SCIENTIFIC ABSTRACT YAROV-YAROVOY, M.S. - YAROVENKO, G.I.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001962210015-4
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: September 1, 2001
• Sequence Number: 15
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

85538
AUTHOR: Yarov-Yarovoy, M.S
S/026/60/000/009/003/010
A166/AO29
TT=-. Automatic Devices of High Accuracy and Reliability
q
PERIODICAL: Priroda, 1960, No. 9, P. 5
TEXT: The automatic braking device of the second Soviet space ship braked
it somewhat in orbit and the ship began -to descend. As it came lower It encoun-
tered increasingly denser atmosphere layers which increased the braking effect,
causing, however, overheating of the surface to very high temperatures. A reli-
able system of heat-proofirlA.was therefore needed. When a certain speed was
reached the animal cont ine was catapulted free and landed safely with the Fli-_
mals intact and unharmed. The shiD had a built-in television control system and
a superaccurate system for orientaiing the ship in space so that it could be land-
ed at the scheduled point on earth. 01%
ASSOCIATION.- Gosudarstvennyy astronomicheskiy institut imeni. P.K. Shternberga
(State Astronomical Institute Imeni P.K. Shternberg), Moscow
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23688
S/035/61/bbO/004/006/058
AO01/A1O1
AUTHOR: Yarov-Yarovoy, M. S.
TITLE: The interpolation-analytical theory of motion of Ceres
PERIODICAL: Referativnyy zhurnal. Astronomiya I Geodeziya, no. 4, 1961, 12-13,
abstract 4A173 ("Tr. Gos. astron. in-ta im. P. K.-Shternberga",
1960, v. 28, 25-90)
TEXT: This work represents the application of the Interpolation-averaged
variant of the N. D. Moiseyev three-point problem to the determination of an
intermediate orbit of the particular celestial body, minor planet Ceres. The
observatioradata on ft normal positions from 1801 to 1938 were used from the works
of G. Hill, E. Rabe and V, F, Proskurin In the ready form. The author Investi-
gates perturbations of canonleal elements very close to the first system of
Poincare canonical elements-
x k Yi = M+w+f)- lip
x ra
k ( - Yp), Y2 - W r
x3 k ( rp - rp Cos 0y), y3 -
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23686
, 1/000/00 11/00 F3
3/035A
The interpolation-analytical theory ... A001/A101
where Y Is mutual Inclination of the orbits of Ceres and Jupiter, n is ascending
node or the Ceres orbit with respect to the Jupiter orbit, 1 Is mean longitude
of Jupiter In the orbit. The difference from Poincare eleme9ts consists In that
all three generalized momenta contain 1 J, The charanteristlo function looks as
follows: k4 + (x + k2M Wil
2x2 1 - x2 - X3) i
I
where W I/A roos Y/r 2 is perturbqL#on function. The averaging of the
characteristic function Is performed QA236~644pect to X2 and x , and then Wi is
averaged with respect. to Y3 - As a r4412 M funoZlon f) depends on
x + 1
y + M Y
1 3 31
m(2) y
/""2 Y2 + 3 3P
where 1 131 mil), M~2) are constants which are determined by the methods of the
correlation theory from statistical processine of empirical data, Variables
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'3688
SZ035/61/000/004/006/058
The Interpolation-analytical theory ... AW1A1O1
The ortho-interpola-
A are named by the author interpolation elements,
tion con~ltlon has the form-
+ 1 m W . 0, 1 ' + M(2) 1 - 0
3 3 (1) (2) 2 3 3
and quantities 12, 13 and m3 , m3 are determined by the same formulae as in the
circular restricted-problem of three points. Terms of the second order in e, 1
and ~ = sin 21/2 are preserved In the perturbation function, Under all these
conditions, generalized coordinates xl, N, x will have secular perturbations
of the order k2m and y y2 and y peri ical perturbations containing factors
k2m 1 To consiruct ae' practic2 interpolation-analytical theory of Ceres
motionj: the author determines from empirical data interpolation elements
and/t2 and checks the condition of ortho-interpolation. To do this, he-determines
from observations (normal posIti;sj a spries of osculating elements from which
he calculates constants 1, 1, M(2) average values of preliminary 6lements
C
X11 X" Y-.21 Yis Y y and the average value of perturbation function W
initial vAlues o?~IeAe'nts were compared with normal positions, and then these
initial values were improved and compared again with the normal positions, The
obtained approximate intermediate theory of Ceres motion describes the observa-
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23688
S/035/61/000/004/006/058
The interpolatlon-analytical theory ... A001/A101
tions used with -the root-mean-square error of 98" in direct ascension and 115"
In declination. There are 20 references.
N. Yakhontova
[Abstracter's note: Complete translation]
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0.0000 '(80.~o
SOV/33-37-1-30/31
AUTHOR: yarov-Yarovoy, 14. S.

TITLE: Review. E. Finla~-Freundlich, Celestial Mechanics,
Pergamonn Press, 1958, 150 PP
PERIODICAL: Astronomicheskiy zhurnal, 1960, Vol 37, Nr 1,
pp 188-190 (USSR)
ABSTRACT: This is a review of the book by Scotcli astronomer Finlay-
Freundlich giving the fundamentals of modern celestial
mechanics. The book contains an introduction, two
prefatory chapters, and six chapters of main text. The
reviewer gives a brief abstract of each chapiter and
states that the book can be recommended as a pre-
liminary introduction to the problems of celestial
mechanics and as an additional course of studies of
theoretical astronomy and celestial. mechanics for
student astronorper3.
SUBMITTED: September 29, 1959
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AUTHOR:
S/033/6O/037/o04/ol5/O15/XX
E032/E314
Yarov-Yarovo)L, M.S.
TITLE: X On the Explicit Expression of First-order Secular
IPerturbations in Terms of Elements
PERIODICAL: Astronomicheskiy zhurnal, 1960, Vol. 37~
No. 4, pp. 764 - 777
TEXT: Using a general expansion of the perturbation function
in accordance with the Newcomb method, a study was made of
explicit expressions for the fiist-order secular perturbations
in the form of series of powers of the eccentricities and
sines of one-half of the mutual inclinations of the orbits.
Analysis of the number of terms which are necessary in these
expressions shows that the secular perturbations can be
calculated just as rapidly with the aid of analytical formulae
as by the Halphen-Goryachev method. However, -the method
proposed in the present paper has the advantage that it does
not involve harmonic analysis and the residual terms can be
estimated. Moreover, expansions are obtained for the
perturbation function averaged only over the mean anomaly
of the perturbing planet.or only the mean-anomaly of the
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85109
S/033/60/037/004/015/015/XX
E032/E314
On the Explicit Expression of First-order Secular Perturbations
in Terms of Elements
perturbed planet, as well as in accordance with the Hill-
Delauney scheme. As an.example, first-order sec,41ar perturbations
in the elements of Ceres dueto the eight major'j~lanet, are
calculated. Numerical values of the secular perturbations
were found to be very close to those obtained by Proskurin and
Merfield (Ref. 8). Secular perturbations were also found
empirically. In distinction to previous investigations the
secular perturbation in the mean anomaly 1.1 was calculated in
addition to the secular perturbations in the elements i, W
and X4 . It was found that the secular perturbations deter-
mined empirically agreed with the first-order secular
perturbations derived from analytical formulae to within the
limits of precision of the direct determination.
Acknowledgments are expressed to the Staff of the Chair of
Celestial Mechanics and Gravimetry of MGU for valuable
discussions.
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W~

S/033/60/037/004/015/015/XX
E032/E314
On the Explicit Expression of First-order Secular
Perturbations in Terms of Elements
There are 5 tables and 8 references: 7 Soviet and
3 English.
ASSOCIATION: Gos. astronomicheskiy in-t imeni
P.K. Shternberga (State Astronomical
Institute imeni P.K. Shternberg)
SUBMITTED: November 10, 1959
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811931
S/033/60/037/005/016/024
3, N J0 go, o) E032/E314
AUTHOR: Yarov-Yarovoy, M.S.
TITLE-. On the Application or-ffaitsen's Ideal Coordinates
PERIODICAL~ Astron6mi4,,heskiy zhurnal, 196o, Vol. 37, No. 5~
pp. 908 - 917
TEXT: In various problems of celestial mechanics the
perturbations are frequently determined analytically., not only
in the orbi-t elements but also directly in the coordinates.
Depending on the nature of the problem, the principal plane
is taken to be either the plane of tile orbit of the perturbing
body or the plane of the unperturbed orbit of tile perturbed
body,~ The latter plane is then assumed to be stationary.
Moreover, it is usual to assume that the plane of the osculating
orbit of the perturbed body approaches the above principal plane.
This assumption is, of course, only justifiable when secular
and periodic perturbations in the longitude of the ascending
node and the inclination, in a time interval in which the
analytical theory of motion is being set up, are sufficiently
small. This is particularly significant in the case of secular
perturbations, since it is these perturbations which may give
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8h931
S/63-3/60/037/005/O,i6/021*
E032/P,314
On the Application of Hansen's Ideal Coordinates
I
rise to an appreciable departure of the plane of the osculating
orb-it from the principal plane, and thus upset the underlying
as5umption, namely, that first-order perturbations relative to
this plane are small, A consideration of special cases sucli as
the motion of an asteroid, or an artificial Earth satellite,
suggests that in such cases a rotating plane is best chosen as
the principal plane, This plane should have the same secular
motion as the plane of the osculating orbit. Among the various
foirms of solution of this type of problem, Hansen's coordinates
appear to provide the best approacht Here, the plane of the
osculating orbit is taken to be the principal plane and it can
be shown that the above perturbations simply vanish,and the
introduction of the so-called mean elements ensures that the
secular term in the longitude will also be zero, It is shown
jLn the present paper that this approach ensures that C:Lrst-.
or-der perturbations are small. The derivations of the corres.-
poriding formulae are -wery similar to those given by Hansen
himself in Ref. l. Thus, integral equations are obtained for
the perturbations both in the orbit elements wh:Lch determine the
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B4931
s/o33/60/037/005/016/024
B032/E3.14
On the Application of Hansen^s IdealCoordinates
position of the plane of the osculating orbit, and the ideal
rectangular coordinates in this plane for large and small
values of the inclination. Integral equations are also derived
for the perturbations in the ideal polar coordinates whieb can
be employed if either time or the true anomaly in unperturbed
motion are used as the integration variables. The method can
be employed to construct an analytical theory of motion for
both artificial and natural celestial bodies. Acknowledgments
are acpres-sed to the staff of the Chair of Celestial Meclianics
and Gravimetry of Moscow State UniversljLy for valuable
suggestions. There are I figure and 7 referencesi 4 Soviet,
1 English, I French and 1 German.
ASSOCIATION: Gos. astronomicheskly in--t imeni P.K. Shternberga
(qtA~L"atronominaj Ingtitute imeni P.K.ShteEnberg)
SUBMITTED: December 15, 1959
Card 313

39312
S/035/62/000/007/012/083
0 0 AOO1/A1O1
AUTHOR: Yarov-Yarovoy, M. S,_
TITLE: On seriesidetermining the motion of a satellite
FERIQDICAL; Referativn~y zhurnal, Astronbmiya i Geodeziya, no. 7, 1962, 18,
abstract 7A128 ("Soobshch. Gos. astron. in-ta im. P. K. Shternberga",
1961, no. ill, 15 - 38)
TEXT: Differential equations of motion of a satellite around an oblate
planet'are reduced to three differential first-order equations for Delon's
variables 0, 1, g, if integrals of energy and areas existing in this problem are
made use of. Solution of equations is sought for in the foam of series in
powers of coefficients of expanding the planet potential by Legendre polynomials.
Coefficients of these power series are polynomials with respect to vo, sin vo,
Cos vo, where vo is true anomaly in unperturbed motion. The following results
are presented without derivationj 1) The series of the form under consideration
converge for a time span it - tol-e- 114 Oays for an orbit-with e - 0.15, 1 -_ 650
and perjg~e altitude over the Earth's surface equal to 225 Icn; 2) the series
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S/035/62/0W/W7/01Z,1683
On series determining the motion of a satellite AOO1/A1O1
converge for the time span It - to I/_454 days, if canonic Poificar6ls variables
are used instead of Delonets variables: L, ?,,,,
C11 C21 ~11 ~2; 3) the series
converge for the time span It - toj