-A 1/1 -exz-~

A
L 05679-67 E7,-.JT( e' IJP(c)
lfi= NRt AR6023242
SOURCE CODE: UR/0044/66/000/003/B106/B106
AUMOR: Alishavev, M, G-, Mbit0v, G, ra -
REF SOURCE: Tr. Tz.tarsk. neft. n.-i,__~n t, vyp. 8, 1965, 336-344
TITLE: On the spcitrwir and stability conditions of several difference schemes
SOURCE: Ref. zh. 4atematika, Abs. 3B557
TOPIC TAGS; diffe_~_-nce equation, stability condition, partial differential equation
TRANSLATION: The wethod of separation of variables is used to investigate certain p:
perties of the tot--'Lity of eigenvalues of difference equations fn particular suffi-
cient conditions for stability are adduced) which approximate the heat equation with
variable coefficients
and the simplest boundary and initial conditions.
SUB CODE: 12/
SUBM DATE: none
UDC: 518:517.944/.947

TAKHITOT, 14j.
-.3 -`,*,,,-,-'-',,
,,- Ifirl"e'se analysis of a raked wing of monol7thic design. Izv. vys.
ucheb. say. no.1:61-68 058. (MM 11:3)
1. Kafedra strottellnoy mokhaniki samoleta XELzanskogo aviatsion-
nogo inatituta.
(Airplanes--Vings)

83793
5/124/6o/boo/boB/on/b_~i
A005/001 .
Translation from: Referativnyy zhurnal, Mekhanika, 1960, No. 'j, pp. :54-155,
# 10867
AUTHOR: Vakhi"-ov, M. B.
-
V-,
-
-
MMUNUAWASK16i"
TITLE% The Calculation of the-Monolithic W1n;4trerZth W11% A].1cwa_-e-6 for,
Variability of the Load In the Deformation Process
PERIODICAL- Tr. Kazansk. aviats. in-ta, 1958, Vol, 38, PP. 135-159
TM, The author presents an approximate proQedur-~ of the statul;a!
strength calculation of a monolithic swept-back wing, which takes into at~count
the variability of the aerodynamIc load in consequence of the dsf-irmation of the
wing in flight. It Is assumed that these deformations do no" affsot the aer-o-
dynamic characteristias of the wing and are reflected only In the magr-It-ide of'
the angle of incidence. 'The wing is considered as a -.hin *,apered plati~- rein-
forced by stiffening ribs parallel to the oblique coordinate axes. Tnp defi&,2-
tion function W(~ 13 exparded into a serfee.
w
To (1) + ?I
T2
Card 1/2

Aw
8379)
S11241601000100810--'10211,
A005/AOOI
The Calculation of the Monolithic Wing Strength With Allowance for the
Variability of the Load In the Deformation Process
from which or-ly a finite number of terms is retained, The author expresse-, t";- e
variation of the elastic potential plate energy through th~i
of the series, equates this variation to the psrformanf~-e of" the 6xt.s-nad
in the possible displacements, with allowance for .--ompo.-aents whi-h
owing to the wing deformation, and obtains for the '.~wkn:wr fIX-IC '1CM5 q~
system of linear differential equations and ba-indar-), ce-nditicns -L-. a r'--~.mtEtr
sufficient for the complete determination of rf (-q) , '117e detili~-d
presented for the case, when one rest~~I,~ts ta exptLnsio:, Of t'n~- fl'r---t
and certain possibilities of simplifluattons are oonslde~~d,
N, A. Rosto-vt9ev
Iranslator's notei This is the fall tranelation of the original F~i-~5!an
abstract.
Card

SOV/123-59-15-61175
Translation from: Referativnyy zhurnal. Mashinostroyeniye, 1959, Nr 15, p 319 (USSR)
AUTHOR: Vakhitov, M.B.
TITLE: Functions of Monolithic Wings
PERIODICAL: Tr. Kazansk. aviats. in-ta, 1958, Vol 43, PP 3 - 16
ABSTRACT: For the calculation of arrow-like wings with a thick covering which are
reinforced by longitudinal framing along the generatrices and by ribs,
plates are taken as calculation models. The functions of the plate-wing, re-
presenting deflection at a given point produced by a single force applied to
another point, are determined. An expression for the deflection functions
of the plate is chosen, which is expanded into a series on the coordinate
along the stream-line chord. Expressions for the variations of the internal
energy of the plate and the work of external forces are correlated. The
equalizing of these expressions after integration results in an equality
from which the equation for determining the coefficient of the deflection
function is obtained. From this equation, on the other hand, both the
boundary conditions and the conditions of conjugation in the cross sections,
Card 1/2 to which concentrated loads are applied, are obtained. Because of the com-

3011/123-59-15-61175
Functions of Monolithic Wings
plexity of the equation for deriving the functions which serve as coefficients of the
series of deflection function, the solution is limited to two terms of the series, re-
presenting the deflection of the wing axis relative to this axis (the axis is chosen
conditionally). It is shown that the obtained equations permit to determine the functions
affecting the wing separately for the conditional bending and twisting unit loads obtained
by transposing the applied loads onto the conditional axis. The order of determination of
the functions of the bending and twisting effect is given. The deformation of the shape
of the cross-section of the wing can be taken into account by the third term of the ex-
pansion of the deflection funniction, but this would lead to complex formulae. It is
mentioned that the solution of the obtained equations for the constant cross-section can
be obtained with the aid of electro-integrators, but for the wings with variable cross-
sections with the aid of electronic digital computers.
K.I.L.
Card 2/2

SOV/147-59-2-6/20
AUTHORt
TITLEi Determination of the Modes and Frequencies of
Bending-Torsional Oscillations of a Helicopter Blade
Using Matrices (opredeleniye form i chastot
izgibno-krutilInykh kolebaniy lopasti vertoleta s
pomoshchlyu matrita)
PERIODICAL:Izvestiya vysshikh uchobnykh zavedeniy, Aviatsiorinaya
tekhnika, 1959, Nr 2, PP 39-48 (USSR)
ABSTRACT: Only the bending in the flapping plane (i.e. the
plane perpendicular to the plane of rotation) is
considered. Bending in the plane of rotation
following the recommendations of Ref 5 is not
included. To evaluate the dynamic strength of a
helicopter blade it is necessary to know its modes
and frequencies of free oscillations. As shown in
Fig 1, a blade is essentially a rod, hinged at one endi
the modes and frequencies of a deformable blade (but
which does not rotate in the plane of flapping) are
usually obtained from the differential equation for
the transverse oscillations of beams (Eq 1) by
Card 1/6 introducing suitable boundary conditions, in conjunction

SOV/147-59-2-6/20
Determination of the Modes and Frequencies of Bending-Torsional
Oscillations of a Helicopter Blade Using Matrices
with the method of successive approximations, similar
to the procedure used for calculation of the airscrews
(Ref 3)- In this method, at each successive step,
it is necessary to consider the orthogonality of the
given (obtained) tone with all the preceding tones,
due to which a great volume of work is involved. If
this method is extended to include the simultaneous
bending and torsional oscillations, the solution
becomes even more difficult (because there are two
simultaneous differential equations) and the volume
of calculation increases still further. Howeverl
if the matrix method is adopted instead (see Ref 4)
the labour needed to evaluate higher overtones
decreases firstly, bezause there is no necessity to
ana.&yse the orthogonaaity of the modes and secondly
because the order of the dynamic matrix decreases with
the order of the mode. In addition, the effort to
obtain the solution in the same whether the mass is
distributed or concentrated at a number of points.
Card 2/6 Finally, the matrix method has the advantage that it

SOV/147-59-2-6/2o
Determination of the Modes and Frequencies of Bending-Torsional
Oscillations of a Helicopter Blade Using Matrices
is suitable for electronic digital computors, the
programming being the same for all possible cases.
The matrix method has not been used previously
because, in order to form a dynamic matrix, it is
necessary to know the influence coefficients for
the blade (i.e. deformations due to unit loads) and
these are indeterminate since the geometry of the
blade is variable. In this paper the author makes use
of the influence coefficients of a cantilever beam
(with one end rigidly fixed) in order to develop the
equations for free oscillations of the blade in
matrix form. The beam is further divided into a
number (n) of small segments each of a length 6xi
(Fig 1) and the segments are then replaced by
concentrated loads at the centre of mass of the
segments. Assuming now that the tangent (og in Fig 2)
to the deformed neutral axis of the blade at the hinge
makes only a small angle Ir with the original form of
Card 3/6 this axis (straight line ox), deflections fi of any

SOV/147-59-2-6/20
'Determination of the Modes and Frequencies of Bending-Torsional
Oscillations of a Helicopter Blade Using Matrices
point of the blade are given by Eq (2) and from the
approximations of Eq (3), Eq (4) is obtained, from
which eventually Eq (5) follows where 7 and X are
the columns consisting of 2n elements. Introducing
next the influence coefficients Aik for bending and bik
for torsion (these represent respectively deflections
and angles of rotation of the croAs-sections at x = xi
due to unit transverse load and unit torsional moment
applied at the sections x -xk),and forming the matrices
for them, Eq (6) is obtained; whenc" by Eq (7) we
get Eq (8) Then by Eq (8) and (5), we obtain Eq (9).
To eliminaie W' from this equation the equilibrium of
the blade is considered (moment of all inertia forces
with respect to the hinge must be equal zero), then
Eq (10) may be derived, which together with Eq (9)
leads to Eq (11). Separating variables and using
relations (3) and (4) we got Eq (12) (where -%4 is the
circular frequency) and with its help, Eq (5), (8) and
(10) transform into Eq (13) to (15), while Eq (11)
Card 4/6 leads to Eq (16). Thus the well known result that the

SOV/147-59-2-6/20
Determimati.on. of the Modes and Frequencies of BendIng-Torsional
Oscillations of a Helicopter Blade Using Matrices
blade has a zero mode of oscillation with zero
circular frequency (Ijo - 0) and yo = X, corresponding
to the rotation of the blade as a rigid body about
the axis of the hinge Q'W axis in Fig 1) is
exhibited. It is then shown that the modes of
oscillations as given by the roOtB of Eq (16) possess
the property of orthogonality, this in done through
Eq (18) to (23)- Transforming Eq (16) so as to
exclude the zero mode of oscillation (the non-zero
modes of oscillation must wtisfy Eq (25) ), Eq (26)
is obtained which is again transformed to Eq (27).
Thus the problem of finding the modes and frequencies
of oscillation reduces to that of finding from Eq (27)
some natural numbers Xi (with the largest value of the
modulus) and the corresponding natural vectors yi,
which may be done using the method of successive
approximations. A simplification of the problem is
obtained, if the centres of gravity of the cross-
Card 5/6 sections coincide with the elastic axis of the beam,

SOV/147-59-2-6/20
Determination of the Modes and Frequencies of Sending-Torsional
Oscillations of a Helicopter Blade Using Matrices
further oscillations are not coupled; Eq (29) gives
the bending and Eq (30) torsional oscillations,
respectively. In Table 1 and Fig 3 a comparison is
made between the results obtained by the above method
(Eq 29) and from the known solutions of the
differential equation (Eq 1) for a blade of a
constant profile (cross-section). The fundamental
(Ist) and the 2nd mode only are considered. The
frequencies so obtained show good agreement. In
conclusion it is stated that the method can be
extended to the case of coupled oscillations by
taking into account bending of the blade in the plane
of its rotation. There are 3 figures, 1 table and
5 references, 4 of which are Soviet and I English.
ASSOCIATION: Kazanskiy aviatsionnyy institut, Kafedra
stroltellnoy mekhaniki samoleta (Kazanllnstitute of
Aeronautics, Chair of-The~~ Aircraft
SUBMITTED: January 6, 1959
Card 6/6

68933
It
.2~. 9/00 s/147/59/000/04/008/020
/A CDOO Eigi/E481
AUTHORt Yakhitov, M.B.
- ------------
TITLEt Static Analysis of a Helicopter Blade for Flexure in
the Flapping Plane
PERIODICALsIzvestlya vysshlkh uchebnykh zavedeniy, Aviatsionnaya
tekhnika, 1959, Nr 4, PP 70-78 (USSR)
ABSTRACTs Russian strength requirements are based on the "static"
flexure of rotor blades presumably because dynamic
flexure analysis has not yet yielded good agreement
with tests. The basic equation of flexure is adopted
from Flax (Rof 6). Successive approximations have a
slow convergence. The Morris method is mentioned in
which algebraic equations in bending moments and
deflections at sections which are boundaries of blade
portions are solved. The complicated coefficients of
this system are computed by means of Berry functions,
The method proposed by the author is better suited
for work on electronic digital computers because it does
not require the introduction of Berry functions into the
computer memory. Moreover, concentrated axial and
Card 1/4 transverse forces can be introduced without alteration

68933
S/147/59/000/04/008/020
Elgi/E48i
Static Analysis of a Helicopter Blade for Flexure in the Flapping
Plane
of the method. The blade is divided into a number of
portions of equal length. The distributed axial load
is replaced by concentrated axial forces at the
computing sections which divide each two neighbouring
portions. In each section the moment of the internal
elastic forces is equated to that of the external
forces. The second derivative of the deflection is
replaced by a second order finite difference. The
friction torque of the flapping hinge is introduced as
one of the boundary conditions. A matrix equation is
derived which represents the system of equilibrium
equations for all the computIng sections. From this,
a final matrix equation follows which expresses the
deflections. The computation consists of the
multiplication, addition and inversion of matrices.
Two of the matrices consist of whole numbers which are
introduced into the constants store in the computer.
The computer memory requires the intr,3duction of
Card 2/4 flexural stiffnesses, axial loads and transverse loads.

68933
s/147/59/ooo/o4/008/020
E191/F,483.
Static Analysis of a Helicopter Blade for Flexure in the Flapping
Plane
Examples of two different blades (one weightless with
concentrated tip mass and the other with uniformly
distributed mass) are given and compared witl~ the Horris
solution and with the exact solution (for the first blade
only). The accuracy of the proposed method is
satisfactory with 10 sections. The computation of the
real bending moments Is obtained from another matrix
equation and basically signifies differentiating of the
deflection from its values at the computing sections.
In computers with 9 significant figures the loss of
accuracy is acceptable. The formulae can be
generalized for unequal blade portions. The matrix
formulae for the deflections can be used for blades with
built-in roots. One of the matrices of constants
changes. The method can be extended to the analysis of
flexure in the presence of an axial force of a beam on
two supports. There are 7 figures and 6 references,
Card 3/4 5 of which are Soviet and 1 English.

589234
8
S/147/59/000 0 /00 /020
E191/E481
Static Analysis of a Helicopter Blade for Flexure in the Flapping
Plane
ASSOCIATION:Kafedra stroitellnoy mekhaniki samoleta Kazanakly
aviatsionnyy institut (Chair of Aircraft Construction
Mechanics, Kazan Aviation Institute)
SUBMITTED: June 13, 1959
Card 4/4

VAKHITOV, M.B,
Calculation of actual forts and frequencies of vibrationA of
a m9nolythio airfoil, Izv, vys, uchebt mrs; av,tekh. 2 no,i:
16-27 '59- (MI" 12:3)
lqKazanskly aviatsionmy7 institut,,Xafedra stroitelluoy makhaniki
Samoleta.
(Airfoils-Vibration)

VAXHITOV, M.B.
-11.
Strength analysis of a flexible moualithic wing, Izvevys.
ucheb.zav.; av.tekb. 2 no.3:24-32 159. (MIRA 12:12)
1. Kasunakiy aviatsionnyy institut. lafedra stroitellnoy
mekhaniki samoletov.
(Airplanes-4ings)

SOV/124-59-8-9358
Translation fromz Referativnyy-zhurmal, Makhanika, 1959, Nr 8, p 142 (USSR)
AUTHOR: Vakhitov. M.B.
-t.U
TITLE: The Influence of the Elastici of the Riby on the Stresses
in a 2Shell
PERIODICAL: Tr. Kazan5k. aviats. in-ta, 1959, Vol 33 - 34, pp 201 - 217
ABSTRACT: The effect of shap(Ldistortion of a cross section on the stresses
in backswept yings"Is studied..which have ribs perpendicular to
the wing axis and those parallel to the flow. The shell of the
wing Is presented schematically in the form of a four-girder
prismatic box. It is assumed that the ribs fill up the internal
space of the box continuously. The backswept wing case is pre-
sumed to be consisting of two sections separated by the root rib:
the elastic triangle and the non-backswept part. The solution is
carried out for the non-backswept part, for which the elastic
triangle determines the boundary conditions in the root cross
section. This solution is reduced to determining the axial
Card 1/3 displacements of the spar girders from the system of differential

SOV/124-59-8-93,58
The Influence of,the Elasticity of the Ribs on the Stresses in a Shell
equations: d4 Ul d2 u1
r dz Ij dz2 + a (u, - u2) - d,
d u I d u2 (u d
dz4 dz2 1 - u2) 2'
where u, und u2 are the axial deformations of the girders of the first and
second spars; r, a are constants*dependent on the dimensions of the cross
section and the characteristics of the material; d is a quantity taking in-
to account the external load, This syRtem has the same form for both the
backswept wings having the ribs perpen,licular to t-lie wing axis and having the
ribs parallel to the flow, and differs merely by the expressions for the co-
efficients r, a, and d. The general solution of the system Is obtained, which
contains the solutions for the non-backswept shell as special cases. The re-
sults of calculations are presented in the form of graphs of the rib elasticity
effect on: 1) the distribution of the axial stresses over the girders of the 1B
Card 2/3

SOV/124-59-8-9358
The Influence of the Elasticity of the Ribs on the Stresses in a Shell
rectangular box under the load of a force concentrated at the end; 2) the
distribution of the normal forces in the girders of the backswept box with
"perpendicular" ribs and with ribs parallel to the flow; 3) the distribution
of the tangential stresses in the backswept case. The author shows that the
effeet of the rib elasticity on the distribution of the axial forces in the
fixing is unessential for the backswept box with ribs parallel to the flow.
When the ribs are arranged perpendicularly to the axis of the backswept wing,
the calculation neglecting the rib elasticity can yield errors. The author
shows that a sufficiently satisfactory approximate solution can be obtained,
if the elasticity of one front rib is taken into account.
I.L. Kats
~173
Card 3/3

VAKHITOV9 M.Be i
'-- ~Lat~eral b~endiig of cantilever platefi. Trudy KAI 46-.5-13 159.
(NIRA 14:2)
(Elastic plats~s and shells)
Y

MATVEYEV, G.A.; YEVGRAFOVA, L.N., otv.za vypusk; XURSIM, N.V., prof.otv.rod.;
dotsent, red.; GALIULLIN, A.S., doktor,
VAKHITOV M tekhn.nauk
nauk, red.; MITRYAM, kand.tekhn.nauk, dotsent, red.;
RADTSIG, Yu.A., doktor tekhn.nauk, prof.,, red.; FMOROV, A.K.,
kand.tekhn.naukj, dotsent,, red.
[A method for generating tooth surfaces of hyperbolical gears)
Odin iz sposobov obrazovaniia poverkhnostei zublev giperboloidnykh
koles. Kazan' 1960. 23 p. (Kazan. Aviatsionnyi institut.
Trudy., no.60). (Gearing, Bevel) (14DA 15:3)

88622
ID.Uo B/14r//60/000/004/014/016
E031/E235
AUTHOR: Vakhitov,,,, _~ _-'J~_
TITLE: On the Numerical Solution of the Equation of
Transverse Bending for a Slab Wing
PERIODICAL: Izvestiya vysshikh uchebnykh zavedeniy,
Aviatsionnaya tekhnika, 1960, No. 4, pp. 132-141
TEXT: The problem is that of solving the equation
(tj(P + t (1) for the boundary conditions 91(0)-yi=0,
3(pi = F
(2), where (p, is the angle of wing twist
at a section defined by the co-ordinate -q, and Z is the semi-span.
The method of solution is based on the replacement of the differ-
ential equation by an integral equation, and representing the
integrals in the form of a finite sum, the equations being
described in matrix form. It is assumed that the range of inte-
gration is split into equal intervals. The usual quadrature
formulae of the Newton-Cotes type determine the value of the
integral in terms of the values of the integrand at points within
the interval of integration. In contrast, the method of this
Card 1/3

83
S/147/60/00 600204/014/016
E031/E235
On the Numerical Solution of the Equation of Transverse Bending
for a Slab Wing
paper represents the integrand in any segment of the range of
integration by a polynomial of odd degree 2p+l which agrees with
the integrand at the ends of the segment and at p points to the
left and right outside the segment. The integrals over the
segments of the range can be expressed in matrix form asAA - LYt
where Y is a collimn vector of function values and L is a square
integrating matrix. It is to be noted that this method leads to
some loss of accuracy at the ends of the range of integration
since the same degree polynomial cannot be used. Some examples of
L for different values of p are quoted. Five special cases are
derived. Taking Y,, as the variable of integration, the first two
cases are the integration of y(Y0 from x to -6 and from 0 to x
respectively. In the third case r(Z;)y(r,) is integrated from x to
6, in the fourth case the limits are the same and the integrand is
(rQ;) - r(x)) y(~) and in the fifth case the limits are the same
and the integrand is s(r,)(Y(4)- Y(X)). It is now possible to
return to the original differential equation, which is integrated
Card 2/3

88622
8/147/60/000/004/014/016
E031/E235
On the Numerical Solution of the Equation of Transverse Bending
for a Slab Wing
from Tj to t. The integrals occurring are replaced by the matrix
representations derived in the preceding section. We now have
(P ' represented as a matrix product which can conveniently be
evaluated on a digital computer. A simplification is obtained in
the case of a triangular wing. A singularity in one of the matrix
elements which arises in this case is eliminated by using
L'Hospital's rule. Results are quoted for an example in which
three slab wings are compared (two are triangular and the third
is swept with parallel leading and trailing edges). In conclusion
it is stated that the advantages of the method described over the
usual finite difference technique is due to the smoothing effect
of integration. There are 5 figures and 6 references: 4 Soviet
and 2 non-Soviet.
ASSOCIATION: Kazanskiy aviatsionnyy institut, KafeO-ea stroitellno~
mekhaniki
(Kazan' Aviation Institute, Department of Structural
Mechanics)
SUBMITTED; Yebruary 15, 1960
Card 3/3

VAK f I;qv 4 D~-
------ L~
Using matrices in calculating natural vibrations of the rotating blade
of a helicopter rotor* Izv* vyo, ucheb, zav.1 av. tekh. 3 no. 201-
4.1 160. (~MiA 14-5)
1. KazanBkiy av~atsionyy instituts kafedra stroitellnoy makhaniki
samoleta.
(Ro~oro (Helicopters)-Vibration)

2-ti " toc)
10 IDOO
AUTHOR Valihitov, M.B.
24526
S/147/61/000/002/005/015
E031/9113
TTTE.B1 Calciiiation of the strength of a slab wing with
non-parallel spanwise ribs
11-JOUDICAL,t lzvestiya vy9shikh uchebnykh zavedeniy,
Aviatsionnaya takhnika, 1961, No.21 PP. 47-58
TEXT-. This paper was presented at the scientific conference
of Schools of uigher Education on problems of strength of aircraft
structures, held at the Moskovskly aviatsionnyy institut (Moscow
Avintion Institute) in May 1959.
The wing has a thick upper and lower skin capable of taking normal
and tangential stresses and It Is strengthened by spanwise and
chordwise ribs, the Latter being parallel to the plane of attach-
ment of the wing. It is assumed that the elements which can be
displaced by the intersecting forces are uniformly distributed over
the span and chord of the wing. The wing is taken to be an
anisotropic cantilever plate for which the problem of transverse
bending can be solved using the method of the present author (Ref.ls
present journal, 1958, No.l), Canqider then a slab wing with a
Card 1/4

24526
Calculation of the strength of a s/147/61/000/002/005/015
E031/E113
transverse load p( q) over its surface and a load on the free
edgp. Then the benlinIg of the wing may be assumed to have the formi
,~) *' (PI, ( q ) p.. k
The unknown function `Pk(l) Ls determined from the principle of
posei'ble dlaplatements which., with earlier published results of the
author (Ref.1) learls to a ~%ystem of differential equations. In
many case-n sufficiently good agreement with experimental results is
obtained If m n I An Eq.,(I). The equation for w1 is
i.ndependent of 9,) and can bt solved numerically by the method
described earlier (Ref.3a same journal, 196o, No.4) by the present
author. Substituting this solution in the equation for yo, the
latter function can be determined. In order to determine the mode
and frequency of free oscillations, distortion of the profile may
have to be taken Into account. Then a reasonable approximation is
obtained by taking m = 2 in Eq.(I). The coefficients of the
differentlal equations in this case may be simplified by assuming
a particular planform for the wing. The above approach is not
sdtisfactory If at any section there are concentrated forces, or if
Card 2/4

1 24526
Calculation of the strength of a s/147/61/000/002/005/015
E031/E113
either the trannverse loading or the cross section have
discontinuities. Then it is necessary to consider the wing as
made up of several sections, in each of which the above method can
be applied. Thus the case of a wing which continues through the
fuselage can be considered, bearing in mind conditions of symmetry
about the centre line of the aircraft. The same differential
equations as before have to be solved, but the boundary conditions
are different. It turns out that there are two more boundary
conditions than equations, but they are satisfied identically in
any case. The theory is applied to the case of a triangular wing
with a sweep angle of 450v and different directions of the span-
wise ribs. The character of the stress distribution in the plane
of attachment of the wing in the case where the skin (toes not have
normal striisses corre5ponds qualitatively with the results of
fL, Schuerch Otef.6~ Aeronautical Engineering Review, No.11., 1952).
The case of wings passing through the fuselage ig also described.
As the length of the wing inside the fuselage increases, the
stress concentration in the plane of attachment diminishes, as is
to be expected. Ackncl-iledqment is expressed to the student of
the Kazan' Aviation Institute V.M. Mustafin for assistance.
Card 3/4

2b526
Calculation of the strength of a ... S/147/61/000/002/()05/015
E031/EI13
There are 9 figures and 6 references, I English and 5 Soviet.
Thc- English language referencc-% reads as follows.,
Ref.64 H.u. Schuerch. Aeronautical Engineering Review, No. 11,
1952.
ASSOCIATIONi Kafedra stroitcI'nov mekhanliki, Kazanskiy
avlatsLonnyy insf.fkut-
(Department of Structural Mechanics, Ikazan' Aviation
Tnbtitute)
SUBMITTED- May 21, ig6o
Card 4/4

S/11j7/6i/ooo/c,o4/oi6/G21
of stress ... E200/E435
The author refers to his previous work on torsionless wing
bending (itef.l and 2: Aviatsionnaya telchnika, no.1, .19561, an-d
no.2, ig6l). There are 10 figures,
ASSOCIATION: Kazanshiy aviatsionnyy institut
Kafedra stroitellnoy i-,iekhanik.1 samioletov
(Kazan' Aviation Institute. Department of
Structural Mecbanics of Aircraft)
SUBMITTED: February 15, 1961
Card 2/21

39779
S/i47/62/000/002/007/020
E031/E435
AUTHOR: Vakhitov. M.B.
TITLE: The constriction of an influence matrix for a albb
wing and Its application to the calculation of free
oscillations
PERIODICAL: Izvestiya vysshikh uchobnykh.zavedeniy.
Aviatsionnaya tekhnika,~no.2, 1962, 48-55
TEXT: The determination of influence coefficients is normally
carried out by repeatedly solving a complex system of differential
equations and is therefore only to be recommended for wings of
special form. If finite difference methods arg applied to the
differential relations of the plate theory, the expressions become
extremely complicated and if accuracy is not to suffer the number
of nodes must be very large and this may lead to instability in.
the solution. A new method of constructing influence matrices,
depending on Integrating matrices is proposed. The influence
matrix is found according to the approximate bending theory of a-
slab wing (IVUZ "Aviatsionnaya tekhnika", no.2, 1961), according
to which the mean deflection of the wing is sought in the form
Card 1/3

s/147/62/000/002/007/020
The construction of an influence E031/F,435
TOO ~ k
k=O
where TOO are suitably defined functions. The Yk are
determined from the equation
k, + of I/
= S I(k - 01 19 ...,m)
~)k0 k2 k.
with the boundary conditions
(Pk (0) W 9~(O) - 0 (3)
The wing is divided into n +- I spanwise sections of width he
The influence matrix is found by integrating each equation of
the system (2) from il to ~ ( ~ is the span) and applying
the thethod of volloostion, DetermInAtkan of the lowest
frequencies and the corresponding modes of free oscillations
reduces to the determination of the eigenvalues and eigenvectors
of the matrix U ~Pl, where ZI is the influence matrix and
Cax-d 2/3

S/147/62/000/002/007/020
The construction of an influence ... E031/E435
I is a symmetrical matrix of diagonal submatrices Iq whose
elements are the bending moments of inertia for the-various
sections of the wing. Comparison of the results with experiment
showed that for m = 2 the deformation of a transverse section
for a plate of small span Is given with sufficient accuracy.
There are 2 figures and 2*tables.
A�SOCIATION: Kazanskly aviatsionnyy inst:Ltut*
Kafedra stroitellnoy mekhaniki samoleta.
(Kazan' Aviation Institute, Department of the
Constructional Mechanics of Aircraft)
SUBMITTj3D: July 7, 1961
Card 3/3

!-.,ACCESSION NR: Ap4oo9642 S/0147/63/000/004/0037/0054
I AUNOR: Vakh I tov
TITLE: Calculatlo" ol he free ,,lot bendlng-twlsllog vl1rall 0"5 'of a rotollng
helicopter blade
SOURCE: IVUZ. Avlatslon"aya tekhnikal, ri6. 40 1963, 37-54
TOPIC!TAGS: helicopter blade vibration, bending vibrat;on,.tw;sting vibration,
vibrat!on calculation, helicopter, helicopter blade
ABSTRACT: The author calls attention to a previous work (R. L. Bisplingkhoff and
others. Aerouprugost'. IL, )958) In which a matrix method was developed for the
calculation of the free bending vibrations of a blade, based on the substitution
of a weightless beam with concentrated masses for the blade. In the present paper,
as a further refinement of that method, the author has considered the real (con-
tinuous) distribution of the mass along the length of the blade, as well as the
t ;oint bending-twisting vibrations set up by the setting of the stroke regulator
and the failure of the center of strength of the section to coincide with its cen-
ter of gravity. The finite strength of the control line Is also taken Into consid-
eration. The joint vibration equations are derived on the basis of the following
C.rd 1/3

ACCESSION NR: AP4009642
suppositions: 1) the blade has no geometric twisting; 2) the flexural center In
each section lies on the main central axis of Inertia; 3) the flexural axis is
straight, being, In fact, a continuation of the axis of the axial hinge-joint;
4) the horizontal hInge-joint lies on the ax(s of rotation of the blade. The
author has reduced the determination of the frequencies and forms of the lower
tones of the free joint end separate vibrations to the computation of several
largest eigennumbers and elgenvectors of matrices. The methods to be used to de-
termine these values are well developed in linear algebra. it Is pointed out that
the most convenient and effective, from the point of view of the application of
electronic computers, Is the method of sequential approximations (Ro Frezer and
others. Teorlya matrits. IL, 1950). Separately considered In-the article are the
Integro-differentlal equations for the joint vibrations, the matrix equation for
separate flexural vibrations, the matrix equation for separate twisting vibrations,.
the matrix equation for joint bendIng-twisting vibrotions and, f1mally, a discus-
sion of the finite strength of the control system. "in conclusion, the author
considers It his pleasant duty to express his gratitude to engineer Mo S. Safarlyev
and to junior scientific staff worker L. F. Shatrukov, both of whom took part in
carrying out the approximate computations for this article." Orig. art. has: 5
tables, 17 figures and 22 formulas.
Card 2/3

i-41 :I.
ACCESSION Nit: AP400042
ASSOCIATION:
SUBMITTEbt O6FQh63
sue CODE.. PR
DATE ACQ1 12Feb64
NO REF SOV01 005
ENCL: 00
OTHER: 003
Card 3/3

ACCESSION NR: AP4033055 S/0147/64/000/001/0175/0180
AUTHOR: Vakhltov. M. 8,
TITLE: The derivation of equations for a plans problem on the theory of elasti-
city in oblique-angle coordinates
SOURCE: IVUZ- Avlatsionnsys takhnika7wo. 1. 1964, 175-180
I'l TOPIC TAGS: elasticity, elasticity theory, tensor analysis, elastic deformation,~
elastic stress
ABSTRACT: The present paper deals with the derivation, by means of tensor ana-
Jysis, of a complete system of equations for a plane problem of the elasticity
theory in oblique-angle coordinates, and also of formulas for the conversion of
stress and deformation components. Equations of the classic theory of elasticity
(that is, with small deformations) are considered. The general tensor equations
given by 1. N. Sneddon and D. S. Berri (Kiassicheskaya teoriya uprugosti.
Fizmatgiz, 1961) and by J. W. Mar (Theory of Shell Structures, Cambri4ge, MIT,
1962) are used. in a concluding section, a transition Is made from tensor nomen-
clature to physical components and the nomenclature current in the applied theory
of elasticity. The article is in 7 parts. The first deals with fundamental
i ratios the second with displaceinent components, the third with strain tensor com-
Card 1

J-ACCESSION NR: AP4033055
ponents, the fourth with stress tensor components, the fifth with Hooke's law,
the sixth wtth Kirchhoff ratio#, and the seventh with the conversion of the
nomenclature discussed above. Orig. art. has: I figure and 19 formulas.
ASSOCIATION: none
SUBMITTED: 06Feb63 DATE ACQ: Iihay64 ENCL: 00
SUB CODE: ASpGP. NO REF SOV: 003 OTHER: 002
Card 2/2

L 11.293-67 krOP-7 ekx)/ kw
ACC NRt AF-SO30251 SOUIC2 COD'_~;
Valdiitov, X. B.
ORG: none
:S: Integrati-m- matrices -a tool for numerical solutionz of difforont-'al Oquat-o:-,5
T L, - " , - A
of stMetural mochanics
SOURCE. IVUZ. Aviatsionnaya tokhnika, no- 3, 19606. 50-61
.LO?IC TAGS: mathomatic matrix, differential cquation, solid mechanical prop,-Irty
A3STRIXTI: 7he papor is'a contJnuation of a r-roviou5 woz-k by the author (Avl~,t3ionnaya
:,toldinikaa, 4, 1964) -~f-Lich in turn is a developn-.ont and gonoralization of the by
~A. F. SmArnov (Stability and vibrations of constructionG, Transzholdorizdat, 1 `3).
1 195
;'It deals vith a now method of niraorical solrA-~-J.on of d'"'forential oqu_-tior,:; -wrhiclh, in
I
:contrast to the nwnerical differantiatio-n (the r,,o,;hod of finito difforanco5), conzists
~of finite numerical intearations of fho -iven function si~bdividod into a number of
Lt--
:s0c,4ions. In each section the furction is ap?roximatod by a pai-abola of a sui
ordGr and then the nwwrical values of the sectional bntograls are tabul-a-Lod With tho
,holp of special integrating matrices. L- a result, Vho discrGto value of th,_-- 'L unc t -., on
'to be determined is obtained in a colw7mar form, and the solution J*ILs obtLZALiod from a
!r.atrix equation using a computer. Me conskruc'tion of the integrating aatricas of
L _CQ -rd-I 2 ULCI

L 11293-67
ACC NR: AP6030251
;various forms is demonstrated. 27.a me,:-,od is illuztrated by the solutio,-. o.." an
I
equation for buckling and transversal bandi=. Crig. art. has; 26 cqur~zions zand
'7 figures.
!SUB CODZ- 20/ SUBM DATE: 04Dac65/ CRIG REF: 003
E

VAKHITOV, M, Kh.: Master Med Sci (diss) -- "Some data on the infection rate of
workers in the oil industry of the Tatar ASSR for 1954-1957". Kazan', 1958.
17 pp (Kazan' State Med Inst), 200 copies (KL, No 7, 1959, 128)

-- __ j kand.raed.nauk (Kazan'); TAPTOPOLISKIY9 Ya.I.9 kand,
VAKHITCIVLvM.Kh
mad nauk (Kazan')
"Organization of the work of the dispensary in an urban hospital" by
S,IA. Freidlin. Reviewed by M.Kho Vakhitovj IA. I. Tarnopoltakiio
Kaz, meds, zhur, no* 2:105-106 Mr-Ap 161. (MIRA 14:4)
(HOSPITAIS--OUTPATIENT SERVICES)

_YALOgTQV-,-14.KiTri-~ispolnyayushchiy obyaZmnosti dotsent
Life span of Lhe urban population of the Tatar A.S.S.R. in
the period from 1958 to 1959- Kaz. m1d. zhur. no.1.7&-78
J'a-F 163. (RIM 16:8)
1, Kafedra organizatsil zdravookhrancaiya s istoriyey medi-
tsiny (zav. - prof. T.D.Epsliteyn) Kazamkogo ineditsinskogo
inatituta.
(TATAR A.S.S.R-LONGEVITY)

VAKHITCjVl, M.Kh.
Some data or the longevity of the Fopulaticn in th-e- Tatar
A. 3. S. R. acc(,,-('ing -..o cenriis maf.e~,,,!als of 1939 and 1959.
1j: 6ch. truiy Ka~,. gos. 15 d. inst. L4:15-16 16/4- (MIRA 18:9:)
1. Kafedra organizatsii zdravookhruneniyu s istorlyey meditsiny
(zav. - prof. T.D.Epshteyn) Kazanskogo meditsinskogo instituta.

KH T
V
A ~TOVY N.G.
Effect of a surrounding liquid on the velocity of fle=-al wave
propagation along an elastic strip of finite width. Akust.zhur.
10 no.4:407-411 164. (MIRA 18:2)
1. Akusticheskiy institut, Mos-kva.

-1- - -
I
" ! 2-
Cord ,

L 1380-66 EV1T(1)/EY1A(h)
Ifft: AP5022433 UR/0109/65/010/W9/1676/1683
62 2 3535.312
ADTHORt Vakhitovp N. 0.
TITLEt open resonators with variable-reflection-factor mirrors
SOURCE: Radiotekhnika I alaktronika, v. 10, no. 9-, 1965, 1676-1683
TOPIC TAGSt resonatorl~open resonator
ABSTRACTt Q. D. Boyd, J..P. Gordon (BSTJ, 1961, 40, 2, 09) and others Livestigated
natural oscillations in open resonators formed by uniform (perfectly reflecting)
mirrors operating in a homogeneous medium. The present article presents a
theoretical analysis of the same problem, but with the mirrors' local reflection
factarvarying along the mirror according to the Gauss law. First, a two-dimensional
problem of natural oscillations between unbounded parallel planes having variable
impedance is considered. Second, the open concave-mirror variable-reftection
resonators are examined by a method which substitutes a parabolic equation for the
Helmhols wave equation. Formulas for-the complex natural frequencies and field
distributions are developed. It Is pointed out that the natural-frequency spectrus
in such variable-reflection resonators is rarefied to a higher degree than that
in the case of perfect-reflection resonators. HThe author wishes to thank
cardi/2,

L 1380-66
MCESSION NRt AP5022433
L. A. Vaynshteyn for his direction of the work, V.,P. Bykq and L. P. Lleovskiy
for discussing the revults,11 Orig. art. hast 3 figures and 45 formulas. 10211
ASSOCIATIONt none
SUMMT01 25Mv64 99CM 00 M COD91 SC
NO REF SOYt 004 OTMt 003 ATD PRESS:

ACC NR# AP7008125
AUTKORs Vakhitov, N. G.
ORO: none
SOURCE CODEs
TITLE: Electromagnetic oscillations of an open resonator consisting of plane mirrors
with a dielectric prism mounted between then
SOURCE: Zhurnal tekhnicheskoy fiziki, v. 37, no.2, 1967, V*2-253
TOPIC TAGS: laser r and d, laser resonator 01;A.,w. y,.&+"A.Ij f C,
ABSTRAM. The author discusses the normal modes of an open resonator consisting of
plane mirrors between which is mounted a rectangular dielectric prism that does not
completely fill the intervening space. The problem is treated In two dimensions, It
being assumed that all the fields are Independent of one rectangular Cartesiaa:co-
ordinate and that the mirrors and the dielectric prism extend tZ infinity in the
direction of the corresponding coordinate axis. The calculations are performed In the
geometric optics approximation with the aid of Helmholtz' equat .Ion and the boundary
conditions at the mirrors and the faces of the dielectric prism. Approximate formulas
are derived for the frequencies of the normal modes# and the field distributions
within the dielectric prism and in the gaps between the prism and the mirrors are
calculated. It is shown that the diffraction losses and the ratio of the field
none

ACC NR: "7008125
strength in the dielectric to that'in the gaps depend not only on the transverse
index of the mode, but also on the longitudinal index. This feature of the system is
of practical significance, for it makes it possible to effect dilution of the eigen-
frequency spectrum with respect to both the transverse and the longitudinal indices.
An regards dilution of the spectrum with respect to the longitudinal index, the
system behaves approximately as a pair of coupled resonators, one of which is consU_
tuted by tte dielectric prism and the other, by the gaps between the dielectric an~
the mirrors. The author thanks L.A.Vaynobteyn for his guidance of the work. Orig.
art. ban: 65 formulas and 4 figures. .[WA-14] [15] 1
MM OWEs 20 SUBM DATM 2YAaj69'
ORIG, RV; 005
Card 2/2

- TMITOT. U.Sh.
Measuring the effective porosity of souzA-abnorbing materials.
Tray LlKr no.3:52-57 155. (KLRA 9:8)
1. Ilafedrs, akmettki.
(Acoumtleal materials)

-A-R "IOWV-61010:~-5h-
Structural cooffLcient of a homogeneous and isotropic porous
sound-absorbing material. Trudy LIKI no.4:45-47 '56. (MI&A 10:5)
1.1&fadra akustiki.
(Acoustical materials)

VAXHITOV, Y&,Sh,
I
Application limits of the Helmholtz formula for the acoustical
resistance of cvlindrical channels, Trudy LIKI no.4:48-50 '56.
I.Kafedra, akustiki.
(Sound-Keasurevant)

1j, iw ;-I
AUTHOR: Vakhitov, Ya.Sh., Manlkovskiy, V.S. 46-2-3/23
TITLE: _Them_' rm of directional pattern of microphones for stereo-
phonic sound transmission. (0 forme kh~arakteristik
napravlennosti mikrofonov dlya stereofonicheskoy zvuko-
peredachi)
PBRIODICAL: "Akasticheakiv ZhurVgl" (Journal of Acoustics), 1957,
VM.3, No.2, pp. 109-114 (U.S.S.R.)
ABSTWT: The authors formulate analytically requirements for any
stereophonic systen'to reproduce without distortion the effect
of displacement of the sound source.
Assuming that any n-channel stereophonic system may be
considered as a combination of (n - 1) two-channel systems,
they restrict their analysis to a two-channel system only. The
secondary acoustic field is considered first. Formulae
relating the sound intensities 1, and I. and the directional
patterns of loudspeakers 11(9~ and jl(e~) to the apparent
displacement V of the source from the microphone are
derived, using (1), (2). As shown in (3) jt(6,) and tl(%)
C"4 1/5
may be assumed to be equal to uniV.
The primary field is analyadd next. Considering the

46-2-3/23
The fona of directional pattern of miscrophones for stereo-
phonic sound transmission. (Cont.)
parallel displacement of the sound source with respect to the
microphone, it is shown that the first condition for distor-
tionless transmission of sound from a moving source is the
equality of normalised displacements of the real and of the
apparent sound sources, i.e.
X1 (3)
which, when applied to the emf of the microphone, may be
written: jelN2
log F1 f(xl) (4)
the condition (4) does not satisfy for the phenomenon of the
"displacement On depth" of the apparent source, so that the
second condition to be satisfied is the elimination of the
Card 2/5 above effect. It is found that this condition is given by;
e2 + e2 = e2
1 2 0

46.2-3/23
The form of directional pattern of microphones for stereo-
phonic sound transmission. (Cont.)
where e 0 is a constant omf. Thus, eombiningsJ4), which
secures the full use of the frontal displacement of the apparent
source, and equation (6), which satisfies for the linearity of
its displacements, the law of the microphonds directivity with
respect to the source position is given by:
al e 0 (10 -f (XI ) . 11 -1/2
e2 e (x I) t 1 1 -1/2
It is further shown that
tan E)
Card 3/ 5 tan Omean
where ID is the angle between the vertical and the source-to-

46-2-3/23
The form of directional pattern of microphones for stereo-
phonic sound transmission. (Cont.)
microphone direction (for the parallel relative displacement)
and :
tan t
..an 7
Card 4/ 5
where half distance between the microphones and y
the distance at which the sound source is displaced parallel
to the microphone's line. Also, if in the extreme position
(x = I ), the source produces a pressure p at the microphone,
then for its intermediate positions this p~8ssure will be:
Pl = Pot 1 (0) Cos E) (9)
combining eqs. (7) - (10) the required directional characte:-
istics of the microphone is given by:
k
(e) (O)CUS
tan 4
F
TaMO mean) +
1/2
(12)

116.2-3/23
The form of directional pttern of microphones for stereophonic
sound transmission. (Cont.)
e
where k = - ; GO = poTl (91 being the microphone sensi-
e 01 0
tivit-Y).
It is shovm, therefore, that for a stereophonic sound trans-
mission microphones should possess a highly directional pattern,
varying in its characteristics according to the distance between
the -microphones and the source. Facility for remote control of
these characteristics should be provided. 2 diagrams, the
Card 5/5 graph of the position angle of the apparent source against the
difference in energy levels of the transmittin,-, channels and
two graphs of required directional patterns of microphones are
given. There are 5 reference's, 1 of which is Slavic.
ASSOCIATION: Leningrad Institute of Motion Pictures Engineers.
(1-aningradskiy Institut Kinoinzhenerov)
SUBMITTED: March 1, 1956.
AVAUABIL: lAbrary of Congress

Y~I i-i
AUTHOR: Vakhitov, Ya., Sh., and ManIkovskiyj V.S. 46-2-4/23
reproduction of the sound source move-
TITLE: I
ment in stereophonic systems. (Iskazheniya v peredache
dvizheniya istochnika zvuka pri s-uereofonicheskom zvuk-
ovosproizvedenii)
PEMDICAL: IlAkusticheski:Y Zhurnallo (Journal of Acoustics), 1957,
Vol-3, No. 2, pp. 115-126 (U.S.S.R.)
ABSTRACT: In the present article the authors investigate analyti-
cally distortions in stereophonic reproduction, which distortions
are due to the fact that the latitudinal and longitudinal dis-
placements of the apparent scurce in the secondary field do not
correspond to the true displacement of the primary field
source. P.G. Tager (1) et al. (2), (4) have shown that the
choice of the MiCrODhones type and their relative position
with respect to the source 'is of prime importance. Usin,-, th Ue
notation of the preceding article in this issue (pp.109-114)
the authors analyse mathematically first distortion in the
M-rd 1/4 reproduction of lateral displacerint and derive a formula for
the relative change of the total sound level, which determines
the distortion in this case. The formula is derived as:

116-2-4/23
Distortions in tae reprocbaction of the sound source movement
in stereophonic systems. (Cont.)
10 log ra'%cos + 2 2 ID2) (9)
If kIPV I~L f (02)COS
For omni-directional microphones it becomes%
2& 2o
N 10 log (COs 1 + Cos 2 (10)
When bl-direct-Ional mlerophones are used eq. (9) becomes:
Hk = 10 log (Cos 49 1+ Cos 402) (11)
and for highly directional patterns one obtains:
NS = 10 log cos2e~(l + cos &1)2 + Cos 20 (l + Cos ()2 ) 2] (13)
1 2
Jordan (2) has shown that in order to achieve undistorted re-
production of the longitudinal source movement it is necessary
card 2/4that the difference in sound levels at reproducers change
according to a pre-determined law. The formula for the diff-
erence in sound levels of two loudspeakers, which determines

41-4-2-4/23
Distortions in the reproduction of the sound source movement
in stereophonic systems. (Cont.)
the position of the apparent source is derived as:
N = 20 log J(%) Cos 90, (16)
ROT" 1~2
The equation is analysed for all three directional patterns.
Fonrulae for both longitudinal and latitude displacement dis-
tortions have beeA experimentally verified with good results,
The theoretical and experimental results permit the following
conclusions: the increase in the relative speaker-to-aicrophone
distance improves the latitude and increases the longitudinal
displacement distortions; the magnitude of both types of dis-
tort4on depends on the micxophone directivity and on frequency
to the same extent as the directional pattern of the microphone.
When microphones are facing each other the latitude displace-
ment effect is somewhat smaller but the distortion of the longi-
tudinal displacement reproduction of the sound picture is made
much worse. If the acceptable distortion in Ititude movement
Card 3/4 reproduction is assumed to be acceptable for the total level
variation of A to 4 db and the !-on%-Ltudi-n?j uo--ment distn-1-4.--

46-2-4/23
Distortions in the reproduction of the sound source movement
in stereophonic systems* (Cont*)
acceptable for 19;~ change in the lateral distance, the(y/1
latitude to longitude distance) ratio for non-directional 'aicro-
phones should be 0.6 to satisfy the first condition and 0~1 to
satisfy the second. A compromise value of YA = 0.3 -; 0.5 is
usually used, for which the total sound level variation to be
expected would be 5 -. 9 db for the sho3:tening of the lateral
apparent sound distortion of 20 -Ipt 40/1~. For the uni-directional
microphones the ratio 7/17 0.7 should be adopted with the
corresponding level variation of 3 .1 5 db and lateral displace-
ment shortened by not more than 20%o For bi-directional micro-
phones YA = 0.8 -~ 1.0 , with level variations of 3 z.- 4 db
C nd - 2(Y
41r4 4/4 alateral displacement shoitening of 10 ; /;. One diagram
of relative microphones and source positions and 18 grahs of
numerical and experimental results are given. There are 4
reference, of which 1 ii Slavic.
ASSOCIATION: Leningrad Institute of Motion picture Engineers.
(Leningradskiy Institut Kinoinzhenerov)
SUBUITTED: March 1, 1956.
AVAILABLE: Idbru7of congress

H 17-6) V,
46-4-13/17
AUTHOR: Vakhit~i, Y~.
TITLE: A Ballistic R_~verberomotor with a SLoall Spread of Readings.
(Ballistuich-o-siziy r,--vorb ro-.,ietr s:lym razbrosom -:)o,- zaniy
F1E'R1',:)DI,-/AJ_,: A1:us'ichcs1-.iy Zhu-lmal, 11,157, VA.III, Nr 4, 14j.372-373
US SR
AJ'~.-TIUCT: A block dia, ram of tac is sh-,mn in Fit,
Tiic soitnd si-, 1 is fed into -the
`_r-al from tile :Acropho-rie,I
am-,~lifier, 2, and the detector, 3, and then to a lo-,,ari'uh-
tnut o' ahich is connected to t1he in-
:-Iic devic-7 4 Uhc ou
.A-
Ue-rati.n- elcmcnt, 6. T-Nic leDw-.11 at t-o outT)ut of the in-
clement i.3 controlled b.7 the device I-, while 7 is
A_
.1-c b-11istic indicator rc,,-..,1,berati,_)n. The intezratin.-
is shovm in Il. the timp. constant of t'lis
n Ulic U if f
circuit i4; sufficiontly _Ic,-L%'c WiL 'i r P-,i c c
Ulv~ capacitOr Is aj)- -to tho
Ti Of t'ne j.1pat difff,,r-jrce. Thu:; such a
circui'U7 in diotincti~Dn to a pro'111c'eS a
lia-~Dar inte-ration. Tiac dcvice, 4, uoed to
lo,sor ti-lo effect of fluctu.,~.ti. Jn thc )f 'u-'hc
o-ot-,r, i.e. I to rcO.Uc-, 'U'lle 3, r.;ad of
iS CLUO _L;() _GhO f,-,,ct that, at t'i~~ out-_tt of t"is d3v-;-c-,, the
_U1 ", , 7r,
Card 1/2 of Lh-~ fluc-'Uu_!,t-2'_-)n.-, ,:_oc:~ not chan~;c LL c';!~' _C,

46-4_17/1?
A "Jul. -I mv--r-~)~-.!ro "ot ~_- %-!it`,! a
iL
. i-, -L.- 1~ Is
I CUD-
-,.,3ro. 12~_lc Iol-1--ari'Uhnic devic-c consists of c. triode
DC in zeries %,,,i-'U-h a Oinc_- tlic
I
.;rid current charact2ristic is c_-:yonc_ntiL.1 -the -vo1t-_:.,*'3 DO-
wo,,~ ~h; ~L_.,id ond the cu~hode o" vaIvc i:-, a
U
. u
functio-a of the input vo3:t,.k,-,o. T.,i--, i-astrumont wu.-, founL
~',V_GLLrUto and con-v,.~Tiicnt Jr~-,cticc. Tli,~=~. arc
2 fi--;urcsI.
A;330CIATICI-IT: Lcliin,~,-rad Institute for
February 19, 1957.
AVAITABI~-,,: LibrELry of Congress.
C3
Card 2/2 1. Reverberometer-Operation 2. Reverberometer-Characteristics

20)
AUTHORs Vakhitov Ya Sh ' Candidate of SOV/119-59-4-11/18
TITLEs A Novel Ballistic Reverberometer (Novyy ballieticheskiy
reverberometr)
PERIODICALs Priborostroyeniyet 1959Y Nr 4, pp 21-23 (USSR)
ABSTRACT: The ballistic principle has in spite of its simpliaity not
found a widespread application in reverberation measurements,
as it has inherent errors of measurement. These errors are
due to the following factsi 1) a considerable straying of
the deflections of the instrument in different positions due
to the fluctuation of sound attenuation. 2) by the small
depth of integration of the reverberation process. These
error causes are almost completely eliminated in the
reverberometer developed by the author. The principal circuit
diagram of this instrument is given in a figure. The sound
signal which has been transduced by a microphone is fed into
an amplifier, which drives a logarithmic circuit, the output
of which is connected to an integrating device. This finally
feeds the ballistic reverberation indicatoz. A circuit
Card 1/2 proposed by N. Ya. Batyrev is used as an integrating element

A Novel Ballistic Reverberometer BOV/119-59-4-11/18
instead of a thermocouple. The calculation of the linearly
integrating circuit is outlined. The current passing through
this circuit varies as the pressure, and hence the errors
of the individual measurements can be compensated statically.
In the reverberometer under discussion the errors of the
individual measurements can be minimized by means of the
logarithmic device. A d. c. amplifier with a triode is used
as logarithmic device. A figure illustrates the principal
circuit diagram of the reverberometer. The tests carried out
with this instrument confirmed its reliability. The results
of individual measurements deviate by no more than 10 % from
the average value and the results of measurements taken at
individual points practically do not differ at all. A
measurement at 5 to 6 points guarantees an accuracy
sufficient for practical purposes. There are 3 figures and
2 Soviet references.
Card 212

,-._IAKHI OYAA.
2
Theory of the two-sided electrostatic symmetrical loudspeaker,
Trudy LIKI no. 5:76-81 159. (MIRA 13112)
1. Irafedra akustiki Imeningradskogo instituta kinotnzhimerov.
(Loudspeakers)

ACCESSICK M AP4039287 S/0046/64/010/002/0 W /0244
AMIKORt Vakhitovo YA. 3h.
TITIZ: Highly sensitive subsonic aicrophone with a movable coil
-244
SOURCEs AkuL*tichoskiy shurnalt v, 10g no. 2, 1964, 242
TOPIC TAGSz microphone, infrasoundt sensitivity, coil, frequancyp resmatorp
membrane
ABSTRACT: The %uthor developed a highly sensitive receiver for a relatively narrow
frequency band. Become it in intended for field workl,*the instrument was made a
:resistant to changing atmospheric conditions. The receiver constitutes a aicrophcue
'with a movable coil. Its arose section and schematic drawing are shown in Fig. 1 on
,the Enclosures. Aside, from the standard elements, the receiver contains a resonator
.involving the air In the hole within the core and acoustic compliance C of air
m3 3
-in an auxiliary space. If the frequency of the resonator in properly adjusted; the
microphone acquires the properties of the band filter Wum in Fig. 2 of the
'Enclosures. The upper limit of frequency range is determined by a C and z~C' and
1 1 2
:the lower limit by The decrease of,frekwincy W. may be attained by
Cord