INFORMATION ON SOVIET BLOC INTERNATIONAL GEOPHYSICAL COOPERATION - 1959

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP82-00141R000200980001-5
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 30
• Document Creation Date: November 9, 2016
• Document Release Date: February 17, 1999
• Sequence Number: 1
• Publication Date: December 18, 1959
• Content Type: REPORT

G a,nd V. 131631.2-~9,\ Sanitized LQ Jiij7Rw~Wl-dTR0002)W4VbORMA11 ION ON --)OV I ET
~ECEMBE.R 18 4959: -199 '' - - ` .~; :,:1 OF 1 .
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Yd 131632-97
iN~?o '~?TI0N ON 3011 BLOC L U &N.-TIONAL U170Pk1L 10AAL UkkW LION ? 1959
December 18, 1959
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INTRRNATIONAL GEOPHYSICAL COOPERATION PROGRAM
(First Photographs of the Far Side of the Moon)
Table of Contents
Pa
Forward
2
Introduction
I.
II.
Equipment on the Automatic Interplanetary
Station
Flight of the Interplanetary Station
8
III.
Photographing and Transmission of Pictures
13
IV.
Invisible Side of the Moon
19
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(Translator's Note: The first official publication on the pre-
liminary processing of photographs of the far side of the Moon obtained
by the automatic interplanetary station was issued by the Publishing
House of the Academy of Sciences USSR on 10 November 1959. A transla-
tion of the 34-page booklet, Pe Foto rafii Obratnoy Storony Luny
(first Photographs of the Far side of e on , with an introduction
by Academician A. N. Nesmeyanov, President of the Academy of Sciences
USSR, follows)
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) CSrewar"d
'.%;parimmon't.al ii-Ludy of 't.hr co,,3mo'?? .'.3 ont.t,nu I.ng. On.
I? i); i:Cit:,':'r' '(lcir)! t,l7.'w Sovio'G ~.ti,1.on t?1.1?~.~!'f:!'tiJ. dy lour .tried the t.h.trd nos-
affil l?.tAo c't,rtl of whi.c.t^ was t,h:` a Msa;i:t.t't i ort of a scry '' a~~ of rr
w p. oblemc)
oJ' oEltni,~ e,paco and the ph.ototrraphi.ng o.t' thw, far :ride of the Mcon at:i
its per.! pt:eral areas. :(n pre^"t c co f'orYnity vlt"h caiqu.lat+ons., the
aua.oma''; ..c tu'rry r3tt1 t.i,o.rt, : pC, ?ictl.1.,y equi ,pad for photographing
the fur F"t" of thr, M(.) 7,n, flew .par; tr at, ra c.1:.i t.rsv:.,e from the Moon,
turned. on Its course and, in ar:c:ordance with a g7.ven program to0:c
photographs of the aide of the Moon which is not vtutb.le from the
l r~r. ttt. With the aid of a television apparatua on board the inter-
1],.'l.rle{,Lll.' t:rt't.i.on. the iina(ge of the Moon was tra.n~Q.n.' ttera,., O. ?o!l1mAnd
t roin t..be Earth. .from digtan;:;es of several hundreds of thou-gand.E4 of
k?a.J.cnneter'e?
A new o.::a t'ta, begltn in the hi.r;to ':y of astro.o.vYigy.. ?rt ba.' Z,,w_en
that not coly Is it. po:s.r;i.bl..s to study the phy t':a.l parameters of
pr:c,e utid va,rlous em:r.ssione of ~-left;j.a:l bodj,,,. without hindrance,,
'-it, al.a:-) a L .i possible to obtain close-up photographs of the planets.
1'11. s.:t;,rcnorner will not have to wait 15.17 years for the great opposi-
Lion o.' Mars, when the distance 'between It and the Fa'rtfi v11.1 be reduced
b 50.?50 riiI:i.on kilometlers, NOW :lt: I.s pra3E':t.b~._ , in pri.n:ri.ple; to send,
vehi.:,l.e?, to within close distances of the pl.artet?s in order 'U) p':otograph
their c:,:.rfa:e
Man 1,s no lciriger ~:ha'ined to tb.e Earth. lie Soviet people have made
our generation contemporarieo of interplanetary flights,.
At t-T_e Th.s,r.d ge ;slon of the: Supreme Srltiriet' U.30 R, N. S~ Kk>r"v. h:the~~'
ai.d.; r : gHrd ,.ng this ur_px:v : edent'.`(d aeeompli,: hmer.t of yovi.e ;
"How happy we are how prouu.d we are of the a,2? ompA:..rykuuelts of the Sotr.tet
people, sub as the sut;ceseful launcb55.ng, within one year,, 1959, of three
o+smi^ ro~:k ta, evoking the delight of all mankind. l;hev ent? re Soviet
nation hor.erc the people of science and labor who paved. the way into the
ccsmc: 1,
Since the time of Gal "Cleo and Newt.cn, who founded contemporary
natural scien::e, a ci.enc e ha scored many an outstanding victory. Among
these were the prediction of the ex::r:.t.en?::e and the dl;s,:overy of new
planet.s in. the r:o.lar sy:steiii, 74ept,u.ne and Pl7.;to.. But not. unti.1 off. time
were the ff..rst.. artificial. celevt .a.l. hrdieisy those of !.re Earth and. of
the :?unr created by the labor cf the Soviet pt'pie, r"epr'er3e.ating the
first tine in the history of niankk.:ac. thrtt, a flight was .taade from one
celestial body to another, bringing remarkable i.nlre .t:Igation of the
study of co,mi.c spa:?.e.. Already the l.a~~.r ,1~'i.rzg c..i' the Scoviet ar't;::.fi-
oi.al satellites of the Earth and, ,:omic roc:ket.s has t?rou.ghi, to a
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number of discoveries of universal value: the outer radiation belt and
the extraionospheric ring of current around the Earth were discovered;
u living organism was sent into flight in cosmic space; new data were
obtained on the structure of the magnetic field of the Earth; it was
established that the Moon lacks an appreciable magnetic field and has
no radiation belt surrounding it; the density of interplanetary gas
was determined; and the first photographs of the far side of the Moon
were obtained.
The current publications of the Academy of Sciences USSR contain
the first published results of the preliminary study of the photographs
of the far side of the Moon, taken on board the automatic interplanetary
station. The study of these data is being continued, and in a short
time, the Academy of Sciences USSR will publish scientific works con-
taining the obtained photographs, a description of the,formations on
the far side of the Moon, and a description of the method used in de-
termining the nature of these formations, as well as other data.
Scientists of the Soviet Union are hopeful that the publication of
the data on the photographing of the tar side of the moon will contribute
to the further progress of science an the road to the conquering of the
universe. -- Academician A. N. Nesmeyanov, President of the Academy of
Sciences USSR
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:1c7'[(Ot ON
On LE October 1939; the Soviet '''inl,on n~t;.c= ,tifvi1y lati?. hed the third
ohmic rocket. The goat of th1.ss 1ai.,v:hinq was the r.olut;.on of a serifs
of problems of cosmic research. The merit. :mp.rtart of these was the
photographing of the surface cf the Moon. There, was particular scien-
tific interest in obtaining photographs of t:+wt part of the lunar sur-
face which, because of the nature of t:. he motion of the Moon, is not
directly vi ??ible frota the Earth, as we...l as that part of the surface
which is viewed at s= b. an acutc2 angle that. It cannot be studied ac-
curately.
An automat.i._ interplanetary station., put into orbit around the
Moon by means of a multistage rocket; was built to provide a detailed
stud.y of cosmic space and to obtain photographic recoraings of the Moon.
In precise conformity with calaulationns, the automatic interplanetary
station passed the Moon at a distance of several thr w:and kilometers
and, as a result of the attra:.ti.cn of the Moon, changed the direction
of its motion and moved into a trajectory which was conven.i.ent both for
photographing the side of the Moon which is not visible from Earth and
for transmitting scientific information back to Earth.
The accomplishment of the of the third cosmic rocket and
the placing of the automatic interplanetary station into a given orbit
required the solution rr;" a. rTambQxr of new zcient1f:i.c and techniz-al. prob-
lems The interplanetary :statism was launched by a priHerfu.l multistage
rocket, characterized by a high design provided with powerful
engines which operate on `~i,a~h.,?,c Ior.i,:'.ty .f.ual. The realization of a
VFi ^.k ` at the end of the accelerated
given characteristic motion of t'
portion of its flight was g, aranteA.by a p1?,:._ee sy3tem of control.
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I. Equipment on the Automatic Interplanetary Station
The automatic interplanetary station is a cosmic flying device
equipped with a complicated array of radio engineering, phototelevision,
and scientific apparatus, a special orientation system, devices for the
programmed control of operations of the station's equipment, a system
for the automatic control of temperature within the station, and power
sources.
By means of a radio engineering device located in the station, it
was possible to make measurements of the orbital parameters of the station,
to transmit television and telemetric information to Earth, and to trans-
mit commands from Earth for control of the station-borne apparatus.
The station's phototelevision apparatus made it possible to auto-
matically photograph the far side of the Moon, process the film, and pre-
pare it for transmission of the image to Earth.
The complex of scientific equipment in the automatic interplanetary
station was designed for the further study of cosmic space and space in
the vicinity of the Moon begun by the first two cosmic rockets.
All control of the functioning of the station's apparatus was accom-
plished by means of radio links from points on Earth and also by means of
independently programmed station-borne devices. Such a combined system
makes it possible to more easily control the conduct of scientific experi-
ments and to receive information from any sector of the orbit within the
range of radio visibility from ground observation points.
An automatic temperature control system operates continuously to
maintain a given temperature in the station. With this system, the heat
given off by the instruments is lead out through the radiation surface
into the surrounding cosmic space.
Heat emission is controlled by means of shutters on the exterior of
the satellite which open the radiation surface when temperature within
the station reaches p 250.
The power supply system comprises individual units of chemical
sources of current for supplying the short-term operating equipment and
also a centralized reserve chemical battery. Solar current sources com-
pensate for expended energy from the reserve battery. Supply of the
station equipment is maintained through converter and stabilizing devices.
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The automatic :Lnterplanctax,?y station is a thin??wa1led h,;,,i ne ttca.lly
sealed capsule havinL,c a cylindrical shape with sphesrica 1. within
which are located the equipment and chemical power sup~lios. Some o"
the scientific instruments, the antennas, and sections of the ,solar bat-
tery are on the exterior of the station. In the upper end is an i.lltunin??
ator with a cover which automatically opens beforr: photogr.aphi.riL; 1:r ;,p
Under the illuminator are the camera lenses and a .L.,_clt wir for .)rierita-
tion with the moon. In the upper and lower ends are ;small iliumina-tors
-Cnr.? the solar pick-ups of the orientation system. In the lower end are
the control motors for this system.
The maximum diameter of the station is 1,200 millimeters, and the
iangth is 1,300 millimeters (without antennas).
For photographing the moon., it was found to be more expedient to
point the photographic equipment by rotating thc. entire automatic inter.
planetary station. The orientation system rotated and maintained the
automatic interplanetary station in the required direction.
The orientation system was turned on after approaching the moon,
at the moment when the station was located approximately in a straight
line between the Earth and Moon. At this time, the Earth was located to
o?.ie side of a line between the Sun and Moon.. The distance to the Moon
at the moment the orientation system -?3s to _rned on was. , in accordance
with computations, 60,000-'(0,000 kilometers. The possibility of
realizing the necessary position of tl:.e r,-17.a -'ion during its orientation
was accomplished by a specially selected trajectory. This position per-
mi.tted the station to be oriented with respect to the Moon under condi?.
tions of illumination from three bright celestial bodies -- the Sure, Moon,
and Earth.
At the beginning of operation of the crientation system, the compo-
nents of which included optical and gyrosccrica v.r..i tr., electronic logic
devices, and control motors, it was necessary to stop the, arbitrary r,ota?-
tion of the automatic interplanetary station around its center of grad.ty
which had began at the moment of separation of the station from the last
stage of the launching rocket.
After rotation had ceased) the lower end of the station was d.i.rected
toward the Sun by means of solar pick---ups. In th .e position, the optical
axes of the camera were directed toward one side cY the Moon.
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Then, the appropriate optical device, in the field of vision of
which neither the Earth nor Sun could then appear, turned off the pick-
up orienting on the Sun and .directed the photographic apparatus pre-
cisely at the Moon. From the optical device, the incoming "presence"
signal from the Moon initiated the photographing process automatically.
During the entire photographing operation, the orientation system con-
tinually directed the automatic interplanetary station at the Moon.
After exposure; of a.1.l the frames, the orientation system was shut
off. At this moment, the system 'imparted to the automatic interplanetary
station a well-regulated rotation with such a specific angular velocity
that, first, the temperature regime would improve and, second, the effect
of rotation on functioning of the scientific equipment would be excluded.
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11. 'lir;Yr1; of thc: Irrterpl.ane L:r xry S to t' on
Problems concerning orientation and radio communication with the
automatic interplanetary citation impose special requirements on the
flight trajectory.
An initial requirement for the normal operation of the orienta-
tion system is that the Moon, the station. and the Sun be in approxi.-
mate'! y a single, straight line at the instan the system begins to func-
tion, since at this time the station would. be within the diatar-ce range
indicated in the preceding section.
In connection with the large volume of information to be transmitted
from the interplanetary station to earth, the flight trajectory must per-
mit the re.:eiving points throughout the territory of the USSR to obtain
the maximum amount of information on the .first orbit. particularly at
distances close to the surface of the earth.
it was also very desirable for purposes of scientific research to
obtain a trajectory which would ensure that the station continued in
flight for a sufficiently long period of time.
'Investigations showed that these requirements could be most fully
satisfied by using the gravitation of the Moon in the formation of the
orbit. To obtain an orbit, with the required character. isti.cs, it wa::
necessary that this effect be fully determined as to magnitude and direc-
tion. The Moon can exert a considerable effect on the motion of the
satellite only if the Moon's attraction is sufficiently great. To achieve
this, the station must pass close to the Moon. For a directional change
in the orbit characteristics, the station must pass along6.de the fully
determined side of the Moon. More exactly,, the di.re'ition of the Moon's
effect is determined by the inclination of the, station-Is orbit to the
plane of the Moon's ort i t in its selenocen..tri c motion.
The firing velocity for flight around the Moon with return to Earth
must be several times less than the so-called second cosmic (or parabolic)
velocity, which is equal to 11.2 kilometers per second at the surface of
the Earth. Flight around the moon may be accomplished with various types
of trajjectories.
If the flight trajectory passes at distances of several tens of
thousands of kilometers from the Moon, the effect of the Moon is com.
paratively slight, and motion relative to the Earth will occur in a tra-
jectory which is close to an ellipse with focus at the center of the
Earth. Circumlunar trajectories which pass at several tens of thousands
of kilometers from the Moon have many great disadvantages. It is impos-
sible in a flight at great distances from the Moon to make a direct i,n-?
vestigation of the cosmic space in the neighborhood of. the Moon. If. a
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rocket is launched in the northern herii?sphere of the Earth, the return to
Earth is toward the southern. hemisphere. Motion close to the Earth on
the return is outside the limits of visibility from the northern hemis-
phere, and, therefore, radio communication close to the Earth is impos-
sible. In returning to Earth, the rocket enters the, dense layers of
the atmosphere and burns; the flight is ended after the first turn.
The us? of the directional nction of the lunar attraction at close
proximity to the Moon to form the orbit of the automatic interplanetary
station made it possible to obtain an orbit which did not have the
disadvantages common to trajectories which circle the Moon at great dis-
tances.
The flight trajectory of the automatic interplanetary station
passed at a distance of 7,900 kilometers from the center of the Moon
and was calculated, to be south of the Moon at the time of closest ap-
proach. Due to the attraction of the Moon, the trajectory of the auto-
matic station is deflected to the north in accordance with the calcula-
tions. This deflection is so considerable that the return to Earth is
toward the northern hemisphere. After approaching t._, Moon, the greatest
height of the station above the horizon increases daily for the various
observation points throughout the northern hemisphere. There was a cor-
responding increase in the time intervals within which direct communica-
tion. with the station was possible. Luring the approach to Earth, the
automatic station could be observed in the northern hemisphere as a
nonsetting star.
In returning to Earth on the first orbit, the station did not enter
the atmosphere and did not burn. It passed at a distance of 1+7,500 kilo-
meters from the center of the Earth, moving in an elongated orbit, almost
an ellipse. The greatest distance of the station from the Earth was
1+80,000 kilometers.
The flight of the station in the vicinity of the Earth was at such
great distances from its surface that there was no braking from atrnos.?
pheric resistance. Therefore, if the motion were only a result of the
gravitational force of the Earth, the automatic station would be a satel-
lite of the Earth with an infinitely long lifetime.
Actually, however,, the duration of the station is limited. As a
result of the perturbing effect of the attraction of the Sun, the closest
distance from the orbit to the Earth (the height of the perigee of the
orbit) is constantly decreasing. Therefore, after having completed a
certain number of revolutions, the station, in returning to Earth, will
enter the dense layers of the atmosphere and cease to exist.
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The inaFrnitucle of ttis decrease In the h(yiktht, crC the perig;oc in one
r?ovolu'tioli depends on the d1.merteione of the orbit and, In ps.rt.l:u.Lar on
;.))c heii;ht of the apogee, the e',rcatcnt distance from the orbit to the
girth. The height of the perigee rises sharply w:tth an tnc; treae,G to the
height of the apoi see. Therefore, in Aioosing the trajectory of the inter-
planetary station, it, was necessary to approximate the situation i.n which
the height of the apogee is as small as possible and dr,te n not mw-h ,;xeoed
the distance from -the Earth to the Moon. It is also ntcessary that the
height of the perigee on the first orbit be any great as possible. The
number of rotatt.onc of the automatic station around the Barth and its
lifetime depend on the degree to which both the a requirements are fu;l.-
filled.
The effect of the Moon is not 1.ianited to the effect which it exerts
during the fir. st approach. Perturbations a n the station orbit cau;'ed by
the Moon's attrae:tic'n do not have the same regularity as th.~3e caused by
the Sun's attraction and depend greatly on the period of rotation of the
station around the Earth. The Moon may have a substantial effect if the
trajectory of the station again approaches sufficiently close to the Moon
on one of the subsequent rotations. In this case, the approach of the
station and the Moon would occur at approximately the same point in the
lunar orbit as the first time. The character of the motion of the station
may change substantially. If the interplanetary station passes around
the Moon from the south side, i.e., if the approach is the ewne an the
first, then there will be a sharp increase in the number of rotations and
the lifetime of the station, and. the main property of its traje r:tory.. ap..
proach to Earth from the northern hemisphere, will 1e preserved. If it
goes around from the north side, the height of the perigee will decrease.,
and if the perturbation is sufficiently strong, a co:..lision with the Earth
may occur on the next return.
On those t r -; of the orbit w :ere n. sufficiently close approach to
the Moon does not occur, the Moon, neverthele,s, exert. a considerable
effer,t on the motion of the station, although ,he Me!:in.'s attraction in
this case is very small, over a consid rable number of turns of the tre..-
jectory, the Moon's attraction exerts a con~,idt~rable effect on the motion
of the automatic station and. caur es a decrease in the height of the perigee
and the ].ifetim.F of the station in orbit..
The picture of the moti,:i of the automatic station under the simul?-
.tanecus gravitational effects of the Earth,, Moon, and Sur. is very complex.
The character of the passage near the Moon on the first approach is the
dete..3nini.ng factor for the further motion of the interplanetary station.
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Since there is no correction in the motion of the interplanetary
station in flight, itr whole flight is determined, in the final analysis,
by the parameters of the motion at the end of launching sot;ment, (barsi-
mally, the magnitude and direction of the velocity.) It is clear then
hat it is possible to obtain the trajectory described above only with
can extremely accurate system for controlling the flight of the launching
rocket in the launching segment.
It may be imagined that through the center of the Moon perpendicular
to the Earth-Moon line, there is a plane, which we shall call the mapping
plane. The trajectory relative to the Moon may be characterized by the
position of the point of intersection of the trajectory with the mapping
plane.
Calculations show that a deviation of the point of intersection of
the trajectory with the mapping plane from the intended position by 1,000
kilometers changes the minianun distance of the station from the Barth at
the end of the first revolution by 5,000-10,000 kilometers and the time
of return to Earth by 10-14 hours.. Such a substantial change in the values
of the trajectory parameters close to the Earth is connected mainly with
a difference in the effect of the Moon on the motion of the station in the
cases of the calculated and deviated trajectories.
Although satisfaction of all the conditions imposed on the circling
trajectory admits of greater deviations from the calculated position of
the point of intersection of the trajectory with the mapping plane than
there could be in the case of impact with the Moon, realized with the
second Soviet cosmic rocket, the accuracy required in the launching seg.
ment remains as high as in the case of impact. This is mainly because
errors in the magnitude of the velocity at the end of the launching seg-
ment in the case of elliptical circling trajectories cause deviations in
the point of intersection of the trajectory with the mapping plane which
are 3-4 times greater t.ian in the case of hyperbolic trajectories, which
are convenient to use fat, impact.
In addition, for good. radio communication between the interplanetary
station and observation points on earth, it is necessary to know with suf-
ficient accuracy the change in the characteristics of the motion of the
station with time.. This, is necessary in order that the measuring points
can carry out calculations on th.c tar-get with the required accuracy and
determine the times for switching on the transmitting devices on board,
This requires systematic measurement of the trajectory of the interplane-
tary station, analysis of the data, and correction of the characteristics
of the motion of the station, both during its approach to the Moon and
after its flight around the Moon. The effect of the Sun and Moon on the
evolution of the orbit of the interplanetary station in the process of its
further flight also requires constant measurement and correction of the
characteristice of the motion of the station.
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These conditions impose great demnndn on the automatic Earth complex
intended to measure the parameters of the trajectory of the interplanetary
+tation, calculate a prediction of Its motion, calculate targets by meaeur...
ng and observation points, and calculate the tunes for switching on the
transmitting devices on board the interplanetary ;tat.i,on throughout ite
flight around the Earth.
The Earth complex includes a radio-technical station for measuring
the distance, angular parameters, and radial. velocity of the motion of
the objek;t; a station for receiving tel.emetering information; and auto-
matic lines connecting the measuring points with the corrdinating-computing
center, which, in turn, is connected with Earth points for giving cammands
to switch on the transmitting devices on board the automatic interplanetary
station.
The command radio line made it possible to switch on the radio-technical
communication devices at definite time intervals .orresponding to favorable
conditions for radio communication between the apparatus on board and the
Earth points throughout the territory of the Soviet Union. Selection of
the duration and time for switching on radio communication with the station
was determined by operating conditions of the apparatus on board, the need
for conducting trajectory measurements to correct characteristics and pre-
dict the motion of the interplanetary station, and conditions of the rated
power supply of the devices on board.
Data established through analysis of trajectory measurements on 'the
position of the interplanetary station at the time of the photographing,
necessary for tying in the observed. objects on the Invisible side of the
Moon to the selenographic net of coordinates, are presented in the table.
Selenographic
Di Pr. o,ject?On AI:S*
;ta,n.ce.
Tme From Center
Date N28 ,10w) of. Moon km,, Latitude 'Lon itg ude
Beginning of
photographing 7 Oct 59 0630 65;,200 16.9? 1.17.6?
Completion of
photographing 7 Oct 59 0710 68,00
*Automatic Interplanetary Station
1.7.3?
:1.17.1?
A preliminary processing of the trajectory measurements on the first
turn of the orbit made it possible to establish that the automatic inter-
planetary station will. continue in orbit up to the end. of March 1960 and
will complete 11 revolutions around the Earth.
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III. PHOTCORAPHING AND TRANSMISSION OF PICTURES
In developing the complex means for photographing sand transmitting ?a
picture of the invisible side of the Moon from on board the automatic
Interplanetary station, the problem of producing it phototelevisiori system
which would make it possible to obtain sufficiently clear half-tone pic-
tures and transmit them at distances measured in hundreds of thousands of
kilometers was solved.
The phototelevlsion apparatus, installed in the interplanetary sta-
tions, contained the following principal devices: a camera with two ob-
jectives, a small-scale device for automatically developing and fixing the
photographic film, a miniature cathode ray tube, a highly stable photoelec
tric amplifier, an electron circuit containing amplifiers and scanning
devices, and a systam for automation and programming.
The design of the phototelevision apparatus ensured its reliability
under the complex conditions of cosmic flight; the safety of the photo-
graphic materials from the harmful action of cosmic radiation and the
normal functioning of the unit for processing the photomaterials and
the other units of the apparatus in conditions of weightlessness were
ensured.
For the exceptionally long-range transmission of pictures with a
very low-power radio transmitter, an image transmission speed tens of
thousands-of times slower than the transmission speed of the standard
television transmission centers was used.
In the first photographing of the reverse side of the Moon, it was
expedient to photograpLi as large a portion of its unknown surface as
possible. This led to the necessity of photographing the fully illumina-
ted disk whose contrastivity is always considerably lower [at this time]
than during lateral illumination which creates shadows from the details
of the relief. Automatic contrast control of the transmitted image was
applied for best transmission of the low-contrast picture by the photo-
television apparatus
The camera was equipped with two objectives with focal lengths of 200
and 500 millimeters and apertures of 1:5.6 and 1:9.5, respectively.
The objective with a focal length of 200 millimeters gave a picture
of the disk of the Moon fully entered in the frame. The objective with
a focal length of 500 millimeters gave a large-scale picture of part of
the lunar surface.
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Photographing waci nnde on social 35??mtlli,moter photographic film
which can be proceresed under high temperature.
Photographing was conducted with automatic exposure change for diffe-
rent frames to obtain negatives with the best densities and lasted about
1+O minutes, during which time the reverse side of the Moon was photographed
repeatedly.
The entire photographing process and film processing was done auto-
matically, according to a fixed program.
For preventing fogging of the film under the action of cosmic radia-
tion, a special safeguard was provided which was selected on the basis of
investigations conducted with the aid of the Soviet artificial satellites
and cosmic rockets.
Upon completion of photographing, the film moved into a miniature de-
vice for automatic processing, where it was developed, fixed, and dried.
Then the film moved.into a special holder for transmission of the image.
Transmission of images of the Moon was performed by commands from the
1,?irth which switched on the power supply of the station television appara-
tus, started the transport of photographic film, switched in the television
apparatus to the transmitter on board.
Coordination and regulation of the operation of all members, including
the electronic circuits and the optical, mechanical, and photochemical ap-
paratus, were accomplished by a system of automation and programming.
The method of "trans illumination" was used to transform the image
contained on the film negative into electrical signals. This method is
analogous to the one employed by television centers in transmission of
motion-picture film. A small cathode ray tube of high resolving power
produced a bright spot which was projected onto photographic film by means
of an optical system. The light which passed through the photographic
film fell upon a photoelectric multiplier which transformed the light
signal into an electric one.
The light spot on the screen of the cathode ray tube was displaced
in relation to the controlling electric signals produced by a special
scanning circuit. The image of the light spot on the photograph was
uniformly displaced across the photograph from one side to the other,
after which it quickly returned to the initial position and again continued
with steady movement across the film. This provided "line" scanning of
the image. The photographic film itself was pulled slowly past the cathode
ray tube, permitting "frame" scanning.
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Intensity of the light which passed from the cathode ray tube through
the film to the photoelectric multiplier is determined by the density of
the negative at the point at which the light spot is located. In move
inept of the spot over the negative, the amount of current in the photo-
electric multiplier changed in relation to the change in density of the
image along the line; thus, an electric "image signal" was formed at the
output of the photoelectric multiplier, repeating the change in density
of the negative along the scanned line.
Amplification and shaping of the image signals were accomplished by
a specially developed, stabilized, narrow-band amplifier.
Since the average density of the negative and image contrast were not
known exactly beforehand, a device was incorpora-red in the amplifier for
automatic regulation of compensation to counteract the effect of variation
in the average density of the negative on the output signal. Automatic
brightness regulation of the illuminating tube, to compensate for changes
in contrast, was also provided.
Test sings were exposed on the film, a part of which were developed
while still on the Earth, and the other part of the sings were developed
aboard the station in the course of processing the exposed frames with
the back image of the Moon. These signs were transmitted to the Earth,
permitting control of the process of photographing, processing, and trans-
mitting the image.
Transmission of the image was possible in two variants: at a slower
rate of transmission at great distances and at a faster rate of transmission
at closer ranges, i.e., during the satellite approach to the Earth.
The number of lines into which the image was broken up could be varied,
depending on the variant selected for the transmission. The maximum num-
ber of lines would reach 1,000 per frame.
A method assuring high-noise immunity and reliability of performance
of e4uipment was used to synchronize the transmitting and receiving scann-
ing devices.
The radio-communication line provided a two-way transmission of radio
signals? In the "Automatic Interplanetary Station-Earth" direction were
transmitted television signals, the signals of scientific instrument read-
ings, and the signals for measuring the parameters of motion of the satel-
lite station. Powerful radio transmitters,- high-sensitivity receivers,
and recording instruments, as well as the receiving and transmitting antenna
assemblies, were part of the ground installation. Transmitting, receiving,
and antenna equipment, as well as the command and programming radio-engineer-
ing devices, were part of the automatic interplanetary radio station.
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The Moon-image was transmitted from the automatic interplanetary sta-
tion via the line of radio communication, which also served to measure the
j +axrtrrte:t: ,rc, of the: r3tata on motion.
The transmission of the Moon-image, and all other functions of the
line in radio communication with the station, were carried out with the
aid of continuous radiation of radio.waves (as contrasted with pulsed
radiation). Such a combination of functions in a single line of radio
communication utilizing continuous radiation was tried out for the first
time and provided reliable radio communication up to the maximum distances
with the lowest power consumption from the power sources on board.
All of the radio-communication line equipment, both aboard the inter-
planetary station and on the ground posts, was provided in duplicate to
improve the reliability of communications. In case of failure of one of
the radio instruments aboard the station or upon reaching the limits of
its usefulness, it can be replaced by a reserve instrument by transmitting
an appropriate command from the ground control post.
The total volume of scientific information transmitted via the radio
communication line, including the frames of the Moon-image, considerably
exceeded the volume of information transmitted from the first and second
Soviet cosmic rockets. This required the application of more efficient
methods to secure photographs and to transmit the signals via the radio
communication line. These methods assured lowest power consumption from
the power sources.
Semiconductors, ferrites, and other modern components and materials
were used in the radio equipment on board. Special attention was given
to securing the least space for and weight of the instruments, which, in
turn, permitted the increase of the weight and space assigned to the elec-
tric power sources.
To conserve electric power, the power radiated by the satellite radio
transmitter was set at several watts.
The difficulties of maintaining a reliable radio contact with an inter-
planetary automatic station can be realized if we calculate what fraction of
the power radiated by the satellite radio transmitter will reach the receiv-
ing ground installation.
In order that the radio contract with the satellite station would not
be interrupted during its rotation, the station antennas had to radiate
the radio signals uniformly in all directions, so that the radiation power
per unit of area would be approximately equal at all the points of an im-
aginary sphere, at the center of which is located the satellite station.
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The fraction of radiated power reaching the ground receiving antenna
is determined by the ratio of the effective area of the receiving antenna
to that of the surface of a sphere with radius equal to the distance from
the satellite station to the receiving ground post. Large receiving an-
tennas are used to increase the effective area of such antennas for effi-
cient reception of signals from the satellite station.
However, even under the above-mentioned conditions, in the case of
the greatest distance from the Earth to the satellite station, the inter-
cepted radiation signal from the satellite transmitter will be 100 million
times smaller than the average power received by a conventional television
receiver. The perception of such a weak signal can be accomplished only
by a very sensitive receiving installation with a very low level of set
noises.
The set noises at the output of the ground receiving installation
were reduced to a minimum with the aid of special measures.
In accordance with the postulates of information theory and the theory
of noise immunity, the reception of rather weak signals with a noise back-
ground can be secured by lowering the rate of information transmission.
The degree of lowering of rate of information transmission depends on the
selected method of transmission and reception of radio signals.
In the radio-communication line, such methods of processing and trans-
mission of signals at the satellite station and at the ground receiving
post were used which, to an utmost degree, have lowered the noise level
and, at the same time, maintained a satisfactory rate of transmission.
Economic utilization of power sources, on the satellite station,
availability of radio communication line with continuous radiation and
performing several functions, use of special receiving antennas at the
ground post, use of highly sensitive receiving installations, and ua liza-
tion of special methods for processing and transmission of signals -- all
contributed toward the maintenance of reliable radio communication with
the automatic interplanetary station, an uninterrupted operation of command
radio line, and planned photographing of the Moon and telemetered informa-
tion.
The reception of Moon-image signals on the ground was carried out with
special devices for registering the television images on a film, with
magnetic recording devices having very uniform speed of the magnetic tape
with skiatrons (long persistance cathode-ray tubes), and with open-recording
devices where the image is recorded on an electro-chemical paper. The
data thus secured from all kinds of recording were used to study the far'
side of the Moon.
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The transmission of images was carried out for various distances up
to 470,000 kilometers with the aid of radio-television equipment installed
on the automatic interplanetary station. Thus,the possibility of trans-
mission in cosmic space over extra-great distances of the half-tone images
with high resolution and without appreciable distortions in the course of
radiovave propagation was confirmed experimentally.
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IV. INVISIBLE SIDE OF THE MOON
The period of rotation of the Moon about its own axis coincides
with the period of its revolution about the Earth, and for that reason,
one and the same side of the Moon is always turned toward the earth.
In the distant past, millions of years ago, the Moon rotated about its
own axis faster than now, completing one rotation in a few hours.
The forces of affluent friction, arising by the attraction of the
Sun and Earth, braked the Moon, lengthening the period of its rotation
about its axis to 27.32 hours.
During the course of 350 years of telescopic observations, maps were
made of the side of the Moon turned to us. Beginning with the first rep-
resentations of the lunar surface, these maps continually became more exact
and were supplemented according to the degree of existing means and methods
of observation. At the present time, maps exist on which are plotted
tens of thousands of circular mountains which are craters, numerous moun-
tain ridges, dark regions of lunar soil called seas, apparent fissures,
and many other details of the lunar surface.
The occurrence of the so-called librations of the Moon that is, the
periodic oscillations of the Moon about its center, permits the terrestrial
observer to investigate and plot 59 percent of the lunar surface on a map.
Certain lunar forms situated on the very edge of the visual disc become
visible only during appropriate librations of the Moon. The drifting of
all these circular regions on maps is caused by perspective distortions.
The selection of the time for photographing by the automatic inter-
planetary station enables us to obtain photographs of the extensive por-
tion of the lunar surface not visible from the Earth and of a smaller
region with already known formations. During this time, almost the entire
Sun-illuminated-disk of the Moon was rotated toward the station. In
similar conditions of illumination of the lunar surface, its formations
do not give shadows, and several details are made less conspicuous. The
presence on the photographs of part of the never-before-studied portion
of the Moon permitted objects located on the far side of the moon to be
tied into already known formations and, in this manner, a determination
of their selenographic coordinates. On the photographs, the boundary
between visual and nonvisual portions of the Moon from the Earth is design-
ated by a dotted line.
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Among the objects photographed from the rim of the interplanetary
station and visible from the Earth are the Humboldt Sea, the Sea of
Crises, the Marginal Sea, the Smyth Sea, a portion of the Southern Sea,
and others.
These seas, distributed on the very edge of the Moon and visible
from the Earth, appear long and narrow to us as a result of perspective
distortion. Their actual form has not yet been determined. these sear
are located far from the visual edge of the Moon on the photographs ob.
tained from the rim of the interplanetary station, and their form is in-
significantly affected by perspective distortion.
On the basis of a preliminary study, of the photographs obtained, it
is possible to report that there are few mountainous regions and seas
similar to the seas of the visual portion on the far side of the Moon.
Abruptly, there appear crater seas lying in the southern and priequatorial
regions.
Regarding the seas located close to the edge of the visible portion,
the Humboldt, Marginal, Smyth, and Southern seas are clearly discernible
almost without distortion. It was found that the Southern Sea, for the
most part, is located on the far side of the Moon and that its boundaries
have nonstraight, meandering form.
The Smyth Sea, in comparison with the Southern Sea, has a more cir-
cular form, and its southern side is notched by a mountainous region. The
myth Sea, for the most part: is also located on the nonvisible side of
the Moon. The Marginal Sea has a drawn-out form with an indentation in
a direction opposite from the Sea of Crises. The Smyth Sea also continues
on the far side of the Moon. The Humboldt Sea has a peculiar pear-shaped
form.
The entire region adjoining the western edge of the far side of the
Moon is characterized by a reflecting power intermediate between those of
moun"*ainous regions and seas. According to reflecting power, it is analo-
gous to the region of the Moon located between the craters of Tycho and
Petavius and the Nectaris Sea.
South-southeast from the Humboldt Sea, on the boundary of the indi-
cated region, a mountain chain with an extent of more than 2,000 kilo-
meters passes over the equator and reaches into the southern hemisphere.
iyond the mountain chain stretches, apparently, a continental shelf with
higher reflecting power.
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A crater sea with a diameter of approximately 300 kilometers is
located in the region bounded by coordinates of 4.20 and ?30 degrees
latitude and plus 140 and plus 160 degrees longitude. The southern por
tion of this sea terminates in a gulf. A large crater with a diameter of
more than 100 kilometers, having a dark bottom ark, bright central peak,
encircled by an extensive light embankment, is located in the southern
hemisphere, in the region having minus 30 degrees latitude and plus 130
degrees longitude.
A group of four craters of medium dimensions is located in the
proximity of the above-mentioned chain in the direction of the Marginal
Sea at plus 30 degrees north latitude. The largest of these craters has
a diameter of approximately 70 kilometers. A detached crater of circular
form is located close to this group in the region with coordinates plus
10 degrees latitude and plus 110 degrees longitude. Two regions with a
sharply reduced reflecting power are located in the aputhern hemisphere
at the edge of the disk.
In addition, individual regions with a slightly increased and reduced
reflecting power and numerous minute details are to be found on the photo-
graphs. The nature of these details, their forms and dimensions, will be
established after a more complete study of these photographs.
Thus the fact that it was possible for the first time to televise
pictures of the nonvisible portion of the lunar surface from on board the
interplanetary station opens wide possibilities for study of the planets
of our solar system.
[Figures and Figure Captions. Follow:)
[Figure 1 (photograph) not reproduced here.]
Figure 1. The automatic Interplanetary Station on Assembly Stand.
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LIJELJ L:~ E1= _M
Figure 2e General View. of the
(1) - illuminator for
orientation system;
sections;, (5) ,alous
ml shields; (7) ant
investigations.
tomatic Interplanetary Station (diagram)
otographic equipment; (2) -motor of the`
3) solar transducer; (4) solar battery
a of the heat regulation system; (6) ther-
ms; and (8) instruments for scientific
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oa
I
n~tCGT IAN Of
..G
a?1.?
00- soy. 161t
00~'MINo
4
IL -
c~ H
It b _
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(Figures 5 (drawing), 6) 7, and 8 (photographs not reproduced here.]
Figure 5. Position of the Automatic Interplanetary Station in Space
During Photographing of the Far Side of the Moon (arxows on the
right indicate the direction of the Sun's rays).
Figure 6. Photograph of the Far Side of the Moon Taken From on Board
the Automatic Interplanetary Station.
Figure 7. Photograph of the Far Side of the Moon Taken From the
Automatic Interplanetary Station.
Figure 8. Distribution of objects on the side of the Moon not visible
from Earth which appeared in the preliminary processing of photo-
graphs taken frr.n on board the automatic interplanetary station.
(1) large crater sea with a diameter of 300 kilometers p Sea of
Moscow; (2) Bay of Astronauts in the Sea of Moscow; (3) Con-
tinuation of the Southern Sea on the back side of the Moon;
(4) crater with central. peak, Tsiolkovskiy; (5) crater with
central peak, Lomonosov; (6) crater, Juliot Curie; (7) Moun-
tain range, Sovetskiy; (8) Sea of Mechta.
The continuous line iftersecting the diagram is the lunar equator;
the dotted line is the boundary of the visible and invisible parts
of the Moon from the Earth. Objects satisfactorily established
during the preliminary processing are connected by an unbroken
line; objects requiring better definition of shape are joined
by the broken line; objects, the classification of which has been
more accurately defined, are surrounded by dots; in the remaining
part, further processing of the photomaterials obtained is being
made.
Roman numerals denote objects on the visible side of the Moon:
(I) Humboldt Sea; (II) Sea of Crises; (III) Marginal Sea, which
continues on the invisible part of the Moon; (IV) Sea of Waves;
(V) Smyth Sea, which continues on the invisible side of the Moon;
(VI) S.'a of Fertility; (VII) Southern Sea, which continues on
the invisible part of the Moon.
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