SCIENTIFIC ABSTRACT YENENKO, O.K. - YENGIBAROV, V.N.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001962630011-2
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 57
• Document Creation Date: November 2, 2016
• Document Release Date: March 15, 2001
• Sequence Number: 11
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

VOLKIIOIISKAYA) 4.A.; YUMIKO) O.K.; IVAJIUVA) SX.; MOTINp Yu.D.;
OZEROV, I.M.; PXIUAJII.5"-"D;A.- FOLM', Y.F.; ZOLOVUr'MOVA,
G.E.; SUVG,".OVA, G.F.., red.; M-ISELI, I.) red.izd-va;
BELOGUROVA, I.A., tekhn. red.
(Building materials made of waste products from oil shale
winning anti processing) Ijtroitellnyo matorialy iz otkhodov
dobychi i pererabotki goriuchikh slantsev. Leningrad,
1963. 35 P- (Leningradskii dom nauchno-takknichaskoi pro-
pagandy. Obmen peredovym opytom. Soriia: S#oitellnye ma-
terialy i konstruktsii, no-4) (MIRA 16:11)
(Oil shales) (Buildir4; materials)

VOLKHONSULYA) R. A.; YENENKO, 0. K.; 071"ROV, 1. 14-
Us.Ing shale ash in the production of pipes. Trudy VNIIT no. 11:
199-210 162. (YJPA 17: 5)

SHABADASHI A.L. (14oskval G-151., pr. Kutuzova) 240 kv.314);YEIIINKO, SA
(Moskva, ul. Belinskogo, 5, kv.7): )RLOVA, L.V. (Moskvap Lenln-
gradskiy pr.p 78., kcrp. 5~ kv*69)~-
Cytochemical examination of the glycogen of 'he central nervous
system of frogs after gamma irriu.-iation. A-,kq. anat.9 gist. i
embr. 41, nt,15t26-36 MY 163. (MIFLA 17:6)
1. Institut biologicheskoy fiziki AN SSSR, Moskva.

YENENKOs, S.C.; NIKOIAYEVA, N.D.; SHIJNGSKAYA, V.Ye.
Cytochemical study of the succinic dehydrogenase actl7lty
in nerve celJs of an adult rabbit under the conjitions o.i~
a *,issue culture. Arkb. anst., gist. i embr. 49 no.11:301-
42 N 165. (m I PI! 19, 1
1. TAboratoriya biofiziki zhivykh otruktur (rukovoditell -
chlen-korrespondent AN SSSR prof. G.M. Frank) Instituta W01rgi-
clieskoy f Iziki All &SSR, Movkva.

Y12112MD, Yu.A.
Igg inside an egr,. Priroda 49 uo.9:111-3-12 S 160. (MIRA 13:10)
1. Iaiganskiy gosudarstvenny7 meditsinskiy inst'itut, Donbass.
(N999)

BULGARIA/Cultivated Plants Fruits and Berries. M-5
Abs Jour Ref 7-hur - Biol., 110 3, 1958, 10955
Author Yeney As
InGt 4~~
Title Grafting Wild Trees and Regrafting Trees of the Cultiva-
ted Varieties.
Orig Pub Ovoahcharstvo i gradinaretvo, 1957, No 3, 6-12
Abstract No abstract.
Card 1/1

USEVICH, B.F... LlEnevy--h, B.F.1
t
Possibility of ,-ondwiting side searahes for undergrumd.,
~n so5lam.-t-, prospezAing as revealle4 by a study In the rhiepem-
Ubnetj Lwland. [Prate!] That. geol. nauk AN URSR# S"r. h1dru-
Vol, and inA.,. geol. no.A546 90 (MIRA Y!v-)

KOrKOVA, K.I.j ORLOVSKAUp N.N. [Orlovsikag N.M.); YENEVICIlp T.F. [IEnevychp
T.F.]p studentka
Photosensitized oxidation of the amino acids of eeg albumin and
ohangoo in the maorostructure of its moleaule. Ukr. biokhim
zhur. 33 no.10-13 161o (MIRA 14;3)
1. Institut biokhimii Akademil, nauk Ukrainskoy SSRf 99Ki
'IT"
'(ALBUMIN) (OXIDATIONO PHYSIOLOGICAL
(PHOTOCHEMISTRY)

T. 1-1. OIMOTSn=-~ D. E., --dl T 1.Aj1'YN0V,-'., G. P.
"Determining the Time of Esixtence of the txtificial Earth Setellite nnd
Studying Secular Perturbations of its Orbit," a paper presented at the
8th International AstronouticalCongress, 6-12 Oct 1957, Barcelona.
a

# We 4904 CLINA 400r,.LDT, Lo no
.-
"Determination of Lifetime of an Artificial Earth Satellite.'
"The Zst#blishment of Artificial Satellite In Orbits*
,reports presented at the 8th Intl. Astronautical Congress, Barcelona, Srpain,
6-10 Oct 57

AUTHORi OKHOTSIMSKIY,DXS. o ENEYEVqT.M.
TIOLEt Some Variation eroBTe-m-F-C-6-n-n-e-oted with the Launching
of an Artificial Earth Satellite. (Nekotoryye
zadachi evyazannyye s zapuakom iskustvennogo
Ru siani
PERIODICAM =khi Piz. Vauk, 1957, Vol 6), Nr la, PP 5
53-la-2/18
into Space
variatsionnyye
sputnika, zemli,
- 32 (U.S.S.R.)
ABSTRACT: The present paper investigates the problem of conveying the
artificial earth satellite to its orbit. This conveyance is as-
eumed to be carried out by means of a rocket booster having one
or more steps. The problem is investigated here as to what nature
the law of the modification with respect to time of the direction
of the trajectory motion of the reactive forces must be in order
that the satellite may be conveyed on to a given orbit with the
least possible fuel consumption. Also the most favorable fuel
consumption is ascertained. The authors solve this problem 'for
several simplifying assumptions, and this solution conveys a
definite idea of the characteristic peculiarities of the optimum
conditions for launching the satellite into space. By making use
of these data it is then possible to construct recket booster
with the lowest possible weight.
Card 1/4

Some Variation Problems f!onnected with 53-la-2/18
the Launching into Space of .r. Artificial Earth Satellite.
the optimum program for trajeotoyy motions Tne rollowing assumptions
form the basis of the solution of this problems Aerodynamic forces
are assumed to be lacking and the field of gravitation is assumed
to be plane-parallel. These assumptions apply only very approximate-
ly in reality, but also in this form of approximation the problem
is very interesting. First the equations for the motion of the
satellite with its booster are giveng after which the boundary
conditions are formulateds At the beginning of the motion a certain
height Y 0 is assumed to be attained at t - 0, and likewise also
certain "alues of the horizontal and vertical projection of the
velocity (here denoted with u 0 and w0 respectively). The velocity
V at the beginning of the motion iop of couree, put equal tG zero.
At the end of the motion, i.e. at the moment t - T, the height
must be y - Y and th4 velocity must be horizontal (w - 0). 'he
amount of V must at the end of the motion be equal to a certain
fixed value V . Certain simplifying circumstances prevailing,
k
the assumption of a definite value V k corresponds to the as-
sumption of a certain ratio between initial and final weights. With
Card 2/4 a given value of the earth satellite this means assuming or

Some Variation Problems Connected with the 53-1a-2/18,;~
Launching into Space of an Artificial Earth Satellite.
presupposing a definite initial weight of the rocket booster.
The rocket motor need not be in operation during the entire flight
of the accelerator. The authors then construct an auxiliary
functional which is varied according to the funotione and variable
parameters occurring in it. The various operations of computation
are deocribed. In the case of an optimum program, the tangent:of
the "angle of pitch" (called "tangagell angle in the Russian text
and moaning the angle formod by the axis of the rocket and the
horizon of the place from which the rocket is launched) must be a
linear function of time. Various varieties are then mentioned
(combustion of the entire fuel at the beginning of the motion
or at a later stage, combustion of fuel during the entire duration
of the motion, and various combinations of these possibilities).
All these possibilities are realizable at certain conditions.
Next, the case is 3tudied in which the duration of motion is not
fixed but is ascertained from the maximum condition of final
velocity. Also the 1-iitial angle is not assumed as fixed, but is
chosen to be as favorable as ppasible. Also a numerical example
is given.
Card 3/4

Some Variation Problems connected with the 53-1a-2/18
Launching into Space of an Artificial Earth Satellite.
ASSOCIATIOY~
PRESENTED BTs
SUBMITTEDt
Card 4/4
Motion with assumed regulation of fuel consumptiont The beat rule
for acceleration is the linear dependence of the tangent of the
11tangage angle" (see above) on time. By integration of the equations
of motion expressions for the projections of velocity and for the
coordinates at a given point of time are obtained. For the practical
computation of the integrals it in necessary to know the dopendenee
of reactive acceleration on time. There follows a detailed in-
vestigalw,ion of the optimum motion of a composed rocket. 2he ne-
cosoary computations are followed atop by atop. A special examin-
ation is made of a composed rocket the n steps of *hich have similar
main characteristics.
Conveyance to the orbit in consideration of the variability of the
Ti-eld of gravity and of the rotation of the earths Here the motion
of the rocket is investigated in relation to a system of coordinates
connected with the earth. The formula for the optimum control pro-
gram, which is found after complicated computations and is valid
for various geographical conditions is explicitly given.
(With 9 illustrations)
Not given
Library of Congress

AT"'OH
2ARATY,;(), A -.p.

3-la-3/18

TITLF Th,z D e t c r..,. an A-vt-ficial Satellite and the
of the Perturbaticna Of i ts Orbit.

IM
(0]~redeleniye vrc;~,"eni !~
I tvovdni;

1
i3 lcdov.-;ri.,'U VL407.14.1
01711Y' Ye go
;.;rljit;,
PERIODIC IL Fiz-Al'-kuk,%~57,Vol 63, Jr la, pi~ 3.1) - )o
ABST,UCT At heights of frou about 100 to 150 IM tile life of tile eatellite
is short and in the case of low transv,~rual strusst-z the satellite
does not eveit perform a full revolution.W(;r-s exicting to now On
the life of srti.-icial catellites use only approximatio:i ac-thods
and for tho general case do not give a fall solution of thn problem.
Jeside3,un3ubstantiated neti-ods of approximation ::-,ay lead to
tial errors.3y means of the Lethcd discussed here the lifc of the sa-
tellite can -for the 6anaral case be coi;q,ated sufficie,,,.,tl~ q.1ickly
and rc-liably.This inventigation proved the exi3tence of u:-.iver2al
e,ependences bet.,jeen the :2ain parameters of the oscilatory ellipze.
T-hene relations apply in the case of any satellites and deijend only
upon the density distribution of the air at increazjin,3 hei~;ht.Jith
the help of the dia_!rar:x and tables given here the life of the satel-
lite as well as the c;-an,-Ie of its orbit parameters with reopect to
time can be deter--ained quickly.The euaations Used here were con-puted
bymeans of the electronic rapid co.-.futor BESE of the Acadcmy uf Sci-
ence of the U.S.S.H.Because of the hitherto urikno-in dependeLce on
Card 1/4 height of the air density,the nuLierical resalto Given here are natur-

The Determination of the Life of an Artificial Sfttellite 53-la-3/18
and th-) Invoutieation of the J,.ci~lar Perturbationu of its Orbit.
ally suited only te.,L-,orary or-. cz-,tat ion. flic valli,-:~E; --.-orded by
the satellites .;4111 mak-e it nosrible to carry ~,--t computa-
tions
The d-)undencG of the donsit.-, o4' thF- atmosphere L).,)on heig%tt A.-I
..imated fo-.-,Lila for U143 io -iven,
The e!juation of motion: Th-,~ rjetior, of the satellito is ;~eterLined
here by =akin_.,, use of the "-cuiator., orbit elum;-:jtz;; thc corresi;oll-
ding. eqaation3 of motion aze written down explic!tIy.T-;ia 3.istem of
equatiors is then transforaed b:j =cans of the ec~1e.Aial-~.'echa-
nical theoreLis. Equations for the variable "arga.-.-Iezit of br,~adtllll u
are more suitable for computations than the ecu~_tiuns of '.~-,c true
anomaly -)- .
The method of the determination of the life of an. artififial satal-
litet The authors hsre investigate the Liotio-11 of th,~ in
the terrcstrial atmosphere in the case of a rentral gravitational
field of the earth.The s1z=ltaneous riltion of tli,--- at~lo.-I,A~.ere
ther rite the daily r~--volation of the earth is i-.a,;lQctcd herc.The
corresponding system, of equations is Given.The resi-ita--,on of the at-
Mos.)here does not cause ar-1calar p;~,-rt arba t ions of the ricdal len,-,th and
the inclination of the orbit.Th~a problem invei;tigateC. hc-re leads to
the inteEr- ,tion of a r3,,steu cf tv,,,o diffirential
Card 2/4 out of inte.,ration is discusZed.Thc- c o,,.,il)utat i oils arc car;:icd out
r~ -

The Deteraination of the Life of an A.~~ifiaial Satz!'_'ite 53-1a-3/18
and the InventigfLtion of the Secular Perturbations of its Orbit.
here for the initial height of the apogee h,,w 16oo 11= and for in-
itial heights of the perigee 16o km,