SOVIET BLOC INTERNATIONAL GEOPHYSICAL YEAR INFORMATION

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP82-00141R000200330001-6
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 23
• Document Creation Date: December 9, 2016
• Document Release Date: July 10, 2000
• Sequence Number: 1
• Publication Date: September 19, 1958
• Content Type: REPORT

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SOVIET BLOC INTERNATIONAL GEOPHYSICAL YEAR INFORMATION
September 19, 1958
U. S. DEPARTM T OF CONII4ERCE
Office of Technical Services
Published Weekly from February 14, 1958, to January 2, 1959
Subscription Price !70.00 for the Series
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PL1,A;;E NOTS
This report presents unevaluated information on Soviet DJ.oc
International Geophysical Year activities selected from foreign-
language publications as indicated in parentheses. It is pub-
lished as an aid to United States Government research.
SOVIET BLOC INTE-RITATIONAL GEOPHYSICAL YEAR INFO1NATION
Table of Contents
Page
1.
Rockets and Artificial Earth Satellites
1
II.
Upper Atmosphere
4
III.
Arctic and Antarctic
15
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I I. ? OCK1*T; AND ARTIFICIAL EARTI[ SATI.LLI77
Satellite Recovery Vehicle Proposed by Moscow Graduate Student
An interesting variation for returning satellites to Earth is reported
by R. Grigor'yev, in "Interesting Project," an article in the July issue of
1auka I Z izrr', a Soviet popular science monthly. The method was proposed
by K. Seevast'yanov, a Moscow graduate student. This scheme, which is illus-
trated in the original source, is described as follows.
The satellite is assumed to be moving around the Earth in a slightly
elliptical orbit. The apogee is designated as A and the perigee as P. The
descent must be made in the plane of the orbit in the direction of the
Earth's rotation. The return or recovery trajectory is divided into five
parts. When the apparatus is at A, and aligned so that the jet of its com-
bustion chamber is directly counter to the motion of'the satellite, a re-
verse thrust is created. With this, the motor of the apparatus uses approx-
imately half the fuel it had on board.
The reserve of fuel for the first braking is selected according to
K. E. Tsiokolskiy's classic formula, providing such a decrease in the satel-
lite's energy which will permit it to pass into a new orbit the perigee of
which is designated as P', nearer the Earth. In addition to this, the heat-
ing arising as a result of the entry of the apparatus into the upper layers
of the atmosphere must not exceed the permissible temperature. In order
that the apparatus may be "submerged" in the rarefied atmosphere with less
velocity, and consequently with the least heat, the motor must again be
switched on at point I (which it reaches before arriving at point P') for
achieving a second braking in part I-P' of its trajectory.
An estimate of the amount of fuel necessary for the second braking
indicates that its weight is considerably less than the weight of coolant
reserves and cooling systems, which are necessary in other recovery methods.
Part P'K of the trajectory is covered in a supersonic glide.
In braking, the angle of attack of the wings of the apparatus is in-
creased so long as this is possible without overheating the shell. As the
apparatus gradually drops into the denser layers of the atmosphere, braking
becomes more intensive, and the temperature after reaching a maximum begins
to abate. Finally, at point K, the velocity of the apparatus has decreased
to sonic and in part K-L of the trajectory the usual gliding and landing
occur.
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Thty' the di ool 3,ti Ju u, oat.:llite' u unlu. rt`y io acr.omlp:I.iuh,~:O. cr:L?ih
I.llu ixicl ui LmrLk111L; by nnot:uy' ai,d atmosphere. Thcrcforu, in cr,irtxc~.ci, t(.,
u tr:l L(:tiut; airp:l.uuuc of great rarsge, thu wiu3 of which must have a h .ci
I LCt%ddr: rat:Lo, the prc>pnsud. recovery apparatus snout puoaeua high :I:i.i't-
.ituf capacity and frontal resistance. Because of this) the speed c.ii cle-
;;c_,.ut" frcM liit;h al.titudus is decr::as eel and heating of the apparatus is
Lv0:;ci1 ~.1..
This ocl(nau is presented as one of the possible -variations a or
t.irai:irs~ satel.:l.ites. (ilaui:a i a-iizn', Ifo 7, Jul 58, p 66)
,Amu:! a.?L,.c[ Ue e F:Li Uhto by Laboratory Animals
"C'osm:i., e Breakfast, " by Lieutenant Colonel I I. Krestivskiy, recently
:i.xi Covetskkaya itviatsiya describes a simulated space flight with
oniiia.:i.3, as fo:LI.owo:
"' 600
as at z 230-600, we evidently must obtain reduced values of N(z) as
compared with the actual values. The values of N(z) for x = 3.5.10-3 km-1
are given in Table 1 and Figure , 4. ? (Footngte: Added in proof:'
The two values of N indicated by dots in Figure 4--were measured with a high-
altitude rocket -- see Pravda, 27 March 1958. It should also be noted that
it was shotm in a recently published work that the ratio of the total number
of electrons above the maximum of the layer to the niunher of electrons in
00 zOfzm
the lower half of the layer, i.e., ) N dz : ) N dze 3 and varies only
zOf zm z0
slightly. This is in good agreement with our data, since for X.- 3.5.*.l0-3,
this ratio is of the order of 3.6.)
The second line in Table 1 gives the value of the density n of neutral
particles recommended in various works for altitudes up to 400 km (H. K.
Kalman, W. B. White, H. E. Newell, J Ge h Res, 61, 513, 1956; D. Horo-
witz, It. E. Lacow, J. Geophys Res, 62, 57, 1957, For higher altitudes,
the values are computed on the assumption that the barometric fo mmla is
applicable, that T here is approximately 2,000?, and that the main gas cc n-
ponent is atomic hydrogen, such that the effective altitude H 100 km. The
third line gives the values for n computed below.
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We shall now analyze the data in Table 1.
In the first place, it is evident that under the above assumptions
the electron concentration for z " 2,000-3,000 km varies within the limits
10-3-10-2 el/cm-3, as does the number of positive ions. However, the
great path lengths, reaching many thousands of kilometers as the particles
move away from the Earth, the fact that the gas is irradiated by the Sure,
the long lifetime of the electron, the free influx of particles from with-
out, etc., indicate that the gaseous medium here may hardly be considered
as the Earth's atmosphere. We therefore can draw the conclusion that the
atmosphere at these heights is evidently contiguous with the interplanetary
gas. (Footnote: This value for the density of the interplanetary gas was
determined from observations on the polarization of zodiacal light [H.
Siedentopf, Zs f Astrophys, 32, 19, 1953]?)
Secondly, we will estimate the distribution of neutral particles n
at z > 400 km on the basis of the electron concentration data. The follow-
ing values may be taken for the amount of ionizing radiation incident on
the region F2 of the ionosphere and for the recombination coefficient oG
for electrons at various altitudes (M. E. Szendrei, M. W. Elhinmy, J Atm
Terr Phys, 9, 118, 1956; Ya. L. Al 'pert, V. A. Ginzburg, Ye. L. Feynberg,
Rasprostraneniye Radiovoln [Propagation of Radiowaves], 1956):
zm (lon)
SM (erg/cm2?sec)
M (cm3/sec)
~. 320
M 0.2
10-10
.~ 400
~ -0.3
..~
10-13
z ,Z 1, 000
S--10.6.
10-12
chief microprocesses in this region of the atmosphere, we find that the
lifetimes of an electron T e = 6C N)-1 sec and the times between differ-
ent ionization events 'r n - (o' 3/60 -1 sec - take on the values: p-0
1
Therefore, ass?aming that photocombination and photoionization are the
2.10-18 cm2 and 6 X01 = 13.5 ev)
z (lam) 320 400 1150 1850 2450
T'n 5.107 3.107 2.107 2.107 2.107
e 5.103 7.104 107 .108 109
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Since n/r1 -.'f 'rl/ '[' . under quasi stationary conditions, we obtain in conclu-
sion the densities of neutral particles given in the third line of Table 1.
It can be seen that these values for n are 5-10 times or more greater than
the figures in the second line of Table 1. It may therefore be assumed
that the values of n also exceed those given in the literature for z - 320-
100 km and that for z ti 2,000-3,000, n is of the order of several units per
cm3.
These conclusions have an important significance for the physics of
the outer ionosphere, thus emphasizing the necessity for their further
verification by other methods.
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s (kits)
N (e1/ci 3)
it (cm 3)
n = (2"n/?"e)N
Fig 2
'!'able 1
200 320 1100 1100
105 1.8.106 1.1j.106 105
5109 2.108 108 105
5.108 20.105
Fig 3
1760 21400 3050
1014 103 102
102