SCIENTIFIC ABSTRACT V.G. DEMIN - V.G. DEMIN

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• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

The Stabil~ty of Circular Orbits s/i68/6o/ooo/oo1/ooa/oio
B019/BO56
ISSOCIATION: Kafedra nebeenoy mekhaniki i gravimetrii (Chair of
Celestial Mechanics and Gravimetry)
\Z-
SUBMITTED: September 22, 19"59
L/R
Card 2/-~~

( DEMN.. V.G.
Elliptic orbits in the problem of two stationary centers.
Soob.GAISH no.113:35-4.?z 160. uaRA 14:3)
(Problem of tvo bodies)

AKS24OV9 Ye.P.; DEMINg V.G. _
Periodic orbits of an artificial moon satellite. Biul.Inst.
teor.astron. 7 no.10:828-832 160, (MIRA 14:3)
(Artificial satellites--Moon)

DE24IN . V. G.-
A class of periodic orbits in the restricted ciruclars problem
of three bodies. Biul.Inst. teor.astron. 7 no.10:844-849 160.
(MIRA 14:3)
(Problem of three bodies)

'- - - P ~IN, ~V.G - _ _
One particular case of integrability of the Hamilton-Jacobi equa-
tion. Vest. Mosk un. Ser- 3',Yiz-,astron 15 no.1:80-82 160.
(HMA 13:10)
1. Kafedra nebesnoy mekhaniki i gravimetrii Moskovskogo univer-
siteta.
(Differential equations)

AUTHORS:
TITLE:
PERIODICAL:
20338
3/168 60/000/006/011/011
B101 3204
YB
Demin, V. G., Akeenov, Ye. P.
The perioaio motions of a particle in the-gravitational
field of a slowly rotating body
V
Vestnik Ko4kovskogo universiteta. Seriya 3, fizika,
astronomiyaq no. 69 1960, 87-92
TEXT- The following problfm is dealt with. A material point moves in
the gravitational field of a solid, which rotates slowly round one of its
inertial main axes and has dynamic symmetry with respect to the plane
passing perpendicularly to the rotation axis through the center of mass.
For tbri gravitational potential of the body, in the system of coordinates
Oxyz with origin in the center of mass of the body, direction of axis
agreeing with the inertial main axis, Is written down:
k
U = (fM/r) f, + N (X,Y,Z)/r where f is the gravitational
(d/r)
constant, M the mass, r =Vx 2 + y 2 + z is the radius vector of the
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20338
The periodic motions S11881601000100610111011
B101/,B204
most remote point of the body, Qk(xtyoz) homogeneous harmonic polynomials
of k-th order with respect to x, y.' z. If m is the angular velocity
of the rotation of the body round the Oz axis, the differential equations
1br the motion of point P are:
d2x/dt 2 2mdy/dt - m2x M aU/8xj d2y/dt2 + 2mdx/dt - m 2y - Way;
d2z/dt 2 all/az (3). The MOtiOnB of P in the plane z-0 are investigated,
the variables ~,i are introduced (x - b , y - b~ ), and furthermore
m a, (d/b )k ra k-1 const) is put, and the following equations
are obtained: d ;f/dt2 -2a9dj/dt - a 2Y2 av/a~ ; d 2I/dt2 + 2avdf/dt
a2Y 211- aV/aj ; where T - (k 2/Q) f, + ak-1 [-Qkq'~)/Q2k]j
For the required fun6tions u and v with the independent variables -r,
- ch v COB U - 1; -1 - sh v sin u; dt - (ch2v cOB2u)dT is written
lown. Herefrom result the equations of motions u" 2aVIv' + W 11.
u
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The periodic motions... S11881601000100610111011
B101 B204
v" - -2avIul + W v (5), where W - k 2 (Ch v + cos u) + 0.5h(ch 2v - Cos 2u)
2 2 Cos U)2 + -;
+ (a V /2)(ch v - IW
OD
k 2 a k-1 rQk(u,v)/Q2k+l
r Yj
ka 2
2 2
I - ch V - COB U,
I Q - oh v - Cos u. With a - 0,
U11 -k2sin u + h sin 2u ; v" - k2 sh v + h sh 2v (h - constant of
0 0 0 0 0 0
the Jacobi's integrals) These equations give the solution v - const;
0
UO . 2 arctan th(v0/2)tana~j' I where v 0 satisfies the equation
eh vo - -k 2/2h; and U2 - k 2,3h2v O/4oh v0. To this solution corresponds a
motion of the point on an elliptical orbit whose major semiaxis equals
ch v 0, whose eccentricity equals - 1/ch vo. One finds;
Cos UO a (ch'v 0Cos 26T - 1)/(oh v 0 - Cos 20T); sin u 0 sh v0sin2cr-r/(shv0
- sin 2a-01 ul - 2 sh v Itch v - cos 26T) (7). u u + U-;
0 0 0 0
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The periodic motions... S/188/60/000/006/011/011
B101/B204
V . v + v is put and for the differential equation one writes down
0 - - - 7 .
..f(u,v,ul, ",~"T'a); 9(zgU1 971 PTO) (8). The functions f and
9 are periodic with respect to 7 with the period T - 2%/cr. Therefore,
it is possible to a ply the theorem of Poincarfi to (8), and the solutions
of the equation's (83 are found by means of*power series of the 'small
parameterr a. The following solution is given:
v sincaT + F(T); u u u1(A1/8u)dT
I - PIOOB(4.r + 02 0 0
I ~ (1/uj,2ff
+ 0,5] d-r + 0 u 1 (10), where P,, are arbitrary conet-ants,
4 0 P2' PV P4
6)2 k2sh 2v /ch v . In consideration of (6) one puts u Auf.(l
0 0 1 0
+ 2ch 2vO)P3 r/8cr2sh2v0+ ~(T) (11). P(T) and ET) are pbriodio func-
tions of v with the period T. The result'is formulated hs a theorem:
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AUTHORt Demin, Vo G.
TITLEt On Orbits in the Problem of Two Fixed Centres
PERIODICALt Astronomicheskiy zhurnal, 1960, Vol-37, No.6,
pp.lo68-1075
TEXT: The motion of a mass point M under the action of two
fixed attracting centres M 1 and M 2 is considered. The moving
point is attracted to the fixed centres in accordance with Newtonks
law. The motion is considered in a rectangular set of coordinates
chosen so that M 1 and M. lie along the x-axis, the origin is
at the mid-point of the line M 1M2 and the coordinates of the
moving point are denoted by X, y and Z. The integration of the
differential equations of motion is most conveniently carried out
In terms of the elliptical variables of Tiele (Ref.19), Only the
plane case is considered. The coordinates x, y and z are trans-
formed into a new set u, v, w in accordance with the following
equations
x = -c cos u ch v,
y = -c sin u sh v sin w, (1)
z = c sin u sh v cos w.,
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On Orbits in the Problem of Two Fixed Centres
where 2c is the distance between M I and M,, The kinetic energy
of the mass point is
2 [1: (A2 + ~,2 2 2 2]
T = a- ) + sh v sin W-k (4)
2
and the force function is
u = -2--Ef (,l + in 2)ch v f(in I - in2)(,0S u] (5)
c1
where
2v '6)
1 ch Cos U
2
c
and mi. M 2 are the masses of the attracting centres and ri,r 2 are
the distances M 1 and *1 22 respectively. It is shown that for
the plane case the differential equations describing the motion are:
---- "I/C

8
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E032/E514
On Orbits in the Problem of Two Fixed Centres
dj I-)l L;2 G% + - 1 )1 (26)
dT jq2 I ~(X2 + 1 2 1 1
2 ID
(112 + + (4 2 [n-(11, + 1) + (v 1 - (27)
dT 12 [n j
t 2)/(, _ ~2), 2)/(]L 2),
where k = Ch v = (1 + 11 cos u + n _. q
IdT = dt and X 1' X2' V, and '~L2 are the roots of the following two
equations: 2 f(Ml + Md
hk + - C3 J\ + c = 0 (24)
2 f(ml M2)
h1i + C = 0 (25)
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On Orbits in the Problem of Two Fixed Centres
In these equations C is an integration constant. The above
differential equations are then solved for the following cases.*
1. ?
2> Xl> .-"' 112) "1')"
2. 2> Xl> -l' 1,> 112)
3. k2~ "I) -l' 112) 10 1,
4. X2) kl',~ 1, li2) 111) '-
All these cases are characterized by a negative value of the total
mechanical energy (h < 0). Tn the first cast the motion takes
place in a region containing one of the masses and lim:Lted by an
ellipse % = X2 and one of the hyperbolae V. = ji1or 4 = Ii 2- In
the third case the possible region of motion is limited by the
ellipse X = X29 and in the fourth case the mass point moves inside

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On Orbits in the Problem of Two Fixed Centres
an elliptical ring limited by the ellipses X = kiQ X2 and the
trajectory is alternately tangential to these ellipses. There are
19 referencest 4 Soviet, 15 non-Soviet.
ASSOCIATIONt Gos. astronomicheskiy in-t imeni P. K. Shternberga
(State Astronomical Institute imeni P. K. Shternberg)
SUBMITTED: February 11, 1960
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AUTHOR: Demin, V.G.
TITLED On ILLmost-cir-.,-ular,
Sat allat as
268--4
;3/56o/61/000/008/003/010
EOWFUIA
4"' W,
Ortttv of Eartl-,,
PERIODICAL,, Akademkya nauk -S.SSR., Iskussk-veTinyy6 spt~t-n.tki zem1d,
1961, No. 8., pp. 57 - 63
TEXT-. Ar-zifi-,ial Earth -Ratellltev moving oj*er periodic
orbits are particularly conv-etnient. fcr taleulLsion and
similar applIcializzis. The prrraant pti,per is --oncerned with
the calculation ol- such orbitiF. Sinve the -4alk~ulation of
periodic orbit.a,, which would includ-z, all. the perturbations,
is elceedingly difficult, The xc41j*'JPn of tb& pxablem may be
divided into twc parta. To tiv-gin w.Li:h., The periodic orbit.
is obtained for a simpliSled prob.','.~m foz-- which the equatiortr,
contain all the main pertvirbatiot.s WLd thin erblt, is looked-ap3n
as an "intermediate orbit.". N&.xt- lrasqual:iiias are derived
which -aper-ify the perturbatiLons whx'~b are neglec,~r.ed in the
simplified prablwa. The basvc; -Jdea (.,Pt' the method Is borrowed
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~H,-4
S/36D/6.i./O00/008/003/010
On Almost -c- irc;u Lar Orbits EOWE3JA
from Hill3s work,on the mqtion of' theMoon CRef. 2 - Amer.
5, 1878). The present author derives an
J. Math., J..
intermediate orbit a,3.~uming that the MooL and Sur, ms-ve
rel.ative to tbe Earrb in the plano of the ticliptir- over
circular orbits with .,onstant. angu.lar treloz:i-tieia., One
possible method of approach Is aimllar 4 - 14, '1' "s method
(Ref. 2) . where the eff -;~ (- of' the Moon t7;~J ~:'IkSa, i3 -;~,jaluati-d
without taking into'a,~-cqunt iheir para...,:xx, ioi~. by taking
the first term in the eirpans.xcn for tb,4 pezrurbation function.
this simplification is fi~L-Samed, then th,:, piri,,zlem to
Hill's rastricted problem of four bod.~.,-:i. The pre3,ant author
does not admit this assiunption a.ad hsn~,,-e the intermediate
orbit is obtained under, lbss restxl~kjxtg I t jL.
shown that with a syi:i.table cho".c;t, cf th~ xriltial conditions,
it is possible to construct aji intermid-idt-,; ortlt. which will.
be period.-Lo in lie pa.rti -.ular frame of :.hoisen by
the pr,66ent authGr. Th,, seri6s rep,e~-Aiting thiz PeTicdic
solution will converge fo-,i- a smE~11 value of a
If
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On Almost-circular Orbits .... Z03 2/ E-, I It
certain parameter Ii . These values of the parameter
correspond to circx%lar generating orbitis whose radii are
sufficiently small compared with the distance of the Earth
from the Moon and the Sun.
There are 5 references: 2 Soviet and 3 non-Soviet.
The t*d English-language references quoted are: Ref. 2
(quoted in text); Ref. 5 - F.R. Moulton - Periodic Orbits.
published by Carnegie Institution, Washington, 1920.
SUBMITTED: may 14, ig6o
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AUTHORS:
TITLEt
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9032/9514
Aksenov, Ye. P., Grebenikovi Ye. A4 and Demin, V.
General solution for the motion of an artificial
satellite in the normal gravitational field of the
Earth
PERIODICAL: Akademiya nauk SSSR, IskusetN,ennyye sputniki zemli,
1961, No.8, pp.64-7i
TEXT: In the majority ?f papers concerned with the motion of
artificial earth satellites,.'the problem is treated analytically
with'the aid of various series and successive approximations
leading to the final solution of the differential equations of
motion. There is then the attendant problem of the convergence of
the series which is often ignored. Papers in Which convergence
problems areldiscussed are those of A% M. Lyapunov (Ref.lt
Sobraniye sochineniy, Vol.1, Izd-wo A14 SSSR, 1954), A. Wintner
(Ref.2: Math. Zsf. 24, 259, 1926), G, A. Marvian (Ref%31 Byull. ITA,
7, L., izd-vo AN SSSR, 1959, p.441) and M. S. Petrovskaya (Ref.4:
Byull. ITA, 7, L, izd-vo AN SSSR, 1959, p.441). These workers were
concerned with the convergence of Hill's series representing the
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General solution for the motion ... s/Oo/Wooo/oWooVoio
20!12/2514
motion of the Moon. A further problem which appears to be
unr4solved in that of whether the secular and mixed terms are due
to the shortcomings of the particular method employed or whether
the are inherent in the problem. Finall, r
Y F,, it is ve y difficult to
develop a quantitative theory by these m*bkods.- It Is, therefore,
very important to derive a general and alop-prap.ti"lly conven .ient
solution of the problem. J. P. Vinti ('Ref'.5.--~.'R'e_'s'.of Nat.Bur.
Stanld.Math. and Math.Phys., 62B, No.2, 79, 1959) and M. D. Kislik
(Ref.6z Sb. Iskusetvennyye sputniki Zemll, No.4,. t-zd-vo AN SSSR,
1960, p.3) used the Hamilton-Jacobi method to solve the problem of
the~artificial earth satellite in quadratures. An Kislik has
pointed out, the general solution,even ifit in in a very unwieldy
form,turns out to be more convenient for use with computers than
numerical' integration of the differential equations of motion.
The amount of computer time taken up by numerical integration of
differential equations in very much greater than the time necessary
in the case of quadratures. Moreover, the Hamilton-Jacobi
method leads to complicated elliptic quadratur-en whi-ch means that
theiquantitative analysis is difficult to accomplish. The present
authors point out that the general solution of the problem can also
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be obtained on the basis of a certain anal-igy withthe problem of
two fixed gravitating centres. If one considers the motion of a~
mass point in the gravitational field of two fixed centres having.
equal masses, which are at a complex distance from each other,
then the force function for the problem, when the complex distance
is suitably chosen, can be made to approximate the real potential
of the Earth. The introduction of the complex distance is due to
the fact that at least the first few terms in the expansion of the
Earth's potential in terms of the Legendre polynomials have
alternating signs. It is pointed out that if all the coefficients
of the Legendre polynomials were positive, then the satellite
problem would be analogous to the classical problem of two fixed
contres. If. on the other hand, all the coefficients except the
first were negative, then the satellite problem could be solved
with the aid of the solution for the case of three fixed centres,
one of which attracts and the other two repel. The above scheme
has been found by the present authors to be suitable for the
solution of the Earth's satellite problem without taking into
account atmospheric resistance. It is shown that the problem can
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General zolut~.on for the motion ... S/560/61/000/008/004/010
Z032/9514
be reduced to the following elliptic integrals:
d1i T + C (31)
hil4 + 2(c 2 - h)112 2c2 + CI
S dX T+c If
2h). 2fM 0 + 2(c h)). 2 2fM h + (2c + C 2 (32)
1 C3 2 C3 2 1
where the independent variable t is given, by
..t = -S (X2 + 42)dT
(34)
nd h, c C4, C are arbitrary constants. The
11 C21 c3v 5
:artesian geocentric coordinates of the satellite are then given
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Gerieral solution for the motion s/56o/61/ooo/oo8/oo4/oio
2032/11-514
byt
+ &2) (l 02).
x = c min w,
Y = C JU + X 2 M ig 2)-cod W's (35)
where w is given by
W = C1~,(&2 202 )dT 2 c5* (33)
(I - M + h )
A detailed analysis of these results, i.e. the detumdnation of the
possible regions of motion, the nature of the secular and mixed
terms, stability problems etc., will be given in a future
publication. Acknowledgments are expressed, to Professor
G. N. Duboshin for advice and suggestions. There are 10
referencest 6 Soviet and 4 non-Soviet. The two English-language
references not mentioned in the text readirg as follows:
J. A. O'Keefe, E. Eckels, R.K. Squires. Astr.J., 64, 820, 1959;
P, Herget, P. Musen. Astr. j., 63, 430, 1958.
SUBMITTED: November 22, 1960
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DEKIN, V*G*.% naucibn)7 sotrudnik
Start w-w made in February. Nauka i ishiial 28 no-4t8-11 A '61.
(MIRA ~- '. 5)
1, Goaudarstvennyy astronomicheskiy institut imeni Sliternberga.
(Space f3.igbt to Venuo)

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AUTHOR: Demin, V.G.
TITLE: New Classes of Periodic Solutions in the Restricted
Problem of Three Bodies
PERIODICAL: Astronomicheskiy zhurnal,- 1961, Vol. 38, No. 1,
PP. 157 - 163
TEXT: The differential equations of motion in the plane
restricted circular problem of three bodies in the barycentric
rotating set of coordinates can be written down in the form:
2nj + v I
x
(1)
2n:k + V
where the force function V is defined by
n2 2 2 fm1 fm2
V (x + y ) + (2)
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New Classes of Periodic Solutions in the Restricted Problem
of Three Bodies
Eq. (1) has a Jacobi integral given by
.2
x 4 j2 = 2(V +~h) (3)
Using the Thiele transformation (Ref. 2) one obtains
x = c ch v cos - 1 2)
ml + M2
y = e sh v sin u (4)
= W(ch 2v - cos2u) d7t:~
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-New Classes of Periodic Solutions in the Restricted Problem
of Three Bodies
In the latter equation C is one-half of the distance between
the attracting points and n' is an arbit:~-ary quantity which
is chosen so that the quantity Ii = u/n, is sufficieiitly small.
Instead of Eq. (1) one then obtains
2 2
Ulf = 2-4 (ch V -COS U) V, + W
U
(5)
2 2
vil = - 21L (ch v- cos Oul + W,
V
where the force function W is given by
f.(m,+ C11 v +I (,,,I -n,2) cos u + h(cb 2v - cos 2u)
1112C3 n"'C3 24t,20
+ J~- 'Cli 4 v - cos 1w) - ~"" (nil - 1112 (cos u cli 3v - cos ;!, a eh v). (6)%
160 40 (nil + 1112)
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The Jacobi integral c~n then be writi;en. in teams of the
Thiele variables in the following form
u12 + v12 - 2W = 0 (7)
It can be shown*that when IL = 0 , Eqs. (5) represent the
differential equations of the problem of two fixed centres
and can be integrated in quadratures. In order to obtain
a solution of Eqs. (5). the Poincare' small-parameter method
(Ref. 3) can be employed. In using the small-parameter
method simplified equations can be obtained from Eqs. (-5)
by rejecting the Coriolis and centriletal terms. From the
mechanical point of view this approach is therefore similar
to the method used by Hopf (Ref. 6). Using the Poincar~-
niethod one can*seek periodic solutions of Eqs. (5) in the
form of the series
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New Classes of Periodic Solutions in the Restricted Problem
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00
YJ tLkuk.'
k~O
co
V YJ ~OVAI-
k=G
(8~
(8)
where 11 0 Eqs. (5) can be integrated to obtain
u and v as functions of -L, Each-of these functions
will be periodic in -t~ althoug h, in general, the-periods
of these functions will be incommensurable. Of the
4 3 .1
solutions, __10 will be periodic. Let T be the
period of these solutions. Only those orbits will be
considered for which the pericentres and the apo,~entres
lie along the line of centres. For simplicity, it will be
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considered that the.moving point intersects the line of
centres at -- = 0 The periodicity conditions can then
be written down in the form
U T) - u T" 0,
2 )
u'(1 T) - u'(- -1 T) 0. (9)
2 2
PV
(7,T) -V
VP I T)-v'(-!T)=O.
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and these can be transformed with the aid of the symmetry
theorem given by Moulton (Ref. 7) since the system given
by Eqs. (5) is invariant with respect to the transformation
v = ~;' u = Z' -t = - -,E (10) .
It then follows that
1
V(J__T) =
2
V(_4),
2
V'(!T) =
2
-v' (-IT),
2

_T
U( =
2 ) 1;
-U HIT
~ ) 0
2

'( 121L T) (_ IL (12)

= +Ut -ZT 3
2
and the periodicity conditions become
fl. ~ 1
U(O) - 0 u - V1 T = 0
, 0. v'(0) = 0'
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New Classes of Periodic Solutions in the Restricted Problem
of Three Bodies
It follows from the above equations that the latter
conditions can be used to establish the existence of
periodic orbits which are symmetric with respect to the
x-axis and intersect this axis at rightangles. Eqs. (5)
are also invariant with respect to the transform
V = - -~, u = ~,, V = - -,j (14)
so that using analogous arguments to those leading to
Eq. (13), one can obtain the following periodicity conditions
I
UO(O) = 0, u1(- T) = 0, v(O) = 0, v T~ = 0 (15)
2 2
This theory is applied to the following simplified
system of differential equations
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u(,=-'("-'2sinuo+4 sin2u.,
h-les
/(Ml M
I+ 1~ $11 vo A 2v
n wici 0.
Using the Liouville theorem, integration of Eq. (16) leads
to
U (MI COS 110 cos 2u, - (17)
0 n'to
(-I + ell p,, + h ell 2v, + 1.
Vo
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New Classes of Periodic Solutions in the Restricted Problem
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where is an arbitrary constant. The fir;t-order
approximation equations can be written down in the form
+ h
Cos UO os 2ug] ui 2 (6P os' tio) Vol (19)
--:07V -vo - r
+ h
~ ch
11,163 2v0) v~ 2 (eh' v0 - cos" u.) u'. (20)
- cla v, + ~n k3 0
and it is easy to verify that
u u v vo,
1
are special solutions of the homogeneous equations
corresponding to Eqs. (19) and (20). Assuming that
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E032/E3i4
New Classes of Periodic Solutions in the Restricted Problem
of Three Bodies
u u v vin (22)
.0
Eqs. (19) and (20) are replaced by Eqs. (23) and (24) and
when the latter two equatiohs are integrated with the aid
of Eq. (22), one obtains the general solutions of the
first-order approximate equations which are given by
(25)
0 uO ]d
V, + 0, It 2L0 - ecs 2ttu) Wv0dr dvj. (26)
VO ivo- (ell 0
The above theory is then applied to the case where the motion
Card 11/12

89331
S/033/61/038/001/01.4/019
E032/E314
New Classes of Periodic Solutions in the Restricted Problem
of Three Bodies
takes place in the neighbourhood of one of th~o attracting
masses and the existence of.certain periodic solutions is
established in detail.
There are 10 reterence.s: 4 Soviet and 6 non-Soviet.
ASSOCIATION: Gos. astronomicheakiy- in-t im. P.K.Shternberga
.(State Astronomical Institute im.
P.K. Shternberg)
SUBMITTED. rjay 18, ig6o
Card 12/12

L)
AUTHORS-
TITLE-
5 0~5. a) 007/013/G-21
A001/A101
Aksenov, Ye.P.,.~mln, V-G.
On Periodic orb-ilts of an artifi~~;.ai satellite of !:he Moor.
PERIODICAL: Referati-,-.vy zhurnal. Astronomly,:i 1. Gecdezlya, no. 19;6,11,
atist'ract 74 "'Eyul. -In-ta astrcn. AN SSSIV, 1960, v. no.
,A
10, 828 - 832)
TEX~.~ Tne auth~-rs cc!nslder the m3tion ::)f an ar-~.ifi-,Ial
takina in-~-) acc:-unt verturbatlon-,,, frz:!r,,, the E-ir,;h and the shapa cf the Mf-=.
ing Poincar~'s method, they prcve the existencit of per-'---JL~: c---t-"-E
cular cnes. A bar-7ic,.zlar example of such a periodic orb-it, is rreBen,,ed. Da-,,a--
on the lunar shape g'ven :~y Tisserand 0891) w;--re uslc-d in The
circle of radius a = 2,250 kz. waz taken as a gz~,neratlfng, erbil.. -T-~ Zan rna SE-en
from this E~xample, tha-, perturbati.- from -,he ianar Shape taken
consid~rat.ion in determining the crt,-'s of lunar safe' ites :5---Iffic- -~rtly - 'os i! tc~
the Mo;n (There iz, an Importan-, misprint. 'In tn,l ar+.~'-_-!; val%-
Card 1/2

24364
3/035 Aj D 0 /00 -/,) 1 -3/0 2 1
On perlod-ic orbi-ts ACOl/AlO-
efficients a arJ b In Fo7-mula (21) must --e redticed ny a factor of 10. Reviewer).
- -ar&v
0 let 0
[Abs--rac--,er's note: CDmple!-e trans lation
Card 2/2

2 !1 ", 5 '
S/035/6 1/,-,00/00 7/003/0 21
AC)01/AIOI
AUTHOR: Demin, V.G.
TIT'LE- On onr class of periodic orbits In the restricted circular three-
body problem
FERIODICAL: Referativnyy zhurnal. Astronomiy.a I Geodeziya, no. 7, 1961, 4, ab-
stract 7A49 ("Byul. In-ta teor. astron. AN SSSIV, 196c), V. 7, no.
lo, 844 - 849)
TEXT: -The author considers the plane r-astricted circular three-body prob-
1E--. Differential equations of the problem are regularized and reduced to the
canonical form . The characteristical function is divided into two parts accord_
Ing to Charlier. As a generating solution, the author assumed the solution of a
simplified system, which represents a family of elliptical orbits with foci in
attracting masses. The periodical solution is sought for In the form of a series
in powers of the mean motion of the attracting masses. Using the Poincar6 method,
the author proves V- existence of a class of periodic orbits embracing both at-
tracting bodies. M. Volkcv
[Abstracter's note: "omplete translation]
Card 1/1

24359
S/035/(51/000/007/005/021
A001/AlOl
AUTHCR: Demin, V.G.
T_--LE: On elliptical orbits in the problem of two fixed centers
PER16D.ICAL: Referativnyy zhurnal. Astronomiya I Geodeziya, no. 7. 1961, 4, ab-
stract 7A51 (",")oobshch. Gos. astron. in-ta im. P.K. Shternberga",
19060, no. 115, 35 - 43)
TEXT: The author considers the proble.n of two fixed attracting centers,
which is integrable in elliptical functions. For the case of small mass P_/of one
of -the attractIng centers, the author gives t:ae solution in the form of geries
in powers of whose ooeffi(Aents are periodlo functions of a regularized Inde-
pendent varik:e Introduced by -the autlior In ,)lace of time.
G. Merman
[Abstracte_r's note: Complete translation]
Card 1/1

- - I
DEMIN, V. G.
Cand Phys-Math Sci - (diss) "New classes of periodic solutions -
of bounded circular problem of three bodies." Moscow, 1961.
7 pp; (Moscow Order of Lenin and Order of Labor Red Banner State
Univ imeni M. V. Lomonosov, State Astronomical Inst imeni P. K.
Shternberg~
); 150 copies; free; (KL, 6-61 sup, 192)

24352
S10261611000100810011004
D051/D113
AUTHORS: Aksenov, Ye.P., Grebenikov, Ye.A., and Demin, V.G.
TITLEi An outstanding scientific experiment. Celestial mechanics
and the first mannkd space flight
PERIODICALt Priroda, no. 8, 1961, 7-15
TEXTt The article deals with the launching, orbiting and landing of space
ships, the instrumentation and conditions on board the Soviet-built "Vostok"
space ship, and. the creation of astronomical observatories outside the earth's
atmosphere. Multi-stage rockets are said to be superior to single-stage ones
because the thrust chambers can be separated from the rocket during flight.
The authors give a detailed account of the general mechanics of orbital flight
and refer, in particular, to the flight of the "Vostok" space ship. The -
"Vostok" moved along an elliptical orbit with a perigee of 161 km and an
apogee of 327 km. It took 89.1 min to revolve round the earth and the ec-
centricity of the orbit was equal to approximately 0.01. The ship passed
over the USSR at an altitude of 175 to 200 km and covered a total distance of
a little less than 50,000 km. The cosmonaut could see the earth's surface in
all directions at a distance of 1,500 - 11800 km. All quantities character-
Card 1/4

2
5/026 000/008/001/004
L
An outstanding scientific experiment ... D051/D113
izing the orbit of a space ship are subject to change due to the non-spheri-
cal shape of the Earth and its varying internal density. Atmospheric re-
sistance and the displacement of the orbital plane of the space ship due to
differences in the earth's equatorial and polar radii must also be taken into
consideration in order to guarantee the safe landing of the space ship. The
authors discussed the difference between "hard" and "soft" landing. The
former, which is due to high velocity of the space vehicle at the moment of
its impact with the surfaoe of a planet, results in the destruction of the
space ship. The latter is used for space r..:hips with cosmonauts, experimontal
animals etc. on beard and is nxtremely difficult to accomplish if, as in the
case of the "Vostok", the shi-.) is to be landed in a pre-determined locality.
"Soft" landing methods are baded on the simultaneous application of cel6s-tial
mechanics and the aerodynamics of supersonic speeds. After a certain amount
of speed is lost through passing through the dense layers of the atmosphere,
a further reduction in speed is realized br means of rocket braking systems
and parachutes. The space ship enters the braking zone several thousand
kilometers from the landing place, but the braking mechanisms are put into
operation only after the position and the -velocity of the space ship have been
exactly determined. At this moment it must be oriented towards its center of
mass in such a way that the nozzles of the thrust-chambers are in a suitable
Card 2/4_

21052
S/026/61/000/008/001/004
An outstanding scientific experiment ... D051/D113
position. This can be done thanks to a sp~acial system of stabilization.
"Soft" landing can also be made possible by the cosmonaut, using load para-
chutes etc. As far as the construction and equipment of the "Vostok" were
concernedjall measures were taken to make the cosmonaut's flight comfortable.
The authors discuss the problems presented by meteoric and miorometeoric
hazards and state that these hazards were successfully coped with by adjust-
ing the design of the space ship and by supplying the cosmonaut with special
clothing, which, in fact, played the role of a sort of second hermetic cabin.
To avoid radiation hazards, manned space ships flying near the earth's-sur-
face, must fly on orbits below the dangerous belts of radiation surrounding
the Earth. On route to other planets, these ships must fly on trajectories
passing near the earth's axis. The orbit of the "Vostok" was calculated only
after taking these radiation factors into consideration. In addition to the
many automatic installations guaranteeing, for instance, the maintenance of
constant pressure and normal humidity of the air, regeneration of oxygen etc.,
the cabin also contained a device which enabled the cosmonaut to take up a
graduated horizontal position. In this way he could more easily stand the
overloads during the launching and landing of the space ship. On account of
the cosmonaut;s position, the overloads did not ac% along the spinal column,
but in a perpendicular direction. The distribution of the blood and the heart
Card 3/4

2052
S/026/61/000/008/'001/004
An outstanding scientific experiment ... D051/D113
4. a n
function were normal. During the entire -flight, the oosmonaul wa in co -
tinuous communication with the Earth. The authors point to the new possi-
bilities in astronomic research opened up by space flights and state that
projects are at present being developed to establish astronomic observatories
outside the earth's atmosphere. These observatoriesare to be installed either
on large space stations moving along orbits near the Earth or on the Moon.
There are 2 figures.
ASSOCIATION: Gosudarstvennyy astronomicheskiy institut im. P.K, Shternberga
(state Astronomical Institute im. P,K. Shternberg)
Card 4/4

3, Aa0c)
AUTHOR: Demin, V.G.
S/124/61/000/011/'001,/.0406
D2371/ D3 05
TITLE: On one class of periodic orbits in the restricted
circular three-body problem
PERIODICAL: Referativnyy zhurnal, Mekhanika, no. 11, 1961t 11,
abstract lIA92 (Byul. In-ta teor. astron. AN SSSR,
1960, 7, no~ 10, 844 - 849)
TEXT: A plane restricted circular three-body problem is conside-
red. Differential equations of motion of the third body (zero mass)
re~ the center of mass of the other two bodies are expressed in
terms of canonical elliptic variables and normalized. Poincar6;s
method of a small parameter is used to show the existence of the
class of periodic orbits containing both attracting -,lasses and ly-
ing in their orbital plane. [Abstrau-tor's note: Conolete transia-
tion].
ard 1/1

DEMIN, V.G.; AKSENOY, U.P.
Periodic motion of a particle in the gravitational field of a alewly
rotating body* Vest, Moak. un, 1.1;er. 3: Fiz.,, astron. 15 no. 6:87-92
R-D 160* (MIRA 140)
1. Kafedra nebesnoy melchanild i gTavimetrii Moskovskogo
gosudarstvemogo universltst4Le
(Gravitation)

. DE rX, VG,
Near.-circular orbits of artificia1earth satellites. Isk.sput.Zem,
no.8:57-63 161. (Artificial nktAiliteo-Orbits) (MMA. 14 16)
t~-

AKSENOV "e.
.. ~ *P*; GREBFILULOV.. le*Ao; DEM V4.
General solution of the problem of the motion of an artificial
in the natural gravitational fie.U'Lof the earth, IkespatoZem.
no.8s64-71 161. (MM
satellite
14:6)
(Artifiol.al satel3ites)

8/025/6 1 /000/011/003 /003
D243/D302-
AUTHORO~ Demin, V.G., Candidate of Physice mithematical
%- _'-'iencea
TITLEz Cluad-satellites
PERIODICAL& Rauka i zhim', no. 11, 1961, 104-105
TEXT& The author gives an account of soae cloud satellites
recently detected near to Earth.:The existence of such large gaa
and dust clouds has long been post-ulated. Doctor K. Xordyievskiy,
a- Polish astronomer-j, recently observed two weakly shiiiing misty
spots in space which may be regarded, for practical purposes,
as occupying the same position in space. They reproduce closely
the Moon"s pat4 , maintaining from the latter a constant angular
distance of 60 - It has been shown that they are natiiral Burth
satellites, 4OOyOOO km away, whi6h form an equilateral triangle
with the Earth and Moon revolving steadily around the center
of gravity of those two bodies at a rate of one revolution a
Card. 112.

AKSUIOV, Xe.P.; GREBENIKOV, Y-e.A.; D&U, V.G.
Outstanding scientific experiment; celestial mechanics and the first
space flight of mani Priroda 50 no.8:7-15 Ag t61. (MIRA 14:7)
1. Gosudarstvennyy astronomicheskiy institut im. P.K. Shternberga.
(Space flight)

ESSM AR: AT4035YA
SASUAW000/123/0022M37
~~JWHORI. Aks6nov, Ye. P.; Crebenllwv, Yo. At.; Deoln, N. G.
,-.'TITLE: Trajectories of a parabolic class in the problem of motion of a material
:Particle in the earth's normal gravitational field
:SOURCE: Moscow. Universitet. Gosudars:tvenny*,f astronamichaskly Institut.
Soobshcheniya, no. 123, 1962, 22-37-
TOPIC TAGS: artificial satellit-ev ietificial satellite orbit. artificial satellite
orbital element, artificial satelitte.parabolic orbit, normal gravitational field
ABSTRACT: This article discusses the motion of a material particle in the earthos
normal gravitational field. The normal gravitational field Is determined by the i
potential of two attracting fixed centers situated at some apparent distance from
one another. The authors give the results of,a qualitative analysis of the aqua- i-
:,:tions of motion for a case when the total mechanical energy is equal to zero. le
is shown that there are five types of motion. Parametric orbital equations are
derived for each of these types. The paper is divided into 7 Parts*: I - Investi-
gation of the elliptical coordinate u; 2 - Investigation of the elliptical co-
ii ordinate 4 0 3 - formulas for the coordinate w; 4 - Relationship between time 4- and
thqk regularizing variable -C 5 Polar trajectories of the class h 0; 6 Equ-i

:.ACCESSION NR: AT4035346
:~atorial crbits of the class h u 0; 7 Summary of the formulas for the five types
of wtio-i. It is concluded that motion Ina 11, the types of the parabolic class
,occurs in unlimited trajectories in an infinite period of time. orig. art. has:
J3 formulas.
::ASSOCIATION: Gosudarstvenny*y astronomicheskiy institut MoskDVskogo universiteta
''(State Astronomical Institute of Moscow University)
SUBMITTED: DATE ACQ: 26PIay64 ENC'A 00
00
_1SUB CODE: AA, SV. NO REF SDV*. 003 OTtE R-. 001
2/2
-T7-7

AKSENOV, Ye.P.; GREBENIKOV, Ye.A.; DEMIN, V.G.
Polar orbits of artificial earth satellites. Vast. Mosk. une
Ser.3: Fiz., astr. 17 no,5:81-89 8-0 162. (HIM 15-10)
1. Kafedra nebasnoy mekhaniki i gravinetrii lj.*oskovskogo universitat,,.t.
(Artificial satellites)

E 44 IV, ~i
f3~M, Y~e.., GREWM=V, Is. A. and WW'( Y. G.
"Generalized problem of two stationary centere"
Report presented at the Conference on Applied Stability-Of -Motion Theory and
Analytical Mechanics, razan. Aviation Instituu," 6-8 D*cember 1962

....ACCESSION NR: AR3000009. S/0p69/63/0D0/007/O0O8/OO09
SOURCE: RM. -Astronomlya, Abe 7.51-94
AUTHCR: bemin, V.. 0.,

TITLE: 'Approximate solution t~ the problem of-the movement of an artificial
earth satellite..
.
P.' K. Shte ibe g no. 125, 1962
CITED SOUR.M., Sotbahch. Goo. astron. In-te, A'A ri f ap j.
~3-11
:TOPIC TAGS: satellite notion,, xatellite movement".artificial earth'satellite,
'Hamilton-Jacobi method
TRANSLATION: It was shovn earlier.that-the pro'bles of two stationary centers in
~
I
its generalized fcii~ulation. may be U'Sed'in the problem of motion of artificial
earth satellites in the non central gravitatiotal field of the earth. The

generalization of the problem consists in the V.'act that the masses of the at- 7
tr~acting centers and the distances between thea are taken equal to certain com-
plex quantities which are chosen in such a vi y,that the potential assumes real
Card i/2

A=SION NR: AR3DO6DO9
values for any position of tbe,satellite in space.
In th6 geocentric equatorial system of coordinates x, y,, the earth's
gravitational potential is represented in the form
LM 1~~,V+ X
Ubere
Here f in the gravitatio ,f Z I'a and. a-
oal'constantp N In-tba.earth's Mass, i.
are quantities characterizing the compression and asymmetry of the earth and ex-
pressed in terms of the coefficients of the second and third harmonics in the
expensionof the earth's gravitational potential+.
The kbproximite a6lution takes1nto account the effect of the second bar-m
; i
monle.. This solution in found by the Hamilton-Jccobi method in the spherical,
:V system of coordinates'. N. Yokhontove.
"I'DATS ACQ:-.15AU963 StM*'CODE: AS' INCL: '00
-Cird

GREBENIKOV, Ye., kand.fiziko-matematichaskikh nauk;_.P~N,,_Y,ka.nd.-
fixiko-matematicheakikh nauk
Spaceship flies to Venus.. AvA kosm. 45 no.8:18-21 t62.
(MIRA 15:8)
(Space flightto Venus)

AKSENOV, Ye.P.; GREBENIKOV, Ye.A.; DEMIN, V.13.; PIROGOV, YO.N.
Sam problems coneerning the dynamic3 of flights to Venus.
Soob. GAISH no.125%1241 162. (MIRA 16:3)
(Spaes flight, to Venus)

SUBBOTIN, M.F., otv. red.; GREBENIKOV, Ye.A., kand. fiz.-matem. nauk,
red.; DEMIN, V-G kand fiz.-matem. nauk, red.; DUBOSHIN,
G.N., 5~6~ ~or ff--~~tem: nauk, zam. otv. red.; OKHOTSIMSKIY,
D.Ye.,, red.; YAROV-YAROVOY, M.S., kwid. viz.-matem. nauk, red.;
NIKOLAYEVA, L.K., red. iad-va; SREVCHENKO, G.N., tekhn. red.
[Problems of the motion of artificial celestial bodies)Problemy
dvizheniia iskusstvennykh nebesnykh tel; doklady. Moskva, Izd-
vo Akad. nauk SSSR, 1963. 294 p. (MIRP 16:2)
1. Konferentsiya po obshchim i prik1ndnym voprosam teoretiche-
skoy astronomii, Moscow, 1961. 2. Chi.en-korrespondent Akademii
nauk SSSR (for Subbotin, Okhotsimski,
y).
(Artificial satellites) (Meoh&Aics, Celestial)
(Spaceships)

ACCESSION NR:. AT3006845 S/2560/63/0001016/0163/017Z!
AUTHORS: Akeenov, Ye. P.; (Nebehilcov,, Y'e. A. I Demin, V. G.~
TITLE: On the stability of some classes of orbitS of artifictaf Earth satellites
SOURCE: AN SSSR. Iskusst. sputniki Zemli, no, 16, 1963, 163-172
TOPIC TAGS: satellite, Earth -satellite, artificial satellite, artificial Earth satel,
lite, sta' .1ity, orbit stability, equatorial orbit, circular -:~quatortal orbit, polar
orbit, elliptical orbit, polar elliptical orbit, ellipsoidal orbit, hyperboloidal orbit,
hyperbolic orbit
'ABSTRACT: This theoretical paper issues from the authors' antecedent study, in
lithe same series of booklets, no. 8, 1961, b4. in which the motion of artificial Earth
E) satellites ~S) was examined in the normal gravitational field tNGF) of the E.
iThe NGF, in the geocentric system of cylindrical coordinates, r, ~, z, the prin- i
cipal plane of. which is as sumed to be the equato rial plane of the E, and the z axis
iis the a3ds of rotation of the E, is expressed by the formula
U L111 I
+
2 + (z
i Calrd 1/3

iA-CCESSION' N_R:_.&_T'300_684_5______
,Where f is the gravitational constant, M to the mass of the E, and c=210 km is,a
,quantity determined by the flattening of the E. The present paper investigates the
,stability (in the sense of A.M. '..vapunov) of the particular solutions admitted b
ithe differential equations of moton of this dynamic problem, also their stability i
!
tunder constantly acting perturbations (CAP) of a given form. Thes'e solutions, In
correspond to polar elliptical orbits, circular equatorial orbits, and
'periplegmatic orbits located on several ellipsoids, etc. The stability analyses set!
forth here comprise: (1) Stability of circular equatorial orbits (CEO); it is provi4
:that CEO's are stable under CAP. In the potential of the NGF of the E, there are
i
ino longitudinal tern.-is characteristic of triaxiality and also no terms that might be
ioccasioned by asymmetries of the E relative to the equatorial plane. Harmonics
.of higher orders are also not fully considered. (2) Stability of ellipsoidal and polar
,elliptical orbits (PEO). It is demonstrated that th'e PEO's are stable with respect.
~to the major semia.,ds and the eccentricity of the ellipse. It is also found that for
:sufficiently small values of clo, ellipsoidal orbizs will also be stable in the
~Lyapunov sense re~,ative to the major axis and tho eccentricity of the ellipsoids
along which the artificial S moves. (3) Stability of hyperboloidal and hype -bolic
orbits (HHO). It-is demonstratbd that these-orbits are stable with respect to the
semiaxes of the hyperboloid along which the motion oc~cu~'s and with respect to its
,eccentricity. Orig. art. has,61 numbered equations.
!Cord

AKSENOV, Ye.P.; GIMENIKOV,
Qualitative analysis of the forms of motion in the problem
of the moticm of an artificial earth satellite in the normal
field of' the earth's attraction. Isk. uput. Zem. no.16:173-
197 163. (MIRA 16:6)
(Artificial satellites)

GREBENIKOVY Ya,, A,,,, kand. f iza-zatem. nauky DWIN, V, G., luind,, f is.-
matem, nauk
Study of the miv&r'bodles of the solar system; astronomical
confer-once at Baku. Vest, AN SSSR 311 no.l,.326-127 Ja 163.
(MIM 16, 1)
(Planets Minor)
(Astron ' Congresses)
OMY-

0/033/63/040/002/018/021
3001/2120
AUTHORS: liksenov Ye.P., Giebenfko-ir Ye-A., and Demin V. G.
TITLE: The generalized problem o:l~ two fixed centers and its
application in the theory~of motion of artificial
carth sat4llitas
PERIODICALI Astronamicheskiy zhurnal*.~v*40, no.2, 1963, 363-372
TEXT: The classical problem nf '16',wo fixed centers consists in
..a study of-the,motion.of a passively 1;ravitating materirl point
subjected to attraction.by two fixed waterial points P.1 and P2.
In the present paper this problem i investigated in application
to the motion of artificihl,sa*telliteiii. The potential U in the
'problem under-consideration can be prii)sented, if inverse distances
r, and rp bare expanded in series in Legendre polynomials$ in the
f orm:
Co
fm
'n
r 1.+ T - . r
r
n
a
1 .1 + M2 2
whare M in mass bf.-bo,th.fixed,:bodieii1 and
Yn
card 1/3

DEMINP V.G,
Stability of the permnent rotatiam of a heavy solid having
one fix*4-point and differing little from S.V. Rovalevskaia's
gyroscope. Trudy Un. drusho liars 5 Tooro m9kh, no.2tl36-140 164.
(MRA l819)

r
o the-planet, bl-
ele- fAs, 11,he:. constant,, thel :mass f
1. the L~-coord_'Inata. jDf the ipoilat _oU the apbere of :inertia; r , 6$ and It are
the'' spbericial coordftid_teg!~~df 'the sate-Ilite.; and R is a -disturbAng
The na Aisturbing forces: is not taken Into
1unction, ture of the
they, re sufficiently small. For
account ; it;is,assuned~:o nly tha a
the .:qualita:tive an Itonian system of' d4s-
alys,is of' the mation'- alMami
turbed motion is written in canonical; variable It Eqsoniq- and the!
an- function Vis eetablishec'4 Using the lmogorov-Arnol'd
Ham:~ltoni
methodi the': author provas~ the stabilitty of saltellite orbits and the
t all- - -----
-C
-thal.1-1 18`4~.Aualyti~c dbl~ain and that -thok n6n-
-;con iti .(a-'etkrtain~, acoman a ift*lt aqua to
-d- On racy d zero) is
a a on
th lite will be
satisfiedo, t a P lalte 'out at Ok4i motion Of a satel
0
conditionali.y periodic:'~atkd 1agrange-gitable, for~any initial.% conditions!'
a A. Or
t whan:,'tfie dij turbing fw,_~tlon:'R does nPt depend igs. art* has i
2 Jorou x,
la
_r7.
.bifi.
a -n;_::4.*OAO -
Cari 213

27215 ~i6 EWP (M) -2/EWT(l )/EWA ( d Za/w
ACC NR% Am6oolo4q -Monograph - wiT
1,Grebnikov,')M-vgeniy Aleksandrovich.- D~
~nV~o~dimir'Grigor 'Yevich
Interplanetary ;~~ightq (Me'zhplanetnyye polety) moscov, iza-vo, "Nauka, 1965 199 ps
illus. 16,500 copies' ptinted.
at
TOPIC TAGS: Arrterpltnetary flight, InterplantitM tfaje_ ory, space flight motion,
flight.mechinies, cosmic dust
~PUMSE AND COVERAGE:: This book is int4nded ~i!or a vide circle. of readers interested
in space-flight mechanics. It can be arb1trarily divided into two parts: thl~'
first two chapters contain fundamentals oJ' astronomy,,vhich are necessary*for
solving aetronautical problems-, the last three chapters present a description of
various interplanetary trajectories from 1;he point of viev of flight. mechanics
TABLE OF COYMTS:
'Foreword
V,t! -.Ch. I. The ilamily: of, planetG.-, -11
1. 1. The kkead of the family of planets 32
1.2. Acquitintance with superior planets L 16
1.3. Inferior planets and comets 30
1.4.. Interplanetary.dust 32
Card l/A
b~c: 629.198

-1 27215-66
-.,.,.-'ACC NRt Am6OO:Lo4g
Ch. II. Acquaintance with'celestial mechanics 35
2.1. The law of universal gravitation --.35
2.2. The two-body problem. The first Keplerian lav 39
2-3. The aecond and the third Keplerlan i,aws -- 45
2.4. Orbital elements of celestial bodies.- 47
2.5. What is a perturbed motion? 52
2.6. Astronomical constants,-- 55
2-T-'~ The integral of energy 58
2.8. The three space velocities 6o
2.9. The most favorable elliptic trajectory 65
2.M Visible motions of artificial and neitural bodies,,of'the solar system' 67
Z~
Ch, III. Rockets and space flights -73
-.3.1. The lavs of reaction, motion. TALyouf of arocket 73
3.2. W tistage rockets 77:
3.3, The future of rocket.technology
T9
3.4. The povered flight.trajectoiry - 83
3-5. Land:Ldg of spaceships --ID
3066 Dangers involved in space, flights. aiid the 'ways and means of overcoming
e'm
t
h 96
Man In a space6hi '102
3 T.
MAV. Preli6inary 6 6k-interji~e6etary tidjectories 110
3,

27,21$-66
-Aco., Am6oolo4l
_9
4-16 The platis and the-outlookJor interplanetary flights 110
4,2. Some preliminary 14
remarks
"ralectoriewto.Nenu-Iv
4.3.-- Flight 1, .117
r
h.4 h Flight. trajectories to,HarsU- 130.-
o~. -,Zovf'et and American Interplanetary a ',ceship stations 136
flights pro,44ing a return to the earth.-- 142
4.7- Interpliinetary overflights along unliwited trajectories -- lh5
4'0' 8. A roach trajectories involving severeil planets __ 147
pp
154:
4.9. Launching of an interplanetary.spaceskiip from aboard a satellite
kilo.~Flight trajectories to the distant p1tinets of the solar system- 159
.4.no. ArtificAal satellites of Mars and Venxiz 163
-,~Pe#ui!bi-;d motion of an interplanetary'spaceshi
P
s'in:app`oximate calculations 171
-Basic ri-i-duction r
'2s: -Interp tane-ary overflight trajectorieti considering the ellipticity and the
. t
5
inclination of the planetary orbits relative to each other - 1T4
-5 3. Consideration of gravitational forces of planets exerted upon a space-
ship~- 179
-.Consideration of the,effect of light ]:.ressure on the notion of a space-
ship 181
5.5. Interplanetary flights with low-thrust engines 183
5.6. Launch-phase trajectories in the vicinity of the planets 190
rpi anetary impulse trajectories 193
3.98
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elm
e1 of
1, 0. Novik, and I. MmIti. Stomaldogiya 1954, No. 3,
7 A-
-
-7r
I:Kkim
1955
MOM
=
.
to
.
.jm
If
,
1
is tils"y
The inorg: PA tettji, (1) was dold. first, Iwvitiol
Sol. mr; ill low aclo Concus. The ii'ly, of I Ill I'tlitli,
where the %"ater hits a high F msitent was ),-imr thum in
vicinitiesn Ith %vattit.of a IuW 1; coutf at. Theuw~0'1-'rllg.
Imith Pastt inerva!.ts the ie-,istumc of the ellutIO it, the
action d aci&, B. ~N. 1.E.% ilm

UMNOVICH, TL.I., assistent (r1yev); DMrN, V.I., Imud.biol.nauk (11yev)
Charwber of the proteins of the saliva of patients vith para-
dentoais. Ptobl.stom. 4.,151-155 158. (KM 13:6)
(M*S--DI=AnS) (PRMIM)

SALITM, V.A., prof. (Iiyev)l JWISOV' N.V., Prof. (Xiyey); DIMIN, V.I.,
kaud.biol.nauk (IELya-v); POMDTILO, Ts.D., lmud.sted.nauF yei~. -
Significance of the COMPlex of D TItamIns In the treatment of
paradentosis. ftobl.stom. 4:237-240 15B. (MIU 13:6)
(VMMINS--B. WC.--THnUWTIC USE)
(Ovs--DISFASIS)

Der-Lin, V. I., ?%orL-unov, 1. U., -7,atuia, D. k;. and Ya,vd, S. L.
Tp-,L-im- of dinlitherial toxin by nevriq oi* r-.dicEctive Substances
'-.E,-- t
(isotopes) - -1
. ~11 " 7 o
!;'Iaterialy nauchnykh konferentsii, Kiev, 1959. 2 6 " ,~n'7)
Odevskiy 1%7aziclino-issle(iovitellsk-iy imnlitut Enicle-li(I.Loc'Ji i idkroldoL'CH)

GROMASHEVSKAYA, L.L.;_ DEM, V.I.; SHAPAMIKO, V.N.; SOKOLOVSKAYA, A.P.
Evaluation of some biochemical indicators in the diagnosis
of aborted forms of infectious hepatitis. Nauch. inform, Otd.
neuch. med. inform. ANN SSSR no.lt27-28 161. (MIRA 16:11)
1. Institut infektsionnykh bolezney (direktor - chlen - kor-
respondent AMU SSSR prof. ro-L.Bogdanov-) AMN SSSR, Kiyev.-.

DMIN, V.I.; SOKMOTSKAYA, A.Ps
Importance of determining bile acide in blood senm for the
diagnosis of aborted forms of heyatitis. Nauch. inform. Otd.
nauch. med. inform& AM SSSR no.1t26-27 161 (Min 16:11)
1. Instytut infektsiom7kh bolewley (direktor - chlen-korres-
pandent AMN SSS prof. I.L.Bogdanov) ANN SSSR, Kiyev.

DWINVYII. ('~uyov); WETIrEV, V.M. (Kiyev)
h,-otein fraotiom of tho blood serum In complica-tad and uncomplicaWd
Ijifluenza. Sbor.nauch.trud. Inst.ir-fe1c.bol. no.41l.73-179 164,
(FITF,A 18:6)

Y-JI.
Bc RA
IG nD.3.-246-252 M.:-Je 164.
Uki~SSR, K!'Yev.

D,L-,N / A/,
15-1957-7-8965D
1957,, Nr 7,
Translation from: Referativnyy xhurnal, Geolog;Lya,
p 13 (USSR)
AUTHOR: Demin, V. Me
TITLE: Upper Permian and Lower Triassic Variegated lRocks)
of the Northeastern Border of the Great Donets Basin
(Verkhnepermskiyel nLzhustriasovyye pestrotsvety
severa-vostochnoy okrainy Bollshogo Donbassa)
ABSTRACT: Bibliographic entry on the author's dissentation for the
degree of Candidate of Geological and Mineralogical
Science, prevented to the Rostov-na-Donu University
(Rostovsk. n/D. uneei), Rostov-na-Donn, 1956.
ASSOCIATION: Rostovsk. n/D. un-t (Rostov-na-Denu University
Card 1/1

DIMIN, V.M.
Stratigpaphy of variegated sediments in tho Don Bend. Uchi zap,
RGU 44:43-54 159. (KIRA 14:1)
(Don Valley--Geologr, Scratigraphic)

DR-IIN, V.Y,.;PMAPOV, I.I.j, prof... otv. red.; KOVALENKC., Yu. .V., red.
PAVLICHENKO,, M.L., tekhn. red.
[Radiometric methods of searching for urtTdum ores; land
survey]Radioraetrichoskie ratody poiskov uranovykh rud; pe-
shekhodnaia s"emka. Rostov-na-Donu, Izd-vo Rosto,--skogo univ.,
1962. 105 p. (MIRA 15:9)
(Uranium ores) (Radioactive prospecting)

DEMIN, V.M., 6otsent kand. tekhn. nauk, polkovijik
Determining the position of an airplane over the ocean by the
measured altitudes of heavenly bodies. Mor. sbor. 47 no.4:51-57
Ap 164. (MITA 18: 7)

DEM1211 V.M.; KHRUSTALEV, Yu.P.
Some characteristics of the early hicton, of the Sea of Azov.
Okeanologiia 4 nc-5:850-855 164 (MIRA 18:1)
1. Rostovskiy-na-Donu gosudarstvenny
.), universitet.

ABRAMOV, SM., prof.; BAIHOV, G.A., prof.; BLLNOV, II.I., prof.;
GADZIiIYEV, S.A., prof.3 GODUNOV, S.F., prof.; GOFIZYAKOV,
G.A.,, prof:; DEMIN, V.N,.. prof.; ZVORYKIN, I.A., prof.;
KAPITSA, L M-.~=~-ied' ROVSMA, S.P., kand.
y . m . nauk; MOK
med. nauk-. POSTNIKOV B.N., prof.; PORKSHINAN, 0.10i.,
prof.; SIDORENKO, L.N.., ka-nd. mod. ;,,iauk; TALIMAN, I.M.,
prof., FEDOROVA, A.D.., kand. med. nauk; FlIJIT011, A.N.,
prof.5 MOMOV, B.M., prof.; SARKISOV, M.A.) red.
[Errors, hazards and complicationg hi suri2ery] Oshibkiy
opasno sti i - oslozhneni-4a v khirur - - I ~ LanI rq rad, Me-
F.L L 1,
ditsina, 1965. 563 p. (MIRA 18:7)

1. IMIN. V. N., LITVINOVA, YE. V.,.RTROV, M V., CHMIN, A. V.
2. ussR (6oo)
4. Stomach-Cancer
7. All-Russian conference on diagnosis and therapy of gastric cancer, on
precancerous conditions of the stomach. andon methods in control and
organlzation of prevention of gastric cancer.
KhIrw:qiia No. 11, 1952
9. Monthly L~sts of Russian Accessions. Library of Congress. March 1953, Unclassified.

Da"IF, V. !".
Rectum - Cancer
~o--anato;iiical tudy of rcLro-r;~.dc in c~-tncpw of the
Experimental and patholof I
rectum, Arkhiv pat., 14, Nlo. 2, 1952.
Ilonthly L12L of Hus!5ian Accessions, Library of Corirr-2s:,~, October 1952, Unclasz~ified

v.DLI1.7111, ITTD C7RTS
U
"An all-Urdon confcrovce or prvbIf-ITIq of tho diarno'As [kill irovtv!(~nt of
gastric cancer cad prEcancerour starcs an we:11 as en met),,c(Is rand orc-silization
of the strugp-le against gastric cancer" T~-. from 'tie R-..issian F-86
(ITAL LE ROMUC~-SCVIETIGAF . SERIA II-EL-11CINA Ul 1ERliLA Vol . ~, f,.0. 3, Yayl
June 1953 Pucuresti, Rumania)
SO'. East LC, Vol. 2, NIo. 1-0,Dec. 1953

IMIN. Y.N.,
wwowv
Restoration of recto-anal reflexes and functions of the sphincters
following resection of the rectum and the sigmoid flexure in oancer.
Vest.khir.74 no.2:53-57 Kr 154. WMA 7:4)
1. Iz kafedry onkologii (saveduyushchiy - professor A.I.R&ov)
Leningradskogo, instituta unoverebene tToraniya vrachey im. S.K.Kirova.
(Rectum--Surgery) (colon (Anatomy)--Surgery)