SCIENTIFIC ABSTRACT OKHOTSIMSKIY, D.Y. - OKHREMENKO, N.M.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001237910008-0
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Sequence Number: 8
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

0
S 208/62/002/001/008/016
/1
On the behavior of shock vmves at ... D299/D303
thereby the computntioris were cttrried tbr-n1!t,'h to a pre!isure gradi-
ent equal to 1,0018. The coinpiitationp vere further continued by
meanz of S.A. Khristianovich's apizriximate method (Ref. 2: Udarnayn
vo1na na znachitellnom rasztoyanii ot nests, vzry-va, Prikl. matem.i.
mekhan.y 1956) 20) no. 5y 599-605). In additionj results are given
relating to the formation ol the second shock wave in the negative-
phase region. Denoti-ng by p) u, p, I) and e-, the presBure~ particle
-velocity, density, shock velocity and coordinate of the shock front,
one obtains (after transformations), thesystem
+hziu+g-fP+d=0. (2.17Y
aT 07) all
fp + (2.18).
OP a7 OZ (2.19)
+ 6~jj'+ C + h 0,
b=. V-7)D C_ P
V __ , e=
1. + t' (2.20)
I 27j. jD -PU PD
card 2/6 _F T.-

812061621002100110081016
On thi behavior of shock waves at ... 3)299/D303
The problem amounts to the integration of system (2.17)-(2.19) un-
der the following boundary conditions: At the shock front
e, 2
U= D - D7
7+1 (2-21)
P 7 4:1+ IT
7-1
P 2
and at the left boundary
u = 0. (2.22)
System (2.17)-(2.19) was integrated by means of a second-order di'-
ference scheme. The partial eerivatives were written in the form
a/ ~ P, ++,, + n-, I - P, +, - n
2 JT"+3
(3.2)
T)J+j - 711 <
Replacing in Eqs. (2.17)-(2.19) the partial derivatives by finito
Card 3/6

S/208/62/002/001/008/016
On the behavior of ffliock wives at D299/D303
differznceD, one obtains
+ ~ngn) 1/4 A.
+V3 1+1 14,11, (3-3)
CX-nP",~n+1 + + me
4~'Y- (u-+1 - B.
J4-VS S+j W4 , 6+3 (3.4)
aj"++"""' + M qVIVIJ Iij-in++,] + 1)
R'++', + X (3-5)
Tile system of difference equations (3.3)-(3-5) was solved by the
.iell-Bhaft" m-ethod (developed by I.M. Gellfand and G.V. Lokutsi-
yevskiy), Thereupon, S#A. Khristiwiovich's approximate method is
used, involving the integral of the equations of motion of a sphe-
riezil shock-wave, viz.
7--
6= I] in -1 + -L6- (4.1)
'where (4.2)
Ilith low pressures, one can pass fron the nuncrical coLlcul.,Alon (by
the '"well-shaft" nethod) of the ~wive form to calculation by formu-
la (4.1 ). The diotribution of the excess uressure rutj ciilculated by
Card 4/6

'j ~J.:'/ U
On the behaviox of shock waved a--. D 21 9 9/ D.-- 0
the appiox-Imate formula
Z-% 17, - vi 14
Fur-ther~ the results of calculatiOM-_5 OrE given in fi~gureq an't t"..
ble-9, The value oil m In formula (3~2) was iiie~- m 1- 112, The
time-!3tep was 11~ -c - 0-:21,17988 t%0,730-~ se-- The nu-merl-a.
tion was carried out 'to -rhe ra~)ment T
could not. be carried out beycn6 hat ae the smoo-.hness ~f -th~e
tion vas -Inpaized. The s&:c,,;laIVjon5 by he approximate me"lind ~v'.,e
star,ted a litt"-7e earlier (a--. r - 58~,4;5'i ~,- The r e s i I T T
65-2342 c;cim:-ided for botLh th;- mmerical and approxm-,
The approximate method was used for cal-,--,13-t-ing the ve-~ --ity r,-,,3- j/,
trib-aticn -a, the rad2u~~ of the shock front and the -!e-
locity i=ediately behind thp front. F '-om a figure, tbe tcna-~.,~-y
profile reversal and sh,,)-I-.k-vmve -,n th;: neZ-L"I,E, '11,'na3c' r---
gion, is evident~ The tables sh.-1w the nosit.~-:)n -.z 'ni. fr3r~.
the values of the uarameters i=ediately behir-id the shocck fr,'!nt ne
a function of time, the distribution of -~he ex~es,, prossure,
cle velo0ity and densiiy, the magmiudeL7 of the meas of
-L.ive and negattlive ph--ses are also listed -,n a table; Th,3-r- m-
Card 5/6

On he
S li B 111 TT 2 D0,-
A
Vi;
Card 6/6

O)WOMDEXTY., 1). Ye., and DUBCSM., 0, N.~
"Some problems of natrodynamice and celestial meebanies"
report to be submittea for the 14tb Congress Intl. Astronautien 7ederation,
Paris, FTance, 25 SeP-1 Oct 1963

icciSSIO-N, N" *R-,.-, A-T-3-006 8__3_4_____
AUTHORS: Okhotsimsi~4y,_D,Ye.; Sar hev, V.A.
YC
/61/0001016/000510009:
TITLE: Gravitational stabilization system for artificial satellites
SOURCE: AN SSSR.'Iskuset. sputniki Zemll, no. 16, 1963, 5-9 1
TOPIC TAGS: satellite, earth satellite, artificial eatellite, stabilization,
stabilizer, satellite stabilization, satellite stabilizer, gravitational stabilizor,
;aerodynamic stability, aerodynamic stabilizer
ABSTRACT: This theoretical paper examines the possible stabilization (STN) of a~
satellite (S) relative to a trihedron (TH) formed by the radius-vector, the tranfiver-
sal, and the binormal to the orbit (0). This TH Is designated "the orbital coordi-
nate system." The principle of STN Is based on the utilization of tha properties of
the central Newtonian force field (CNFF) In order to orient a body moving therein
.'in a specified manner. The body is assumed to have nonuniform moments of
inertia relative to its-principal central axes. The existence offour .stable posItlons
of relative equilibrium for a S moving in a CNFF Is stated. The scheme pi oposed
;includes the use of a dissipative element which consists of a central spherical
cavity filled with a viscous liquid within the gravitationally stable S. The cavlt
y
~_Card 1/3

AC-CESSION NR: AT3006834
~'May also consist of a cavity lying between a spherical cavity -and a smaller spherl-
Ical body. For a given thickness of a layer and a given density of the viscous fluid,
!there exists an optimal viscosity which'affords the greatest damping rate for the
~oscillatory energy. A description Is given of the stabilizer (ST) proposed by the
author in 1956 consisting of a spherical hinge attached to a satellite, with
~-!,equally long rods-carxying equal weights at their ends extending therefxom, Such
_i
.!a scheme is affective at elevations at which the aerodynamic drag is negligible.
'However, at 0 elevations below 600 ]an, the atmospheric effect must be talten into
:account through consideration of the drag forces applied to the center of pressure
:of the S and the ST bodies, directed In a sense opposite to that of the motion of the'
iS. The gravitationally stable S-ST system -will be also a e rodynamic ally stable with
~a constant equilibrium position of the S and the ST relative to the orbital systern of
;coordinates, if the following conditions are satisfied: (1) If the axes connecting the'
:center of mass of the S and the hinge point.of the ST and that connecting the hinge
~point of the ST and the midpoint of the two ST weights are axes of geometric Bym-
metry of the S and the ST, respectively; (Z) both the S and th-s ST are not aerody-
namically unstable; (3) the aerodynamic braking (ratio of the drag forces to the
mass) of the&ST I a not greater than the aerodynamic braking of the S, that Is, them
i
acts as a kind of pa- -tational sta-
rachute relative to the ST. The system of gravi
"bilization proposed here can operate for a long time and does not require any
C-2rd. 2/3

1,ACCESSION NR: AT3006834
~expenditure of energyfor stabilization. The accuracy of the 13tabilizatlon olit S IBI!
.'determined only by the manufacturing accuracy of the S-ST co-r-nbinatlonand can be'
:extremely elevated. The weight of a ST required to achievo an optimal transient
.,process, assuming rods having a length equal to twice the maximum linear Lmen-~
sion of the S, does not exceed a few percent of the S weight. (:)rlg. art. haB 2 figso-
none
SUBMITTED: 02jul6Z DATE ACQ: 08Aug63 EN C L-. 00
;SUB CODE: AS, AP NO REP SOV: 001 OTHER: 001
i-Card.
A-&.-

L - 18275--6a- ERA(b)/EWT ) FOC(w)/ .FS(v)-2/BDS/EED-2/,Ef1(v) _AFFIC/
AF1VQ F_S5-%kPGCASSD Pd-4/Pe-4 P -4
ACCE;~
011
ACC Olt S72~9/63/00o/016/009 4/0123
ALTMOR Okbotaimagyx D, Ye,,;
TITLE i Use of an earth-oriented satellite for'nolar investign~i"n xv
SOURCE,. AN SSSR. lslmss4v*. swtni%i Zemai., no. .16, 19163 94-1
23
TOPIC TAGS: satellite attitude, orbital eleme'n't., solar -investigation, instra-
rient illumination, satellite instnunentation
ABSMACT: An analysis is made of soloz-41lumination of :Lnj3tr=cnts =.,ant,!d -on
a satellite vith triaxial ctabjjkLq~jgp\Lona axis oriented to the earth, the
second along the normal to the orbital plcLnc,, and the third along the tm,3-
versal. A slight change occurs in the atttitude of the orbit relati" -to the
sun oving to the yearly =tion off the ear"th around the sun and the regression
of the orbital node of the satellite due to the oblatences of -the earth. The
problem of determining the total ti= of ill=ination is solved 1) by dcte=.'_n-
ing the illwmination time at a constant anple v bAmmen the direction to the
sun and the normal to the orbital plane., tnd 2) by considering chanl--B in
angle V vith time. Illumnination tiTn-- is the t:L-r-- the zwn 2--mains vithin the
Card

L 18275-63
ACCESSTON M AT3006840
angle of viev of the instrument, To solve the first part, tbi naxim&l tl-n-- of
instrument illumination during one orbit of the satellite at givenvnluis of
angle v and instru:ment a-vigle of view.0 and with a Varying angle "bet,---cn -the
optical axis of the instrir--nt and the axis of the satellite is sousbt. It �3
found that the maxin=1 illumination time --l-creexes as angle V decreases. The
determination of angle V as a function of time makes it possible to establish
its dependence on the angle of orbital inclination to the equatorial-21ance =d
on the initial conditions (hour and date) of natellite launching. For a ty2icy~'
orbit. (inclination to equator i - 65*; period of rotation TO - 90 min) the total
ti= of i-l-Iii-Ina-tion taring a satellite lifetimo. can reach abo'At 60 bx
optimal conditions and only about 15 hr for an instruwnt vith an anglo,- of 1-iev
of 5'. Increasing the an-gle of viev Increases the 111,xnination ti--. Th~ totna.
time of depend.9 on the bour and date of 1,munching, the positi--p of
the. op-tical nxis of the in3tru=nt relative to the aatellite,, and the inclina '-
tion of t'Zc- orbit. to the equatorial plane. Opti=-Itation of tbi orbital elcm-ents
and ;)ro,(-ra.=-,d control of the position of the axis of the instrument can ln-.reasc
illio,,%ination tite 2-10 timan. The amalysis supports the feasibility of UsLn-g
eai~ ;-or;,ente(.1 satell1tes for, solar lnvestiration3, Orig. art. has: 25
and 23 formulas,
Card 2/1

131 =V oha-lco.

~SW, D. YE. (Noscov)
"Study of notion in a ccntral -figl-! under tho effect oil colist"Int
acceleration"
Report prese4ted at the 2nd A 11-Union Congress on Theoretical and Ap-II.-Al
Mechanics, Moscow 29 Jan - 5 .'eb 64.

LIDOV, H.L.; OMOISRraKY, DJE. (Yoscaw)
"On a'method of investigating cebits in a restricted three-body problem".
report presented at the 2nd All-Union Con,,-ress on I'heoretical and Applie3
Nechanic's, Moscow, 29 Zan - 5 Feb 6h.

DUBOSM., G.N.1 OKHOTSTMSKY. D.Ye. (Moscow):
"Some problems of astrodynamics."
report presented at the 2nd All-Union Congress on Theoretical and Applied
Mechanics, Moscow, 29 Jan - 5 Feb 64.

MAIVUSTOV, C;*r-::;GTz-
- ---------
"Periodic solutions in the problem of two dimermional oscillatioru; of a
satellite in an elliptical orbit."
report submitted for !5th Intl Pstronaut.1cal 'long, Warsaw, 7-12 Sep 64.
Corm flor Syace Research UBSSM.

OKHOTSIMSKIY., D. le.; ZLATOIJM"OV, V. A.; V. A.; -IVRDIFVSKrY, A. F.
".PeriocLic solutions in the problem of tvo-dimenBional oscillations of a oatellite
In an eliptical orbit."
report submitted for lltb Intl Cong of Applied Ypchwilci3) Mmichj, W. Geminy,
30 Aug-5 -Sep 64.

LIDOV, I.; OYJiUTSIWKIY,D . 'Ye.
"Research on the categor.; of tra,,ectorj in the reBtrictei 3)roblem of t?zee
bodies."
report submitted for 15th Intl Astronautical Cong, Warsaw) 7-12 Sep 64.

'TiPIM ;7w7:. i
S/0293/64/002/M~'06 5
ACCESSION NRI A?4046?71
__ V, A, C hoy'._V
AUTHORt jjkjkqp U t ALA-R. y9
A
T
raheya jj
0
TI TLE iOaCtlIZ-L-Iong avi earth &acellite in the plane of ar.
elliptic orbit
ti ~r
dY j JCosmic-heskl~ya isslodovaniya, v. 2, no, 5, 1964, 657-hlb
?1C TAGS: rth r8teilILV oncillationt p
pailodic oacillation stability
ARSTRAM 0(1CL1J*L!0,n1 of an artificial earth satellite LR tt~i:
of an elliptic orbit under the oction of gravitational force a-F
analyzed. The stated problem is reduced to determinins stable
periodic oscLllatiana deficiibed by Lhe equation
dO
I + 41n V_16 4- v Rill 6 CoA 0 m 28 list V
Where a in tho eccentricity of tho a:bit, v is the tr"e

ACCESSION NRI Aplli,146 1,
18 th* angle ~atwean one of prinr LtAll axqs of the a] lipsal d
Iwartis vf the satelli!.e and the radi-as vactor of the orbit,
A C w h ti r e A . B . and 1: are the principal cunt rt,,1 mc ,k
a of the 'ki t F~ f. ;i u a u d e rintisfy ineq%ialltie-
inerti
101 14 3, 0 < e C C, I-. r- ~i ~7 o 1 A F . To r E he vs k I y [ Kti iim 4
'bli, 66-1-6661 concerning th.1-
fifladovantya. V. i, Qo~ 5 ,
1FAtL-jq1;*tj~s a j ai%d the be!iavior of the adri, 2-,r-partodtc iolutlon~~
(1) are V58d for su~'Paquent qualitative analysis of r o
1~o tf- rm i t, a t 11 on o odd 2v-reriodic solutions is redl C -
n r
1m, v-01~7*r ~.T-r-a-blem- for equatioti ~1'
Ri I r v 0'~--t ti T --d-e Y
U8:P
N~
Variations is written for qjuatlon (1),And the root$ of ita
t*vtstic equation bro aualy e d The results of the analyzi~,, 1'
-~tic nrb t4 with arbltrary ecceiatricity, t~ t-
tk4t. for plnne a
a range of a valmea it ulhict; atabia psrio4Lc autiou i:f a SMLC-
Is patzible. 1! e 4 0 4(,5 , lhofi stable DOCIllatiour of thC C A I
arg possible for till vpluku of ir. t!lu ~rltervel 0 <
0.465, th2 larg*st pormistlbla vs;6e of a decreave
DoCtILAtioue or tte satelliLe will, trace out n dumb-hel! sl#tap, ~i:-
ja*vt jaku or i 8t 4A S f. flatirea and 10 form-alas.

ACCESSION 'RR AP40AM77'
-ASSOCIATION t noile
SUBMITTEDI 10 11 0 SUB CODE
90,111 a0vt 009 OT li E P. 009 ATD PRESS

17FS
8,1027,3/94/002/ 606/09 7'
AFFIRt
AUTHOR: Okbotsismskiy, D~ Ye
TITLE, Investigation oi motion in F, cent-) field under the influenze of Donstant
aweleration
SOURCE: rzamichef;k1ye inv;l,~6uvaniya_ v 2. T-). 6, 1564, 817-842
TOPIC TAGS- 9-pacecraf t mation. tangentO,l acceleration. circular oe)it. space- it
velocity, &,-Yar';_~raft thrust, gptcecraft tra)pctory,
_ffight, circtdav velocity, hypcrt_-~.~iic v(I1,o,,jtv. (,i0,ctmj0t evne
ABSTRACT, Due to the v-1BsJ1A'1ittet3 of using tJnctro)ect engines ior space flwhj~~
noed has arism for an In-s*;t1gr-t4on of the motion of apacocraft with givall thrust,
Electrojet engtnaa can impai t to a apac-_rraft "tremely small acceleratitma #m t- e
several mm/sec2. The usb uf a sinall, thrtist for pro. pulsion is pas8R).e only id, i,
lbo spscevrvdi iota a satellitn orbit b-y engioes with a large thrust. Fitrther
by electrojet enginea leade to motion of the apacer-rdt ir. a spiral trajectory 71 iv
presents a method for computing mc4l!3n in a central field under the irdlulwee )f -av~--
aca*leratian of a oonstant value The authivre eonsideT a raW of velocitles fror (i -
to hyperW110. Mho equationo of mation are presented " radvaW to tibnewrion) e,gi,
cafd 1/2

L 21822-