NRQ APPROVED FOR RELEASE 'SeD \ I-v-1OC i-7__ - 

t , "SEOSTARECIAL-KANDLING1 ,AU ES U ST 2015 (1- ,,.._. , _

MC I j / 1 Mit 

-Al*e7t949r7 - 

12 August 1965 

Jim 

2 (Lc.c.) i 4 

APR 19G8itiivt 

• " h.LO_LI2PL" 

MAY ,1969 IWVTT 

SQUARE TWENTY SYSTEM MA? 19Ggitita1 

TECHNICAL DESCRIPTION 1B7DWY14 

MISSION 7223 SE.P 1973 INV111 

• 

Prepared by ,pac 

L. J. Doll 

Approved by 

Approved by /A. 

- • • • . '„.Y" • 

""'SEC-REZAPECIAL HAN:LING 
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CONTENTS 

PAGE NTJr/TER 

i. SQUARE-TWENTY SYSTEM SIM'L&RY 1 

A. Mission Objectives 1 

B. Signal Of Interest 1 

C. System Hardware Description 1 

D. System Performance 2 

1. Direction Finding Ability 2 

2. Receiver System 2 

II. ANTENNA SYSTEM 

A. Pencil Beam Antenna 3 

B. Fan Beam Antenna 3 

C. Intercept Time Correlation Between The Pencil and Fan Systems 

D. Probability of Intercept 5 

III. PAYLOAD RECEIVER SYSTEM 5 

A. General Receiver Description 5 

B. RF Section 

C. Mixer Section 6 

D. II, Amplifier Section 6 

E. Video Amplifier 7 

F. Video Processors 7 

1. Wideband Video Amplifier 7 

2. Video Peak Detector 7 

3. Narrow-Band Filter Detectors 8 

G. Receiver Outputs Available For Analysis 10 

H. Recognition Signal Outputs 11 

A410 I. On-Orbit Calibrator 12 

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CONTENTS (Continued.) 

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PACE NUMBER 

J. Voltage-Controlled Oscillators 13 

K. Blanking Signals and Band Markers 13 

IV. COMPOSI1E SYSTEM 14 

V. DATA ANALYSIS 14 

A. Signal Identification, Measurement, and Video S/N Analysis 14 

B. Data Correlation Between Receiver Channels 19 

C. Duration of Signal Intercept 19 

D. Receiver Link Calculations 19 

E. Payload Timing 20 

VI. CALIBRATION DATA 21 

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SUPPLEMENTAL INFORMATION 

PAGE NUMBER 

nn Payload Receiver Block Diagram - Appendix I 

Appendix I Abbreviations 

Band Marker Identification - Appendix II 

Orbital System Block Diagram - Appendix III 

Payload Commutator Instrumentation Schedule - Appendix IV 

Pencil And Fan Antenna Plots - Appendix V 

23 

24 

25 

26 

27 

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411 I. SQUARE-TWENTY SYSTEM SUMMARY 

A. Mission Objectives 

The primary objectives of the Square-Twenty System (Mission 7223) are 

to receive and recognize the desired signal of interest, and to locate its 

geographical coordinates. 

B. Signal Of Interest 

The signal of interest is a pulse position modulated (PPM) signal in 

the frequency range of 1550 to 1750 Mcps (twenty-one 10 Mcps channels). 

The peak power of the pulsed carrier at the transmitter output terminal is 

nominally +43 dbm. The signal PU is about 0.5,us and average PRF of the 

composite wave train applied to the transmitter is either 96 or 192 Kpps. 

The 96 Kcps signal represents 12 data channels, each sampled at an 8 Kcps 

rate. The signal modulation frequency range per data channel is 300 to 

"i400 cps. 

C. System Hardware Description 

The payload system is comprised of two directional antennas, two 

receivers, a dual channel recorder/reproducer, and a telemetry system. This 

hardware is mounted on the aft rack of a stabilized Agena which revolves 

about the earth in a nominal 200 nm polar orbit. The stability of the 

vehicle will be maintained within +1.25° about the roll, pitch, and yaw axes. 

The life of the vehicle is anticipated to be 7 to 10 days. 

The directional 6° pencil beam antenna is pointed along the vehicle 

nadir and the energy that it intercepts is presented to the pencil beam 

receiver channel. The 6° x 45° fan beam antenna is oriented such that the 

wide portion of its beam is along the vehicle path with the upper and lower 

3 db points forming angles of 70° (horizon) and 25° respectively with the 

vehicle nadir. The fan beam antenna feeds the fan beam receiver channel. 
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D. System Performance 

1. Direction Finding Ability. 

The pencil beam receiver system can geographically locate the 

target emitter within 2.0.8 nautical miles excluding vehicle attitude 

and timing errors. The fan beam receiver system covers a relatively 

large geographical area thereby enhancing the probability of intercept. 

The degree of resolution will vary widely, depending chiefly on the 

duration of the intercept. 

2. Receiver System. 

The dual receivers cover the frequency range from 1550 to 1750 

Mcps. The target emitter frequency can be measured to within +5 Mcps, 

and the peak power within 3 db from -97 to -57 dbm. 

Because of the limited telemetry bandwidth available to convey 

the received information, a relatively narrow-band video processor is 

employed, rather than a wide-band video analog device, for the purpose 

of recognizing the target signal. In each receiver four sharply tuned 

filters(100 cps bandwidth) are used to monitor the video signal for 

the presence of four discrete frequency components. Two of these components, 96.0 Kcps and 192.0 Kcps, would normally be contained in the 

12 channel target signal, while the other two components, 91.8 Kcps 

and 191.8 Kcps, would not be present therein. 

A simultaneous comparison of the relative amplitudes appearing in 

each filter provides sufficient information to decide whether or not 

the received signal was the one of interest. 

The four discrete frequency components are down-converted to 150 

cps signals, and then frequency multiplexed on the two tracks of the 

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orbital tape recorder. The payload system Is turned on over the 

geographical area of interest. The recorded data are later telemetered 

to the vehicle tracking stations. 

II. AN'T'ENNA SYSTEM 

The two antennas are deployed when the vehicle achieves orbit. The pencil 

beam antenna is directed to intercept the near- 90° side lobes and the fan beam 

antenna to intercept the main beam and higher amplitude side lobes of the ground 

emitter antenna, whose main beam (14° horizontal x 8° vertical) is directed 

toward the horizon for line-of-sight communications. 

A. Pencil Beam Antenna 

The pencil beam antenna is a 6 ft. diameter parabolic dish which is 

oriented such that its 6° pencil beam (+26 db directional gain relative to 

isotropic) is directed along the nadir, or offset by a small angle to 

optimize intercept probability. The pencil beam pattern projects as a 

circle on the earth whose diameter, based upon a 200 nm orbit, is 20.3 nm. 

The field of view includes about 374 square miles and the ground target 

emitter will be in the field of view for a maximum of 5.2 seconds (assuming 

the vehicle speed is approximately 4 nm/sec.) depending on its offset from 

the center of the field of view. The pencil beam antenna provides pinpoint 

location (within 20.8 nm) by,intercepting only the extreme lower amplitude 

side lobes of the ground emitter antenna (20 to 40 db below isotropic) as 

the vehicle passes directly overhead. 

B. Fan Beam Antenna 

The 6° x 45° fan beam antenna, whose directional gain is 17 db relative 

to isotropic, is a 6 ft. long curved rectangular section (truncated cylindrical dish) with a parabolic taper that is positioned to look straight 

forward in the direction of vehicle motion with the wide dimension directed 
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along the orbital path. The upper 3 db point of the 45° beam intercepts 

the earth's horizon at an angle of about 70° with the vehicle nadir, and 

the lower 3 db point at an angle of 25° with the nadir. The slant ranges 

for these angles are approximately 1240 and 368 nautical miles respectively, 

c57, 

The fan beam projection on the earth is a nominal llxbqp nm long; it is 38 

nm wide at the 25° beam point and gradually widens to 130 nm at the horizon. 

Coarse positional fix information may be obtained from the fan system 

by noting the duration of successive intercepts, signal peak power, the time 

of occurrence, and the period between the intercepts in both channels. If 

the intercept occurs only in the fan channel this implies that the signal 

received is either outside the 20.8 nm wide pencil "scribed" path or the 

lower amplitude side lobes of the signal are of insufficient power to be 

received. 

The attitudes of the fan and pencil antennas may be adjusted slightly 

from the angles described herein to optimize signal intercept probability. 

C. Intercept Time Correlation Between The Pencil And Fan Systems 

As the vehicle moves in a northern direction, for example, the fan 

antenna intercepts ground emitter signals at the horizon whose main beams 

are pointed in a southern direction and are within the "view" of the fan 

beam. Then the higher amplitude side lobes of the ground emitter are intercepted, and finally the lower 3 db point passes out of range of the beam 

about 290 seconds after initial horizon contact. The pencil beam follows 

in the same path traced out by the fan beam, except that the width of the 

path is considerably narrower, and should intercept the lower amplitude near 

-90° side lobes of the same ground emitter approximately 310 seconds after 

the signal was first seen at the horizon. This assumes that the signal was 

in the center of the fan beam within +10.h nm when at the horizon. 

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D. Probability of Intercept 

The probability of intercept and the number of intercepts are higher 

for the fan beam system when compared with the pencil beam system. The 

directive gain is 9 db less and the signal attenuation due to space loss is 

up to 15 db more than pencil beam channel, but the fan beam is directed 

toward the main beam and higher amplitude lobes of the ground emitter signal 

whereas the pencil system intercepts the near-900 side lobes. Also the 

area of earth coverage by the fan beam is 974,000 square miles compared to 

374 square miles for the pencil beam. Link calculations reveal, assuming 

the sensitivities at the input to both receiver channels to be -97 dbm that 

the directive gain of the ground emitter antenna must be equal to or greater 

than 10 db to be intercepted by the fan beam at the horizon, compared with 

equal to or greater than -14 db for the 90° side lobes to be intercepted by 

the pencil beam directly overhead. 

III. PAYLOAD RECEIVER SYSTEM 

A. General Receiver Description 

Electrically the fan beam and the pencil beam receivers are identical, 

except in their data presentation of the "no modulation" signal outputs as 

will be described. The receiver block diagram is shown in Appendix I. The 

two receivers are independent, except that they share common sweep circuitry, 

local oscillators, blanking circuitry, band marker generator, and on-orbit 

calibrator. Their sensitivities are -97 dbm; they are synchronously swepttuned (non-locking) linearly across the 1550 to 1750 Mcps frequency band in 

1.8 seconds with an additional 0.2 seconds flyback time. Each new RF sweep 

begins in synchronism with the vehicle clock. Carrier frequency is measured 

• within 4-5 Mcps by noting the time position of the intercept within the sweep 

period. 

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The receivers have linear-logarithmic 3.3 Mcps IF bandwidths capable 

of compressing 40 db RF dynamic range to 25 db at the output of the video 

peak detectors. Each receiver employs 4 active narrow-band filter detectors 

subsequent to its video amplifier for the purpose of identifying whether 

particular modulation frequencies are present in the signals received. Full 

particulars concerning the narrow-band filter detectors are given below in 

part F-3. 

B. RF Section 

The energies from the fan and pencil beam antennas are fed to the fan 

and pencil beam receivers, respectively. The following discussion pertains 

to either receiver channel. The RF energy from the antenna is directed 

through a low-insertion-loss directional coupler to the fixed-tuned, 200 

Mcps pass band, tunnel diode RF amplifier. The RF energy from the on-orbit 

calibrator also passes through the directional coupler, which serves to 

isolate (25 db) the antenna and the calibrator. The receiver pass band is 

further limited by employing 1,925 Mcps low-pass filters on each side of the 

RF amplifier. The filter response is below 40 db from 2,400 to 5,400 Mcps 

where the filters again pass the signal. The effective noise figure for the 

receiver is 5.0 db maximum. 

C. Mixer Section 

The fixed-band RF energy is mixed with the LO frequency which is tuned 

linearly from 1520 to 1720 Mcps in 1.8 seconds. The mixer provides 20 db of 

image signal rejection as a result of using two hybrid 900 couplers, two 

pairs of balanced modulators, and a hybrid ring power splitter. 

D. IF Amplifier Section 

The IF section is comprised of a pair of 30 +4.Mcps preamplifiers, each 

one following a balanced modulator, and a linear-logarithmic 30 +1.65 Mops 

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amplifier which compresses a 40 db RF input dynamic range to 25 db at the 

output. The first 10 db of the response is linear. The effective receiver 

passband for any particular LO frequency is 3.3 Mcps. 

A bandpass filter follows the log IF amplifier. It has a 3 db bandwidth of 3.6 Mcps and a 40 db bandwidth of 8.3 Mcps. Its center frequency 

is 30 Mcps. 

E. Video Amplifier 

The receiver design, from RF to video, is optimized to provide maximum 

video output S/N for signals whose pulse widths are nominally 0.5,ns. The 

video amplifier preserves the 25 db receiver output dynamic range and 

provides sufficient signal to drive three video data processors, i.e., (1) 

via a delay line pulse stretcher and buffer amplifier to provide a wideband 

1 Mcps video output (not used in Mission 7223), (2) a video peak detector, 

and (3) the four narrow-band filter detectors. 

F. Video Processors 

1. Wideband Video Amplifier 

The delay line pulse stretcher is adjustable such that the receiver 

wideband video output pulses can be stretched from 0.5 to 5.0 microseconds. A 1 Mcps reference tone (sine wave) is added to the fan beam 

receiver channel wideband video for the purpose of monitoring wow and 

flutter of the wideband orbital recorder (not used). The frequency 

tolerance of the oscillator is +15 ppm at 25°C. The maximum frequency 

deviation is +30 ppm from 0 to 145°F. 

2. Video Peak Detector 

The peak detector employs an equivalent RC circuit that has a short 

charge time and a long discharge time constant. It depends on a minimum 

charging time of 7.2jus during a 2 millisecond period to perform its 
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its function properly. This corresponds to 16 pulses of 0.45 )is 

duration each. The pulses charge the capacitor to within It of its 

final value. The resistance in the discharge path is sufficiently 

great to hold the capacitor charge to within 1% of its maximum value 

for a minimum of 3 Ms, the time required to be within the transient 

response of the peak detector telemetry channels. The 25 db output 

voltage range of the peak detector will be calibrated in terms cf the 

40 db RF input dynamic range. 

The peak detector circuit is capable of resolving carrier frequency 

bands within +5 Mcps, except in the case where a high-level signal is 

adjacent to a low-level signal. The peak detector output will appear 

as a sinx over x function as the receiver sweeps through the high-level 

signal, and its lower order side lobes may cover over the low-level 

adjacent channel signal thereby making the latter undetectable. 

3. Narrowband Filter Detectors 

Since the wideband video signal is not being telemetered, another 

method is used whereby certain frequency components are filtered from 

the video amplifier output and "read out" for the purpose of identifying 

the signals received. The signal of interest is known to contain very 

stable 96.0 Kcps and/or 192.0 Kcps frequencies, and does not contain 

modulation frequencies below 300 cps. For example, a spectrum analysis 

of the 12-channel signal of interest appearing in the receiver video 

amplifier output would contain a 96 Kcps.channel rate frequency, and 

the second harmonic thereof (192 Kcps). The nearest frequencies to the 

channel frequency and its harmonic should be 95.7, 96.3, 191.7 and 192.3 

Kcps. The pencil and fan beam receivers each employ 4 sharply tuned 

filters to analyze the frequency content of their respective video 

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• signals. Two of the filters (96.0 Kcps and 192.0 Kcps) are tuned to the 

channel-rate frequencies of the signals of interest and the other two 

(95.8 and 192.8 Kcps) are tuned to frequencies not contained in the 

signal. Thus every signal received may be analyzed for frequency content 

by noting the relative amplitude levels appearing in each of the four 

filters, and a judgement can be made as to whether or not it has the 

characteristics of the signal of interest; i.e. if the energy appearing 

at the 96.0 Kcps filter is many times greater than energy appearing in 

the 95.8 Kcps filter, and/or the energy appearing at the 1920 Kcps 

filter is many times greater than the energy in the 191.8 Kcps filter, 

the signal is said to have been identified. 

The video signal is passed through a limiter, which eliminates the 

upper 15 db range of the video amplifier, and is presented to four 

parallel narrow-band filter detectors. Each narrow-band device includes 

a mixer, stable local oscillator and 150 +50 cps band-pass filter. Each 

local oscillator is tuned to a frequency that is 150 cps above or below 

the desired filter frequencies. It is necessary to "down convert" the 

96.0, 192.0, 95.8, and 191.8, Kcps frequencies to a lower frequency 

such as 150 cps in order to conserve information bandwidth. 

The four crystal oscillator frequencies are held to within +150 ppm 

over the 0 to 145°F temperature range. 

The 150 cps active filter bandwidth is 134 cps at -3 db and 242 

cps at -30 db. 

In the pencil beam receiver each of the four 150 cps filter output 

frequencies modulates a voltage-controlled oscillator whose output is 

• directed to the telemeter system. In the fan beam receiver only the 

150 cps analog signals proportional to the 96 and 192 Kcps "yes" frequencies are made available for analysis. The "no" or "not" frequencies 
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are combined via a comparator circuit into a four-level digital signal. 

The "yes" signal amplitudes are compared with the "no" signal amplitudes 

resulting in four possible conditions as described below in Part H. 

The four-level signal modulates a voltage-controlled oscillator and 

thereby serves as a "recognition" signal for the fan beam channel. It 

is important to note that this signal should not be relied upon 

entirely as an indicator for whether or not to monitor the "yes" 

signals from the fan beam channel. The digital level indicates recognition if either or both of the "yes" energy levels are 15 db or greater 

than the "no" levels. If the received signal power is marginal (near 

-97 dbm) it is possible that the energy in a "yes" filter could be 

considerably greater than the energy in its "negative" counterpart, but 

not 15 db. Thus there would be no recognition indication; however, the 

received signal Would be the one of interest. 

Also a two-level recognition signal is developed as a byproduct 

of the four-level signal. It therefore has the same limitations as 

the four-level signal, and it provides a recognition indication only if 

the video amplifier S/N exceeds about 4 db and either of the two 15 db 

S/N level requirements is exceeded. The two-level signal is routed to 

the payload commutator, and to the wideband recorder to serve as a 

"start signal". The wideband recorder will not be used in Mission 7223. 

G. Receiver Outputs Available For Analysis 

Signal outputs recorded during the payload system operation period and 

later replayed via the telemetry link for analysis are as follows: 

1. Payload commutator - provides payload temperature and power.supply 

voltage data; vehicle time; radio frequency monitor, fan beam 

channel recognition indicator (2 level), and on-orbit calibrator 

on-off monitor. 

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2. Pencil Beam Channel - 5 analog outputs, one RF peak detector, and 

four 150 +50 cps filter outputs whose energies are proportonal 

to the amplitude of the 96.0, 95.8, 192.0 and 191.8 Kcps frequencies contained in the received signal video. 

3. Fan Beam Channel - 3 analog outputs and one four-level digital 

output. The analog outputs are the fan beam RF peak detector and 

two 150 +50 cps filters whose outputs are representative of the 

96.0 and 192.0 Kcps energy detected in the fan receiver video. 

The four-level digital output serves as a recognition indicator 

for the fan channel. It is derived from threshold and comparator 

circuitry which logically examines the video signal threshold and 

compares the amplitude ratios of the four 150 cps filters 

identical to those used in the pencil channel. The four-level 

digital signal was developed in lieu of using the analog outputs 

of the 95.8 and 191.8 Kcps detectors because: (1) only one telemetry voltage-controlled oscillator is required to convey the 

digital signal while two would be required for the analog signals, 

(2) a recognition signal was required to start a 1 Mcps recorder 

(not used for this mission). 

H. Recognition Signal Outputs 

Two recognition signal outputs, one two-level signal, and one four-level 

signal are available for analysis from the fan beam channel only. The fourlevel signal is a logical signal, developed as mentioned above in paragraph 

0, which relates the following information about the signal received: , 

1. Level 1 - negative recognition (0.0 V) 

2. Levels 2, 3 and 4 respectively: the 150 cps energy from the'96.0 

Kcps detector is greater than 15 db above the 95.8 Kcps detector 

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energy (1.65 V); the 150 cps energy from the 192.0 Kcps detector 

Ss greater than 15 db above the 191.8 Kcps detector energy (3.3 V); 

both of the last two statements are true (4.95 V). 

The two-level signal is developed from the four-level logic. It provides 

the following information: 

1. 0-VDC level - negative recognition. 

2. /1.5 V peak, 100 MS pulse - implies that both the peak RF signal 

power at the fan receiver input terminals is equal to or greater 

than -93 dbm, and the 96 Kcps detector output is 15 db greater than 

95.8 Kcps detector output and/or the 192 Kcps detector output is 

15 db greater than the 191.8 Kcps detector output. The two-level 

recognizer is disabled during the on-orbit calibrator period. 

411 I. On-Orbit Calibrator 

An internal payload calibrator simultaneously applies signals to both 

receiver RF amplifiers to verify normal payload performance. The characteristics of the calibration signal are: 

1. Power: -87 +3 dbm. 

2. Freq.: 1575 + 2 Mcps. 

3. Duty Cycle: On for z second every 32 seconds in synchronization 

with the vehicle clock and the receiver sweep generator. 

1. Modulation Signals: On odd-integer multiples of 32 seconds the RF 

carrier is pulse modulated at a 96 Kcps rate thereby causing 150 

cps energy to appear in the 96.0 and 192.0 Kcps detector output 

circuits and no energy in the "not" filter outputs. On even-integer 

multiples of 32 seconds the RF carrier is pulsed by a 96 Kcps wave 

train which is gated on and off at a 200 cps rate thus causing 

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energy to appear in all filter circuits. The 150 cps energy 

appearing in the 96 Kcps and 95.8 Kcps detector is 3 db and 10 db 

respectively below that for a continuous 96 Kcps wave train. The 

same relative ratios are true for the 192 Kcps component whose 

amplitude is about 1 db less than the 96 Kcps component. 

J. Voltage-Controlled Oscillators 

Standard IRIG VCO's are used as FM subcarriers to convey the pencil 

beam and fan beam channel output signals. 

listed: 

Pencil Beam 

VCO Channel Channel Output 

The channel assignments are 

Fan Beam 

Channel Output 

10 Peak detector Payload Commutator* 

11 150 cps (191.8 Kcps) Peak Detector 

12 150 cps ( 95.8 Kcps) Four-level Comparator 

13 150 cps (192.0 Kcps) 150 cps (192.0 Kcps) 

14 150 cps ( 96.0 Kcps) 150 cps ( 96.0 Kcps) 

*Conveys pencil and fan beam receiver data. 

The five VCO outputs from the pencil beam channel (pencil beam composite 

video) are summed and directed to track one of the 25 Kcps/100 Kcps recorderreproducer. The five VCO outputs from the fan channel are combined. with a 

stable 25 Kcps reference tone (fan beam composite video) and applied to the 

second track of the payload recorder-reproducer. 

The 150 cps analog signals which drive the VCO's directly, are amplitude 

limited. to a 25 db range in order to be compatible with the input dynamic 

range of the VCO's. 

K. Planking Signals And Band Markers 

Kanking Signals are generated and inserted as required in the video 

processor to blank the fan and pencil Channel output signals during the 0.2 
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sec. flyback portion of the receiver sweep. Also )40 millisecond pulses 

are added to all processed output signals which serve as amplitude calibration markers. The leading and trailing edges of these markers provide 

time reference points for receiver sweep start and stop. The band markers 

are specifically identified in Appendix II. 

IV. COMPOSITE SYSTEM 

Orbital System Description And Operation. 

A block diagram of the pertinent composite orbital system showing tho payload 

receivers, antennas, commutators, clock, tape recorder, and telemetry system is 

shown in Appendix III. 

The payload receivers, commutator and tape recorder are turned on simultaneously by preprogrammed punched-tape commands for a 24 minute read-in period. 

The composite pencil beam video and the composite fan beam video are recorded 

simultaneously on tape recorder tracks 1 and 2 respectively (300 cps to 25 Kcps 

response). Vehicle timing and payload response and status data are commutated 

and modulate a channel 10 VCO which is multiplexed in the composite fan beam 

video signal. 

Another preprogrammed command and/or real time command initiates a 6 minute 

read-out period whereupon the recorder data are relayed, at four times the readin speed, via two FM transmitters to the tracking station receivers. 

In addition, real-time timing outputs and vehicle attitude information are 

commutated by a real time "housekeeping" commutator and telemetered via a third 

vehicle FM link. 

V. DATA ANALYSIS 

A. Signal Identification, Measurement, And Video S/N Analysis. 

To decide whether or not the received signal has characteristics 

identical to the one of interest, it is necessary to compare simultaneously 

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- 15 - • the amplitudes of each of the 150 cps signals contained in a given receiver 

channel composite video signal, i.e., for example, in the pencil channel 

note the simultaneous S/N's of the peak detector and the four narrow-band 

detector outputs. The bursts of energy from the detector outputs are 

delayed about 15 Ms from the peak detector output because of the rise time 

of the 150 cps filters. The center of the burst of peak detector energy 

relative to its time position between the band start and end markers 

determines the received signal frequency. The peak detector S/N is directly 

proportional to the received signal RF power. The peak detector S/N measurement may be used as a guide to decide whether or not to analyze closely the 

narrow filter outputs. Received signals whose peak powers are greater than, 

say, -80 dbm, are not likely to be the signal of interest. 

The S/N ratios of the four narrow-band detector outputs should be carefully analyzed since they provide the greatest weighting for signal 

identification. To understand the implication of the narrow-band filter it 

is necessary to consider the characteristics of the video processor and its 

associated interface. Refer to the receiver block diagram in Appendix I. 

The wideband video signal input to the narrow-band detector is limited to 10 

db maximum and the narrow-band output is confined to a nominal 25 db dynamic 

range. It is possible to predict the S/N appearing at the output of a given 

narrow-band detector using the following expression: 

Narrow Band Video C/A 

Detector Output S/N = S/N 

(db) (db) (db) 

Video S/N (db) is the signal-to-noise, expressed in db, at the input 

to the narrow-band detector. 

C is the amplitude in volts of a frequency of interest contained in t'o 

receiver video, e.g. 96 Kcps. 

"N4 e 

t5',4) L,L1AL A N 

NIT 

(db) 
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• A is the amplitude in volts of a PPM pulse train contained in the 

receiver video. 

C/A (db) is 20 log C/A and varies as a function of pulse width, duty 

factor and percentage channel modulation. 

NIF (db) is the signal-to-noise improvement factor (in db) gained by 

band-passing only 100 cps out of a 1.65 Id cps video signal. 

For illustration consider a 12-channel signal with the Pollowing 

characteristics: pulse width 0.7,usec, sync channel modulation 107), data 1

channel modulation 401. To determine the narrow-band detector output signalto-noise ratio for a 96 K cps component proceed as follows: 

Narrow Band Video Video 

+ (-19.6 db) ± 37 db = 

Detector output S/N (db) S/N (db) 

17.h db 

S/N (db) 

Note: The 96 K cps component is about 19.6 db below the video 

peak signal. 

The NIF (db) for a 150 + 50 cps filter output is about 37 db. 

If the resultant expression is evaluated for a video S/N range of 0 to 

10 db the narrow-band detector output range for this particular signal is 

17.4 db to 25.0 db, 1.e. signals 7.6 db above the nominal receiver sensitivity 

db 

of -97 dbm would be limited taCJI because of the filter output range 

restriction, and signals 10 db or greater than -97 dbm would also be 

limited because of th 10 db Ti.17;;C:sle3)on the narrow-band detector input. 

The latter limitation is of no significance in this example since the output 

range limitation prevailed first, but may take precedance in other situations. 

In this particular example, the input signal power can be less than -97 

dbm, thereby resulting in a negative wide band video S/N, and yet provide a 

positive narrow-band detector output S/N ratio as large as 17.4 db. 
NRO APPROVED FOR RELEASE 

' 1 AUGUST, 2015 

■•■

41 

v t. 1? 

AA AW01884 

• 

- 17- 

Consider, for comparison, a 12-channel signal identical to the previous 

except that all channels are present but not modulated. C/A is about -17.4 

db therefore the narrow-band-output range would vary from 19.6 to 25 db if 

only positive wide-band video S/N ratios were considered. 

Consider another example for a 12-channel signal identical to the 

previous except that all data channels are modulated at 80%. C/A is about 

-31 db thus the narrow-band output range would vary from 6 to 16 db if only 

positive wide-band video S/N ratios were considered. 

In summarizing it is apparent from the preceding equation and the 

associated examples that the output range of the narrow-band detectors is 

restricted to a maximum dynamic swing of 10 db which may occur anywhere in 

the 25 db output range (.28 to 5.0 volts). This conclusion is based on 

positive video S/N ratios only. The relative position of the 10 db band 

within the 25 db range is determined by the signal power, pulse width duty 

factor and percentage channel modulation, and the narrow-band filter 

detector noise improvement factor. The 10 db band is widened when negative 

video S/N ratios are considered, the degree of which is directly related. to 

the capability of the narrow filter to remove the desired signal from the 

video noise. 

Knowing the general capability of the video processor and recalling the 

signal identification criterion established in III-F3 it is interesting to 

note that any of the following combinations, referred to as "cases", of S/N 

ratios could be due to a valid signal. Only the 96 K cps "yes" filter and 

the 95.8 K cps "no" filter are considered in this illustration. 

• 
, 1 AUQUS015 4CarreSPECIAL. IIADLING NRO APPROVED FOR RELEASE 

AW018e4 

Case 

Possible Filter Combinations Due To Valid Signal 

"Yes" Filter Output "No" Filter Output 

S/N Range S/N Range 

1 1 to 14 db 0 db 

2 15 to 25 db 0 to 10 db 

3 filter output saturated ( 25 db); 10 db to saturation; 

or limited to a 10 db band or limited to a 10 db band 

within the 25 db range within the 25 db range ' 

Case 1 indicates that the received signal may be defined as valid with 

as little as 1 db S/N appearing in the "yes" filter. Obviously the confidence factor improves directly as the yes-to-no ratio increases. Case 2 

shows the range of optimum receiver performance. The yes-to-no ratio of 15 

db used in the fan channel recognition circuitry should not necessarily be 

considered as the ultimate signal identification ratio when evaluating the 

pencil channel analog signals. 

Case 3 is theoretically impossible since there is no 200 cps energy in 

the modulation signal, and no 95.8 Kcps carrier sidebands exist; but 

practically it should be considered, especially since the dynamic range of 

the narrow-band filters could be limited to a 0 to 10 db S/N band over the 

25 db VCO input amplitude dynamic range. Depending on the amount of 95.8 

Kcps noise present, particularly in the fan channel which views a relatively 

large geographical area, it is possible to have enough energy appear in the 

95.8 Kcps filter output to affect the valid signal confidence factor. 

A detailed analysis of the fan beam channel data will be more difficult 

relative to the pencil beam channel in regard to determining whether or not 

the received signal was valid, because only two analog "yes" signals and a 

foar-level digital recognition signal are available. The digital logic • responds as indicated in Part III-N. This signal would indicate positive 

c:'ECIAL HANDLIN 
NRO APPRO

UOUST 2015 

VED FOR RELEASLL,,, a 

1 ,A HAND LIN' 

AW0194 

- 11 

recognition for Case 2 only. It would never indicate recognition for 

Case 1 and may or may not indicate recognition for Case 3 depending on the 

relative yes-to-no ratios. 

B. Data Correlation Between Receiver Channels 

It is desirable to correlate signals appearing in the pencil channel 

.with those in the fan channel. particularly since the pencil channel refines 

the geographic location. 

There is a time lapse between when the signal appears in the fan 

channel and reappears in the pencil channel which may vary from 20 to 310 

seconds. Thus it is necessary to slide the data from the pencil channel 

backward along the time scale and correlate them with signals in the fan 

channel which have identical carrier frequencies. 

C. Duration of Signal Intercept 

Pencil Beam Channel - The pencil beam antenna intercepts any particular 

ground emitter signal for a maximum period of 5.2 seconds, assuming tie 

vehicle speed to be 4 nm/sec Therefore a maximum of 2 successive bursts of 

energy, spaced 2.0 seconds apart, will appear in the receiver video. One 

burst occurs each time the receiver sweeps through the IT carrier (receiver 

sweep rate - q Ms/Mcps) and each burst lasts about 29 Ms (effective 

receiver bandwidth - 3.3 Mcps.) 

Fan Beam Channel - Theoretically the fan beam antenna could intercept 

a ground emitter signal for 290 seconds, thus 1i5 consecutive bursts of 

energy would appear in the fan beam receiver video. The burst duration and 

the spacing between intercepts is the same as for the pencil beam channel. 

D. Receiver Link Calculations 

A comparison of the link calculations for the fan beam and pencil beam 

receiver channels shows that for signal identification in the fan receiver 

---•-■77..r.r7, 7,11;:,..j... 
' • 

NRO APPROVED FOR RELEASE 

1 AUGUST 2015 `4. 

Awo1884 

• channci the ground emitter antenna gain must be +10 db or greater at 70° 

(.h-rl-rr) andq or greater at 250 (lower 3 db point), and for signal 

identification in the pencil receiver channel the ground emitter antenna 

gain (lower order side lobes) must be -14 db or greater. 

- 17 • - - ; Al 

These results were obtained using the following expression: 

Mi T= nimum Receiver 

Ground Space Sensitivity Ground 3 db Point 

Emitter = Atten. Required XMTR Gain of 

Antenna In For Signal Peak PWR Receiver 

Gain DE Identification in DB Antenna 

In 177 In DB 

csi 

TY.k Receiver Ground 3 DB 

Antenna Space Receiver XMTR Receiver 

Angle With Range Atten. Sensitivity Peak Pwr. Antenna 

dadr (N (DB) (PPM) (PPM) Gain 

70° (Nori7on) 1240 101 -W (Fan 4- 14 (Fan) 

Chan) 

25° ":168 154 .40T (Fan 43 14 (Fan) 

nan) 

, , (nadir) o 200 145' AMr (Pencil 1-[ 23 (Pencil) 

...,•,56 

c,-..., -:•;. / • ) /Li'--. -/o-o Chan ) '22), •-:,,,,,./:', 

A 200 rim orbit is assumed. 

E. Payload Timing 

A special 32 hour (nominal)cicck is incorporated in the vehicle which 

serves to back up the FT-timer data, and provides timing resolution during 

the fead-in. period. In addition to its five eight-level timing outputs (-

second least significant bit) it has a 1 pps output which is used. to 

s ,nchronize the start of each receiver frequency sweep once every two 

seconds. (Recall that both receivers are swept simultaneously by a common 

ramp generator.) 

The f? ve 

pc.r: . 71ey 

vehicle timing outputs are recorded during the payload read-in 

are read out with the other recorded data when the vehicle 

• /',sses over the tracking station. While the stored data are being read out, 
NI APPROVED Pc:5R RtL 

' 1 AUdUST,2015 k Iii !L..: 

- 21 - 

the clock 4 sec level is also read out, thereby providing evidence that 

the vehicle clock is functioning, and a cclerse reference to check the 

timing accuracy of the Ii-timer data. 

VI. CALIPRATION DATA 

System level calibration data will be provided in a supplement to this 

document. 

• 

• 

AW01884 
NRO APPROVED FOR RELEASE. 0<" 

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AWO1PP); 

- 23 - • APPENDIY T ABBREVIATIONS 

D/C Directional Coupler 

P/D Power Divider 

LPF Low Pass Filter 

RF TDA Radio Frequency Tunnel Diode Amplifier 

HYB COUP Hybrid Coupler 

IF P/A Intermediate Frequency Pre Amnlifier 

IF 0/A IF Output Amplifier 

DET Detector 

V/A Video Amplifier 

BLK Blanking Signal 

M1(B Marker Signal (Band End and. Band. Start) 

• UJO Unijunction Transistor Oscillator 

BW Band Width 

STR Stretcher 

S/A Summing Amplifier 

F2 96.0 KC Energy Present in Video Signal 

Fp 95.8 KC Energy Present in Video Signal. 

2F2 192.0 KC Energy Present in Video Signal 

2F2 191.8 KC Energy Present in Video Signal 

NBV Narrow-Band Video 

WBV Wide-Band Video 

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- 

APPENDIX IV 

PAYLOAD COMMTATOR IUSTRUKENTATION SCITEDULE 

Comm. 

Chan. O.T.E. 

Comm. 

Chan. O.T.E. 

No. No. Monitor (Voltage Level) No. No. Monitor (Voltage Level) 

1 1 Freq. (1 to 5 V) 31 1 Freq, 

2 2 Fan. Recog. (0; )4.5 V) 32 Recog. 

3 3 +28 V Reg. (4.6v) 33 9 Pwr.Supp. Tempi (.3 to 5V) 

L_: /I On-orbit Cal. (0; 1i.5 V) 34 4 On-orbit Calib. 

5 Vehicle clock - 4 sec. 35 Spare 

6 1 Freq. 36 1 Freq. 

7 2 Recog. 37 2 Recog. 

8 5 +4, g, -6V Pwr.Supp.(2.0V) 38 10 +12 Reg.Pwr.Supp. ()4.5V) 

9 Cal Z 39 Veh. Clock -2,04e sec. 

10 14 200 MS Planking (-Flyback) 40 14 200 MS Blanking 

11 1 Freq. 41 1 Freq. 

12 2 Recog. 142 Recog. 

13 6 +12 V Pwr.Supp. (4-5 V) 43 11 Pwr. Supp.Temp, 2 (.2. to 5V) 

14 Veh. Clock -32 sec. 44 Spare 

15 Spare 45 Veh. Clock - 4 sec. 

16 1 Freq. 46 1 Freq. 

17 2 Recog. 47 2 Recog. 

18 Rectified LO RF Pwr.(2.5V) 48 12 On-orbit Cal Osc.Temo. 

(.3 to 5V) 

19 4 On-orbit Calib.- 49 4 On-orbit Calib. 

20 Spare 50 Spare 

21 1 Freq. 51 1 Freq. 

22 , 2 Recog. 52 , 2 Recog. 

23 8 +6, & -8v Pwr.Supp. (4.5V) 53 13 Grd.plane Temp. (.3 to 5V) 

24 14 200 MS Blanking 54 Veh. Clock - 16,394 sec. 

25 Veh. Clock - 4 sec. 55 14 200 MS Blanking 

26 1 Freq. 56 1 Freq. 

27 2 Recog. 57 2 Recog. 

28 Veh. Clock - 256 sec. 58 Sync 

29 Cal + 59 Sync 

30 Cal 60 Sync 

• 

• 

HANA1NL 
N SPILLOVER 

‘ 1-21-4--1- FROM FAN-FLEX 1 

AW01.884 

APPENDIX V. 

E TICAL POLARIZATION COMPONENT 

FAN-FLEX AND FLEX-RIB REFLECTORS 

FED WITH A 

CONICAL SPIRAL FEED 

ON THE AGENA VEHICLE 

8-9-65 

crrorT enrri AI A MINI Mit 

CtrAtEitAN: 

- 27 - 

EARTH SIDE 

FAN--FLEX 

FAN BEAM 

- FLEX-RIB • VEHICLE 

PENCIL BEAM 

180° 

270° 
NRO APPROVED FOR RELEASE 

1 AUPUST 2015 

SECRET-,,' :LIZLING 

28 

AW01884 

ADDENDUM 

27 October 1965 

SQUARE TWENTY 

SYSTEM CALIBRATION DATA 

MISSION 7225 

THIS DOCUMENT IS A SUPPLEMENT TO AW01884, 12 

AUGUST 1965, "SQUARE TWENTY SYSTEM TECHNICAL 

DUCCRIPTION" 

Prepared by 14.4 Approved by -, - - 

L. . Doll W. M. Harris 

Prepared by, adri 

L. P. Whitlock 

• 

VMr 
• 

NRO APPROVED FOR RELEASE 

1 AUGUST 2015 

•tS, ' II'INDLING h 

29 

7225 CALIBRATION DATA PARTICULARS 

I. CALIBRATION DATA CONSTANTS 

AW01884 AddendUm 

A. Temp: 75°F unless noted. 

B. Low pass filters used to generate CEC records from which calibration data 

was reduced: 

SCD LFFFAN LPFpEN 

10 125 cps 160 cps 

11 160 cps 160 cps 

12 160 cps 160 cps 

13 160 cps 160 cps 

14 225 cps 225 cps 

C. Values for calibration markers used to obtain Cal data from CEC records. 

Values were measured at receiver test points. 

Receiver 

Outputs 

Band Start 

Markers 

Band End 

Markers 

PK DET +2.4 4.85 

F

2PEN -2.45 2.4 

F2PEN -2.4 2.3 

2F2PEN -2.5 2.4 

2T2PEN -2.4 2.3 

PK DETFAN 2.5 5.0 

F2FAN -2.4 +2.5 

2F2FAN +2.4 2.6 

4 level Detector +2.4 +4.8 

SECRET. 57"C::4,7.4 1111NDLING 
NRO APPROVED FOR RELEASE 

1 AUGUST 2015 

, 

IELeRET7S 47 : it la IIANDLING 

AW01884 Addendum 

II. SCOPE OF CALIBRATION DATA 

Al] calibration data represents receiver performance via the entire orbital 

system. 

III. ON-ORBIT CALIBRATOR 

The internal Radio Frequency Calibrator (RFC) power response was measured and 

superimposed on the power response graphs. The Input Signal power required 

to equal the RFC power response of the particular detector is shown. The 

Input Signal constants, which are applicable, are listed on the graphs. 

IV. FAN BEAM CHANNEL CALIBRATION DATA 

In general the calibration curves for the pencil receiver will suffice for 

the fan receiver. If a more precise fan beam receiver calibration 

data accuracy is desired, see the tabulated chart which shows the "fine" 

differences between the fan and pencil receiver response to input signal power 

and the on-orbit calibrator. 

S 
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