INFORMATION ON SOVIET BLOC INTERNATIONAL GEOPHYSICAL COOPERATION - 1959

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• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP82-00141R000200970001-6
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• Document Page Count: 19
• Document Creation Date: November 9, 2016
• Document Release Date: February 11, 1999
• Sequence Number: 1
• Publication Date: December 11, 1959
• Content Type: REPORT

l.r 1 n r 0 ~~:O j C L 7 V Approved For RelelskM19I(B R eMka lBnOk V870aIM r lJ ^ rl rl T I U r. Urif 25 U Y 1 C I
UL M t-N F tKNH 1 i UNHL CitTaYHYS i CHL LUUF'tKH ~T i U~1
DECEMBER ~i 1959 _ -- 1959
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PB 132.632-96
INFORMATION ON SOVIET BLOC INTERNATIONAL G EOPHYSICAL CCOPEaATION - 1959
December 11, 1959
U. S. DEPARTMENT OF COP NFE CE
Business and Defense Services Administration
Office of Technical Services
Washington 25, D. C.
Published Weekly
Subscription Price $12.00 for the Series
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approved by the Director of the Bureau of the Budget, October 28, 1959
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on Soviet Bloc International Geophysical Cooperation - 1960 and enclose
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INTERNATIONAL GEOPHYSICAL COOPERATION PROGRAM--
SOVIET-BLOC ACTIVITIES
Table of Contents
Page
1
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Latest Issue of "Artificial Earth Satellites"
The third of a series of publications by the Academy of Sciences
USSR, titled Iskusstvennyye Sputniki Zemli, No 3, 1959, contains 13
articles oz artificial earth satellites and related subjects, abstracts
of which are given below.
"On the Problem of Capture in a Restricted Circular Three-Point V
A theorem is proved, according to which, in a restricted circular
three-point problem in the case when one attracting mass is rather small in
relation to the other, a point of zero mass arriving from infinity cannot
remain forever in the sphere of attraction of the smaller mass, i.e., be-
come its satellite.
An approximate consideration of the problem concerning the possibi;Lity
of capture by the Moon and planets of a missile launched from the Earth is
given. The above theorem is not considered applicable to the Earth,Moon
system. If the trajectory beginning at the Earth enters the Moon's sphere
of influence on its very first turn around the Earth, then it is possible
to show, ignoring perturbations, that this trajectory must leave the sphere
of influence on its first turn around the Moon. The capture of a missile
by the Moon is impossible for such trajectories because portions of them
are located inside the sphere of influence of the Moon in a shifting seleno-
centric system of coordinates always close to hyperbolas. Thus, within the
boundaries of the sphere of.influence, the selenocentric velocity exceeds
the local parabolic velocity by 383 meters per second, that is, by more
than two times. At initial velocities less than parabolic for Earth, the
upper limit of the transverse component of the entering geocentric velocity
does not exceed 200 meters per second. Inasmuch as the angle formed by the
velocity of the Moon with the entering geocentric radius differs little from
a right angle (not more than 10 degrees) and the Moon's own velocity is about
ors kilometer per second, then one component of the entering selenocentric
velocity, the orthogonal and geocentric radius-vector of the point of entry
in the sphere of influence, already is, at the least, about 0.8 kilometer
per second.
At initial velocities, larger or equal to the parabolic for the
Earth, the radial colaponent of the entering geocentric velocity exceeds one
kilometer per second, and the value.ef the entering selenocentric velocity,
as before, is more than twice as large as the local parabolic ?velocity.
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Perturbations from the Earth cannot noticeably change such a
sharply expressed hyperbolic motion inside the sphere of influence, and
the missile entering the sphere of influence must leave it on its first
turn around the Moon, unless it hits the lunar surface.
It is possible to show in a similar way that for a planet-Sun
system, ignoring perturbations, the capture of a missile launched from
Earth by a planet on its first turn around the Sun cannot occur. The
error resulting from not considering perturbations, i.e., the influence
of the planet outside its sphere of influence and the influence of the
Sun in the planet's sphere of influence, in this case, will be much less
than in the problem of the flight to the Moon. The hyperbolic velocity of
a missile launched from Earth, in the sphere of influence of a planet, is
much larger than in the sphere of influence of the Moon. The entry velocity
of a missile launched from the Earth in the sphere of influence of a planet
will be least for Mars and Venus. They will, however, also be three times
larger than the local planetocentric parobolic velocities at the boundary
of the planet's sphere of influence. Thus, the capture of a missile from
the Earth by a planet on its first turn around the Sun is also impossible.
"Librations of a Satellite," by V. V. Beletskiy
The conditions for the existence and stability of the position of
relative equilibrium of a satellite, i.e., the equilibrium in a system of
coordinates connected with the radius-vector of the satellite's center of
mass, are examined. The libratooy motion about a position of relative
equilibrium is also studied.
It is stated that a number of small perturbing factors act on the
actual libration of an artificial satellite. These are the moments of
aerodynamic forces, perturbing moments caused by deviations of the Earth's
field of attraction from the normal, regression of the orbit because of
the oblateness of the Earth and aerodynamic resistance, moment of electro-
magnetic forces, etc. Investigation shows that if the basic conditions for
stability (for stability of the relative equilibrium of a? solid body in a
circular orbit in a Newtonian central force field, it is sufficient that in
unperturbed motion the major axis of the ellipsoid of inertia of the body
be directed along the radius-vector of the orbit, and the Kinor axis, along
a normal to tai,, plane of the orbit) and certain additional natural conditions
are fulfilled, then the librations in the presence of the indicated perturba-
tions will differ very little from the unperturbed librations.
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"First-Order Perturbations in the Motion of Artificial Satellites
Caused by Oblateness of the Earth," by V. F. Proskurin and Yu. V.
Batrakov
The problem of the motion of a satellite in the field of attraction
of an oblate planet is examined on the assumption that the satellite's or-
bital plane can have any inclination to the plane of the equator of the
planet. It is also assumed that the planet has the form of an ellipsoid of
rotation and that the oblateness of the planet is rather small. As a result
of this, in the expansion of the perturbation function in terms of powers of
the oblateness, it is possible to restrict the expansion to terms containing
the first power of the oblateness. The portion of the perturbation function
being considered is expanded in a series of powers of the eccentricity; coef-
ficients of the series are very simply expressed by trigonometric functions
of the angle of inclination. Integration of ordinary Lagrange equations
gives an analytical expression of the first-order perturbations. relative to
the oblateness of all of the elements of the orbit with an accuracy up to
the fourth degree of the'eccentricity inclusively.
"Perturbations of Artificial Satellite Orbits Caused by the Resistance
of the Air, " by Yu . V V. Batrakov and. V V. F F. Pros kurin
A general form of first order perturbations in' the elements of the
elliptical orbit of a satellite caused only by atmospheric resistance. is
nought. It is proposed that the Earth's atmosphere' has a.strictly spherical
density distribution and that the Earth's attraction can be substituted by
the attraction of a material point located at its center of inertia and
having the some mass as the Earth. Short period perturbations, the periods
of which do not exceed the period of one revolution of the satellite, are
obtained, together with secular perturbations. These short period pertur-
bations caused by the resistance of the air medium have still not been studied,
according to the authors. A numerical example,' showing the comparative value
of first order perturbation caused by the resistance of the -air) is al 6o given.
"Observation of Artificial Satellites by the Expectation Method," by
B. M. Vakhnin and V. V. Beletskiy
A method is proposed which permits making repeated 'observations of
a once-observed satellite if its orbital period is unknown. Proposed initi-
ally is that the orbital inclination, the longitude of the node, and the lo-
cation of the perigee are constant. This holds true sufficiently well for
orbits which are close to circular polar orbits. In this case, it was felt
possible to formulate the following ru e o local. CPYRGHT
"If the inclination of the orbit of a satellite is not equal to
Izero, then the intersection of any given latitude by the satellite will
ways occur at one and the same local star time."
CPYRGHT
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This rule continues to function even if the period of revolution,
eccentricity, or position of the perigee changes. For example, with a
chaua F in the period of revolution, the point of intersection is shifted,
bi.it the time of intersection, calculated for local time has the same value
in the new point as it had in any other in which the satellite crossed this
cnm!- latitude.
The rule is not considered accurate for a real orbit in which exists
precession of the plane of the orbit and the motion of the perigee in the
plane of the orbit and can be applied only for small intervals of time and
for observations with a sufficiently wide angle of view. ? However,' an "ex-
pectation graph" can be calculated for orbits with changing orientation.
Formulas for plotting the "expectation graph" for various sets of
known data are given. It is essential that one variable factor, the rate
of precessicn of the orbit, be taken into account for successful application
of the method.
"Dependence of Secular Variations in Orbit Elements on Air Resistance,"
by P. Ye. El'yasberg
The effect of air resistance on secular variations in the orbit
elements of artificial earth satellites has been considered in three earlier
papers by I. M. Yatsunskiy; D. Ye. Okhotsimskiy, T. M. Eneyev, and G. P.
Taratynova; and G. P. Taratynova, all of which appeared in Uspekhi Fizich-
eskikh Naulc, Vol 63; No ?la, 1957. The present work is the development of
an idea advanced in the first of these papers. The-idea concerns the series
expansion of the secular variations in the orbit elements in terms of fessel
functions of an imaginary argument. This technique produces simple descrip-
tive formulas which can be used to solve a number of problems, such as de
tenaining the dependence of secular variations in orbit elements on the
magnitude of these elements and evaluating the accuracy of air density de-
terminations on the basis of measurements of the secular variations in the
orbit elements.
Analytical. expressions are obtained for changes- caused by air resist-
ance in the latus rectum of the orbit, the eccentricity, the major semiaxis,
the period of revolution, and the distance from the perigee to the center of
the .0arUh. It is assumed that air density is a function of altitude 'alone.
The error .in the' formulas resulting from various 'approximations made for the
sake of simplicity is 1-2% when the eccentricity is greater than '0.O 4., in
creases to 6% when the eccentricity is 0.023, and continues to rise for
smaller eccentricities.
It is further shown that the rate of increase in air density with
altitude is a function of only two' orbit parameters, the-period of revolution
and the distance from the perigee to the center of the Earth.,
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"Problem of Piercing at Cosmic Velocities.," by Academician
M. A. Lavrent'yev
The problem of the puncture of a metallic plate at -,,elocities of
50-100 kilometers per second is studied. A model of an incompressible
medium is proposed for which it is possible to conduct calculations up to
the desired limit.
A one-dimensional case is considered. The problem of the impact
of a plate of a thickness flying at a speed of vo on the end of a cylinder
with a length of 1 is studied. The thickness a is considered small in com-
parison to 1. The problem consists in determining the impulse which.the
rod acquires as a result 'of' the impact. The plate-block is considered as
incompressible and absolutely solid. The shaft is considered as a limited
case of a collection of absolutely solid infinitely thin plates located
infinitely close to one another. Under an inelastic impact.,-the block of
the first plate retains a quantity of motion, and as a result of the in-
crease of mass, a loss of kinetic energy occurs. This will occur with the
involvement in motion of each succeeding plate. Calculations are conducted
in the limited case, of the distribution along the rod of the loss of kinetic
energy of the system.
The three-dimensional case involves the impact of a pellet against
a plate-hemisphere of given radius. As a result of, the impact, the mass of
the pellet (h r) will increase in accordance with the concept of inelastic
collisions; with the increase of mass, the amount of motion will be preserved,
but the kinetic energy of the system will be converted into heat.
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"The Determination of the Density of the Atmosphere at an Altitude of
1130 Kilometers by the Sodium Vapor Diffusion Method," by I. S. Shklov
skiy and V. G. Kurt
A comparison of data on atmospheric density at an altitude of 430
kilometers obtained during the first use of the sodium-cloud method on
19 September 1958 with similar data obtained for 4.50 kilometers with Ex-
plorer I shows very good agreement ((6.7 i 2). 10-15 grams per cubic centi-
meter and 9 6) . 10-15 grams per cubic centimeter,) respectively). How-
ever, on the basis of data on electron concentration in the outer region of
the ionosphere, based on radio signals of Sputnik I (and assuming ionization
aquilibri-tun gt 1100 kilometers), the concentration of neutral atoms was found
to be 5 . 10 per cubic centimeter. Whez extrapolated for 430 kilometers,
this value is 30-40 percent higher than the sodium-cloud data. A comparison
of atmospheric density data obtained with various Soviet and American satel-
lites and z?rith the soditun-cloud method also shows a considerable divergence
of values, apparently resulting; from a considerable space-time variation of
particle density at the altitudes involved. The sodium-cloud method can be
used to record this variation and can also be used for a much greater alti-
tude. range., the lower limit of which is at an altitude (about 200 kilometers)
whore, during the -period of observation (about 10 minutes), sodium atoms will
not disappear into the. atmosphere as a result of chemical reaction. At this
lower altitude, a much smaller amount of sodium (only tens of grams) would
be required. The upper limit of measurement by the sodium-cloud method is
500-600 kilometers and perhaps even higher, provided the hydrogen content
is considerably greater than that ordinarily recorded. The sodium vapors
should be released into the atmosphere near the peak of the rocket trajectory,
not in the course of it.; flight as reported by Edwards, et al. (The Airglow '
and Aurorae, London, 1956, p 122) and Bedinger, et al. (J. of Geoph. Res.,
3, No 1) 1958, p 19)
"Methods for the Control of Interfering Currents Origii.,ating at the
Input of an Electrostatic Flumneter During Its Operation in a Conduct-
tion Medium," "by' I. M. Inyanitov arad Ya M. Shvarts
A brief description is given of the operation of a rotation-type
electrostatic fluxmeter used for measuring the natural charge of a satellite
and methods for controlling interfering currents at the input of the meter.
Noise currents appearing at the input of the measuring circuit and
raising the lower limit of the recorded natural charge of the satellite may
be the result of the following:
1. Velocity of the satellite relative to the thermal velocities of
ions and electrons.
2. The difference between the potential of the satellite at the
position of the fluxmeter and the equilibrium value of potential.
3. Exposure to various types of photoemission.
Directed movements in the ionosphere.
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One method for decreasing interfering currents uses a synchronous
detector at the output of the measuring circuit of the flwmeter and is
based on the fact that a 900 phase difference exists between the operating
and interfering currents.
Another method for decreasing noise involves designing the measur-
ing and screening plates of the flumneter so as to decrease both the modu-
lation of the flow of charged particles reaching the surface and the abso-
lute value of current falling on the surface of the measuring plate.
Experiments performed by the author indicate that this may be accomplished
by making the measuring and screening plates in the form of metal grids
having specific electrical and optical transmittances. Details are given
of the experiment and apparatus used.
The use of negative feedback on the noise voltage is suggested as
another method for controlling interfering currents. The two parallel-
connected detectors, one tuned to the operating voltage and the other to
the noise voltage, are connected to the output of the measuring circuit.
The detected noise voltage is applied as negative feedback to the d-c
voltage at the input, thus decreasing the amplitude of interfering a-c
voltage at the input of the operating synchronous detector.
"Certain Results in the Determination of Structural Parameters of the
Atmosphere With the Aid of the Third Soviet Artificial Earth Satellite,"
by V. V. Mikhnevich, B. S. Danilin, A. I. Repnev, and V. A. Sokolov
Results from the processing of manometric measurements conducted on
the 15th pass of the third Soviet satellite are given which represent the
state of the atmosphere at altitudes from 225 to 500 kilometers on 16 May
1958. Values for different altitudes corresponded to measurements obtained
at different times of the day (1300 to 1900 hours local standard time) and
at different latitudes (57011 to 65?N). Design and operation of satellite-
borne manometric equipment and the method for determining atmospheric values
are described. Calculations of the altitude of homogeneous atmosphere,
temperature, and pressure were performed on the assumption of the applica-
bility of normal barometric formulas to a rarified gas in the presence of
temperature gradients. Structural parameters of the atmosphere (given in
a table for 5-kilometer intervals in the range from 225 to 500 kilometers)
at 225 and 500 kilometers, respectively, are: number of particles per unit
volume, 6.01 x 109 and 8.24 x 107 per cm3; density, 2.12 x 10-13 and 2.21 x
10-15 grams per cm2; altitude. of homogeneous atmosphere, 40.0 and 119.0 kilo-
meters; temperature, 936 and 1953?K; pressure, 7.76 x 10-4 and 2.22 x 10-5
dynes per cm2; and pressure, 6.25 x 10-7 and 1.94 x 10-8 mm Hg. Data are
presented on the values of density at different altitudes as obtained by the
Soviets and the US through manometric measurements and satellite drag. Sur-
veyed information bears out the fact that the state of the upper surface-of
the atmosphere can change sharply, depending on such factors as outer dis-
turbances (i.e., solar 'disturbances), as well as the season, time of day,
and geographical latitude.
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"Radio-Frequency Mass Spectrometer for Investigation of Ionic Composi-
tion of Upper Atmosphere," by V. G. Istomin
The ionic composition investigation of upper atmosphere was begun
in the USSR in 1957, and the data on the mass spectrum of positive ions in
the ionosphere at an altitude up to 855 kilometers obtained from Sputnik III,
and various other high-altitude rockets. A radio-frequency mass spectrometer
used in these investigations consisted of three basic units: mass-spectrom-
eter tube (radio-frequency mass analyzer) with a preamplifier, electronic
unit of the device, and power supply unit. The mass-spectrometer tube was in
the form of a three-stage analyzer. One of the construction peculiarities of
the device is the single-file grids made from tungsten wire wound on "kovar"
rings. Five such grid rings are placed in the ion-source unit and 15 in
the analyzer. The diameter of the grid ring is 30 mm, and the winding pitch
is 0.5 millimeter. The 15 analyzer grids perform the following functions:
1 and 2 are the ion pull-in grids; 3, 4, and 5 are first-stage grids; 6, 7,
and 8 are second-stage grids; 9, 10, and 11 are third-stage grids, 12, 13,
and 14 are retarding grids; and 15 is the protective grid. The mass-
spectrometer housing has a flange for mounting on the rocket or sputnik.
The ion-source unit of the tube serves only for the purpose of laboratory
calibration. The tube of the device is filled with a mixture of argon and
neon at a pressure of 3.10' millimeters of mercury. The electronic com-
ponents of the device consist of a uc amplifier, high-frequency oscillator,
voltage rectifier, saw-tooth pulse generator, 600-volt do voltage converter,
and output switching system.
The mass-determination range of the device is from 6 to 48 atomic
mass units, and the scanning time for the whole range is 1.7 seconds.
"Manometer Error Caused by Slight Flows in the Shell of a Sputnik," by
S. A. Kuchay
Among the instruments in Sputnik III were manometers capable of
measuring static pressures of 10'6 - 10-9 millimeters of mercury. When
measurements are made in the upper atmosphere, molecules which have arrived
with the satellite and entered the upper atmosphere by means of gas separa-
tion from the surface of the satellite or leakage can invade the manometer.
The desorption by the surface will cease at a relatively rapid rate, but the
leakage from within remains practically constant during the time the instru-
ments are in service. Thus, the manometer error depends on the hermeticity
of the shell. The molecules of gas located inside the shell are "intrinsic"
molecules. To compute the absolute manometer error, it is sufficient to.kaow
the normal component of flow of these "intrinsic" molecules over a cross
section of the intake pipe. The calculation involves various types of diffuse
and point flow, for which the manometer error varies from 2.7 x 10-15 to
3.5 x 10-8 millimeters of mercury.
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"On the Problem of the Interaction of a Satellite With the Magnetic
Field of the Earth," by Yu. V. Zonov
The interaction of a satellite with the Earth's magnetic field is
considered. Among the effects of the field are currents due to the constant
motion of the satellite relative to the magnetic field, a change in the
elocity of rotation of the satellite around its axis caused by eddy currents,
and perturbing forces which the magnetic field exerts on a satellite that
does not have its own rotation. Of the 4bove factors, eddy currents which
arise in the metal shell and produce a considerable decrease in the angt4ar
velocity of the satellite'a rotation are the most significant. Charges and
currents which arise as a result of the satellite's motion do not exert any
considerable effect on its motion and need be considered only with respect
to experiments conducted on the satellite.
An expression for the velocity of rotation of the satellite around
its axis caused by the diffei-ence of potential on the shell is found:
W = 40o exp(- 9 P hV2B2 sin2 O( t)
8 Po'I ?r3c2
Where Po is the density of the satellite, Q is the specific resistance of
the shell, h is the thickness of the shell, r is the radius, c is the electro-
magnetic constant, V is the velocity of the satellite relative to the mag-
netic field, B is the magnetic induction, oLis the angle between the velocity
and induction vectors,, and t s.s time .
Eddy currents in the shell and their effect on the angular velocity
are calculated. The perturbing effect of the magnetic field as the satellite
passes over the poles is also discussed.
Radio Contact With Soviet Interplanetary Station Fails
Radio contact between ground stations and the third Soviet cosmic rocket
has been interrupted for stone unknown reason, writes Academician L. I. Sedov,
president of the International Federation of Astronautics, in a Pravda article
on the Soviet cosmic rockets.
This disruptica in communication may be due to a number of different
reasons, says Sedov, one of them being the result of the impact of a meteorite.
In this case, according to Sedov, the breaking of the hermetic seal of the
station's shell would suffice for the stoppage of the on-board apparatus.
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Moacuremcrrto of the - hird cosmic rocket's trajectory show that it is
moving in an orbit which is nearly elliptical, with an apogee of about
500,000 l:ilomctcru cued a L;radualJ.y diminishing jx rigec. The station will
complete about 11, revolutions aid, toward the end of March rand the beginning
of April 1960, will enter tlio aeriuc layers of the Earth's atanosphere and
burn. Despite the hijh periL,eo of the orbit on the station's first revolu-
tion and, the absence of atmospheric resistance on its motion, states Sedov,
it was found that the otat:ton's lifetime is limited. This is une:cpected at
first glance. The effect is caused solely by Nct?rtonitui forces. It is ex-
plained by perturbations of the station's movement by the attraction of
the Sun and Moon.
The successful attempt of photographing in space and of transmitting
pictures by radio to Earth is interesting, not only because of obtaining-
infoi7ua.tion on the Moon's far-side, but also because it has groat value as
a successful test of a new method in modern experimental astronomy, says
Sedov.,
The launchings of each of the Soviet cosmic rockets is called a new,
great stage in the development of rocket i'liglrts. The three remarkable
flii;lrts will go dorm in history as the principal stages in the investigation
of cosmic space and a preparation for interplanetary travel.
The investigations Which were conducted, concludes Sedov, are only the
beginning. Ahead lies the wonderful prospect of future cosmic flights.
("The Soviet Cosmic Rockets," by Academician L. I. Sedov, President of the
International Federation of Astronautics; Moscow, Pravda, 15 Nov 59, P 3)
Lunar Globes Soon To Be Mass Produced
The first lunar globe has been completed in the Moscow Planet.rium,
reports V. Lutskiy, lecturer. It is a relief globe based on both previous
information on the side of the Moon lmown to us and information gathered
from the photographs of the Moon's far side by the third Soviet cosmic
rocltet. The ;lobe will soon be mass produced by the Experimental-Mechanical
Works of the Moscow Planetarium and distributed to all planetariums throughout
the Soviet Union. ("The First Lunar Globe Is Created," by V. Lutskiy,
Lecturer, Moscow Planetarium; Moscow, Izvestiya, 18 Nov 59, P 3)
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Soviets Allegedly Working on Sophisticated Lunar Vehicle
Generally discussing Soviet outer space accomplishments, including
Lunik I and II and touching upon Lunik III, and speaking about cosmic radi-
a t-ion, demonstrated by the instruments aboard Lunik II, the article stresses
the importance of this data to future planning of suitable shielding in CPYRGHT
CPYRGHT space flight vehicles. Referring to a statement by A. Topchiev, Vice-.
President of the Academy of Sciences USSR in which he said that o ow-
ing the second Soviet cosmic rocket, man is to be the next visitor to the
ourface of the moon the article points out that this is not merely a
CPYRGHT theoretical problem. According to the text of the article, the Soviet Union
is already working on a single-stage rocket with a thrust of more than .750
tons. Equipped with 20 such "motors," a five-stage rocket, measuring 70
meters in height and weighing 3,000 tons at blast-off, could transport a
two-story cabin with 2-3 persons aboard to the moon and bring it back to
earth. For this accomplishment, the article continues, the first three
stages of the space rocket would be required for the outward journey, the
fourth for deceleration and landing on the moon, a n d the fifth for the re-
turn flight to earth. T h e [ o u t b o u n d ] trip is scheduled to take 2 days.
The article rives no other details on the project and does not attri-
bute the statements to any person. ("The Moon and Peace -- Man's Flight
into the Universe"; Prague, Pracovnik SVAZABMu, 13 xt 59, pp 6-7, 13)
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II. ARCTIC AND ANTARCTIC
Observationo at Seyernyy Polyus-8
The drift of Severnyy Polyus-8 has been continuing for 6 months.
Despite heavy snowstorms, severe frost, and breaks in the ice floe,
scientific observations have been continuing without interruption.
During the past 6-month period., the ice floe with the station traveled
about 1,000 kilometers on an irregular course in a northwesterly direction.
A large amount of material has been collected. After preliminary process-
ing of these data, scientists will be able to draw some conclusions which
should be of considerable interest.
As a result of numerous measurements made by hydrological stations
operating on a 24-hour basis, some peculiarities in the nature of sub-
glacial currents and in the distribution of warm Atlantic waters have been
discovered.
The study of ice dynamics in the drift area of Severnyy Polyus-8 has
great practical importance, since the ice masses in this area form the main
obstacle for navigation in the eastern part of the Northern Sea Route. The
observations made at the station will undoubtedly provide more detailed in-
formation on the climatic and synoptic characteristics and the radiation
regime of the Arctic Ocean. All of this will simplify the work of scientists
compiling ice forecasts and will, to some extent, facilitate navigation.
During the surmner, the surface of the ice floe was flooded with water
as a result of intensive thawing. A large number of melt water "lakes"
appeared in the camp area. Holes were drilled daily in the ice to drain the
melt water into the ocean. With the help of a tractor, the living huts and
scientific pavilions were repeatedly moved from one place to another.
The short arctic summer is over. A temperature of minus 32 degrees
centigrade has already been recorded, and the polar night will soon begin.
("Our Country's Flag in the High Latitudes," by V. Rogachev, chief of
Severnyy Polyus-8; Leningradskaya Pravda, 21 Oct 59)
Plans of Fifth Antarctic Expedition
The Arctic and Antarctic Institute in Leningrad is completing prepara-
tions for the forthcoming expeditionary research to be conducted in antarc-
tic waters on the Ob'?by the marine detachment of the Fifth Soviet Antarctic
Expedition.
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The main object of these studies will be the southern, ice-covered
regions of BellinGrihauaen Sea. T e southern coast of this sea, o:-.tending
over almost 1,000 kilometers, has never been explored befoa . A wide zone
of almost impassable sea ice has, tuiti nor, prevented :chips fram approach-
int3 the coast.
The expedition will devote much work to the study of sea ice and the
currents and water masses of this sea. The characteristics and drift of
the sea ice in its southern pants will be inve$t:tgated.
Particular attention will be given to the study of the current of
western winds. A very interesting question should be clarified, i.e.,
whether there exists a coastal western `aixj current at the southern shore
of Bellingshausen Sea, as has been observed in many other regions of the
Antarctic.
In the field of marine geoloG7, the expedition will concentrate its
efforts on the study of ocemiic depressions in the .?thern part of the
sea and the stud of the continental slope of Antarctica in the southern
part Cof the sea/. The hydrobiological studies should also be of great
interest. In addition, the expedition has set itself the task of studying
the i:,..culiarities of atmospheric circulation in this little-iQiow,rn re ion of
Antarctica, which is noted for its long-lasting and severe storms. ("To
the South Polar Latitudes"; Riga, Sovetskaya Latviya, 18 Oct 59)
Previous Expedition Members Return to Antarctic
The Fifth Soviet Antarctic Expedition will include a number of polar
specialists with practical experience. G. I. Matveychuk, deputy chief of
the expedition, wintered in Antarctica and at a drift station in the Arctic.
V. S. Sidorov, chief of station Vostok, also participated in a previous
antarctic expedition. L. I. Dubrovin, Candidate of Geographic Sciences,
will be chief of station Lazarev. I. V. Maicsimov, Doctor of Geographic
Sciences, will supervise oceanographic studies along the coast of Antarctica.
He was chief of the Second Marine L::pedition on the Ob'. ("New Antarctic
Expedition"; Moscow, Sovetskaya. Rossiya, 13 Oct 59)
Return of Plane From Station Lazarev
On 1 November 1959, at 1055 hours Moscow time, the LI-2 plane piloted
by B. Osipov returned from its long-distance flight over East Antarctica.
In addition to the crew, A. Drallcin, chief of the Fourth Antarctic Expedi-
tion, N. Shaicirov, aerial photographer, and V. Lugovoy, interpreter, took
part in the flight.
13
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The round-trip flight, from the Pravda Coast to Queen Maud Land and
back, r~aade by -the Soviet twin-engine transport plane covered about 7,000
kiloinet!nrs. For the first time, the two Soviet bases, Mirnyy and Lazarev,
were connected by airplane. During the preceding 7-month period, contact
between 12lrnyy and Lazarev had been maintained by radio only.
After arrival at Lazarev, the plane made two reconnaissance flights
in that vicinity: one, along Princess Astrid Coast, and the other, south
of station Lazarev, in the region of the Wohlthat and Sor Rondane mountains.
On 28 October, the plane left Lazarev on its return flight. Four stops
were made along the way at foreign antarctic stations, including the Belgian
base Rol Baudouin, the Australian stations Mason and Davis, and the Japa-
nese station Showa. The Soviet and foreign polar scientists exchanged
scientific information on problems concerning the exploration of East Antarc-
tica. ("Airplane Returns to Mirnyy"; Moscow, Vodnyy Transport, 3 Nov 59)
New Mountains Discovered by Soviet Plane
Me group of polar scientis?I?.s who arrived at station Lazarev by LI-2
plaice f roan Nirnyy on 19 October remained on Queen Maud Land for 10 days .
The plane made several flights in the vicinity of Princess Astrid Coast
are-'. into the interior of the continent. During the latter flight, two
groups of mountain peaks were discovered at a point with coordinates 72
&c x?ees South and 16 degrees East and were plotted on the map; the height
of these mo?mta?ins was about 3,000 meters above sea level. A xeconnaissaxice
flight over the area was made to determine the best route for overland trans-
port from central regions of Antarctica to Princess Astrid Coast. ("Above
the Ice Cap of Antarctica"; Moscow, Vodnyy Transport, 31 Oct 59)
On their recent long-distance flight from Mirnyy to Lazarev, the Soviet
explorers diocovered a previously unimown mountain area shortly before
arriving in Queen Maud Land. it was determined that the altitude of these
mountain, was about 3;000 meters above sea level. Possibly these mountains
will be named "Oktyabr'sid.y Range" in honor of the October Revolution or
"Moscow Mountains." However, at- the moment, the name is not important. The
Soviet people have given science -- geography and geology -- a gigantic new
object for further study. (Y4rnyy--Lazarev--N'lirnyy"; Moscow, Izvestiya,
6 Nov 59)
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Current Activities in Antarctica
With the arrival of spring in Antarctica, scientific activities have
been greatly expanded. The polar. explorers are now headed toward the un-
exp1ored interior of the continent.
During the current antarctic spr:txig, interior expeditions will be
carried out by scientists of Australia, Belgium, Norway, the US, France,
and Japan. The Fourth Soviet Antarctic Expedition is conducting research
according to an extensive program.
A group of scientists headed by S. Shcheglov, geophysicist, resumed
its complex scientific studies in central regions of Antarctica during mid-
September. The explorers have two "Pingvin" snow vehicles with trailers
at their disposal, with equipment and food supplies for 4 months.
During a one-month period, the group traveled over 200 kilometers from
the coast of Davis Sea. Progress has been greatly slowed down by snowstorms.
The final destination of the group is the south geomagnetic pole. These
explorations will contribute a great deal to the information collected by
previous Soviet expeditions and will enable the scientists to construct a
meridional geophysical cross section of Antarctica, extending over 1,400
kilometers.
The scientists are making concentrated preparations for the great trans-
continental traverse, which will pass through central regions of Antarctica
and the South Geographic Pole. ("Conquerors of the Glacial Continent";
Moscow, Pravda, 21 Oct 59)
USCOMM DC
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