Doploc observations of reflection cross sections of satellites

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mil MEMORANDUM REPORT NO. 1330 MARCH 1961

DOPLOC OBSERVATIONS OF

REFLECTION CROSS SECTIONS OF SATELLITES

y 3 G c

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ARPA Satellite Fence Series

Harold T. Lootens

Report No. 22 in the Series

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Department of the Army Project No. 503-06-011 Ordnance Management Structure Code No. 5210.11.143

BALLISTIC RESEARCH LABORATORIES (ftzosBcawaawBeßNaswftiJmjifc^^

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ABERDEEN PROVING GROUND, MARYLAND

BALLISTIC RESEARCH LABORATORIES

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

BALLISTIC RESEARCH LABORATORIES

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 OK 25

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. Ai\PA-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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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

a

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rA vo 0> JS 0\ CO

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(1) P O

s .& s o U3

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(g #-4 .H H H

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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

4»

T1 O

o ♦;

I« • • •• | •H H H

y

^8 . «I

u o O *J . ä 1. > o ;. ,Q O

« o

VO KN ^a ja Ji CVJ 01 (\l

o c

oj r- w

ra

a> *: i: K -4 • U\ ru 03 CH C M • • •

o Ü lA H H »^ 01 H • a 4/

ta > « > 4J << t>

Ü m > ■H n IQ <3 Pk

o 3 •H

•

Cj fA (A ■O tf\ (M OJ

Ö E ^) V

m 3 & R o

aj

a a a o o o 0) H H

■P -rl -ri w H d h •H aJ P

i) H W W 0) 10 P H 4J U) aj Pt p( (H

^ (U 0)

•H ^ o w w eg o

H a CO o o uS VO vO

o\ ov o 0) -p Ü ir\ IA VO

■p 3 !fl a3 P( •H

CO M p

lü

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

U

s

I

:J 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(iltrFTFBg (I) ri) ' ' 5 5—

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 FB (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

Ho. 6

BRL Tech Hote Ho. I278 - September I959 "Synchronization of Tracking Antennas" by R. E. A. Putnam

(BML 208-59) COHFIDEHTIAL

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

nui lUDOPlJDC 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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RECEIVER

0OPLOC FREQUENCY AND RATE OF CHANGE OF FREQUENCY AS A FUNCTION OF

POSITION IN THE Y2 - PLANE (FOR 80° INCLINATION)

Fig. 123

SATELLITE

FORREST CITY

A •24-. AZIMUTH ANGLE OF TRANSMITTING ANTENNA. •

B-25»- AZIMUTH ANGLE OF RECEIVING ANTENNA.

R, » SLANT RANGE FROM TRANSMITTER TO SATELLITE.

Ra» SLANT RANGE FROM RECEIVER TO SATELLITE.

y- ANGLE THAT R, MAKES WITH CENTER OF TRANSMITTING ANTENNA BEAM.

8 -- ANGLE THAT R2 MAKES WITH CENTER OF RECEIVING ANTENNA BEAM.

a « ANGLE THAT R, MAKES WITH BASE LINE.

ß -• ANGLE THAT R2 MAKES WITH BASE LINE.

Z » ALTITUDE OF SATELLITE IN CENTER ANTENNA.

GR » GROUND RANGE FROM FORT SILL.

FIG. 124 - CENTER ANTENNA GEOMETRY

].8o

SOUTH-NORTH PASS

HORIZON

Z = SATELLITE HEIGHT IN CENTER AND NORTH OR SOUTH ANTENNAS.

X = PERPENDICULAR DISTANCE BETWEEN BASE LINE AND SATELLITE INTERSECTION POINT IN NORTH OR SOUTH ANTENNAS.

Y = PERPENDICULAR DISTANCE BETWEEN 20° PLANE AND 90° PLANE.

AC = r = GROUND RANGE IN CENTER ANTENNA

BC = d = DISTANCE MOVED ALONG BASE LINE.

AB = GROUND RANGE IN SOUTH .ANTENNA.

01= ANGLE BETWEEN SUB - SATELLITE TRACE AND BASE LINE. ,„

FIG. 125 - ALTITUDE AND GROUND RANGE

GEOMETRY IN SOUTH ANTENNA

löl

SATELLITE PATH

B\ • (l'-S0)

N. LATITUDE ^

EQUATCX

SOUTH - NORTH PASS

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EQUATOR

NORTH - SOUTH PASS SATELLITE

PATN

i « ORBITAL INCLINATION AT EQUATOR.

j1 = ORBITAL INCLINATION AT NORTH LATITUDE *.

9\ ' ANGLE BETWEEN SUB - SATELLITE TRACE AND BASE LINE

FIG. 126 - SATELLITE INCLINATION WITH

RESPECT TO BASE LINE

182

FORT SILL

NORTH ANTENNA

SOUTH ANTENNA

FORREST CITY

NORTH - SOUTH PASS

GROUND RANGE (GR)

IN NORTH ANTENNA • f-d

!N SOUTH ANTENNA = r + d

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FORT SILL

NORTH ANTENNA

r

FORREST 0 CITY

SOUTH ANTENIIA

SOUTH-NORTH PASS

GROUND RANGE (GR)

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IN SOUTH ANTENNA = r -d

WHERE r » GR IN CENTER ANTENNA AND IS EAST OF FORT SILL, AND D = DISTANCE MOVED ALONG BASE LINE.

FIG. 127 - GROUND RANGE IN NORTH AND SOUTH ANTENNAS

185

SATELLITE

FORT SILL

FORREST CITY

A »24»« AZIMUTH ANGLE OF TRANSMITTING ANTENNA.

8 = 25°= AZIMUTH ANGLE OF RECEIVING ANTENNA.

R| « SLANT RANGE FROM TRANSMITTER TO SATELLITE.

R2 = SLANT RANGE FROM RECEIVER TO SATELLITE.

y» ANGLE THAT R, MAKES WITH CENTER OF TRANSMITTING ANTENNA BEAM.

8 = ANGLE THAT R2 MAKES WITH CENTER OF RECEIVING ANTENNA BEAM.

a s ANGLE THAT R, MAKES WITH BASE LINE.

ß -- ANGLE THAT R2 MAKES WITH BASE LINE.

Y = PERPENDICULAR DISTANCE BETWEEN SATELLITE INTERSECTION POINT IN 20° PLANE AND 90° PLANE.

GR = GROUND RANGE FROM FORT SILL.

FIG. 128 - NORTH AND SOUTH ANTENNA GEOMETRY

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DISTRIBUTION LIST

No. or Copies

10

Oi'tionl nation

Chief of Ordnance ATTIf: ORDTB - Bal Sec Departsaont of the krmy Washington 25, D. C.

Commanding Officer Diamond Ordnance Fuze Laboratories ATTN: Technical Information Office

Branch 012 Washington 25, D. C.

Commander Armed Services Technical

Information Agency ATTN: TIPCR Arlington Hall Station Arlington 12, Virginia

Commander Air Research & Development Command Andrews Air Force Ease ATTN: RDTS Washington 25, D. C.

Commander Air Force Command & Control

Development Division Air Research & Development Command U. S. Air Force L. 0. Kanscom Field Bedford, hJassachusetts

Commander Air Proving Ground Center ATTN: PGTRI Eglin Air Force Base, Florida

No. Of Conies Organisation

Commanding Officer U. S. Army Communications Agency The Pentagon Washington 25, D. C.

Commanding Officer White Sands Annex - 3RL White Sands Missile Range New Mexico

Commanding General Array Ballistic Missile Agency ATTN: Dr. C. A. Lundquist

Dr. F. A. Speer Redstone Arsenal, Alabama

Director Advanced Research Projects Agency Department of Defense Washington 25, D. C.

Director Advanced Research Projects Agency ATTN: IDA - Mr. R. Jacobson Department of Defense Washington 25, D. C.

Director National Aeronautics and

Space Administration 1520 K Street Washington 25, D. C.

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UNCLASSIFIED

Doploc observations of reflection cross sections of satellites

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