Doploc observations of reflection cross sections of satellites 2

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MEMORANDUM REPORT NO. 1330
MARCH 1961
DOPLOC OBSERVATIONS OF
REFLECTION CROSS SECTIONS OF SATELLITES
y 3 G c
NOX
ARPA Satellite Fence Series
Harold T. Lootens
Report No. 22 in the Series
A S T • A
if
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TAPDR Ä
Department of the Army Project No. 503-06-011
Ordnance Management Structure Code No. 5210.11.143
BALLISTIC RESEARCH LABORATORIES
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PROVING GROUND, MARYLAND

MEMORANDUM REPORT NO. 1330
MARCH 1961
DOPLOC OBSERVATIONS OF REFLECTION CROSS
SECTIONS OF SATELLITES
ARPA Satellite Fence Series
Report No. 22 in the Series
Harold T. Lootens
Ballistic Measurements Laboratory
Department of the Army Project No. 503-06-011
Ordnance Management Structure Code No. 5210.ll.llf3
ABERDEEN PROVING GROUND, MARYLAND

MEMORANDUM REPORT NO. IJJO
HTLootend/bt
Aberdeen Proving Ground, Maryland
March 1961
DOPLOC OBSERVATIONS OF REFLECTION CROSS
SECTIONS OF SATELLITES
ABSTRACT
This report presents reflection cross sections observed for eight
satellites during the period 1 January 1959 to 1 July i960, using the
DOPLOC "dark satellite" detection system developed by the Ballistic
Research Laboratories. Several related areas are discussed; i.e.,
satellite "signature", spin and tumble, scintillation and ionized
trails. A brief description of the DOPLOC receiving system and
antenna configuration is included. The method used for calculation
of cross sections is given in Appendix I.

TABI£ OF CONTENTS
Page
I. INTRODUCTION
II. DOPIJX SYSl-EJ«! DESCRIPTION
A. Equipment
3. Antenna Dlraenoions ond Orientation 11
III. FIELD DATA
Ik
A. Sutolllte Records ..
B. Unidentified Flying Objects jj.
C. Doppier Recordlng 22
D. Signal Strength 25
E. Multiple Antenna Records oj,
F. Meteor's «.
0. Satellite Trails 2O5K
H. Predictions oc 25
IV. REFLECTION CROSS SECTIONS AND POWER RATIOS 2?
V. CROSS SECTION SIGNATURE OBSERVATIONS 55
VI. CROSS SECTION MODULATION DUE TO AITITUDE CHANGE 59
VII. SCINTILLATION k2
VIII. REFERENCES ^ .,-
Appendix I - Calculation of Power Ratio and Croas Section 1+7
Appendix II - Bibliography of Reports in the BRL-DOPLOC 53
Series

LIST OF FIGURES
i. Baale Interim DOPLOC System
A Block Dlu^rain of R. F. Section IJI DOHJOS Station Posalve
Tracking at XüÖ m/a
!>. Block Diagram of DOPIXX) Tijnlng Syataa
•'.. Block Dlu^ru;:! of D^ppJer Diitu Recording Syateti for a
SLutJle Chiinj»«!
5. Block Diagram of AuUmillc !/>ck-On Syßtea
ö. ARPA-BRL DOPLOC Satellite Fence
7. Typical DOPIOC Data Output
8. Typical Slndle Pa;,;; Doppler Orbit Solution
9. Hlj'li Gain Antenna« at ARPA-BRL DOPLOC Tranamltter Site
Located at Fort Sill, Oklahoma
1> . Initial Antenna Orientation
11. Antenna Orientation Foliowlnti Deacclvatlon of White Sands
Station
12. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. C8M
13. ARPA-BHL DOPLOC Doppler Record of 58 D-lta, Rev. TO1»?
1'». ARPA-BRL DOPIXX; Doppler Record of 58 Delta, Rev. 7558
15- ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 8^86
16. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 86l»5
17. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 8085
18. ARPA-BRL DOPLOC Doppler Record of cß Delta, Rev. 8719
19. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 872*
25- ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9255
21». ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9286
25. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9^66
26. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9'i72

29. ARPA-BRL DOPLOC Dipplor Record of 58 Delta, Rev. 9612
?0. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9716
51». ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 98'»2
35- ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 98118
39. ARPA-3RL DOPLOC Doppler Record of 58 Delta, Rev. 99'»3
li0. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9959
'«1. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9975
^2. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 9991
'»3. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 10001
•'i1». ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 10007
!«5. ARPA-BRL DOPLOC Doppler Record of 58 Delta, Rev. 10023
US. ARPA-BRL DOPLOC Doppler Record of 59 Epsilon, Rev. 53
^7. ARPA-BRL DOPLOC Doppler Record of 59 Epsilon, Rev. 60
•»8. ARPA-3RL DOPLOC Doppler Record of 59 Epsilon, Rev. 121
'♦9. ARPA-BRL DOPLOC Doppler Record of 59 Epsilon, Rev. 31'i
50. ARPA-3RL DOPLOC Doppler Record of 59 Epsilon, Rev. klk
51. ARPA-BRL DOPLOC Doppler Record of 59 Epsilon, Rev. U38
52. ARPA-BRL DOPLOC Doppler Record of 59 Epsilon, Rev. 532
55. ARPA-BRL DOPLOC Doppler Record of 59 Zeta, Rev. Ik
51*. ARPA-BRL DOPLOC Doppler Record of 59 Zeta, Rev. 150
55- ARPA-BRL DOPLOC Doppler Record of 59 Zeta, Rev. 2itl
56. ARPA-BRL DOPLOC Doppler Record of 59 Zeta, Rev. 556
60. ARPA-BRL DOPLOC Doppler Record of 59 Kappa, Rev. 183
61. ARPA-BRL DOPLOC Doppler Record of 59 Lambda, Rev. 96

62. ARPA-im DOPLOC Doppler Record of 59 Larabda, Rev. l'iß
65. ARPA-BRL DOPIJCX: Doppler Record of 59 Iûabdu, Rev. 278
6'!. ARPA-BRL !>0PLCC Doppler Record of 59 La-abda, Rov. 685
65. ARPA>BRL ÜOPLOC Doppler Record of 59 Iârabdu, Rev. 1205
66. ARPA-BRL DOPIJCC Doppler Record of 59 Lüuabda, Rev. 1516
67. ARPA-URL DOPLOC Doppler Record of 6'» Ga-aisa 1, Rev. 5l8
CQ. ARPA-BRL DDPLCC Doppler Record of 60 Gassaa 1, Rev. '»öj
69. AIU'A-BHL DOPIÔC Doppler Record of 60 Ga'«na 1, Rev. '»18
70. AJ^PA-HiL DOPLOC Doppler Record of 60 Gar.-rA 1, Rev. 836
71. ARPA-3RL DOPI-OC' Doppler Record of 6ü Gatana 1, Rev. 960
72. ARPA-BRL DOPLOC Doppler Record of 6<; Gamma 2, Rev. 10l»2
75. ARPA-ffilL DOP!>0C Doppler Record of 60 Delta, Rev. JO
7".. ARPA-3RL DOPLa* Doppler Hccord of 60 Delia, Rev. 6l
75- ARPA-HRL DOPIä: Doppler Record of Co Delta, Rev. 117
76. ARPA-BRL DOPLOC Doppler Record of 60 Delta, Rev. 12^»
77. ARPA-BRL DOPIJCC Doppler Record of 6c Delta, Rev. ll»0
79. ARPA-HRL DOPLOC Doppier Record of 6C Delta, Rev. 165
8G. ARPA-3RL DOPLOC Doppler Record of 60 Delta, Rev. 172
81. ARPA-BRL DOPLOC Doppler Record of 60 Epsilon 1, Rev. p5
82. ARPA-BRL DOPLX Doppler Record of 6c Epullon 1, Rev. 99
85. ARPA-3RL DOPLOC Doppler Record of 60 Epsilon 1, Rev. 150
8^. ARPA-3RL DOPLOC Doppler Record of 6c Epsilon 1, Rev. 165
85. ARPA-3RL DOPLOC Doppler Record of 60 Epsilon 1, Rev. 386
86. ARPA-BRL DOPLOC Doppler Record of 60 Epsilon 1, Rev. 522
87. ARPA-.m DOPLOC Doppler Record of 60 Epsilon 2, Rev. 106
89. ARPA-BRL DOPLOC Doppler Record of 6G Epsilon 2, Rev. ll*7
91. ARPA-BRL DOPLOC Doppler Record of 60 Epsilon 2, Rev. I9I+
92. ARPA-BRL DOPLX" Doppler Record of 60 Epsilon 2, Rev. 303
9^. ARPA-BRL DOPLOC Doppler Record of 60 Epsilon 2, Rev, 356
8

95« ARPA-BRL DOPIOC Doppler Record of 6o Epsilon 2, Rev. 61?
96. ARPA-BRL DOPLCX; Doppler Record of 60 Epoilon 3, Rev. 28o
97. AIU'A-BRL DOPIiX; Doppler Record of 60 Epsilon h, Rev. 280
S>3. ARPA-3RL DOPLOC Doppler Record of 60 Epsilon 5, Rev. 569
99. ARPA-BRL DOPLOC Doppler Record of 6ü Epsilon 6, Rev. 265
100. ARPA-BRL DOPLOC Doppler Record of 60 Epsilon 6, Rev. JOl
101. ARPA-BRL DOPLOC Doppler Record of Unidentified Object
102. AiPA-3RL DOPLOC Doppler Record of Unidentified Object
105. ARPA-3RL DOPLOC Doppler Record uf unidentified Object
lOit. ARPA-3RL DOPLOC Doppler Record of Unidentified Object
105. AHPA-3RL DOPLOC Doppler Record of Unidentified Object
lOo. ARPA-3RL DOPLOC Doppler Record of Unidentified Object
1C9. ARPA-3RL DOPLOC Doppler Record of Unidentified Object
111. ARPA-3RL DOPLOC Doppler Record of Unidentified Object
115. ARPA-3RL DOPLOC Doppler Record of Unidentified Object
ll1». ARPA-BRL DOPLOC Doppler Record of Unidentified Object
115. DOPLOC Power Ration, Center Antenna
Ho. DOPLOC Power Ratios, North Antenna
117. DOPLOC Power Ratios, South Antenna
118. DOPLOC Power Ratios, Center, Nortn and South Antennas
119. Doppler Record of Active Track of 58 Delta, Rev. 9958
120. Doppler Record of Active Track of 60 Epsilon 1, Rev. 26
121. Doppler Record of Active Track of 59 Epsilon, Rev. 7
122. Doppler Record of Active Track of 58 Delta, Rev. 10007
125. DOPLOC Frequency and Rate of Change of Frequency as a
Function of Position in the YZ-Plane
12h. Center Antenna Geometry
125. Altitude and Ground Range Geometry in South Antenna
126. Satellite Inclination with Respect to Base Line

127. Ground Range In North and South Antcnnaa
128. North and South Antenna Geoesetry
129. Power Factor vo Angular Pooltlon for an 8 x 76 Degree Antenna
10

I. ItfTRODUCTION
During the period 1 January 1959 to 1 July i960, the Balllßtlc
Research Laboratories, under funding from the Advanced Research Projects
Agency (ARPA Order 8-58), operated a three-station, reflection Doppler
satellite tracking systoin, extending across the south-central United
States frcra Tennessee to Hew Mexico. This system, known as DOPLOC
(DOpplor Phase IXCk), provided a moons of detecting and tracking radlo-sllent,
or "dark" aatellltes.
A transmitting station was located at Fort Sill, Oklahoma and
receiving statlono were located at White Sands Missile Range, Hew Mexico
end nt Forrest City, Arkansas. The stations were Initially manned on a
twenty-four hour, seven-day-per-week basis, as part of the nation-wide
satellite surveillance not. Following permission from ARPA to discontinue
routine twenty-four hour operation, the White Sands station was deactivated
and a basic eight-hour work day was adopted at the Fort Sill and Forrest
City stations on or about 1 October 1959. The actual hours of operation
were chosen to adapt the work schedule to the times of most frequent
satellite passes.
The flexible schedule by which the field stations operated has
provided considerable data from known satellites, Unidentified Flying
Objects (UFO*s) and meteors. Many satellites and UFO's have been
successfully detected and tracked by the DOPLOC technique and their time
of crossing, altitude, east-vest positiun arid effective reflection cross
section determined from single pass data from a single receiving station.
Crossing time and position data was forwarded to Space Track Control
Center for inclusion in their orbital prediction program.
11

II. DOPLOC SYSTEM DESCRIFTIOM
A. Equipment
The DOPLOC ayatm conelated of Q 50-kw contlnuoua wave, ICÖ Mc/ß
transmitter locoted at Fort Sill, Oklahoma, which fed one of three
narrow-beoa, high-gain antennas. These high-gain antennas emitted
narrow, fan-shaped beams, one directed 20 degrees above the northern
horizon, one directed vertically and one directed 20 degrees above the
southern horizon (see Figure 1).
The signal reflected from a satellite passing through the trans-mitter
beam was received at one or both of the receiving stations. Each
receiving station had three high-gain antennas oriented to "see" the
space volume illuminated by the transmitter. The reflected Doppler
signal was fed through a receiver to a bani: of fixed audio frequency
filters known as the Automatic Lock-On (ALO) and, subsequently, to a
narrow band, phase-locked tracking filter. The appearance of a Doppler
signal in one of the fixed filters activated a control circuit which
pulled the tracking filter frequency over to the signal frequency and
caused a phase lock between the two. The tracklüg filter then tracked
the Doppler signal frequency continuously as the satellite passed through
the antenna beam. Block diagrams of the DOPLOC receiving system and ALO
are shown In Figures 2, 3, I* and 5.
A satellite which crossed the base line Joining the transmitter and
receiver traversed each of the three overlapping, fan-shaped antenna beams
(see Figure 6). This resulted In three separate Doppler records, one for
each of the three antennas, separated in time by 50 - 60 seconds. The
length of the records varied, averaging about 7 seconds In the center
antenna and 15 - 25 seconds in the north and south antennas. The digital
Doppler data as a function of time were printed on paper tape and also
converted to binary form and punched into standard five-hole teletype
tape for transmission via commercial teletype to the BRL computer center,
where they were fed to the ORDVAC computer to obtain satellite orbital
12

parainetera. Figure ^ shows typical D0P1,0C data output and Figure 8
shows a typical orbital solution calculated using this type of data.
In addition to recording the digital data, recordings on paper charts
were inade of the Doppler analog frequency and signal strengt)» with
respect to time. Reproductions of these records are presented In this
report.
B. Antenna Diinenslons and Orientation
The special high-gain antennas wore 6o feet long and 10 feet wide
with beam dljnensions of 8 x 76 degrees and a gain of 16 db over
Isotropie. Tliree of these antennas were Installed at each of the receiving
stations and at the transmitting station. The antenna installation at
the transmitting stution is shown in Figure 9.
When the D0PL0C satellite detection system assumed twenty-four hour
operational status in January 1959, the transmitter at Fort Sill served
as the illuminator for both receiving stations. At that time, the high-gain
antennas were oriented in azimuth and elevation as shown in Figure
10. In the fall of 1959, the receiving station at White Sands was de-activated
and it was decided to tilt the antennas at Fort Sill and Forrest
City to produce more favorable coverage. The reorientation of the
antennas to the configuration shown In Figure 11 was made In November 1959.
A complete and detailed description of the DOPLOC satellite detection
and tracking system may be found In BRL Report No. 1123, "The DOPLOC
Instrumentation System for Satellite Tracking" (February 1961).
15

III. FIELD DATA
A. Satellite Reeorda
During the ld-oonth operation of the DOPLOC system, 111 refactions
were received, resulting from observations of 89 Individual satellite
passes. More than half of these reflections were received by the center
antenna alone, while the rest were observed by the north or south
antennas or various combinations of the three antennas.
Reproductions of OOPLOC Doppler reflection data are presented as
follows:
Sputnik III (56 Delta), Figures 12 to U5J Discoverer V (59 Epsilon),
Figures U6 to 52; Discoverer VI (59 Zeta), Figures 55 to 59* Discoverer
VII (59 Kappa), Figure 60; Discoverer VIII (59 Lambda), Figures 61 to 66;
Transit IB rocket (60 Gamma 1), Figures 67 to 71; Transit IB (60 Gamma 2),
Figure 72; Discoverer XI (60 Delta), Figures 73 to 80; Sputnik IV (60
Epsilon 1), Figures 6l to 66; Sputnik IV rocket (60 Epsilon 2), Figures
67 to 95; Sputnik IV fragments (60 Epsilon 5, h, 3 and 6), Figures 96
to 100. A summary of these reflections arranged by satellite and antenna
is given in Table 1, and a detailed explanation of each pass may be found
in Table 2.
B. Unidentified Flying Objects
A number of reflections were received and recorded which could not
be correlated with the predicted position of any known satellite. These
were termed Unidentified Flying Objects and reproductions of Ik of these
reflections are shown In Figures 101 to ll^, with a detailed listing in
Table 3.
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21

C. Peppier Recording
The typical forra in which DOPLOC data we recorded for eatellite
detection is shown in Figure 60, a record of Discoverer VII (59 Kappa).
An explanation of this record and the ALO device by which it was obtained
follows. The upper portion of the chart is an analog record of tracking
filter output frequency. The short, evealy spaced marks indicate the
successive frequencies at which the tracking filter is set while the
system is in the search mode. The tracking filter is stepped in 1 kc/s
intervals to maintain a frequency midway in the 1 kc/o spectrum to which
the comb filters are set. This minimizes the time required to pull the
tracking filter frequency to a nlgnal frequency detected in one of the
fixed filters. The comb filter bank consists of ten filters, each with
a 20 c/s bandwidth, spaced 100 c/« apart. The filter bank "looks" at a
1 kc/s frequency bund for 0.1 :;ccond; then It Is switched up 1 kc/s by a
heterodyne method and this procc:i.> continues, until either the desired
frequency band haa been covered or u signal is detected. Figure 60 shows
the tracking filter output when a 12 kc/s ccan is used. The ALO can also
be adjusted to acan a h kc/s range (see Figure 19) or a 2 kc/s range
(sec Figure 2h), or it may be manually positioned to a desired frequency
value. Manual operation is useful when attempting to lock the filter on
a signal being played buck from magnetic tape, where the initial Doppler
frequency is known within a few cycles per second. Figures 13 and 22
are exumples of manual filter positioning.
The initiation of phase-locked tracking is accomplished quickly when
a signal frequency is detected in one of the fixed filters. The control
circuit pulls the tracking filter frequency over to the received Doppler
signal frequency in about 10 milliseconds and within 80 to 90 milliseconds
all transients have subsided and phase-locked tracking begins. Figure 60
shows this transition from step scanning to continuous tracking at 1714:58
Z time. Concurrently, the digital counter and printer is started and the
tijne period of 1000 cycles of the Doppler is printed at one second intervals
on paper tape. Simultaneously, the period count is converted to binary forra
22

mid punched into five-hole teletype tape. The Doppler period count for
Revolution lö) of 59 Kappa, which correopondß to the Doppler frequency
analog record, is shown at the top left of Figure 60. The right five
digits constitute the count, while the left six digits represent Universal
Time in hours, minutes o«d seconds. The Doppler frequency in cycles per
second is 10 times the reciprocal of the count. A Doppler frequency
record readable to 0.1 c/s is obtained in this manner. If desired, the
Doppler frequency may also be printed dii'ectly in digital form (see
Figure 7).
D. Signal Strength
The lower part of the chart in Figure 60 is a record of the AGO
voltage from the tracking filter. While in the search mode, the AGC is
shorted, giving the clean, otroight line at 2 mm deflection. When a
signal is defected, the AGC voltage first decreases due to an initial
threshold voltage of opposite polarity existing on the AGC line, which
causes a deflection toward zero on the chart. Then, as the signal
amplitude increases, the AGC voltage increases as shown by the scale
calibration. The chart is calibrated in power input level (in dbw) to
the receiver input terminals and also In relative signal In terms of the
signal-to-noise ratio at the receiver output, i.e., in db below 1:1 S/N
at the receiver output. With a 10 z/a bandwidth, the tracking filter can
track signals that are 26 db down in the noise from the 16 kc/s bandwidth
receiver.
The signal strength record of 59 Kappa in Figure 60 shows a maximum
signal of -161 dbw which is 2 db down in the noise at the receiver output.
The rather narrow, peaked signal response curve with the slight dip on the
leading portion is "signature" information indicating considerable attitude
change during the six second passage time through the antenna beam. The
peak cross section for this pass of 59 Kappa was calculated to be 226
square feet from this record. The rather detailed treatment of this one
pass of 59 Kappa has been given to illustrate the detailed nature, quantity,
and quality of the data that are provided by the DOPLOC satellite tracking
system from a single pass recorded by a s.lngle receiving station.
25

E. Multiple Antenna Recordu
The previous discussion of experimental results has been largely
devoted to data received by the vertically directed center antenna.
Figure 63 shows a similar Doppler record of a satellite signal received
by the north antenna and later by the center antenna. The Doppler
frequency has a low value and is nearly constant during transit through
the north antenna beam which Is directed 20 degrees above the horizon.
During this Interval the Doppler corresponds to the flat portion of the
"S" curve. The region between the satellite signal in the north and the
center antenna is of Interest In this record since it represents a period
of unusually high spuriouo signal activity. The short, steep slope lines
are typical of meteor head echoes,"and are easily distinguished from the
satellite record either by their steep slope or their very short duration
AGO record (one second or less). Two of the slopes are of opposite sign
to those of the satellite record due to the extremely high velocity of
the meteor, which places the Doppler frequency on the opposite side of
the heterodyne frequency.
Optimum performance of the DOPLOC system is shown in Figure 80,
which is a record of a satellite passing through the three antenna beams
successively. This record depicts the step-scan frequency search, the
lock-on, and the continuous track sequence as the satellite passed through
the north antenna beam, the center beam and the south beam. It can be
seen that the k kc/s scan range is switched up as soon as the satellite
signal has ended in each antenna. This operation is performed manually
by the operator who is visually monitoring the ALO output. This record
is of particular interest since it is the last revolution of i960 Delta
over the Northern Hemisphere. During the latter part of this revolution,
this satellite re-entered the earth's atmosphere over the Southern
Hemisphere.
F. Meteor's
In addition to the satellite Doppler frequency record in Figure 60,
other short lines of about one second duration are evident In the upper
portion of the chart • These are spurious responses due to strong noise
2k

pulsea or meteor head echoea. It is clgnlflcont to note that a spurious
frequency signal occurred Juat a few tenth.: of a second prior to the
«
satellite Doppler signal reception, yet the ALO was able to respond with
full sensitivity to the desired signal. Spurious signals from meteors ore
identified by their short time duration and ateep slopes. Signal reflec-tions
from meteor trails, which are large ionized columns moving at very
low velocities, are recorded as nearly constant frequency, called "flats",
which are close to or equal to the bias frequency.
G. Satelltto Trails
There is some indication that the passage of a satellite through
12 5
the lonaphere produces a cloud of Ionized particles in ita wake, ' ' '
causing a constant frequency reflection similar to the "flat" reflections
produced by meteor trails. The existence of such an ionized cloud is
further supported by data as shown in Figures 16 and 18, where a "flat" is
seen immediately following the Doppler reflection from 58 Delta. Other
constant frequency reflections appearing after a satellite pass may be seen
in Figures 26, 27, 30, 66, 89, 92 and 100.
Figure 15 shows an interesting example of a satellite pass occurring
simultaneously with a "flat". Revolution 6586 of 58 Delta was detected three
seconds after the constant frequency reflection was observed. This example
demonstrates the ability of the DOPLOC system to detect and track a
satellite in the presence of a large, Interfering signal.
H. Predictions
Satellite predictions computed and distributed by Space Track Control
Center were used to determine base line crossing times for known satellites.
Two chart speeds were used for the analog recordings; 2.5 mm/second during
specifically selected search periods when a satellite was predicted to
cross the DOPLOC base line and 1 ram/second at all other times during
routine surveillance.
Not every satellite known to have passed between the transmitter and
receiver was detected, apparently because of Insufficient reflected signal
25

due to satellite attitude at the tljnc it traversed the antenna beam.
For the some rcaoon, «any paases were detected by one or two antennas
but not by all three antennae. These one or two-antenna reflections
prove extremely usefuli however, when exaalned In conjunction with the
three-antenna data, in analysts and coasparison of cross sectional areas,
"signature", sat .lite attitude changes (spin and tumble) and
scintillation.
26

IV. RKFLECTION CROSS SßCTIONS AW) POWER RATIOS
As previoucly stated, the Doppler frequency vs tljne data are
digitally recorded at the receiving station as the satellite passes
through the antenna beam. From these data, we may calculate the
Doppler slope (rate of change of Doppler frequency) and, subsequently,
the altitude and east-west position of the satellite as it crossed the
base line Joining the transmitter and receiver. Using these values
and the method described in Appendix I, we calculate the power ratio*
(ratio of calculated received power to measured received power) and the
apparent cross section observed for each satellite pass through each
antenna beam. Table h presents these values.
Before calculating the cross section and power ratio for a specific
satellite it is necessary to estimate the dimensions of the satellite and
calculate the power that would be radiated from an object of this size,
assuming It were located at a point in space corresponding to the
satellite position (altitude and east-west location). Subsequently,
when the true measured power is determined using the actual received
signal amplitude reflected from the satellite, the ratio of calculated
power to measured power gives the power ratio. Since all the reflected
power readings from one satellite are compared to the calculated value
for that satellite alone, we are permitted to examine the individual power
ratios as a composite group, regardless of the satellite from which they
were determined. In other words, a power ratio of 1 Indicates that the
measured power equals the calculated power, regardless of the physical
size of the satellite involved. Figures 115, 116, and 117 present the
power ratios measured in the center, north and south antennas, respectively,
and Figure 118 shows all the ratios, regardless of antenna.
* ä power raiiio vaxue of 1 Indicates that the measured power equals the
calculated power; a value of 10 indicates the measured power equals l/lO
of the calculated power.
27

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51

It la noted that '»5$ of the ratios itx Fleure 118 occur between 1 and 5,
and that slightly more than ÖC$ are between 1 and 15. This means that
almost half of the reflections possess a power value which la 1/5 of the
calculated value or larger, while 8 out of 10 reflections are I/15 the
calculated value or larger.
An Interesting situation exists In connection with the cross sections
measured for 60 Delta (see Table h). Of the eight pusses received, six
passes were three-untenna reflections, offering on excellent opportunity
for comparison of cross sections us measured by the different antennas.
It is also noted that, of the six three-antenna passes, five passes
exhibited the largest cross section in the north untenna, and four passes
were almost equal to the calculated value, as Indicated by the power ratio
approaching unity (Revolutions 12'», li»ü, 156, and 165). »0 clear cut ex-planation
can be presented for this preponderance of large cross sections
In the north antenna. All the antennas wore Identiical ir.«configuration,
dimensions and operating specifications, and ail were oriented with ref-erence
to a first-order geodetic survey. Subsequent to installation, a
signal generator was mounted ir. un airplane and a series of flights were
made over the antenna field at each station. In this manner, the radiation
patterns and antenna alignments were measured and determined to be optimum.
Thus, it would appear that each of the antennae should "see" a satellite
in the same way, and any variance in apparent size from one antenna to
another would be purely random, dependent solely on such variables as
satellite altitude, east-west location, and attitude. The observed cross
sections for 60 Delta do not appear random, however.
Further examination of the data, specifically Table 5 which presents
average values for all cross sections and power ratios, indicates that in
three of the four instances where a comparison can be made between the
three antennas for one satellite (58 Delta, 60 Delta, 60 Epsilon 1 and
60 Epsilon 2), the largest average cross section is that measured by the
north antenna. Since i^ appears that the north antennas consistently
produced larger power and cross section values, we might conclude that
the north antennas were perfectly aligned, or possessed greater gain than
either the center or south antennas.
52

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53

A;; iioutx no we nukv Uilü toni^ttlvo uucunplloi», however, wa ore
faced with controdlclory tiiita a« obacrved for Cü Kpailon i. Table S
ohowa six ptt^c;: of IhU üalelllte, Uu-ce meaeurcd by the center anteiuja,
two by the eoulh uud one by the north. Kxcludlng the north antenna pace
for the icoacnt, the five rcaalAlne fkua«'cji ctCibluta have an average cross
section of 2j6.ß squai'c fv^-t and on uvuroge power ratio of 1.8. These
values represent the largest average cross section utid best average power
ratio of any satellite observed, yet the one pass of this satellite received
by the north anunna Sias a crosa section that Is tmaller than this average
by a factor of 12. The fact that we observed this one saail cross section
In the north antenna la not significant, since a single observation cannot
be considered dtatlstlcaiiy oeanlngful. However, it Is significant that the
average cross sections for tne five passeu received by the center and south
antennas are large, nearly -quäl to the calculated value. Why these two
antennas operated so excellently .n •.:.!« an« satellite lu a aatter of con-jecture.
Referring again to Tab,..- I, wc r.-••• tnat the couth antenna produced
average cross scctiona tnat ■.•ere larger In 5 out of V .'nstar.ces than those
observed by the center antenna for the aatx- uatelllte. Here agaljn, it
cost be pointed out that 2 of the 5 are based or. only one pass each (59
Epsilon and 59 Zeta), and r.j valid conclusions can be drawn from sucn a
s-Tiall amount of daia.
51*

V. CROSS SBCTIOK "SIGMATURE" OBSERVATIOIIS
When the signal Btrength reflected fro« a number of paoees of one
catelllto lc recorded In analog foj-n, the sitapc of the oboervcd croco
occtlon envelopea Ray appear very ouch alike, provided tliot the satellite
attitude renains reasonably constant fi-oa pass to pass and that propagation
conditions are similar. Under Ideal conditions, a particular satellite
nay consistently produce a unique "signature", thus perelttlng Identifi-cation
on this basis alone. Others may produce a wide variety of shapes,
which appear to possess nothing In coamon. A satellite with dimensions
omall compared with the wavelength will generate an approximately semi-circular
or semi-elliptical signal strength pattern that Is Independent of
physical configuration. Signal strength changes due-to scintillation and
attitude change (spin and tumble) are usually present with large satellites
which produce a very complex received signal envelope configuration and
make "signature" Identification difficult.
In general, the DOPLOC records obtained by the center antenna are
charocterized by a short duration, syjcmetrlcal envelope that rises and
decays smoothly and possesses a rounded peak, with little or no oscillation
visible at any time. The average duration and signal strength of the 6?
center antenna measurements are 7.5 seconds and -l69.lt dbw. The north
and south antennas produced two general shapes; either a semi-circular
configuration with a smoothly changing signal level or a semi-rectangular
envelope with an abrupt rise and decay and a reasonably constant signal
level. Considerable variations, some quite large in amplitude, are
usually visible in both types. Signals from the north and south antennas
were longer than those from the center antenna, since the beams were
directed 20 degrees above the horizon as opposed to the vertical center
beam. For the 22 observations in the north antenna the averages are
21*.8 seconds and -170.4 dbw, while in the south antenna the averages
are 15.7 seconds and -175-6 dbw. The overall averages for the kk
reflections are 20.5 seconds and -172.0 dbw. A discussion of several
specific "signatures" follows.
35

3Q Pelta - A« outstandliig example of "cignature" Is evident lo
Figure:: 37 and 'JO, whore a sharp null la prominent on each record
approxlmtely 10 seconds after the appearance of the Doppler signal.
In both cases the reflection Is In the north antenna and the length
of record peralts easy observation of this characteristic null. A
severe sl#ml dropout is evident In Figure 25 and, to a lesser extent,
in Figure 22. This any be on Indication of "aignature". Slallarly, a
ssall dip is seen in each of the south antenna portluns of Figures 31,
35, 36 and ^6, approximately 3 seconds prior to signal loss.
59 Epsilon - There is no clear Haication of "signature", despite
the prevalence of periodic change in signal level, especially in Figures
^6, 50 and 52. This c»tunge In signal anplltude is probably caused by
satellite attitude change rather than by satellite configuration.
%> Zeta - A Bhorp spike is easily vleiblo on the leading edge of
each of the envelopes in Figures 53, 55, 50 and 59- The latter two
records show a periodic change in signal strength, whereas none of the
other 59 Zeta records possessed this characteristic. The variations in
Figures 58 and 59 are due to attitude change, which apparently coissenced
(or at least increased In frequency) late in the orbital lifetime of 59
Zeta. Even as late as Revolution 855 (Figure 57), there is no indication
of this periodic nodulation. It is very evident, however, in Revolutions
871 and 877, the last two DOPLOC observations of this satellite before its
re-entry into the earth's aunosphere (estimated by Space Track Control
Center to have occurred between Revolutions 96h and 966).
59 Kappa - Only one pass was received for this satellite and it
shows no significant features.
59 Lambda - The very abrupt signal loss in the middle of Revolution 96
of 59 Lambda (Figure 6l) nay be "signature" information, though two factors
are present which make this assumption appear somewhat doubtful. First,
there is no evidence of this unique signal dropout on any of the other
records of 59 Lambda. Secondly, and of greater linportance, is the extremely
rapid signal decay. It is unlikely that any motion or physical configuration
of the satellite could produce such a steep decay curve. The aLnost instan-taneous
decay strongly suggests that equipment failure or propagation phenom-ena,
rather than satellite movement or shape, caused this sudden loss of signal.
36

60 Conoa 1 - Anotlicr excellent example of "olgnature" in found
in Figures 69, 70, and 71, vhere the Y-ohaped peak ia easily seen.
Fieiu*e 67 also chows traces of this shape, but the high altitude of
this pass ('»'»0 ailes) severely attenuated the received signal and
prevented this characteristic frota being oore prominent. This pass
was the highest pass recorded by the DOPLOC system during its operation.
A further Identifying feature in these data for 60 Qaosa 1 appears to be
the signal losses shown in Figures 68, 69, and 70 which occurred in the
middle of the passes where the signal is normally at a maximum. On two
of these passes, the tracking filter lost lock completely, but the ALO was
able to lock-on again when the signal level increased.
60 Gaaaa 2 - Only one pass was recorded for this satellite and It
displays no uignificaot envelope shape.
60 Delta - Here we see a severe null in both Figure 78 (center) and
Figure 79 (north). Once again, the tracking filter lost lock during the
former pass but the ALO regained the signal automatically when it became
stronger. A hint of a similar null may be visible in both Figure 73 (south)
and Fi-ure 78 (south). It is worthwhile to point out that Revolution 6l
(Figure 7k) was received by the north and south antennas but not by the
center antenna. Perhaps the satellite was oriented In its maximum null-producing
attitude during the middle portion of this pass and, consequently,
this orientation reduced the reflected signal to a level lower than the
ALO threshold level and no lock was obtained. Repeated rerunning of the
magnetic tape of this pass in on attempt to lock the ALO on the Doppler
signal was without success. It appears that the center antenna portion of
Revolution 156 (Figure 78) may have been approaching this complete signal
fadeout condition also.
60 Epsilon 1 - There does not appear to be any clear indication of
"signature" in these data. The record of revolution 150 (Figure 83)
exhibits a nine second signal loss in the middle of the pass. The absence
of signal dropout in the other records of 60 Epsilon 1 makes it difficult
to correlate these data with "signature" information. It may be noted
that data shown in Figure Qk was recorded at 1 mm/second which served to
57

condense the envelope. The 2.5 eta/second chart tspeed would have
enlarged the envelope and produced a trace ulfiiilar to Figure 86.
^0 Kpullon 2 - The distinguishing feature here secas to be the
oscillations observed In the center antenna portions of Figures 68, 92
93 and 95. Reflections frora the majority of other satellites observed
In the center antenna an? scoolh. Again it Is noted tliat the chart
speed In Figures 92 and 95 Is 1 cs/second, vhllc In Figures 66, 69 and
95 It Is 2.5 Bä/second. Had the fonser passes been recorded at 2.5 Em/second,
the resulting envelope would be very similar to Figure 95«
a0 :-:p;:ll0ii 5. k. 5 and ^ - It Is not possible to evaluate
Individually these data in terms of "signature", since only one or two
pasoej of each ssatellite arc avullabic and none jooms to possess any
distinguishing features. Intercomporison is not valid either, even
though they are ail fra^ents from t>0 Epüllon 1 (Sputnik IV), because
the physical configuration of the fragments is probably not the same ~"
and, therefore, any üimiiarity in envelope shape would be purely random.
58

VI. CROSS SECTIOH MODULATIOII DUK TO ATTITÜDE CltAIKJE
Evidence of IXTUNJIC ul^nul nodulaiion« such a» alght W caused by
öpin or tuablc-, la vlulble In the oaJorLty or »i^nal strength records.
This cross section nodulutlan Is visible both In the records of ground-originated
reflected signals and In ihc records of signals which originate
froa a satelllte-bornc irao^altter. For this discussion, we shall tern
the foraer aethod of satellite detection and observation ,,J;asslve,, track-ing,
and the latter tsethod "active" tracking. Measurement and analysis
of signal strength sodulatlun observed with the two methods of tracking
are difficult for several reasons. Propagation variances alone «ay in-troduce
periodic changes in observed signal strength which can be »istaken
for modulation cauued by satellite attitude change. The relatively short
duration of the passive records recorded by the center antenna cake it
iopossiblc to deteralne a aadulatlon periodicity In this antenna of core
than a second or two. The passive records recorded by the north and
south antennas, though fewer in nicabcr, are of greater value in modulation
analysis since they are considerably longer in duration and penait measure-ment
of several cycles of a modulation possessing a period in the order of
1 cycle per 5 seconds or longer. Also, when active tracking records are
exa-alned, especially those taken on Sputnik III and IV which transmitted on
a nominal frequency of 20 Mc/s, the Faraday effect must be considered.
This effect varies inversely with the reciprocal of the frequency squared.
Thus, it is definitely a prime factor in producing periodic signal modula-tion
at 20 Mc/s, considerably less a factor at 108 Mc/s (the DOPLCC reflec-tion
frequency), and virtually non-existent at still higher frequencies
such as the transmitting beacons in the Discoverer satellites. Fluctua-tions
in received signal, while not necessarily periodic, may also be caused
by changes in the amplitude of the transmitted signal or the gain of the
receiver. Within these limitations, an attempt has been made to analyze the
D0PL0C records for evidences of cross section modulation caused by satellite
attitude change.
Examination of passive and active records for 58 Delta (Sputnik III)
and 60 Epsilon 1 (Sputnik IV) show signal strength nulls occurring in a
2;1 ratio, i.e., two nulls are observed on the passive records for every
59

nuil on the active recordo. Flcurto 29 (north), JJ (uouth) and 59
(north) are records of pasalve reflection» fro« 56 Delta and show an
ovcroG« of 1 null per ,J üeconda, while Flgm-e H9, on active record
for 5B Delta, display 1 null pt»r 6 oecondü. Slallarly, Figuren
OS (north), 85 (couth), and 85, p««ölvo obaervatlono of 60 Epsilon 1,
«ase satellite (Figure 120) amua i null per J seconds. It Is evident
froa these data tl^t the physical configuration of the sateUlte
produces a four-lobed pattern when reflecting the ground-originated
DOPLOC slcnal, whereas the transslttlng antennas on the satellite
radiale a tvo-lobed pattern for active tracking. As the satellite
tumbles and spins, these radiation putu-rns produce the 2:1 ratio seen
la the signal strength null frequency.
Evidence of »lailar periodic nullc is seen in the records of 59
Epsilon (Discoverer V). Here, however, the passive to active ratio Is
8:1. Fleures UB (south), 50 and $2 (couth) are passive reflection
records of 59 Epsilon and display an average of i nuil per ^ seconds.
Each of two active records for 59 Epsiicn, one of which Is shown Ix,
Figure 121, show i null per 2k seconds. Apparently, the cylindrical
shape of the Discoverer satellite creates a multl-lobed reflection
pattern, while the transmitting antenna radiates the tvo-lobed pattern.
The validity of this assumption regarding the reflection pattern is
enhanced by the fact that the length of the cylinder (I9.2 feet) is
approxL-nately twice the wavelength of the DOPLOC frequency (9.1 feet).
Where the length of the reflecting object is large compared to the
wavelength, as in this case, the result Is a multl-lobed radiation
pattern.
It is worthwhile to note that a total of nine active records
taken on 59 Zeta and 60 Delta (Discoverer VI and XI) show an average
of 1 null per 2k seconds, with individual values ranging from 11 to
40 seconds. The agreement with the null rate observed for 59 Epsilon
is striking.
Table 6 summarizes the data discussed above and lists null rates
for several other satellites as well.
ho

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vii. scnrriLLATiOH
A nuaber of the DOPLOC rccorde of reflected olgnal otrength chow
trftcea of eclntiliatlon and Table 7 preoents a suscaai-y of the oost
proalneat ejtirapleo, grouped occordhig to pass tlao. The eotlmted
peok-to-peok ajüitlllatlon In db is given for each pass, as well as
the antenna In which the reflection was received. A notation Is also
Bade concerning the season of the year In which the pass was recorded.
Certain qualitative features In the data are rather pronounced and
deserve oddltlonal coanent.
The existence of a diurnal cycle Is apparent, with the scintillation
oaplltude being greater at night than during the day. The average peak-to-
peak signal fade for 9 observations made at night Is 2.h db, while
for 20 dnytLce observations the average value Is only 1.1« db. Also,
the diurnal effect Is auch core pronounced In susaner than In winter,
evidenced by the fact that 8 of the 9 night passes occurred In the
months between March and October. A series of one-way radar transmission
tests conducted by the Bell Telephone Laboratories, at wavelengths rang-ing
from 30^cm to 1? m, revealed corresponding diurnal and seasonal
variations. Similarly, tests carried out by Ross A. Hull, with the aid
of other radio amateurs, the U. S. Weather Bureau and Harvard University
In the 5 to 8 m wavelength region, yielded comparable results. 5' 6
The data in Table 7 show that scintillation occurs more frequently
in the north and south antenna reflections than in the center antenna.
Considering the total number of reflections received by each antenna,
we find scintillation appearing in kft of the north antenna passes (10 of
22), klf of the south antenna passes (9 of 22) and only I556 of the center
antenna passes (10 of 67). The indication here is that the reflecting
and diffracting properties of the terrain and the irregularities of the
atmosphere near the earth's surface combine to produce interference
waves which, in turn, cause variation In signal strength. These
phenomena would heavily Influence reflections in the north and south
antennas, since they are beamed only 20 degrees above the horizon. The
k2

TÄIU-K 7
A-iimiXAm« V4 »re- TIK5:
PcftS-ld-IVftH .
S»teUtt« Rcvatullon * SctALLUAtlOO hiss TUuc
Bane Ruatoer Aft'-cftRfi !a 4b U. T. C. S. T.
60 Bpslioo 2 30) - .'. 0355 2155
60 Deli« :■-: - 2.0 tjteB oa?a
& Epatl^JC 2 :., n ).o uiAS 0CA2
•kJ Dr't« 9937 :; 2.0 tiO.1 (M2
58 tvlia 5-9)7 :■■ :■." <&* 0CA2
fß IfcllA fv."- ' .-. '>V C052
50 Dell« ;. i. ■7'-'- •woo
&ü ••:... 2 i-; « 2.5 crf2i 0121
58 Itollfc .-... :.■ >. 0&.9 C2b9
Smpufl
s
s
s
8
I
:J
U
s
60 Ej-dlloa 2 Jty • 2.0 1)26 Wx, s
53 Dclu» 87% : '.. 1)56 0758 w
cO Epsilon £ 501 : • •: IbCO cöoo s
iö Dcl:n 87> • .. ...> <A9> w
W LDaMa . :•-• « ..^ ■ ',■• C^CA V
^ Dell« 8719 : .. 1530 W V
58 Bell« 9959 n 1.0 15UJ 0^8 s
^8 Dell« ««' n :. 160) 100) s
V6 Dell« e6bj c 1.0 161*7 10i7 H
5? r.eui .'- s .. 1650 -'■'>- w
ÖJ Kpnlloi. 2 :•/. .; :. 173) 11)) s *
60 Dell« 61 :: 1.5 1605 120) s ä
5Ö Dclt« >&*8 s 1.5 1812 1212 s
58 Dell« }6J2 - 2.0 1815 ia) s
60 DclUi JO :; 2.0 iBJiO 121*0 s
58 Delta 9722 ;: 1.5 2C1.5 llti.5 s
5Ö Delta ejac : 1.0 21)6 1536 w
6C Epoilon 2 617 c 2.0 2218 1618 s
58 Delt« 9612 li 1.0 2219 1619 s
59 Lonbda 685 3 2.0 0016 1816 w
S - south, C - center, II - north
W - Winter (November - February)
*S - summer (March - October)
'O

greater leugth of the observationa by the north and south ontemma
Bay aliso contribute to the more frequent obaervations of signal fade
In thejti antennas.
Fro« an examination of a number of active tracking records made
at Aberdeen Proving Ground, Maryland, there appears to be more
gclntlllatlon present In these active records than In the passive
reflection records. Figure 122 ohovs a Doppler record of 58 Delta
obtained at Aberdeen by tracking the 20 Kc/s satelllte-borne transmitter.
Peak-to-peak signal variations for this record are approximately 6 db,
roughly twice as large aa any variations noted In the passive records!
This satellite was probably experiencing severe buffeting when this
recording was made, since re-entry occurred only JO revolutions later.
These drastic oscillations may have increased the scintillation amplitude
to some extent, since records taken earlier in the lifetime of 58 Delta
chow signal fade in the order of 5-i. db. Then too, the very slight
Doppler frequency shift during this Fa3s indicates that the satellite
was at a great distance from the station and that the inclination of
the line of sight to the horizontal was small. Thus, as mentioned
previously with respect to scintillation in the north and south antennas,
interference waves may have contributed to the increased amplitude of
the signal variations.
HAROLD T. LOOTENS
kk

REFEREIKES
1. J. D. Ki-uuß, "Eviüenco yf Sutclllte-Inducc-ü Ionisation Effccto
Between Heaslöphercs"^ Proe. BE, '«Ö, 1913-191^, (i960).
2. J. D. KTAUS, R. C. ':ii;r.,'.y, D. J. Schecr and y. R. Crone,
"observations of Ionisation Induced by Artlflcal Earth Satellltea'',
Mature, 1Ö5, 520-521, (i960).
5. Roberts and Kirchner, QST, r>. jft, (1959).
'». J. C. SchellIng, C. R. Bwi'owö, ond S. 3. Ferrell, "Ultra-Bhort-wave
Propogatlon", Proc. IRE, 21, Ii27, (1933); C. R. Burrows, A.
Declno, and L. E. Hunt, "liritra-short-wave Propagation over Land!*,
Ibid, 33, 1507, (1935); and "Stability of Two-seter Waves", Ibid,
26, 516, (1938); C. R. Burrows, A. B. Cs-awford, and V. W. Kusford,
"Ultra-short-wave Tranaalsslon over a 59-slle Optical Path", Ibid
28, 3Ö0, (i9'iO).
5. R. A. Bull, QST, 19, 3, (1935)> ond 21, 16, (1937).
6. A. W. Friend, Proc. IRE, 33, 3^8, (li^).
ii5

Arraron i
CALCUUTIOJf OF PCWKR RATIO ;jkD CHÜSS SECTIOH
Center Antenna - As prcvloucly stated, tho Dopjilor frequency vs
tlKO inta arc digitally recorded at th«- receiving station aa tho
satellite pasties through tncl: of the tlu'ce antenim beasa. Frea tJje
dUTltttl Doppler daUt wo calculate the Dopplcr slope (j-ate of cJ'^jjge
of Dappler frequency)« Knuvlng the Doppler frt-quvney and slope and
assualng clrcultu* aotlou, U 1^- possible to obtain the altitude and
east-vest location of the atollltc a;; it crosses the base line Join-ing
the trar.scltter uad receiver, with the aid of a chart of the type
prer-er.tcd in Figure 12>. Constant coatoui' ILnta have been coaputcd
and druvn Tor the Dopplcr frequency und the tlae derivative of the
frequency (the elope) In the vertlcul plane conUiinlns both the
transieittcr and receiver. Th« -• oor.toura vary vlth ::ut<;llitö or-bital
inclination, so thai tevorai cliarta u.v: reqv;ired for orbits of
various inclinations. '£tazh cJiart i.» valid, however, only for data
received in the center bens:. Giver, u Doj.plcr frequency of 300 cps and
a slope of 90 crs at, x.':.> :;.l.i. ,.i:.t oV the record, ue locate the cui'ves
representing these vnluej 01. the chart and, ut tiieir intersection,
read an altitude of l/{ nile.i and a sub-satellite point on the base
line located jJ5u ftiies east of Fort ;-:iii. Having determined these
distances, a sketch sinilar to Ficare 12'« is prepared to assist in
cow.pleting the power and CIJ:;:; ..vction calculations.
liortli rtnd .cJ-.>uth Ant'-.'-.-.'-i- - The ^c-unietry and calculations necessary
to locate the point, of int •■:•.>. otii:: of a satellite in the north or south
antenna, and Its correspof.aln,: ground ranjjc froiii Fort Siil, vary some-what
from the method described for the center antenna. In these antennas,
the Intersection point and its corresponding distance east or west of
Fort Sill are function:; of satellite altitude, and the inclination of
the orbital plane and bur,..- line with respect to the equator. For purposes
hi

of thlo vUccusaion, uc oluUl confine ouraclvc» to the ::outh antenmi.
Calcukitlono in tho nox-th nntennti are ;;ißilar. Figxu-o 125 (jlvos a
cmrhlc m-caentatlon of the cectjetry involved.
The uoutl: oatenna is elevated 20 degreoo above the horizon and
oriented In aslcuth ua oh^vn in Figure 11. The altitude of the satellite
Intersection point In the center antenna Is taken aa the height of the
jwtnt of intersection in the south antenna pattern. The curvature of the
earth la Ignored here slaee It la negligible over UR- relatively short
distance Involved. Referring to Figure 125, we calculate X, the perpen-dicular
distance fro« tne base llr.e to the point or Intersection of the
satellite In the south antenna, using the trlgonoaictrlc function
:•:
air. 20°
Subsequently, the perpendicular distance '{, fror, the 20 degree
plane of the south antenna zo the 90 degree plane of the center antenna
is deterr.Lied by
Y--±
•v,an <r0
The next step Is to calculate ^ the angle at which the satellite
crosces the base line. If we let i ^qual the orbital inclination at
the equator and l' the orbital Inclination at any North Latitude 0, then
cos 1'/ = COS i
COS 0
Solving for 1' gives the angle at which the satellite crosses the
particular North Latitude 0. The Forrest City - Fort Sill base line is
a segment of a great circle which is not parallel to the equator; hence
as shown in Figure 126, the satellite crosses the base line at an angle
different from i', the difference being equal to the inclination of the
base line to the equator. The base line is inclined 3 degrees to the
equator so, for a north-south pass 3 degrees must be added to i', while
for a south-north pass j, degrees is subtracted from i' to obtain Q .
ii8

Finally, knowing 3 and Y, the distance d noved along the base
line In Figure l.'~y can be determined by the trlgonooetrlc relation
tan «. • ^ *
I a
This value d oust be added to or subtracted free r (the ground
range from Fort 3111 as deteralned Tor satellite intersection In the
center antenna), depending on the pass direction and the antenna In-volved.
As shown In Figure i:f[, Vor a north-south pass, ground range
In the north antenna Is equal to r - d, while for the saae pass in the
south antenna the ground range Is r ■«■ d.
Having thus determined the distance from the base line to the
satellite Intersection point in the 20 degree plane and the corresponding
ground range from Fort Sill, a sketch is prepared as shown in Figure 128
to aid in coopleting the calculutions.
Power 6nd Crotis Section Caleulations
Having determined satellite altitude (or the perpendicular distance
from the base line to the point of intersection In the 20 degree plane),
as well as the ground range east or west of Fort Sill, and knowing that
the distance between the transmitter and receiver Is ^35 miles, the distances
R and R2 and the angles a and ß con be computed using standard trigonometric
functions (refer to Figures 121» and 128). The azimuth angles of the trans-mitting
and receiving antennas are known (see Figure 11); hence the angles 7
and 6 can be determined and, from the curve presented In Figure 129, the
factors F-, and F , which are decimal representations for the angles 7 and 5,
are obtained. It Is now possible to proceed with the computation of the cal-culated
power Pn, the measured power received P, , the power ratio PD/Pw,
and the apparent cross section of the reflecting object 5~^ .
The calculated power In watts that would be radiated from an object
of known dimensions at a given distance from the transmitter and receiver
is determined first. For example, a length of 20 feet and a radius of
2.5 feet is assumed for the Discoverer satellite. The maximum reflection
h9

croats section that an object huvlnn theüo dlaenalons would preaent ia
calculuted by nuln^ the foraulu
where X. at 106 ^te/s la 9.1 feet. Solving for ZU» « volue of 690 oquare
feet la obtained for the Discoverer aatelllte. Adalttedly, thla proceso
la an approxlcatlon, since accm-ale deteralnatlon of£21« dependent upon
r and / being huge coapared to X. Slallur eatksatea of phyalcol dlaenalona
were aade for Sputnik IH and IV and for Tranalt I, and the reeultlng valuea
of C^re used In the calculations pertaining to thoae sateUltea.
Using the basic ruiar equation,
. ''T'V(ilt
rFTF
ri) ' ' 5 Bg5— (I)
R (''«)^(R.r (R^r
the value of21 and the following DOPLOC syHtea conatonta are Ineerted:
P = power transalttod - 1»0 Jew
G„ » G = antenna gain In power » kO
X « 9.1 feet
Thus, equation (1) becomes
. 1-66 x to8 FTPR
« 5 ö (2)
(RJ- {R^f
where R^ und R are expressed in feet or
-„ • ^ V0'6 rT F
B (5,
(R^ (R2)2
where R and R are expressed in miles.
Next, equation (5) is solved for PR to detennine the power in watts
that would be radiated from an object of this size if it were located at
the point in space occupied by the satellite.
To detennine the measured received power in watts, the peak of the
received signal recorded in db below unity S/N at receiver output is con-verted
to a voltage ratio X.
Tlldenour^ L., "Radar System Engineering", M3T Radiation Laboratory
Series No, 1, p. 66. (l^T).
50

X = log" (max db)
If E1 Is the received algnal for a 1:1 s/jl ratio at the receiver out-put
(which for the DOPLOC oystcm U 0.0? mlcrovoltß) and E2 Is the meaoured
received algnal voltage, the «eaaured power in watto io
PH . <■=/
R
where R, the antenna reslütance, is equal to 50 ohma. The power ratio,
PR^PM cxPreoßeo the relation between calculated and measured power.
To calculate the cross section corresponding to the peak signal
received, equation (1) Is used to solve for JT-After
substituting PM for PH, equation (1) may be rearranged to give
5.'»9 x 10"9 F7. PR
Solving for 23 gives the apparent cross section of the reflecting object
In square feet.
51

APPEHDK n
BRL-DOPLOC REPORTS
No. 1
BRI. Meao Report Ho. 1055 - October I95Ö
"Doppler Signals and Antenna Orientation for a Doppler Syetea"
by L. P. Bolglano, Jr.
COfiTIDEJITIAL
Ho. 2
BRL Hcxo Report No . 1185 - January 1959
Flr.st ScÄl-Aanual Technical Smmoary Report
Purijd 1 July 1958 - 31 Docesjber I958
by L. G. dcDey, V. W. Richard, A. H. Hodge, R. B. Patton, C L. Adans
(EML 39-60) CO.'fFIDrffriAL
Ho. 3
BRI, Tech Hote Ho. 1265 - June I959
"Orbital Data Handling and Preotntatlon"
by R. E. A. Putrma
UNCLASSIFIED
Ho. h
BRL Tech Hote Ho. 1266 - July I959
"An Approach to the Doppler Dark Satellite Detection Problem"
by L. G. deBey
COHFIDEHTIAL
Ho. 5
BRL Meao Report Ho. 1220 - July 1959
Second Serai-Annual Technical Suraraary Report
Period 1 January - 30 June I959
by L. G. deBey, V. W. Richard and R. B. Patton
(BML 208-59) COHFIDEHTIAL
Ho. 6
BRL Tech Hote Ho. I278 - September I959
"Synchronization of Tracking Antennas"
by R. E. A. Putnam
UNCIASSIFEED
Ho. 7
BRL Memo Report Ho. 1237 - September I959
"A Method of Solution for the Determination of Satellite Orbital Parameters
from DOPLOC Measurements"
by R. B. Patton, Jr.
■ UHCIASSIFIED

nuliUDOPlJDC RhitiiCf^ (continued)
No. S
mi Neno Report No. 1093 - Morch I960
"The Dyiuuaic Cliorftctcrlotlcs of PJuuse-Lock Reeelvero"
by Dr. Keats Pullen
tniCLASiJIPIED
Ko. 9
"Station Geccsetry Studies for the DOPLOC Syotea"
3t!inford Research Institute
l^iCL/^ÜIFIED
Uo. 10
Final Rvport, Part B, Stanford Rußearch Institute - July I960
"DOPLOC Syatca Studies"
by H. £. Schurfcan, H. Rothaan, H. Guthart, T. Horlta
UTiCLASSIFIED
No. 11
Phllco Corporation - U May i960
"Poly^tatlon Doppler Syatea"
No. 12
UNCLASSIFIED
Space Science Laboratory, General electric Co. - October i960
"Orbit Determination of a Non-Tranamlttlng Satellite Ualng'Doppler
Tracking Data"
by Dr. Paul 3. Richards
UNCLASSIFIED
No. 13
Final Technical Report - University of Delaware - June 15, i960
"Quantua Mechanical Analysis of Radio Frequency Radiation"
by L. P. Bolgiano, Jr. and W. M. Gottschalk
UNCLASSIFIED
Ho. Ik
Final Report F/157, Columbia University - February 11, i960
"Nummary of the Preliminary Study of the Applicability of the Ordir
System Techniques to the Tracking of Passive Satellites"
UNCLASSIFIED
^

BKUDCPLOC REPORTS (continued)
No. 15
HRL Report lio, 1110 - June i960
"Precision Frequeney Kcasureaent of Jtolay Doppler Signal»1
by W. A. Ikan
UIJCIJU^IFISD
Uo. l6
Third Technical iJuraitiry Report - Period July 1959 through June 30, i960
2RL y.va.0 Report lio. 126?
by A. L. 0. deBey
UltCl^SSIFIKD
Jio. I?
Columbia University Tech. Report Uo. T-l/157 - Auguat 1, 1959
"The Theory of Phase Synchronlxutlon of Osclllutorü vlth Application
to the DOPLOC Tracking Filter"
by ?:. Krelndler
UHCLASSIFIL'D
Uo. 16
BRL Tech I.'ote Uo. 15^5 - Auguat i960
"DOPLCC Receiver for Use with Circulating Mczory Filter"
by K. Patterson
UNCLASSIFIED
No. 19
BRL Tech Note Uo. I'&k - October i960
"Puremetrlc Pre-Amplifier Reaulta"
by K. Patterson
UNCLASSIFIED
No. 20
BRL Tech Note No. 1567 - December i960
"Data Generation and Handling for Scanning DOPLCC Syatem"
by Ralph E. A. Putnam
UNCLASSIFIED
No. 21
BRL Report No. 1123 - January I96I
"The DOPLOC Instrumentation System for Satellite Tracking"
by C. L. Adams
UNCLASSIFIED
55

jgUDOPLOC g^OMS (continued)
Ho. ^2
BRL Kec» Repoi-t Ho. IjJ^) - «arch 1961
"DOPLOC Obaervatlono of Reflection Croaa Section of Sutellltea"
by H. T. Lootena "i^a
UNCLASSIFIED
In Prcpftratlon
"DOPLOC Cosb Filter" by R. Vltek
"DOPLOC Orbit Determination Methoda" by R. Putton, Jr.
"Final Suwory Report on the BRL-DOPLOC Project" by Dr. A. H. Hodge
56

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NORTH AND SOUTH ANTENNAS (TOP VIEW) (EDGE VIEW)
WHITE SANOS FORT SILL FORREST C|TV
CENTER ANTENNAS (SIDE VIEW) (EDGE VIEW)
FIG. 10 - INITIAL ANTENNA ORIENTATION
66

/
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CITY
20o
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FORREST
CITY
CENTER ANTENNAS (SIDE VIEW) (EDGE VIEW)
FIG. II - ANTENNA ORIENTATION FOLLOWING
DEACTIVATION OF WHITE SANDS STATION
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