JPRS ID: 9895 WORLDWIDE REPORT TELECOMMUNICATIONS POLICY, RESEARCH AND DEVELOPMENT

• Document Type: CREST
• Collection: JPRS
• Document Number (FOIA) /ESDN (CREST): CIA-RDP82-00850R000400040007-6
• Release Decision: RIF
• Original Classification: U
• Document Page Count: 41
• Document Creation Date: November 1, 2016
• Sequence Number: 7
• Content Type: REPORTS

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JPRS L/9895
5 August 1981
w
Woridwide Re ort
p
TELECOMMUNICATIONS POLICY,
RESEARCH AND DEVELOPMENT
CFOUO 10/81)
FB~$ FOREIGN BROADCAST INFORMATION SERVICE
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NOTE .
,
JPRS publications contain information primarily from foreign
newspapers, periodicals and books, but also from news a;,:~:ncy
transmissions and broadcasts. Materials from foreign-language
sources are translated; those from English-language sources
are transcribed or reprinted, with the original phrasing and
other characteristics retained.
Headlines, editorial reports, and material. enclosed in brackets
are supplied by JPRS. Processing indicators such as [Text]
or [Excerpt] in the first line of each item, or following the
last line of a brief, indicate how the original information was
processed. Where no processing indicator is given, the infor-
mation was summarized or extracted.
Unfamiliar na~nes rendered phonetically or transliterated are
enclosed in parentheses. Words or names preceded by a ques-
tion mark and enclosed in parentheses were not clear in the
original but have been supplied as appropriate in context.�
Other unattributed parenthetical notes within the body of an
item originate with the source. Times within items are as
given by source.
~The contents of this publication in no way represent the poli-
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COPYRIGHT LAWS AND REGULATIONS GOVERNING OWNERSHIP OF
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JPRS L/9895
5 August 1981
WORLDWIDE REPORT
TELECOMMUNICATIONS POLICY, RESEARCH AIVD DE`v'ELOPMENT
(FOUO 10/81)
CONTENTS
ASIA
JAPAN
'CAPTAIN' Computer Access System Test Results Published
~ASAHI EVENING NEWS, 21 Apr 81) 1
VIETNAM
'VNA' Reports on Printing of 'NHAN DAN' by Facsimile
~VNA, 14 Jul 81) 2
EAST EUROPE
CZECHOSLOVAKIA
CSSR's Magion Satellite Systems Outlined
(SLABOr^ROUDY OBZOR, Apr 81) 4
Mag~on Satellite Design Concept, by Miroslav Studnicka
. Transmitting Equipment Described, by Jozef Plzak
Reception of Signals From Magion, by Vaclav Grim
Prognoz 8 Soft X-Ray Radiation Analyzer Described
(Bohuslav Komarek; SLABOPROUDY OBZOR, Apr 81) 27
WEST EUROPE
UNITED KINGDOM ~
New Communications Satellite Being Built
(Henry Stankope; THE TIMES, 22 Jul 81) 37
- a - [III - WW - 140 FoUO]
F(1R (1FFT/`T A T i fCF IINT V
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JAPAN
' Cc~P7'AIN' COMPU'I'ER ACCESS SYSTEM TEST RESULTS PUBLISHED
Tokyo ASAHI EVENING NEWS in English 21 Apr 81 p 3
[ Text ] 't'he first-stage test ~ of the ~e TV receiving set, ~ monitors and screens to Z,000
"CAPTAIN .iystem," a new During the first-stage test and 200,000 respectively, or
informadon medium which serHice period, the system was double those used in the first-
subscribers may use tu request used an average of 0.72 time stage tesc.
- information from a computer per telephone per day, or twice If the results of the second-
over the telephone and re- in three days. The avcrage stage test ara satisfactory, full-
~eive the answer on their tele- time used per phone call was dress service will begin in fu-
vision screen, ended in March, ~ 3 minutes and 41 seconds. cal 1983. -
and the Posts and Telecom- The average number of fram- To the question "Will you
munications Ministry and ot6- es used per call was 38. subscribe to the system if futl-
er auihorities ihat conducted As to w6ich categories oE fledged service begins?" asked
the test recently released a re- information were used the during the first-stage lest pe-~
port on the system. most, information on events, riod, more than half of the
. . .
CAPTAIN sxands for Char- including movies, hobbiea, 'respondeats replied in the af-
acter and Pattern Telephone, quizzes and games were ovcr-� firmative. It is particuluriy
Access Information Network whe}mingiy popular with 46: � noteworthy that 7S percent of
Linking 976 telephqnes in To- 83 percent, followed by news those who made active use of
kyo, the first-stage test was and weather forecasts with , the tesi service answered in
conducted from Dec. 25, 10.55 percent, education with ibe affirmative.. �
1979, to Mazch 15 this year. 10.36 porcent and sports wiih To the query What is aa
Information contained in the 9.83 perceat. Fields that were adequate fee for the service?"
computer includes about 100,- used the least were healtb, many replied "About ~f3,000 a
000 "frames," including those . beauty culture, childbirth and month." Twenty percent of the
for news, weather forecasts, child rearing with Q.68 per- respondents said they were
quizzes and travel informa- ceni, followed by economic willing to pay more than ~'3,-
tion. and legal questions with 0.60 ~ a moath.
Those making use of the perceat. The new iaformation medi-
system, or monitors, are lim- Household heads used the ~ obviously is enjoying high
ited ta those living in areas system the most at 45 per- P�p~~y' ~
uader the jurisdiction of a cent, followed by children, 30
telephone exchange equipped perceat and housewives, 18
_ with electronic t e 1 e p h o n e ~~eM. �
switchboacds and w6ose phone Users apparently made use
is of the pushphone type. of the system with clear-cut
The telephone line and ihe ' objectives. Most household
TV receiving set at home are b~ads said. that they used ttire
linked by means of an adapter. system "to' obtain knowledge;"
To use the system, one calls ihe houso~vives said they used
che CAPTAIN Ce~ter with ihe it "to obRain information nec-
pus6p6one. After setting his essary for our adivities" and
T'V set for recepdon on an the children answered "for
open channel, ~e designates ~udy aad amusemenL"
what he wants to~ know by ~
pushing designated numbers on Tbe second-stage test sec-
the keypad. Then, characters ~ice is scheduled to get under
or patteros are sent via the tele- way in August this year, with
phone line and screened on ~~e.nuanber Qf
COPYRIGHT: Asahi Evening News 1981
CSO: 4120/240
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VIETNAM
'VNA' REPORTS ON PRINTING OF 'NHAN DAN' BY FACSIMILE
OW210323 Hanoi VNA in Vietnamese to VNA Ho Chi Minh City 1350 GMT 14 Jul 81
[TextJ [no dateline received] After the complete liberation of South Vietnam,
an urgent task arising was tha t NHAN DAN, organ of the party, had to be widely
and rapidly published throughout the country to disseminate the party line and
policy among the people of the newly liberated areas. At that time 1~IiAN DAN
was being printed in Hanoi and then transported by plane or other means to
Ho Chi Minh City and the southern provinces. The transportation often met w~th
difficulties from weather conditions and in means of transportation. Due to
this, we could not assure the up-to-date character of the paper every day.
In face of this, based on results obtained in the transmission of radiophotos
during the war and particularly dur3ng the "Ho Chi Minh Campaign," and relying
on existing equipment, VNA put forward a number of inethods for transmitting
the di.m~y of NHAN DAN from Aanoi to Ho Chi Minh City to be published locally
for southern provinces on the same day. The transmissioi: of the paper was
based on the existing network of radio transmission and reception and Soviet
facsimile reproducing equipment, according to th e narrow-band shortwave trans-
mission method. In the conditions where our country did not yet have a wide-band
newspaper transmission facility, this method was the most appropriate one.
VNA's technical section experimented transmission of newspapers by this method
from July to September 1975 and achieved relatively good xesults, confirming
that it was practical enough ~:o be applied on a regular basis. Lturing the
experimental process, engineers and technical cadres concerned made use of
facsimile and Voice of Vietna~n Radio's transmitting equipment and assured the
quality of reception of the transmitted newspaper within our technical capa-
bilities and under our country's weather conditions.
. Early in 1976, after perfecting this method, VNA joined N~EiAN DAN and the Posts
a.nd Telegraphs General Department in organizing the regular transmission of
NHAN DAN from Hanoi to Ho Chi Minh City. By this method, the first issue of
NEIAN DAN was off icially printed in Ho Chi Minh City on 20 April 1976 and issued
on the same day in the southern provinces, thus supporting in good time the
election to the unified national assembly of the whole country on 26 April 1976.
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In 1978, VNA again joined NHAN DAN and the Posts and Telegraphs General Department
in successf ully transmitting the newspaper from Hanoi to Danang by this method.
- In addition to NHAN DAN, VNA has alsa helped QUAN DOI NHAN DAN in technical and
equipment aspects to apply the transmission of QUAN DOI NHAN DAN to Ho Chi t4inh
City for printing there.
CSO: 5500/2272
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CZECHOSLOVAKIA
CSSR'S MAGION SATELLITE SYStEMS OUTLINED
Magion Satellite Design Concept
Prague SLABOPROJllY OBZOR in Czech No 4, Apr 81 pp 159-161
[Article by Eng Miroslav Studnicka, TELSA-WST: "The Magion Exp~riment"]
[Tex~] Not long after Czechoslovakia entered the Inter-
kosmos organization, TELSA-WST [A. S. Popov Research
Institute of Communications Engineering] began cooperation
with the CSAV [Czechoslovak Academy of Sciences] in the
development of instrumentation and equipment for the astro-
nomical and geophysical study of space by means of satel-
lites. Over the course of 15 years, they have successfully
developed more than 200 types of instrtmments. The high
point of our participation in the Interkosmos program has
been the development and launching oi the first Czechoslo--
vak MAGION satellite. This article describes the purpose
of the experiment and the design concept of the satellite
_ and evaluates the findings that have been obtained.
Introduction
On 14 November 1978, the MAGION satellite (international designation 1978-99C)
separated.from the Interkosmos 18 spacecrafi (1978-99A); this satellite was
intended to study the temporal and spatial structure of low-frequency electro-
magnetic fields in the earth's ionosphere and magnetosphere. The scientific
aim of the experiment and the method of carrying it out were d~veloped by the
Institute of Geophysics, C$AV, in cooperation with the Institute of Geophysics,
CSAV, in cooperation with the Institute of Geomagnetism, the Ionosphere and
Radio Wave Propagation, USSR Academy of Sciences. The Magion satellite was
developPd and manufactured by TESLA-WST and the laboratories of the Institute
of Geophysics, CSAV, in Prague. To carry out the experiment with the Magion
satel.lite it was necessary to provide transmitting and receiving equipment for
' the ground control stations, including the antennas, as well as monitoring in-
- str~Fntation. Some 17 instruments were produced, most of them in several
models. Thus it is clear that the project was rather exteasive and required
considerable effort. Accordingly, the placement in orbit of the Czechoslovak
sateilite, and its prolonged activity, may be considered a considerable success.
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Aims of the Experiment
The scientific aim of the experiment is to study the temporal and spatial struc-
ture of low-frequency electromagnetic fields around the earth. The investigatidn
is carried out through simultaneous measurement of selected parameters on two
spacecraft whose relative position is changing. One of the craf t is the Inter-
kosmos 18 satellite and the other the Magion satellite. These satellites move
in a nearly polar, slightly elliptical orbit whose plane is inclined at an
angle of 82.96� to the equator. The a.pogee of the orbit is 772 km and the peri-
gee 404 km; the orbital time is 96.36 minutes. The Magion satellite separated
f rom the Interkosmos 18 in the area of radio visibility from the Panslaa Ves sta-
tion in Ceska Lipa, from which the experiment is controlled. The Magion satel-
lite makes 15 orbits a day. It is given co~ands during each pass: on the
average 6 to 10, but sometimes as many as 20. The number of comm~nds depends
on the length of time it is above the horizon. Some 64 quantities are measured;
some of these are scientific informa*_ion, while the others are information on
the conditions of the satellite. The lifetime of a few weeks that was initially
assumed~for the satellzte has been exceeded by several times. T1~+is it has be-
come possible to ob~ain much valuable data. Of interest, for example, is the
information acquired on the aging of the satellite's surface as a result of a
gradual rise in temperature, which can be generalized for zonsealed ob~ects.
These and other findin~s can be called the technical objectives of the experi-
ments; they will be used for subsequent projects.
The Design Concept of the Magion Satellite
Equipment for space research has certain specific characteristics. Some of
these are similar to those of equipment for ground-based radio communications
and aircraft onboard equipment, nar?ely small size and weight, minimum energy
consumption, high mechanical and climatic durability, and, not least, high
reliability. Among the specific characteristics of satellite equipment, we
include the requirements for operation in a nonsealed environment and in a
rarefied atmosphere that is close to a vacuum, and particularly such design
requirements as location of the antennas and their release into working posi-
tion and precise balancing. The totality of requirements exceed current prac-
tice in other areas of electronics. Because satellites generally are destroyed
in the earth's atmosphere, it is difficult to determine confidently the causes
of failure. As a result, in developing space objects, considerable time must
be spent in tests and measurements whose results will affect the concept and
design of the equipment. This was the case for the Magion satellite.
The satellite is a rectangular prism with sensors and antennas protruding from
it (Fig. 1). When the satellite separated from the parent vehicle, the antennas
were extended and brought into working position on a command from ~he earth.
The Magion's antennas are linear, unipolar and dipolar types. They are installed
at a certain inclination to the main axes of the satellite and are relatively
small compared to the wavelengths on which they operate. The antennas for 137
and 149 MHz protrude from the bottom of the satellite and are inclined at 15� to
the base plane. The antenna for the 400 MHz band is in the middle of the top of
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.
r
. 4. ~~aG~~~~
Figure 1. The Magion Satellite .
� Key:
A - l. Ejection base
2. Magnetic loop
3. Permanent magnets
Ig ~ 4. Solar batteries
~ A. Magnetic probe
n~,_____ ~ B. Support with amplifier for probe
i o: rt _ J yT L__ rf _~P ~ gi C. Receivers and decoders
I I D, E. Parts of scientific section
I 0,35 ~
i c- ~ ' F. Transmitters and temperature
i I je ~ measurement circuits
i ; ~ G. Constant-te~nperature chamber
i ~
i ~ with oscillator
L_____ H, J. Preamplifiers for scientific
~ sensors
r------'" j K, L. Batteries
~ r"'-~"- "-'1-~' '"-""-'1 ~ M. Connector cables
~Z~`- i.-,~ ~ o ~ ~ 0, P. Balancing weights
I ~
I I I
~ I ~ I I
I H ? G J�-~- rqi
' ~ ~ ~ I
~ - ~ ~ ~ I
i i ~ I
(3L ~ '
I
I � � L F ~
~ t ~ t
iti. I L-�-�-- - I
�
~ y
~oo Fi ure 2. La out of the Satellite
h--
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the satellite body at the feet of the support which holds the ferrite aiil-enna.
It has a length of approximately 0.5a and is inclined at 45� to the satellite's
vcis. The antennas' input impedances are adjusted to 50 ohms by means of a
parallel reactive component attached at a convenient place on the power supply.
Figure 2 shows the layout of the satellite. In designing the Magion it was
necessary to allow for many requirements, a few of which are shown in Table l.
Table l. Some Requirements for the Magion Satellite
Dimensions 300 x 300 x 300 mm
Weight 15 kg maximum
Force of ejection of satellite
from parent vehicle 7.845 N+ 10 percent
Temperature range +10� to +30�C
Highest permissible temperature
of solar cells +130�C
- tdidth of ejection passage on parent
vehicle 320 mm
Deviation of center of gravity from
geometric axis of satellite normal
to launching base 0.35 mm maximum
Linear overload along longitudinal
axis of parent vehicle 10 G
Linear overload along other normal
axes 1.5 G
Vibration along all axes
5-10 Hz 0.2-1G
10-30 Hz 1-4G
30-80 Hz 4-6G
80-1500 Hz 6-lOG
About half of the interior is taken up by the satellite's scientific equipment.
~ The remainder holds the telemetric and monitoring system. The scientific equip-
ment includes receivers for measuring the magnetic and electrical components of
electromagnetic fields in a band from 0.1 to 16 kHz, a device for measuring the
electric field in a band from 0.01 to 80 Hz, a unit for measuring the resonance
properties of plasma surrounding the satellite at frequencies up to 8 kHz, and
equipment for recording ~the flux of charged particles with erYergies above 30,000
eV in the earth's longitudinal and transverse magnetic fields.
Tt~e te].emetry and monitoring system lias two transmitters. One operates at
400.57 MHz with an output of 1.5 W, and the other at 137.15 MHz with an outgut
of 150 mW. A memory unit can be used to record measurement and monitoring data
when out of range of the ground-based telemetry stations. The command receivers,
decoding equipment ancl p.rogram switching unit make it possible to control indi-
vidual parts of the equipment in various ~odes when the satellite is p assing
through the radio reception region.
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The batteries are charged by solar cells which cover almost the entire surface
of the satellite. The energy produced by these cells is relatively small, not
exceeding 3 W. Part of the energy (about 0.7 W) is consumed by the constantly-
on units, while the rest is used to charge 2 onboard batteries, each consistit~g
of 10 NiCd cells and having a capacity of 4 ampere-hours. The scientific appa-
ratus draws about 1.5 W; the most ~ower is drawn by the 400 MHz-band transmitter, .
which accordingly only operates at certain intervals. The individual components
of the onboard apparatus are on standakdized boards with planar contacts and are
connected by knife-type plug-in connections. Four permanent magnet bars 12 mm
~ in diameter and a magnetic loop of permalloy tape under the solar cells stabilize
the satellite in the earth's magnetic field. ~
The speed of ejection of the Magion from the Interkosmos 18 vehicle was chosen
as 0.5 m/sec. The ejection is effected by four microswitches whose combined
force of release is equivalent to the desired ejection force. The use of a
lever mechanism made it possible to decrease the force of release t about one-
tenth of the original v~lue, and increased travel distance was used, providing
reliable action of the ejection equipment. Because the satellite was ejected
through a narrow opening in the parent vehicle, the center of gravity could not
deviate more than 0.35 mm from its geometric axis. To measure the deviation of
the center of gravity, a balancing device based on the principle of slow damped
_ vibrations was produced. Precise balancing of the satellite led to positive re-
sults in mechanical tests, in which no undesirable resonances were fusnd.
Particuiar attention had to be devoted to the temperature regime and energy
balance of the satellite. This required many tests, for which it was necessary
to d~asi.gn and produce various accessories, including a solar illumination simula-
tor. In particular, it was necessary to find out what materials and surface
pr~~tection should be used for the Magion. The result of the work is a framework
consisting of aluminum alloy sheets of different thicknesses. The parts are con-
nected by rivets and screws. The frame is anodized black, and the outer surfaces
which are exposed to solar radiation are faced with gold-plated brass sheet whose
surface was subjected to polishing between applications. A shiny layer of alumi-
num is vacuum-applied to the inner surface of the cap of the constant temperature
chamber, forming a thermal mirror. For the most part, materials with bonded
cher~~cal substances were used as insulators. Tests and the experiment with the
~:agion sat~llite confirmed the correctness of the concept that was chosen.
Findings Obtained
The results of the scientific tests and measurements obtained during the experi-
ment are dealt with in separate publications. In view of the considerably great-
er lifetime of the satellite than was initially assumed, the amount of information
obtained has also increased greatly. Accordingly, we may state that from the
, scientific point of view the Magion expariment exceeded the expected goals. The
technical yield of the experiment may be similarly evaluated. The research and
development of a satellite with sophisticated technical characteristics, made
with domestically produced compunents, and its prolonged activity in space, have
unquestionably demonstrated that correctly designed, carefully manufactured and
thoroughly tested nonsealed objects can operate well and reliably in orbit and
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furnish valuable information. This experience can be used in planning and
implementing new experiments with separable objects, but also in accomplishing
other tasks in other areas of electronics.
Conclusion
The Magion satellite has lived up to expectations. The experiment has made it
~ possible to obtain valuable experience and has created good conditions ror more
extensive projects. One of them may be the simultaneous launching of two or
more such satellites. The instruments developed and fabricated for the experi-
ment gave a good account of themselves and operated reliably. The results ~.on-
firm that the electronics industry is capable of producing instruments with
excellent capabilities and of using its findings effectively in the performance
of other tasks. This is a specific and direct benefit of informal cooperation
in the Interkosmos program.
COPYRIGHT: SNTL, Nakladatelstvi Technicke Literatury, Prague, 7981
Transmitting Equipment Described
Prague SLABOPROUDY OBZOR in Czech No 4, Apr 81 pp 162-166
[Article by Eng Jozef Plzak, CSc, TESLA-WST: "Trar.smitting Equipment for the
- Magion Satellite"; bibliography not reproduced]
[Text] This article describes the co~unications system of
the Magion project and the conception and design of the com-
ma.nd link transmitters and of the onboard 137-MHz ar,.d 400-MHz
transmitters.
l. Introduction
The Magion satellite is a small satellite, but the range of its basic functions
is comparable to that of large scientific satellites. Accordingly, the communi-
cations system must perform all the basic functions of large satellite communi-
cations systems. Thus, one-way telemetric and identification communication is
insufficient: the control center must have the capability of controlling the
satellite's operating mode by means of a command link, supported by a distance-
measuring system and having the possibility of checking from the ground the
transmission parameters of the command and telemetric communications.
Tl~e transmitters of the Magion project were developed by our institute. Tre
200-watt command transmitter operates in the 150 MHz band, the onboard 0.3-watt
transmitter in the 137 MHz band and the onboard 2-watt transmitter in the 400 MHz
band.
2. The Command Link
The command link is intended to transmit commands from the ground station to the
satellite. It consists of the command transmitter, the transmitting antenna,
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the receiving antenna and the command receiver. The command transmitter is
connected with the control console and the command receiver is connected to
_ the unit controlling the operating mode of the satellite. The cou~and-link
is characterized by the following b asic figures:
working frequency 150 MHz
modulation narrow band FM ,
modulation swing fm~ 5 kHz
modulation frequency 100-3,500 Hz~
gain of directional transmitting antenna G1 = 15 dB
maximum distance k= 3,500 km
receiver noise figure n= SkTp
gain of satellite receiving antenna G2 = 1 dB
losses from nonidentical antenna ,
polarization Lpol ~ - 3 dB
ma:cinum gain difference as a result
of directionality of satellite antenna ~L ~-15 dB
losses in cables and connections I.X x 1 dB
= Reference 1 gives the foll~wing figures:
noise figure of receiving system n = 11.1
noise power at receiving antenna NS =-151.6 dB~
required power at receiving antenna Np =-141.6 dBr,,l (for a 10 dB
noise interval at limiter)
attenuation in free space Lp 147 dB
required transmitter power N~ ~ 9.6 W
On closer inspection, it is evident that it would be very difficult to improve
the parameters of the onboard part of the communications system (i.e., the re-
_ ceiving antenna and command receiver). Similarly, the transmitter antenna gain
is an optimal compromise between directionality, dimensions and flexibility.
Accordingly, the only realistic remaining potential lies in the command trans-
- mitter power. In practice, the power of command transmitters is many times
higher than the required value. It is chosen as high as 15 kW, which provides
a reserve for reception under extreme conditions such as powerful interference
signals, decreased receiver parameters resulting from extreme temperatures, a
- decreased feed voltage and the like.
3. The Command Transmitter
The command transmitter is used to transmit coded commands from the control cen-
ter to the satellite, to measure the distance to the satellite and to measure
- the entire communications path. The command link must make possible control of
satellite operation by means of the requisite number of unambiguous commands
during the entire period of radio visibility of the satellite. The reserve
power for unfavorable receiving conditions and extreme situations should be
sufficient to avoid production of spurious radio commands by an undesirable
signal from another command, or by a chance modulation structure. Particularly
great emphasis is laid on the reliability of the command link.
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Careful consideration of the limiting factors on board the satellite (dimensions,
power consumption, extreme working conditions) and availability of components led
to adoption of an economical coding system. The command combination consists of
' a serial combination of thr~:e tones chosen from four differez~t possibilities.
Immunity to random interference signals is assured by a fixed address which pre-
cedes the command combination and a system of tone detectors which are inzer-
ference-resistant. The entire command combination is transmitted during an
- interval of less than a second. There are 24 command combinations available.
This simple commanc: system makes it possible to design simnle onboard evaluating
circuits with satisfactory properties. More detailed informat~on on the coding
and evaluation of commands is given in reference 1.
In addition to discrete commands, 400 and 500 Hz signals can be emitt~d for dis-
tance measurement. Finally, both transmission 1i~zks (command and telemetric)
can be checked by means of a modulating signal fr~nn an external source or a
1-kHz internal signal. The distance to the satellite can be measured by phase
comparison of the emitted and returning 400 and 5U0 Hz signals, which are
switched at intervals of 1/20 second. The entire communications path can be
checked by a permanently-on 1 kHz modulating signal which is sent back by the
telemetry transmitter, or by any other external modulation.
The cotnmand transmitter consists of two units. The control section is a compo-
nent of the control station, which is located about 100 meters away fram the
antenna system. The output section of the transmitter is built into the antenna
system and forms a unit with the transmitting antenna. Because of the extra-
ordinary requirement for command-link reliability, the output stage consists of
four parallel output modules.
Figure 1 is a block diagram of.~i-ie control section. In addition to the signal-
emitting circuit, the modulation circuit and the control components, it contains
radio-frequency exciter circuits. Figure 2 is a photograph of the unit.
a b c d Key:
merem tes~lova a. Command COdeS
� kody povelu . vrddlenosh 1 kHz ~~ryfi disple/ iosu
b. Distance measurement
' ' ` c. Extr:rnal modulation amplifier
d. Tin.e display
~ * e. Limiter
a~to~~ 3 kHr ~ ~ D~ ' 3~D 5 V"~t f. Mod~ilation monitor/decoder
saR g. Am plifier out put control
f - h. Tempe~rature monitor,
mon~rar mo- w~6dan;.y- ~ interference annunciator
Cumce ~~1 ~ nvlowce
deROder i. Operation indieator
_ _ _ . -o
konfrola feplo' M ~ y
fr, hlasen~ ' I
anruch
~ o
�nd~Rare
orovotu ' t~
Figure l. Control Section of the Command Transmitter
11
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' , ii . . ~
t: _.~-~-~+r~"'^"~~+
I{ 1
f,~ ~ , ~
~
i% 'r, . A
~
~ ..,~^c.~,=
~ r~
_ ~
i l
~st � a � "
,~''.'~.yr, . _ . .
r,;~`"r:i�.
_ �1�
9
;�t~ ~
Figure 2. The Command Transmitter. Control section on left, output section at
right. ~
The RF exciter signal is fed from the frequency-modulated crystal oscillator
through the multiplier to the amplifier stage. The RF exciter feeds a power
of 10 W at half the working frequency into the cable which connects the con-
trol section with the output section. The exciter output is protected from
short circuits and disconnection. The exciter uses conventional semiconductor
circuitry. Its specifications are given in Table 1. The control panel, assem-
bled from the Mozaika kit, includes all of the transmitter's control and moni-
toring components, command buttons and a digital clock. It indicates the cur-
rent output power of the exciter and the output and reflected power of the power
amplif.ier. The temperature of the output-section cooling devices and of the
transformer windings in the power supplies is monitored. If an excessive tem-
perature occurs in any location, an audible signal is given. The correctness
of the emitted signal is evaluated by comparing the detected and decoded RF sig-
nal with the resulting code combination and is indicated visually.
The output section is installed in a nonairconditioned vehicle to whose roof the
transmitting antenna is attached. Thus it is exposed to temperatures from -25�
to +55�C. In formulating the requirements it was assumed that a reserve power
of 13 dB would suffice in all extreme cases, and accordingly it was determined
that the output power of the command transmitter would be 200 W. The KT 922 V
output transistors which were available can put out only 40 W, or 70 W in a
balanced connection. The extreme requirements for command-link reliability
could be met only by redundancy of the circuits with the lowest reliability.
Many years' experience with RF power amplifiers indicates that it is they, and
= narticularly their power transistors, which are the most critical part of the
transmitter. Accordingly we sought a design which would make it possible to
combine the outputs of the main amplifiers in such a way as to achieve the
12
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FOR OFFtCIAI. USE ONI,ti'
D , ~
4 :1 KT 922 V '
Dy OZ - SZ D iC H~ H? f:2 ~
9;! Kr922B 2~1
~ ~ ~ ~ : <
KT 922 V
P(W 1 1 10 60
Z(Q) ~ 3~5 2 50
Figure 3. Wiring of Main Power Module
operation is different (the power divider must be scaled to a considerably
higher power). It is worth noting that the power coupler increa~es resistance
to breaks and shorts (it decreases CSV~ to CSV 5).
To the output of the paralleler is connected a 7-component Chebyshev low-pass
filter, followed by a stripline reflectometer. The reflectometer outputs are
used for indication and the reflected power output for protection against mis-
matching. The divider is connected to the multiplier and amplifier cascade,
which uses conventional circuitry, whose power amplification is controlled by
the reflectometer (protection against mismatch). Details of this amplifier de-
sign are given in reference 2. Figure 4 shows a block diagram and Figure 5 a
photograph of the unit. The importance of this mastering of wideband microwave
power amplifier technology and of power coupling on the order of hundreds of
watts goes beyond the confines of the Magion project. Altered versions are
usable for a number of other applications in the frequency range from 150 to
- 185 MHz in both mobile networks, public radiotelephone networks an3 other ground-
based radio communications. But in essence the route to transistorization of
medium-power transmitters has been opened, and the result in prolonged, demand-
ing operation has been positive.
z,
" " " ' zoo w
~ !50 HHr
50 4
D a
~ 2 D -i~ I~ H1 refl -
O.Sw ~ ~lw j~
?5 HNt ISOHHt yl I ~ I f' ~ ~
50 4 .
, . LL._1J---- _I I
I
~ ~S _ , ,
s!
b Pm. Pnl~nC
Figure 4. Power Section of Command Transmitter
Key: H1. Hybrid divider a. Reflectometer
H2. Hybrid coupler b. Reflected power
Z1-Z4. Main power modules c. Transmitted power
_ 13
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Table 1. Transmitter Specifications
Ground-based transmitter Onboard transmitter
Specification Exciter Power amplifier 137 MHz 400 Mhz
Working frequency (MHz) 74-75 148-150 137.150 400.01
Frequency stability 2 x 10-5 2 x 10-5 2 x 10-5 5 x 10-8
Short-term frequency not spec. not spec. not spec. 3 x 10-11
stability (1 second)
Type of modulation FP'I FM ~ M
Modulation shift 2.5 kHz 5 kHz 10 kHz 80�
Maximum modulating 3.4 3.4 50 kHz 40 kHz
frequency (kHz)
Modulation distortion 2 2 l 2
(percent)
Suppression of spurious 60 60 50 60
emissions (dB)
Temperature stability(�C) +5 to ~45 -25 to +55 -50 to +60 -20 to +50
the required power and to assure that the breakdown of one or more amplifiers
would not affect the operati~n of the others, and finally so that the amplifier
would be operational for a long period even if certain of the power transistors

~ broke down. A solution was found in conphasal paralleling, achieved by means of
line ("impedance") transformers.
This paralleling arrangement can be made in a rather wide-band design which util-
izes the superior isolating properties of the individual amplifier branches.
But their output powers can be paralleled only in the case of good conphasality
(~~p ~ 5�) and long-term phase stability. But these preconditions can be achieved
only with broadband amplifiers. The ultimate design of the basic amplifier module
is shown in Figure 3. The amplifier module contains two bypass sections utilizing
]..ine ("impedance") transformers, whose properties and manufacture are described,
for example, in ref~rence 3. The amplifier is a two-stage design: the first
transistor (exciter) is matched to an input impedance of 50 ohms and feeds a
hybrid divider which is connected to the two-element final stage. The impedance
of the divider is matched to the base of the final-stage transistors by 4:1 line
transformers, while 1:4 line transformers match the collectors to the hybrid
coupler, whose output impedance is again 50 ohms. The amplifier is absolutely
stable in the entire range of working temperatures and the phas e stability is
excellent. At the amplifier output is a circuit which allows the amplifier
phase to be adjusted to the desired value.
These four modules are paralleled by means of a conphasal rower coupler at the
output and a conphasal power divider at the input. The divider and coupler are
similarly connected, and their functions are reciprocal, but their actual
ll~
FOR QFFICIAL USE ONLY
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o,zs w
f37 nHr
� -[]--~"-~--0 , 3 ~ D ~
_ moa.
~
' ~ ~
4 r
ek
Figure 5. Group Wirin~ of 137 MHz Transmitter
4. The Onboard Transmitters
The transmitters on board the satellite are used to identify the satellite and
to transm~t telemetric data of a service character (information on the condi-
tion, operating regime and operating conditions of the satellite's onboard
equipment) and scientific data and make it possible to measure certain parameters
of the satell.ite's orbit. The frequencies in the 137 and 400 MHz bands are re-
served for this type of communications. The 137 MHz band is a standard band
and all the countries cooperating in the Interkosmos program are equipped for
reception in it. The 137 MHz band is, however, relatively crowded, there is
interference with other services, and it is designated for only narrow-band
transmissions. Nor is it suitable for determining precise orbital parameters,
for the ionosphere still affects the phase of the reflected signal. The 400 Mfiz
band can be used both for precise orbit determinations and for broadband trans-
mission, however, requires a higher transmitter power.
In the initial communications design it was necessary to allow also for power
levels on the satellite: the average energy drawn from the solar batteries was
not to exceed 3 W, including 0.7 W consumed by constantly-on instrumentation.
Accordingly it was decided to use the specific properties of both frequency
bands and to carry out communications by means of a pair of transmitters.
5. The 137 MHz Transmitter
The transmitter in this band was given the role of the basic, constantly oper-
ating transmitter, functioning in the "beacon" mode from the moment of separa-
tion. In this mode it transmits a keyed carrier with a repetition frequency
proportional to the voltage in the onboard electrical system and with a rest-
to-signal ratio proportional to the temperature of the satellite. Operation
in the "beacon" mode makes it possible to identify thesatellite, track its orbit
and perform basic monitoring of the condition of the onboard batteries and the
temperature of the satellite.
The satellite changes to the telemetry-data-transmission mode only on command
from the control station. This involves so-called "slow telemetry," in which
a series of service data (up to 200 monitored satellite parameters) and certain
slowly-changing output values of the scientific apparatus can be transmitted in
time-division form via the subcarrier. In telemetric monitoring it is possible
to duplicate the transmission of certain data intended to be transmitted on the
other transmitter. Thus the 137 MHz transmitter is the basic piece of satellite
15
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instrumentation. If it were to carry out all of the required functions in a widc
temperature range (for which only estimated absolute values were available) and
in a wide voltage interval with high reliability and low power consumption, it
would be necessary to choose a simple, well-tested and nonproblematical design.
There was no experience at all with nonsealed, nonclimate-controlled satellites.
Accordingly, allowance was made for operating temperatures from -4(i� to +60�C
in a temperature regime which guaranteed all parameters between -30� and +50�C,
- assuming battery voltage variation between 8 and 13.5 V.
The transmitter conception is evident from Figure 6. The paraiaeters are given
in Table l. In particular, it is necessary to raise the frequency stability,
considering that it involves a modulated oscillator and an extreme operating
regime. The oscillator circuitry is given in reference 4. The transmitter not
only achieved the required parameters, but also attained operability in a wider
range than was required, as shown in Figures 7 and 8.
3 I NI
0, J ~
al
6 N
02 5
4 ~
' I 2~ ~e/~
~
,
I AU 40 -20 0 +20 * 40 :~['C ~
Figure 6. Output Power and Frequency Stability of 137 MHz Transmitter as a
Function of Temperature
3., I
. a p
40
rr ~
0, J 70 ~
_ J, ~ 20
~
i
0,1 f0
--.r--.~.~ ~ r---r~--r-
5 6 i 8 9 10 11 f2 U[V) 1~
Figure 7. Output Power and Efficiency of 137 MHz Transmitter as a Function of
Onboard Power Supply Voltage
16
FOR OFF[CIAL USE ONLY
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FOR ONFIC'IA1. USN: C)Nl.ti'
.
~ f~
_ ~ p- - p -r ~
~ J ~
� nHZ lo nHr
_ ~
D
Ht -9F .~W~.
O
I I
;2 ~ Q
~w
_ ~ ~ ~