PROGRESS REPORT MISSILE MONITORING PROGRAM

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• Collection: General CIA Records
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• Document Page Count: 48
• Document Creation Date: December 22, 2016
• Document Release Date: February 1, 2012
• Sequence Number: 4
• Publication Date: January 22, 1962
• Content Type: REPORT

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Progress Report
F
NUMEMMAIM
Of fice of Naval Research
? ? 11
P
ALEXANDRIA, AERO GEO ASTRO
CORPORATION
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SECURITY NOTICE
THIS DOCUMENT CONTAINS INFORMATION AFFECTING THF NATION,
AL DEFENSE OF THE UNITED STATES WITHIN THE MEANING OF THr
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A.G.A. Log No. 1111 Page 1 of 45 pages
Copy of 6c) Copies
PROGRESS REPORT OF
MISSILE MONITORING PROGRAM
(Short Range)
(May to August 1961)
22 January 1962
Aero Geo Astro Corporation
13624 Magnolia Avenue
Corona, California
Prepared under Office of Naval Research Contract 3163(00). A portion
of the effort described is jointly supported by the Advanced Research
Projects Agency and is directed by Rome Air Development Center under
ARPA Order 235-61.
NOTICE: This document contains information affecting the national
defense of the United States within the meaning of the Espionage Laws,
Title 18, USC Section 793 and 794. The transmission or the revelation
of its contents in any manner to an unauthorized person is prohibited
by law.
EXEMPTED FROM AUTOMATIC
DOWNGRADING BY
Capt. H.E. Ruble, Deputy
and Assistant Chief of
Naval Research
BOO ---4- REV DATE ;$ BY 3
ORIC COMP OPI TYPE
ORIG CLASS PAGES REY CLASS
JUST NIX1 REV Auiri: A i8-E
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I. INTRODUCTION
II. DISCUSSION OF SHORT RANGE EXPERIMENT
A. Geometry
B. Artificial Atmospheric Geometry
C. Target Characteristics
D. Expected Signal Intensity
E. Receiving System
F. Calibration
G. Major Difficulties
III0 MEDIUM AND LONG RANGE DETECTION EXPERIMENTS
A. Monitoring System
B. Calibration
C. VLF Bi-Static Radar Equation
IV. DATA
V. PACIFIC MISSILE RANGE TESTS
V+1. ATLANTIC MISSILE RANGE TESTS
SFCR FT
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1. INTRODUCTION
Aero Geo Astro Corporation operated a VLF missile monitoring site located
south of Miami, Florida, from May to August 1961. The primary purpose of the
experiment was to study the reflections from missile trails and/or ionospheric
perturbations using artificial atmospheric noise generators as the illuminating
source. In addition to this, two high range resolution (less than 20 miles)
Floor system,, were operated during this period. They used atmospheric noise
originating in thunderstorm areas as the illuminating source on frequencies of
10 Kc and 25 Kc. Detections on these radars extended the frequency coverage of
VIA' backsc .tter measurements outside the previous 14-22 Kc region. Discussion
of mediirn and long-range detection at other AGA sites has been included in this
report in order to give a more complete picture of the VLF research.
II. DISCUSSION OF SHORT-RANGE EXPERIMENT
A. Geometry
The Aero Geo Astro monitoring equipment was located at Richmond
Naval Air Station, south of Miami, Florida, which is at a range of
about 200 miles from Atlantic Missile Range launches (Figure 1). One
of the ,artificial atmospheric noise generators was shipborne in the
general area of Fort Pierce, Florida. Dater in the monitoring period,
a second generator was activated near Avon Park, Florida. The Aero
Geo Astro site was near the range limit for the direct line-of-sight
to the missile at D layer altitudes. This site location was chosen
{or technical reasons to be described later and since the shorter
range areas were already instrumented.
B. Artificial Atmospherics Generator 1
The transmitter used for part of the studies described in this
report was an artificial atmospherics generator operating in the fre-
quency range of 19-28 Kc. In operation of the generator, capacitors
are charged in parallel to a voltage of about 50 killovolts each and
then switched through an initiating gap system to a series arrangement
to produce an impulse with peak voltages of 1-to-2 million volts. A
multiple gap trigger system is utilized to provide a smooth wave form
with a typical transmitted pulse length of about 1/5 millisecond.
1 "Artificial Atmospherics Generator,'t Lightning and Transients Research
Institute Report No. 326, September 1957.
SF.CRFT
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The peak radiated power is generally on the order of 10 megawatts,
(strongly dependent on the antenna length). The antenna utilized
was either a helicopter- or balloon- supported vertical wire. The
transmitter emitted a pulse every six seconds on the order of 70
milliseconds before the WWV pulse. The direct pulse received at the
monitoring site had a fairly sharp rise and a smooth exponential de-
cay.
C. Target Characteristics
Theoretical studies 792 have predicted scatter cross sections in
the VLF region from about 106 to 108 square meters. Both short and
long range measurements have., in general, yielded within this range.
Theoretical. studies have indicated that the ionization should last
for a considerable time just below the D layer and this has been
confirmed with experimental results which have shown echo durations
of up to 30 minutes or more. The experimentally measured echo
duration appears to be primarily a function of the signal-to-noise
or signal-to-clutter ratio with the large signals lasting much longer.
(Most of the recent Florida short-range measurements have yielded
fairly short duration signatures.)
Tho reflection pattern of the trail, or perturbation., in the VLF
region is far from well defined. Occasions have arisen in the past
where good long-range signatures were detected while the same event
viewed "in-close" produced a poor signature. This could indicate
some aspect sensitivity in the vertical plane and was one reason for
chosing the Miami recording site. This allows a different target
aspect to be viewed than would be seen from the close range recording.
While the shape of the trail may be quite different from cylindrical,
some indication of the possible types of patterns may be obtained by
looking at cylindrical reflection patterns for varicus lengths.
Figure 2a. shows the reflection patterns of thin cylindrical reflectors
of 1/2 and 1-1/2 wavelengths long3. It is noticed that for the
shorter trail, the peak reflection would be normal to the cylinder;
while for the longer trail., the peak reflection has changed direction
considerably. Figure ?b shows the normal, or broadside, cross section
1 "Theory of Exhaust Trail Reflections at VLF.," Paul Von Handel, Symposium on
Detection of Ionospheric Perturbations., Stanford. University, 20 June 1960.
.irroughs, NOLC
2 'tMides Interim Report.," D. J. Adrian, R. H. Espeland., H. H.B
Tech. Memo No. 15-23, 18 January 1960.
3 "-Radar Response From Thin Wires.," C. T. Tai, Stanford Research Institute
Report No. 18, March 1951.
RF,C:R FT
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IOL
.19
.40
..8
.26
.00
Nlsfi'a /1,
SO &: T 80 9!7 1W //D /,20 /.90 AV /GO
DEGREES
Figure ?a. Reflection Patterns of Thin Cylindrical
Reflectors
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Q V 0 V ' T
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versus length. It is seen that if this aspect is viewed, it is
possible for a longer trail to give considerably smaller reflection
than a shorter one. These effects., among others, have made it
impossible thus far to draw any firm conclusions from the experi-
mental data about the cross section versus frequency behavior of
the reflector. Vertical aspect sensitivity can give rise to very
marked differences in detection between two different short-range
receiving stations, while medium and long-range stations, in
general, view the same vertical aspect.
1). Expected Signal Intensity
An estimate of the echo signal intensity may be obtained as
follows: "Assume that the transmitted power spreads out uniformly
over a hemisphere with radius equal to the transmitter-to-missile
range. The power density at the missile trail, or perturbation,
is then
Po Po
Pi W AA 2n (dl 0 h
(1)
where d1 is the ground range to the missile and h is the height
of the ionosphere. The reflected pwer from the trail is then
P = pia-
(2)
where o' is the backscatter cross section. It is then assumed
that this energy spreads out over a hemisphere, with a radius equal
to the missile-to-receiver range, to give the received target power
density., as shown in
p r Pod (hemisphere) 11 9
(2n)2 (dl + h ) (d2 + h )
The power density may be related to the field intensity by the
known relation
E2 = 120n Pr
(3)
An alternate method of computing the signal attenuation is to assume
CL`nID LUT
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that the transmitted and reflected energy spreads out uniformly
in the cylindrical region bounded by the ionosphere and the earth.
Under these assumptions, the received echo power density is
pr 0 Po _ (cylinder)
(2_rih) dld2
It is believed that the hemisphere approximation would be the most
nearly correct at very short ranges, while the cylindrical surface
case would be a better approximation at somewhat larger ranges. The
expected field intensity versus range, asguming a transmitted power
of 10 megawatts and a cross section of 100, n -, is shown in Figure for both cylindrical and in,77ers; range squared appro.ximati.ons.
Receiving System
A simplified block diagram of the recording equipment, is sho-.,rn in
Figure 1.o The operation is as follows: The VLF pulse from either
lightning, or the artificial atmospherics generator, is picked up
on the tuned 25 Kc loop with a 6 Kc bandwidth. (It was necessary too
. ave this wider than desired bandwidth since the transmitted fr:qu^~ r
of the artificial atmospherics generator was not known prior to a teat,)
The reference and echo signals are amplified and the various VLF
station signals are notched out with 50 db rejection .filters. The
reference signal is delayed in a sonic delay line system an amount
equal to the round trip propagation time to the target. This delayed
pulse is then used as reference signal for the dual channel RF corre.-
l.ator. A similar system centered at 10 Kc with a bandwidth of about
2 Kc was also in operation.
The general operating procedure was to record on magnet' (c tape
the four RF signals (two reference and two scatter) and the WWV timing
signal. The station was also operated on 25 Kc with 1trealmtime1e
processing with the time delay et for the artificial atmoepheri o
generator (if there was a possibility that it would be operating
during the test). If word was recei-red that the generator would
definitely not be operating, then the direct paper readout system
was changed to operate in the Licor mode, generally on the 10 Kc
channel. After the test, the usual procedure was to send the taped
signals through the processing system, using several different delsyE
and taus determine the echo range i .." a signature was present.
The advantage of the correlation technique over that of viewing
single pulse echoes depends upon the number of independent samples
occurring during the integration time and on any excess bandwidth
c1`ri imr
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(2) l-qw) Cam) ( 4VO (6) C
D157AMCE(e,W) AVV- lRI.E (FifflM MP ffr)
Figure 3. Field Intensity versus Rang.
circa i'-r
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I --I
a
Q `~ W
g W ~~
la -14b-
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required to accomodate the uncertainty in transmission frequency.
Due to the extremely low duty cycle of the artificial atmospherics
generator, the advantage of the correlation system over a direct echo
system was only about 12 db in this case, compared to between 20
and 40 db in the usual VLF monitoring. However, this advantage was
quite important in the Miami operations since the output signal-
noise ratios were below 12 db. It was also possible that the system
might be of some advantage in seeing a target against a multi-hop,
or clutter, background once both phase and amplitude information
are recorded.
In some of the later monitoring, a direction-of-arrival gating
system was incorporated into the Miami Licor station. This system
makes use of the conventional"look"df system with the directional
ambiguity eliminated by intensity modulating with a monopole signal.
A photo tube picks up the direction-gated reference signal which
appears on the cathode ray tube and gates the reference channel open
only when sferics are received from the proper direction so as to con-
tribute to the in-phase target return signal)-, 2.
F. Calibration
A relative field intensity method of calibration was used at
the Miami Site. This compares to an absolute field intensity measure-
ment method used at the medium. and long-range sites. For use with the
artificial atmospherics generator, the intensity of the echo relative
to the ground wave intensity was determined (the ground wave-produced?a
offset on the paper chart was obtained by using zero time delay in
the signal processing system.) For example, in Test No. 105 (to be
described later), it was found that the echo offset was about lh3 db
below the offset caused by the undelayed ground wave. Using the
cylindrical surface approximation dicussed above, the cross section
would be somewhat less than 2 x 10 m :While using the inverse squared
approximationr~ for the signal attenuation, the cross section would be
about 8 x 10?m2.
In the Licor operation, an estimate of the target cross section
was obtained by calibrating the system relative to the atmospheric
noise intensity. The assumption is then made that the noise intensity
at the target is approximately the same as the noise intensity at the
1 "Distributed Source Effects in Licor Systems," Aero Geo Astro Corporations,
5 August 1960.
2 "Applications of Distributed Sferics Sources," NOLC Ept. 543, 1 April 1961.
c"P ru imr
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monitoring site. This will be nearly true when the noise fields have
low divergence such as occurs for sources located at a very large range.
However, if the sources are quite close as was true much of the time
in Florida, the field intensity at the missile will be overestimated
with a resulting underestimation of the cross section. Thus numbers
obtained by this method should be taken as lower limits rather than
actual values.
u. Major Difficulties
One of the major problem areas in the short-range experiment was
the high atmospheric noise levels. The period of this experiment coincided
with the peak thunderstorm activity in Florida. and local thunderstorms
were very abundant. The second problem was that of obtaining coin-
cidence between operation of the artificial atmospheric generator and
missile launches. The operatiorn of the generator was restricted to
daytime use because of air clearance problems while the great majority
of the large missile launches occurred at night. Weather conditions
further restricted the generator operation. In addition, the long
delays in missile launches quite often outlasted the helicopter gasoline
supply.
A third problem is that of masking the echo by multiple hop
reflection and even the possibility of masking of the echo by the
exponential decay of the ground wave pulse for sites located quite
close to the transmitter. Figure 3 shows the ground wave and sky wave
field intensity for the first four hops, assuming a radiated power of
10 megawatts from a vertical antenna. It is further assumed that the
ionospheric height is 80 kilometers, and that the generally accepted
is.r_ospheric parameters are in effect!. The relative delay between
the various hops in the ground wave will vary with ionospheric height
and the echo, at times, may appear between hops. However, the echo
can often coincide, or be very close to one of the hops and, as seen
from the figure, the magnitude of these skywave signals are many times
larger than the expected echo signal. In general, for monitoring sites
very close to the transmitter or between the transmitter and the target,
one would expect interference from the first hop; while, between about
y0 and somewhat over 100 kilometers distance from the transmitter, one
would expect the second hop to be the primary interfering signal. At
a. distance of 200 kilometers from the transmitter, the third hop sky-
wave would be the primary masking signal. This distance corresponds
The figure was derived from Figure 7 of NBS Report 5019, Multiple Reflections
Between the Earth and the Ionosphere in VI,F Propagation,' James R. Wait and
Anabeth Murphy.
cTZ rR FT
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approximately to the distance to the Aero Geo Astro site. By com-
paring the echo return amplitude to the respective skywave amplitude
it is found that the Miami site shows about a 10 db improvement over
closer sites with the possible exception of those located quite close
to the transmitter. These locations could take advantage of the
transmitting pattern affect of the monopole antenna. This effect is
seen in Figure 3 as reduced intensities at very short distances from
the source,
The Aero Geo Astro Corporation operates two long-range VLF bi-static stations.
The first station., at Boulder, Colorado., uses the station NPG (18.6 Kc located
near Seattle, Washington) as a transmitter for monitoring missile launches at
White Sands Proving Grounds (500--m 1e range) and the Atlantic Missile Range (1600-
mile range)., and uses station NSS (22.3 Kc located near Annapolis, Maryland) as
the illuminator for viewing Pacific Missile Range launches (1000-mile range).
The second station is located at Patuxent, Maryland, and is used for medium-range
detection of lai.m.ches at Atlantic Missile Range (700 miles), for long-range
detection of launches at Pacific Missile Range (2500-miles) and for White Sands
launches (appro d mately 1500 miles). The station NSS was used as a transmitting
source for the measurements described in this report. The operation of the Patuxent
station is somewhat unique in that it allows test by test correlation with an HF
backscatter radar also situated at the same location. From time to time., very
striking correlations have been obtained from these two radars.
A. Monitoring System
The bi-static radar systems used for the medium and long-range ex-
periments are quite similar to the type described above for the short-
range exile::iments. A simplified description is as follows:
!'he VLF pulse from a station is picked up on a reference loop
antenna and is delayed in a sonic delay line system an amount equal
to the round-trip propagation time to the target. This delayed pulse
is used as the reference signal for the RF correlator which consists
of a synchronous detector and an integrator. The backscattered enemy
is picked up on a signal antenna which is currently either a loop or
loop-monopolo combination (card.ioid pattern). This signal is passed
through an elementary atmospheric noise reduction circuit and then
fed to the correlator. The output of the correlator is recorded on a
paper chart recorder. Both the delayed reference channel and the signal
c:ssannel are gated off for the duration of the stationts transmitted
p. Lse. This gating, or blanking, prevents the system from correlating
an that portion of the direct transmit pulse that is received on the
signal antenna.
clrP r. -r
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The first step in the calibration procedure is to measure the
station field intensity at the site. The measurement also serves
to indicate any abnormal attenuation conditions that may be present.
Next, the signal antenna is rotated so that the maximum of the
pattern is in the direction of the station. A calibrated attenuator
is inserted into the signal channel and the deflection on the paper
chart record is correlated with the field intensity. The radars are
calibrated by using both CW transmission and typical pulse code signals.
The calibration is generally indicated in db relative to a CW field in-
tensity of 1 microvolt per meter; i.e., a x?20 db calibration indicates
that a CW signal of 0.1 microvolt per meter produced the indicated
deflection. Code transmission requires higher signal field intensities
than OW for the same deflection due to the lower duty cycle. At the
Boulder-site, for example, this factor is typically about 17 db; thus,,
by knowing the echo field intensity and making use of the VLF bi-
static equation (developed in. the next section), one can calculate
the backscatter cross section. In the various calculations, the
attenuation coefficient is assumed to be 2 db per 1000 kilometers
unless otherwise indicated. The backscatter cross sections thus cal-
culated generally have ranged between 106 and l. x 108m2,
C. VLF Bi-Static Radar Equation
Wahl has shown that the vertical electric field at great distances
can be represented by
a .Ad 12 x 10L
U, 4 Lip X 1U
Ed =
asin_da
(6)
where d is in kilometers, a is the earth's radius in kilometers, f
is in kilocycles, A is the attenuation factor in db per 1,000 kilo-
meters, and E is the effective radiated field at 1 mile from the
source. Making use of the expression for the field at 1 mile from a
short vertical antenna
- 5,9 x 10?3v volts/meter
(7)
where P is the radiated power in watts, the power density p at the
range da can be found from
p v Ed-x`12 0rt
1 "Mode Theory of VLF Propagation" j. R. Wait, June 1957, IRE,, pg, 760
(8)
C1 r1? FT
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Assuming that the power density on the trail is uniform and the same
as on the ground, we find that the power reflected by the trail is
(9)
where 414 is the backscatter cross section of the trail in square
meters. Next, treating the trail reflection as a re-radiation? we
can find the receiver power density at a range d2. Since the atmospheric
noise data is generally given in field intensity, we make use of
equation (6) to find the field intensity at the radar receiver.
Jj Ad2
Ed2 a 5.9 x 10`3 x x10 2ML6' 4 v/m
sinPl
0.284 ' Z
f
dl sin d2
..A(dl+ d2)
x 10 2 x PV/'m (10)
where f is in kilocycles, a and d in kilometers and min square
meters.
The attenuation factor A is about 1 db/1000 km for sea paths
and about 2 or 3 db/1000 km for land paths. For ice caps, it may be
as high as 10 db/1000 km. Equation (10) may be represented in db
relative to a microvolt per meter by the following:
0.284 0 dl d2
A(dl+d2 )
E(db)a 20 log + 10 log Pd" w 10 log a` sin
mw
sin
a
a
103'
(11)
IV0 DATA
The data is presented on a test-to-test basis with the results from all
of the sites being discussed together. In addition to tests occurring during
the period of the Miami operation, other selected data have been included in
order to give a more complete picture of the status of the VLF research. The
geophysical background at the time of the event is given for most of the tests.
Meteor shower data are obtained from the Handbook of Geophysics and the data
on aurora, solar radio noise bursts, magnetic storms, sudden enhancements and sudden
cosmic noise absorption are obtained from the Preliminary Reports of Solar
Activity by the High Altitude Observatory, University of Colorado.
ctrl? V71
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In addition to the ICBM and IRBM launches, some smaller missiles in which
burnout occurs before the vehicle reaches the D layer were detected. This type
of signature is apparently caused by the shock wave associated with the missile
body perturbing the D layer as it passes through. A discussion of a much larger
number of tests may be found in earlier reportsl.
V. PACIFIC MISSILE RANGE TESTS
Two Pacific Missile Range test results have been included in this report
to show examples of long range (2500-miles) detections.
Test. No. 1053. This was a Discoverer launch on 18 February 1961. The
trajectory is shown in Figure 5,. This launch was detected at the Patuxent
site using NSS as the source. The signature is shown in Figure 6 . The
station was off the air from a few minutes before T to about To + 2
minutes. The signature appears to begin at about T0 + 2=1/2 minutes and
reaches a first peak at around 3 mn tes. The calculated cross section for
this first portion is about 2 x 10 m . There is a larger rise beginning
at about + minutes. This time coincides closely to the Agena ignition;
however, this is most probably a c?incidence. The cross section correspond-
ing to this peak is about 6 x 107m . Only one channel was available at this
time so that the decreasing signal beginning at about +7 minutes does not
necessarily inidcate the decay rate of the perturbation but could represent
a drift in the reflecting area.
Test No.
1051
Vehic e-.
Discoverer
Launch-.
203)4-.43Z; 30 March 1961
Geophysical Background: The geophysical conditions within several hours of
this test were quite calm with no meteor showers., flares, solar noise
bursts or magnetic storms. The mean Belvoir magnetic A index for March 30
was 10
Results-. The conventional type of signature is shown in Figure 79 and
Figure 8 for the Boulder and Patuxent sites respectively. The onset of
the signature began at about +2 minutes at Patuxent and at about +2?.1/2
minutes at Boulder. The difference in onset time between these two stations
is attributed to a relative phase difference between the two stations. At
this time, both stations lacked a quadrature channel. The sharp onset of
the signature is followed by a slowly oscillating type of record. This
indicates a drifting in range of the reflection point. The drift velocity
component in line with the radars is roughly 30 miles per hour. The
scatter is still visible on the record out to the end at about +35 minutes.
The scatter cross sections for these figures were calculated using the VLF
radar equation with an assumed transmitter power of 200 kilowatts at an
attenuation factor of 2 db per 1000 kilomet .rs. The sigma for Boulder is
2.5 x 108m2 and that for Patuxent is u x 100m2.
1 "Missile Monitoring Program," Progress Rpts. 1 April 1.961 and 22 August 1961.
r T ,-. T T T
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Cr T 1-1 T7 T T
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h T r\ T T T
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--1
-
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VI. ATLANTIC MISSILE RANGE TESTS
Most of the tests ._reported:'in this section took place during the Miami
monitoring operation; however, some earlier tests of special interest have been
included. For example, Test No. Cj07 shows an hours test background during which
two small flares occurred and Test No. 1263 shows a possible detection in a back-
ground of meteor shower clutter.
Test No. 1i07
Vehicle- Belta IV
La"` un6h a 1517:05Z; 25 March 1961
Geophysical Background: The geophysical conditions were fairly stable with
a magnetic index of There were, however, some small solar flares be-
ginning at about 1J90Z. The two small flares nearest to test time occurred
from 136 t:(~ "4,46 with a ma cLmn. at .i. )J1, and from 148 to 1521 with t1ie_
maximum at 1517. The system was being operated during both of these flares,
and no correlation was noted between scatter received and the onset of these
flares, although scatter was apparent from the beginning of the recording
.
at about 1425Z
Results: The trajectory is shown in Figure 9 and the signature in Figure 10.
The scatter may be associated with the series of flares mentioned above;
however, little change in the s:eatter level was noted during two flares
which appeared during the pre-test recording time. Figure ll shows the
background recording beginning at about P50 minutes. A large signal change
occ~~rs sometime between +4 and +6 minutes when the VLF station was off the air.
The scatter signal was still clearly evident at +20 minutes when the VLF
station went off the air.
Test No, 1352
Vehidle: Polaris
Launch: l0).0:52 ES?; 11 April 1.961
GE p iysica1 Background: The mean magnetic index for April 11 was 16.
Conditions were, however, relatively calm at test time although there were
some small flares a few hours after the launch.
Result,s: The Patuxent signature in Figure 12 shows a drifting reflector
apparent, at about + minutes. The reflector m.ay have had its onset earlier
but may have been at the incorrect phase to show up i this c;: annel. The
scatter signal dropped' below the dete.~,.tion level at about +60 minutes.
Test No. 1263
t7ehic leJupite r
,Launch L+37ol9Z,- 22 April 1".961
G ysicrzl Backgr > ndo The mean mug :eti , index was 6 and there were no
m a g n e t i c nces; how- rer, the edge of the Lyrids meteor show,-,r
was within the range gate at the time of the test.
Result~?: Pretest scatter is noted on the record, probably arising from the
Lyrids shower. Even though the recorder was set on a low gain, Figure 13
shows an abrupt change in level reaching a, peak at about +2 minutes. TFe7
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signature fades into the background scatter at about +15 minutes. This
signature is quite interesting as it shows a possible detection in the pre-
sence of meteor shower clutter. Meteor showers monitored in the past have
not shown the sharp offset type of signature but., in genera , have shown
a slow oscillatory type of response. Since some missile signatures have
been of this type, a multi-gate and multi-,station approach should be used
for the most reliable detectio: ,
Test No. 0404
Vehicles Atlas
T, unch 0200:14.7Z; 12 May 1961
Geophysical. Background: The ma.gneti index: for May 12 was a fairly high
value of 22, but, t ere were no flares or other disturbances within four
hours of the test period.
Results: The Patuxent and Boulder staicns were both inoperative for this
test. The Miami Moor system obtained a signature, shown in Figure 14.
The signature onset was at about +2 ml ute:. corresponding to an alti 5ude of
about 60 kilometers, This signature was of very short duration., fading to
below the detection level by +4 minutes, Even though the signal was low in
amplitude., it was produced by a localized reflector. The experimental range
response for this reflector is shown in Figure 15, The 2 10 mile limits
on the range response are also shown plotted on the trajectory (Figure 16).
It is 'noticed that the measured range coincides quite well with the traA
jectory at +2 minutes. In a short range Licor system., an estimate of the
target cross section may be obtained by calibrating the system relative
to the atmospheric noise power density, Thu, s, on T st 404 the r flectod
signal was about 46 db below the received atmospheric noise. If we assume
that this noise field is incident upon the perturbation, one then gets a sigma,
of approximately 106m2. This figarera--cumes that all the incident n i e
energy contributes to the in--phase reflection. In general, this is not
true so that the actual cross section should be somewhat larger than this
value,
Test No. 406
Vehitl7s nateman
ira~ u~` r!z~oy 1,41.8: 28Z; 19 May 1961
Geophysical Background: Conditions were stable with a magnetic index of 8,
R
THe esultes This' test was viewed by the Boulder, Patuxent and Miami radar:.
Boulder station had a negative result, The Patuxent station had a
weak signature from +3 to +8 minute, which was super=imposed on some fairly
bad system drift at this time so that rt salt., must be labeled `~doubtful%
The Miami site achieved a. small sign,.l on the 10 Ks Licor system (Figures ;LL
and 18 ), The signature began at sligkl tly after +11/2 minutes and wan
visiTe out to about +6 minutes. Even though the signature was not too
large, a good deal of confidence can be placed in the results since the range
response peaked at the correct range (Figure, 19 ), The measured range is also
shown in the cross-sectioned area on the trajectory (Figure 20 ), The signal
change between about +1/2 minute and +1 minute was shown not to peak in range,
and it is therefore assumed not 'to be a .;tattered signal but some type o
noise burst,
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Test No. Lill
Vehicle: olaris
n : 1951:05z; 25 May 1961 (Terminated at 20 Km altitude)
Geophysical Background: There was a magnetic storm which began at 2300Z
on the 24th of May and ended at 0)400Z on May 26th. The mean magnetic index
for May 25th was 20, There were no solar flares or other disturbances noted.
Results: This launch is of particular interest, since it was detected at
three sites on three separate frequencies: 18.6 Kc for Boulder, 22.3 Kc
for Patuxent and 10 Kc for Miami. Figure 21 shows the Boulder signature.
There is a clear signal indication at about +3 minutes, with possibly a
slightly earlier indication. This signature is approximately 2 minutes
after missile termination and may have been caused by the shock wave per-
turbing from the ionosphere. (At Patuxent, the transmitter was on low duty
cycle from -1 to about +1 minute and then off the air until +9 minutes.
When the station returns to code transmission, there is clear evidence of
a scatter signal. The perturbation is evident to beyond +)40 minutes. One-
half hour of background data for the Patuxent record is shown in Figure 22,
and the signature is shown in Figure 23. The two-channel direct readout"
signature obtained on the 10 Kc Licor system is shown in Figures 24and 25.
It is noted that the signature begins in the upper channel at about + 3
minutes and shows up clearly in the lower channel at about 4. minutes. The
lower channel was inoperative until about +2 minutes due to an open circuit
between the integrator and the paper recorder, so this channel does not have
a long background indication. The tape recording for this test was not achieved
due to technical difficulties; therefore, it cannot be shown that the dis-
turbance peaked up at the correct range. However, the signature is quite
clear and did occur with the gate centered at approximately the correct range.
Test No. 10,5
Vehicle: Po aris
aun : 1653Z; 12 June 1961
Geophysical Background: The magnetic index was 10 and very minor flares
occurred from 3.62b to 1640Z and from 1724 to 1732Z. In addition, the
edge of the Arietids and Perseids meteor showers were within the range gate
at the time of the test.
Results: The two daytime meteor showers mentioned above did not produce
amatic perturbations of the nighttime meteor showers previously
reported; however, there were perturbations appearing between the start
of the record at ..2 hours and .1 hour which might be attributed to these
showers. The station NSS went from its regular code transmission to the
low duty cycle (beeping) transmission at about -2 minutes. With this low
duty cycle, the gated noise output is too low to see on the record (Figure 26);
however, even with this low duty cycle transmission, an offset is noticed -`
beginning at about +1-1/2 minutes. The station goes off the air at +L-1/2
minutes and returns to its code transmission at about +7 minutes. At the Miami
site, there was an indication on the 10 Kc Licor system between about +2
and +3 minutes, with a further indication occurring between +5 and +6
minutes. The 25 Kc Licor system showed an indication only between +5 and +6
minutes. The direction-of-arrival gating was not-in the system at this time
-13-
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so that an unfavorable spheric distribution could lead to the small signals
noted. A good signature was obtained using the artificial atmospherics.
generator at Fort Pierce as the source (Figure 27). It is believed that
this signature is generated by the effective reflection center passing
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reaching the peak lobe near +1-1/2 minutes. The cross hatched area on the
trajectory (Figure 28) shows the range to the disturbance as measured from
Miami] assuming that the generator is in the ocean just off Fort Pierce.
The transmitting ship sometimes changes its position from test to test, but
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