Operation Dominic, Fish Bowl Series — Project 6.7: Debris Expansion Experiment (Extracted Version)

POR-2026(EX)

AD-A995 428

(WT-2026)(EX)
EXTRACTED VERSION

OPERATION DOMINIC, FISH BOWL SERIES
Project Officer's Report--Project 6.7
Debris Expansion Experiment

DTIC

P. Dyal, Project Officer

ELE CTE

W.Simmons

JUN19 1986

Air Force Weapons Laboratory

Kirtland AFB,

NM

10 December 1965

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Fish Bowl Series, Project 6.7.

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"RAT
BO0WL SERIES, PROJECT OFFICER'S REPORT; PROJECT 6.7 - Debris
Expansion Experiment, Extracted Version
12. PERSONAL AUTHOR(S)

P. Dyal and W. Simmons
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COSATI'CODES
GROUP
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_

18. SUBJECT TERMS (Continue on reverse if necessary and identify by block number)

Dominic
Fish Bowl
I Atomic Clouds

Debris Expansion

19. ABSTRACT (Continue on reverie if necesary and identify by block number)

This experiment was designed to measure the interaction of expanding nuclear weapon debris
with the ion-loaded geomagnetic field. Five rockets on Star Fish and two rockets on Check
Mate were used to position instrumented payloads at various distances around the burst
points. The instruments measured the magnetic field, ion flux, beta flux, gamma flux, and
the neutron flux as a function of time and space around the detonations. Data was transmitte
at both real and recorded times to island receiving sites near the burst regions. Measurements of the telemetry signal strengths at these sites allowed observations of blackout at
250 Mc.
Data reduction indicates that the early expansion of the Star Fish debris probably took the
form of an ellipsoid with its major axis oriented along the earth's magnetic field lines.
Collapse of the magnetic b..bble was complete in approximately 16 seconds, and part of the
fission fragment beta particles were subsequently injected into trapped orbits.
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OPERATION DOMINIC
FISH-BOWL SERIES
PROJECT OFFICERS REPORT-PROJECT 6.7

DEBIRIS EXPANSION EXPERIMENT

P. Dyal, Project Officer
W. Simmons, Captain, USAF

Air Force Weapons Laboratory
Kirtland AFB, New Mexico

ABSTRACT

This experiment was designed to measure the interaction of expanding
nuclear weapon debris with the ion-loaded geomagnetic field.
Five rockets on Star Fish and two rockets on Check Mate were used to
position instrumented payloads at various distances around the burst points.
The instruments measured the magnetic field, ion flux, beta flux, gamma flux,
and the neutron flux as a function of time and space around the detonations.
Data was transmitted at both real and recorded times to island receiving sites
near the burst regions.

Measurements of the telemetry signal strengths at

these sites allowed observations of blackout at 250 Mc.
Data reduction, which is currently being conducted at the Air Force
Weapons Laboratory, indicates that the early expansion of the Star Fish debris
probably took the form of an ellipsoid with its major axis oriented along the
earth's magnetic field lines.

Collapse of the magnetic bubble was complete in

approximately 16 seconds, and part of the fission fragment beta particles were
subsequently injected into trapped orbits.

5

PRE FACE
The authors wish to express their appreciation for the guidance
and contributions of the following people during the planning,
buildup,

and execution phase of this experiment:

Col Lew Allen
Mr.

Robert G. Bland

Mr.

Edward L.

Breen

Col Kenneth R. Chapman
D. Garcia

Lt

J.

Mr.

Martin Havens

Mr.

Charles Hale

Capt David P.

Milnor

AIC James V. Murray
Lt

Billy R. Parker

Lt

Robert Reynolds

Lt

Dave Thompson

Capt William A. Whitaker
Mr.

Thomas Yium

6

CONTENTS
ABSTRACT

-----------------------------------------------

5

PREFACE-

------------------------------------------------

6

CHAPTER 1 INTRODUCTION-

---------------------------------

9

1.1 Objectives
1.2 Background'and Theory
1.3 Star Fish
-------------------------------------------

9---------------9---------------11

1.4 Check Mate

14

CHAPTER 2

-----------------------------------------

PROCEDURE

-

----------------------------------

2.1 Operations
.....2.1.1 Star Fish
----------------------------------------2.1.2 Check Mate
--------------------------------------2.2 Instrumentation
-------------------------------------2.2.1 Rockets and Instrument Placement -------------------------2.2.2 Telemetry Receiving and Tracking -------------2.2.3 Instrumented Payload
-------------------------------

CHAPTER 3 RESULTS

-------------------------------------

3.1 Star Fish
------------------------------------------3.1.1 Star Fish Instrument Positions
-------------------------

3.1.2 Position P-6 Measurements

---------------------------

3.1.3 Position P-3 Measurements
--------------------------3.1.4 Position P-7 Measurements
--------------------------3.1.5 Position P-2 Measurements -3.1.6 Position P-4 Measurements
--------------------------3.1.7 Hall Effect Magnetometer Measurements -------------------------------------------3.1.8 Johnston Island Magnetometer
3.1.9 RF Attenuation Measurements
------------------------3.2 Check Mate
3.2.1 Check Mate Instrument Positions
----------------------3.2.2 Position P-i Measurements
--------------------------3.2.3 Position P-5 Measurements
3.2.4 RF Attenuation Measurements

CHAPTER 4

4.1 Star Fish Debris History-87
4.2 Check Mate Debris History
4.3 Data Reduction
-

-

15
15
17
18
18
19
21

41
41
41

42
46
49
51
52
55
55
56
57
57
58
60
62

87

DISCUSSION

RFERENCES-

15

88
88

-92

7

TABLES
4.1 Star Fish Debris Expansion4.2 Check Mate Debris Expansion

--------------------

-----------------------------

89
89

FIGURES
2.1 Star Fi.gh rocket trajectories in magnetic meridian through
Johnston Island
-----------------------------------2.2 Star Fish rocket trajectories on earth's geographic surface ---------2.3 Star Fish altitude versus time --------------------------------2.4 Rocket on launcher ------------------------------------------2.5 Rocket and payload in flight--2.6 Cross section of payload
--------------------------------2.7 Block diagram- -----2.8 Betadetector --2.9 Beta detector energy calibration -------------------------------2.10 Faradaycup
2.11 Gamma-neutron detector
2.12 Rubidium vapor magnetometer
2.13 Hall effect magnetometer
3.1 Star Fish composite flux, Position P-6
3.2 Star Fish real-time beta and ion flux, Position P-6 ---------------3.3 Star Fish composite flux, Position P-3
--------------3.4 Star Fish real-time beta and ion flux, Position P-3
3.5 Star Fish composite flux, Position P-7
3.6 Star Fish real-time beta and ion flux, Position P-7 -------------------------------------3.7 Star Fish composite flux, Position P-2
3.8 Star Fish real-time beta and ion flux, Position P-2 -------------------------------------3.9 Star Fish composite flux, Position P-4
3.10 Star Fish real-time beta and ion flux, Position P-4
3.11 Star Fish beta trapping times
3.12 Hall effect magnetometer versus time
- ------------3.13 Johnston Island magnetic field versus time
-----------------3.14 Star Fish signal strengths at Johnston Island
3.15 Star Fish signal strengths at outlying sites -....
3.16 Check Mate rocket trajectories in magnetic meridian through
-----------------------------------Johnston Island
3.17 Check Mate rocket trajectories in earth's geographic surface
------3.18 Check Mate altitude versus time ---------------------------3.19 Check Mate composite flux, Position P-I
--------------------3.20 Check Mate real-time beta and ion flux, Position P-i -------------3.21 Check Mate composite flux, Position P-5 ----------------------3.22 Check Mate real-time beta and ion flux, Position P-5 -------------3.23 Check Mate signal strength from Position P-i
----------------3.24 Check Mate signal strength from Position P-5----4.1 Star Fish debris expansion
4.2 B, L plot with Star Fish belt and 6.7 trajectories

8

28
29
30
31
32
33
34
35
36
37
38
39
40
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
96
90
91

CHAPTER 1
INTRODUCTION

1.1

OBJECTIVES
The primary objective of this project was to measure the

characteristics

of the expanding Star Fish debris which were per-

tinent to weapon effects.

The Star Fish nuclear explosion occurred

at an altitude of 400 kilometers with a yield of approximately 1.15
megatons, and the event was considered to be above the atmosphere
The most

insofar as familiar sea level phenomena are concerned.

important energy loss mechanism for the exploding material at this
altitude is

its

interaction with the ion-loaded geomagnetic

gamma

This experiment measured the magnetic field, ion density,
flux, neutron flux,

and fission fragment beta flux in

field.

order to

obtain a better understanding of the weapon debris expansion.

A

secondary objective was to observe the formation of the Argus
shell of fission beta particles.

Attenuation measurements

of the

250-megacycle telemetry signals propagated through the ionized
regions also permitted a direct observation of blackout effects due
to gammas,
1.2

neutrons,

and the debris

pancake (Reference 1).

BACKGROUND AND THEORY
Sea level nuclear burst phenomena can be adequately described

by classical hydrodynamics.
products,

The low-energy X-rays and detonation

which represent over 90% of the bomb's energy,

interact

with the surrounding airand the resulting shock phenomena are

described in Reference 2.

The conditions behind the normal

shock wave are determined by laws of conservation of mass, momentum, and energy

4nere P, p, and H are pressure, density and enthalpy of the gas,
respectively.

The shock velocity is denoted by U5 and the suffix 1

denotes conditions in the undisturbed gas ahead of the shock wave.
It is apparent that the most important mechanism of containment is
the'surrounding mass of cool air.
At altitudes above 200 kilometers, the burst phenomena of
nuclear weapons is completely different.

There is little air in

this region for coupling of the energy of the detonation products,
and as a result, the particles travel unimpeded for several thousands
of kilometers.

During the early phase of a high-altitude explosion,

a large percentage of the detonation products is ionized

and can

therefore interact with the geomagnetic field and can also undergo
Cou~lomb scattering with the ambient air atoms.

If the expansion is

high enough above the atmosphere, an Argus shell of electrons can be
formed as in the 1958 and 1962 test series.

The theory describing

the motion of a plasma in a magnetic field isdescribed in References
3 and 4.

The equation of motion of a plasma expanding in a magnetic field Is

P6v/6t

=

V(P + B2/8w)+B*VB/4w

10

where v, t,
tively.

and B are the velocity, time,

and magnetic field, respec-

The quantities which are least known in such a plasma

expansion are the state of ionization and the radial velocity disIf

tribution of the debris.

this velocity of the plasma is

greater

than the local sound or Alfven speed, a magnetic shock similar to a
hydro shock can be formed which dissipates a sizable fraction of the
plasma kinetic energy.

The Alfven velocity is

CA = B(4wo )-1/2
where CA is the Alfven velocity in cm/sec
B is

the magnetic field in gauss

3
p is the ion density in ions/cm

S-iMe the Star Fish debris expansion was predicted and measured to
be approximately 2 x 1018 cm/sec and the Alfven velocity is
2 x 10T cm/sec,

a shock should be formed.

about

A consideration of the

conservation of momentum and energy indicates that the total extent
of the plasma expansion proceeds until the weapon plasma kinetic
energy is balanced by the B2/8n magnetic field energy in the excluded
region and the energy of the air molecules picked up by the expanding
debris.

1.3

STAR FISH
The Star Fish device was detonated at an altitude of 400.09
The yield was

kilometers and had a total weight of

and the detonation time was
32409.029 seconds Zulu on 9 ,Tuly 1962 (Reference 5).
in Reference 6 predicted that

Preshot calculating

kinetic energy would be in the bomb

debris at 2 microseconds.
11

A sequential history of the plasma expansion proceeds as follows:

The radioactive debris which rises
to extreme altitudes will form a trapped belt of electrons around
the earth.

The debris which is deposited on top of the atmosphere

will decay and ionize the air, causing attenuation of RF signals,
aurora, etc.

12

An estimate of the maximum radial extent of the Star Fish
magnetic bubble can be made assuming conservation of momentum and
energy.

The magnetic field swept along by the plasma electrons will
proceeds outward.

pick up ambient air ions as it

Denote the mass per

steradian of air ions by Mair/14w and the mass of the bomb per
Conservation of momentum gives

steradian by MB/4lT.

7MB

Ma r

B

the initial expansion velocity of the debris.
where VA
B is

The initial

kinetic energy is given by
2E=
MBVB2

2

The debris energy density can be equated to the energy density in the
given by

magnetic field and is

4 3 B2
8w
3'

12
2

air

+MB

Eliminating V from both equations

32 VB
*3

2MB

B 2 (Mair+ MB)
Both the air mass Mair and the geomagnetic field B are functions of
R, the radius of expansion.
Reference 7

Using the ion density given in

and magnetic field variations as B

13

-

Bo

2 1/2
(1 0 3 cos e)

a table of maximum radial extension of the ionized debris was calculated
to be as follows:
DEBRIS
10%
km
260

IONIZED

Horizontal (40o km)

PERCENTAGE
ioo%
km
550

Upward Perpendicular to Field

980

350

140

Downward Perpendicular to Field

285

210

100

DIRECTION OF MOTION

1%

km
120

These values assume that the expansion is spherically symmetric,
that the ion densities are as predicted in Reference 7 and that
the state of ionization is frozen-in after a few microseconds of
expansion time.

It is also assumed that only ions are picked up

by the expanding debris and field.

These approximate distances were

used as guides in the positioning of instruments to measure the
percentage of the debris which would remain effectively ionized.

1.4

CHECK MATE

Expansion of the
debris was mostly determined by the surrounding atmosphere which had
a density of 4.8 x 10

10

3

particlLs/cm

14

CHAPTER 2
PROCEDURE
2.1

OPERATIONS
2.1.1

Star Fish.

The Star Fish weapon was positioned in

space using a Thor rocket.

Timing coordination to 1-second

accuracy was important since experimental payloads were positioned
around the weapon at detonation time.

Tahe Thor engines were ignited,

and the retaining locks held the missile on the pad until proper
engine thrust was obtained.

The uncertainty in Thor take-off time

due to this unknown thrust was approximately 12 seconds, and H-0 time
was readjusted at Thor lift-off.
seconds,

The Thor left the pad at H-821

then separated from the nose cone containing the bomb.

The bomb was detonated at an altitude of 400 kilometers.

Project 6.7

had five rockets which took off at H-510, 462,

and 140

seconds,

266, 160,

respectively, and positioned the instrumented payloads

around the weapon at H-0 time.

With these take-off times the experi-

mental payloads and rockets could have been saved if the weapon had been
aborted before H-515 seconds.
The rocket trajectories are shown in Figure 2.1.

This figure repre-

sents a slice In the magnetic meridian through Johnston Island using the expression in Reference 10 for the geomagnetic field.
H-0 time are denoted by extra heavy lines.

15

The rocket positions at

The length of these lines repre-

sents the 30 seconds of data which was recorded after H-0.

The sequence of

events for each one of these rockets was as follows:
(])

The three first-stage motors were ignited and the

rocket left the pad.
(2)

The first stage burned out in 36 seconds, and the

rocket coasted out of the atmosphere for about 15 seconds.
(3)

The second stage was ignited,

separated from the

first stage, and boosted the payload up to the proper velocity.
(4)

After second-stage burnout, the nose cone was ejected

forward and away from the payload.

(5)

The rubidium magnetometer was then telescoped approxi-

mately 5 feet away from the rest of the payload.
(6)

The payload proceeded to its predetermined position

(7)

The weapon detonated, and the prompt gammas from the

at H-O.

device triggered the tape recorder timer.
(8)

Thirty seconds of high-frequency data was recorded.

(9)

The timer turned off the erase mode, and the thdirty

seconds of data was continuously played back through a telemetry
transmitter to receiver stations on the earth's surface.

Three

real-time channel measurements were transmitted to the receiving
sites during the entire flight simultaneously with the recorded
information.
Radiation and material arrived at the instrumented rocket positions in a time sequence which depended on the properties of the
device and the surrounding medium.

Project 6.7 payloads located
16

in the hard vacuum surrounding the Star Fish device detected the
tieapon phenomena in the following sequence:
(1) Prompt gammas from the neutron interactions with
bomb Diaterial and from the fission events.
(2) X-rays from the case material.
(3)

14-Mev neutrons from the fusion events during

weapon burning.
(4) Low-energy neutrons from fission events, high-energy
beta particles from fission fragments and case material.
(5) Radioactive bomb debris.
(6) Ionized air.
(7) Argus trapped beta particles.
The arrival times of the above radiations are strongly dependent on
the position of the instruments with respect to the bomb, the magnetic field, and the ambient material between the bomb and instruments.
At later times, the radioactive debris deposits on top of the atmosphere and causes blackout of payload telemetry signals passing
through this ionized region (Reference 1).
2.1.2

Check Mate.

The Check Mate device was positioned in

space with the Strypi vehicle which uses the same rocket motor as
frirst stage of Project 6.7 SWIK vehicles.

Due to the common

flight properties of these rockets, there was no chance to save the
experimental payloads and rockets in case of a weapon abort.

Two

payloads were positioned around the Check Mate device.and their
positions at H--O are shown in Figure 3.16.

The rocket and measure-

ment sequence for Check Mate was the same as described previously
17

for Star Fish.

The weapon phenomenology was quite different,

however, since the surrounding air was dominant in containing the
expansion as contrasted to the magnetic field containment of
Star Fish.

2.2 INSTRUMENTATION
2.2.1

Rockets and instrument Placement.

The rocket used

to position the scientific instruments was a spin-stabilized,
stage,

solid-propellant vehicle.

two-

The rocket was 36 feet long, weighed

13,000 pounds, and boosted a 430-pound payload to an altitude of 1,200
kilometers.

The first stage consisted of three motors (two X-19

Recruits and one XK-33) which were fabricated by the Thiokol Company.
The two Thiokol Recruits were used to initially assist boost off the
zero-length rail launcher, and each generated 35,000 pounds of thrust
for 1.5 seconds.

The Recruit motor had a gross weight of 348 pounds

and was 102 inches long and 9 inches in diameter.

The Thiokol XM-33

generated 50,000 pounds of thrust for 33 seconds.

It weighed 8,732

pounds and was 232 inches long and 31 inchs in diameter.

An Allegheny

Company X-254 motor was used for the second stage of the SWIK rocket.
It weighed 2,085 pounds and was 116 inches long and 31 inches in
diameter.

It

generated 12,000 pounds of thrust for 38 seconds.

exterior hardware including the fins, nose cone,
and constructed by Atlantic Research Corporation.

etc.,

The

was designed

The rocket was

launched from a zero-length rail; and by canting the fins, a spin
rate uf 2.5 cycles per second was obtained which remained constant
during the vacuum coast part of the trajectory.

The ablative nose

cone was attached to the end of the second stage by a marmon clamp
18

which held 48 helical compressed springs.

After the boost phase

was over and the vehicle was out of the atmosphere,

a timer released

the zarmon clamp, allowing the springs to eject the nose cone forward
at E velocity of 16 feet per second.

Immediately following nose

cone ejection, a gas generator was fired which extended the telescope housing the rubidium magnetometer.

Figure 2.5 shows the

payload and spent second-stage motor as it

existed during most of

the flight time.

A 2-Sigma dispersion of 32 mils was measured as

the overall error in placement of scientific instruments.

Trajec-

tories for the five rockets in Star Fish are shown in Figure 2.1
and for the two rockets in Check Mate in Figure 3.16.

These figures

show the trajectories superimposed on a plane in the magnetic
meridian through Johnston Island.

The positions of the rockets at

H-0 time are denoted by the short,

heavy black line on each trajec-

tory.

Magnetic field lines in this meridian plane were determined

from the equation for the geomagnetic field (Reference 10).
The rocket trajectories were programmed to follow the magnetic
meridian as closely as possible.

Figures 2.2 and 3.17 show the

projection of the rocket trajectories upon the earth's surface
for Star Fish and Check Mate,

respectively.

give the altitude of each rocket vs.

Figures 2.3 and 3.18

time and Figure 2.4 shows the

rocket on the launcher before take-off.
2.2.2

Telemetry Receiving and Tracking.

Due to the RF

blackout problems at 250 megacycles, data was recorded in the
payload and retransmitted to various receiving sites in the Pacific
at Oahu, Hawaii,

Tern, Johnston, and Canton Islands.

19

Figure 2.2

shows the relative positions of these receiving sites with respect
to the Star Fish trajectories.

Kaena Point, Oahu, was run by the

Pacific Missile Range and had two auto tracking antennas, and a
TIM-l8, 60-fpot parabolic dish.

The 60-foot dish had a 5-degree

beam width with 28-db gain at 250 megacycles.

Kaena Point received

P-7 and P-2 on Star Fish and P-5 on the Check Mate event.

South

Point, Hawaii, was run by the Pacific Missile Range and also had a
60-foot TLM-18 dish which received P-6 during the Star Fish event.

Tern

Island had an auto tracking quad-helix run by the Pacific Missile Range and
a manual track quad-helix operated by Air Force Weapons Laboratory
(AFWL) personnel. Both quad-helix antennas had a gain of 19 db at 250 megacycles and a beam width of 18 degrees.

The Tern Island facility

received P-2 and P-7 for the Star Fish event and P-5 for the Check
Mate event.

Canton Island had two manual tracking quad-helix antennas;

one operated as part of the Mercury Receiving Net out of AMR and one
by AFWL personnel.

These antennas had 19-db gain at 250 megacycles and

an 18-degree beam width.

Johnston Island had one small mono-helix

antenna used for payload checkout.

Since RF blackout was less than

expected on Star Fish, the low-gain mono-helix antenna was able to
receive some information on all five payloads.

Due to this unex-

pected receiving ability, two quad-helix antennas were installed
on Johnston Island for the Check Mate event.

The receiving sites

which possessed auto tracking capability gave enough data for traJectory determination based on time of flight and look angle information.
Cubic Corporation was contracted by DASA to transponder track
20

all small rockets from Johnston Island.

One rocket was successfully

tracked on Check Mate with Cubic's PME, AME equipment.

RCA had a

project on USAS American Mariner which was to have tracked a 5,776megacycle transponder aboard P-6 Star Fish.

This track was unsuc-

cessful.
2.2.3

Instrumented Payload.

The scientific payload weighed

433 pounds and was constructed almost entirely of non-magnetic
materials.

The cross-sectional view of the payload is

shown in

Figure 2.6 along with the position of the various instruments.

A

nylon cylinder which was 1.5 inches thick, 15 inches long, and 26
inches in diameter was used to enclose the electronics and shield
the sensitive circuits from bremsstrahlung caused by high-energy
beta particles.
materials,

it

Since nylon is composed of relatively low Z

is effective in minimizing the production of

bremsstrahlung.

The magnetometer was located at the end of a

fiberglass telescope which was placed on top of the nylon cylinder
so that magnetic gradients would be minimized in the gas cells of
the magnetometer.

The 10 watts of RF power radiated from the

telemetry antennas,

located directly below the nylon cylinder, was

shielded out of the payload by a laminated copper-clad fiberglass
shield.

The block diagram for the electronics used in this experi-

ment is

shown in Figure 2.7.

The left side of this figure shows

the inputs from all the scientific instruments and the right side
shows the outputs to the antenna.

The telemetry system was capable

of transmitting 100-kc information, but the experiment required 200 kc bandwidth of information.

This was obtained by recording two sets of data in a

21

tape recorder and time-sharing the output of this tape recorder into the telemetry system.

Referring again to Figure 2.7, channels 4 through 18 were mixed

and placed in channel 1 of the tape recorder, and the rubidium vapor

magnetometer was simultaneously recorded in channel 2.

A 40-second

commutator was used to sequentially take the output of channel 1 and
channel 2,, mix this with channels 1 through 3 and transmit the information by frequency modulating a 250-megacycle carrier.

The prompt

gamma detector shown at the lower left hand corner of Figure 2.7 was
used to control the record-erase functions of the tape recorder.

A

transponder operating at approximately 340 megacycles was supplied
by Cubic Corporation for tracking purposes.
Power was supplied to the payload by three sets of batteries.
The largest set consisted of 20 silver cells enclosed in a pressuresealed fiberglass case which supplied 10 ampere-hours at 28 volts.
The two other batteries consisted of a 300-volt and a 32-volt dry
cell for biasing the Faraday cup grid and the solid-state detectors.
Current drain on these batteries was less than 10 microamperes.
Telemetry for the entire payload was provided by an 18-channel
FM/FM system which converted 0-to 5-volt
watts of RF power at 250 megacycles.

instrument signal into 10

The system had solid-state

subcarrier oscillators and a ceramic tube power amplifier sealed in
a vacuum-tight container.

System distortion was less than 1 percent

of the bandwidth in each channel.

Built-in externally con-

trolled calibration relays provided calibration of the entire system,
and a 100-kc crystal-controlled oscillator was used as one subcarrier
oscillator to remove wow and flutter produced by the tape recorder.
22

The transmitter fed a four-element,

bent-stub antenna system which

was set in teflon ablative material and mounted around the periphery
of the payload.

This antenna system was phased for right circular

polarrzation when viewed from behind in the direction of flight.
Frequencies for the seven payloads were 247.3, 237.0,
and 229.9 megacycles for P-2,

3, 4, 6, and 7,

229.9, 221.5,

respectively.

Figure 2.5

shows the antenna positions on the payload during vehicle flight.
Due to complete loss of RF signal at H-0 time, a tape recorder
was used to store information from H-5 seconds to H+25 seconds.
This information was repeatedly played back through the transmitter
The recorder had two channels;

to the receiving sites until splash.

each had a flat frequency response from 0.4 to 100 kilocycles and
had wow and flutter less than 1 percent of the

input signal.

A

timer which was started by a pulse from the prompt gamma detector
was used to stop the record-erase function of the tape recorder
after a preset time.

This method allowed information recorded

during blackout to be received at ground stations after the blackout
had subsided or after the payload had cleared the blackout area.
The prompt gamma detector used three silicon solid-state detectors connected so that a coincidence from any two would trigger the
tape recorder timer.

These detectors were located near the center

of the payload and had an area of one square centimeter,
tivity of 4,000 ohms/cm and were biased at 60 volts.

a resis-

The circuit

triggered on any gamma spike with a rise time less than 2 x 10-6
second,

a flux rate greater than 2 x 104 R/sec,

energy approximately 1 Mev.
23

and gamma ray

The gamma-neutron detector was a silicon solid-state detector
of 1-cm2 sensitive area and had a 5-decade log
ampiifier which converted 10-I to 104 R/sec into 0 to 5 volts for
the telemetry.

It was located on the inside of the 1.5-inch-thick

nylon cylinder which shielded it

from high-energy betas.

are detected by photo-electric,

Compton,

Gamma rays

and pair production inter-

actions inside the depleted region of the silicon P-N junction.
Gamma calibration was accomplished using a linear accelerator, the
SPRF reactor, and a 4-kilocurie Co60 source.

Neutrons are detected

by measuring the recoil protons from the converter foil placed in
front of the detector and by no,p
the detector itself.

andn°,a reactions in the Si of

Neutron energy calibrations have been com-

pleted, but the data reduction is still

in progress.

of the detector and electronics is 10-5 second;

The time response

therefore,

the

limiting time factor is the telemetry set which yields information
from this detector to 10-3 second.

Figure 2.11 shows the gamma-

neutron detector without the polyethylene neutron-proton recoil foil.
Three Faraday cups were located 120 degrees apart on the
periphery of the nylon cylinder looking out at right angles to the
payload spin axis.

Each cup consisted of an outer grounded screen,

a grid biased at -300 volts to reject thermal and secondary electrons,
and an inner -300-volt

grid biased to suppress secondary electrons

from the foil and 0.56-inch-thick aluminum collector.

The 0.001-inch-

thick foil was designed to stop and measure the iharged heavy debris
ions, but electrons above 65 key were transmitted to the thick 0.56inch collector.

The Faraday cups were calibrated with O-to l0-Mev
24

electrons and 0-to 100-kev protons.

The time response of the Faraday

cup system was determined to be 10-4 second,

Figure 2.10 shows the

geometrical positions of the grids and foils.
Six beta detectors were located in the surface of the nylon
payload

(Figure 2.8).

Three were located 120 degrees apart

looking perpendicular to the payload spin axis, and three were
located 120 degrees apart looking parallel to the spin axis.

Each

detector consisted of a 1-mm-thick, 0.25-cm2 lithium ion drifted
solid-state detector behind a 0.002-cm-thick aluminum foil.
Figure 2.6 shows the position of the beta detectors looking parallel
end perpendicular to the rocket spin axis.

Each detector had a 60-

degree look angle due to its recession into the nylon cylinder.

The

energy response to high-energy electrons is shown in Figure 2.9;
the beta detector integrated this energy response, and the current
output was fed into a

5-decade logarithmic amplifier.

This

detector amplifier system had a time response of 10-5 second.

The

telemetry system further limited this time response to 10-4 second.
A time-varying fission beta energy spectra

(Reference 11)

was used with the energy calibration to obtain the number
of fission betas per cm

per second per steradian from the current

output of the detector.
The Hall effect magnetometer was a solid-state multiplying
device.

The output voltage was proportional to the current flowing

through the unit times the magnetic field perpendicular to the unit.
The constant of proportionality is determined by the concentration
of charge carriers and the sign of the carrier and their mobility.
25

The indium arsenide element used in this magnetometer had an outpat
sensitivity of 10-1 volt
field.

per ampere control current per kilogauss

A laminated mumetal flux concentrator enhanced this sensi-

tivity by 102, and with an amplifier gain of i0, the magnetometer
was capable of measuring magnetic fields from 0.03 to 4 gauss (plus
and minus).

The frequency response was limited by the telemetry to

10-4 second, and the instrument was positioned to measure the field
vector along the vehicle spin axis.

Figure 2.13 shows the Hall element

and flux concentrator, and Figure 2.6 shows its position inside the
payload.
The Rb85 magnetometer system utilized transitions between Zeeman
sublevels in the ground state of the Rb8
magnetic fields.

atom in order to measure

The energy separation for the Zeeman splitting is

proportional to the intensity of the magnetic field, and for Rb85 this
is 4.67 cycles per second per 10-5 gauss magnetic field.

An optical

pumping technique was used to observe the quantum transitions which,
in turn, yielded the intensity of the magnetic field.

The output of

the instrument was a 5-volt peak-to-peak sine wave varying in frequency from 0 to 467 kilocycles for magnetic fields from 0 to 1 gauss.
Since the telemetry system could only transmit signals up to 100 kilocycles, a crystal-controll;ed oscillator was used to multiply the
rubidium signals and the low difference frequency was transmitted.
Figure 2.12 shows the optical components of the magnetometer and
Figure 2.6 shows the position of the magnetometer in the payload.
Since a magnetic gradient of 10-4 gauss per centimeter along the
optical axis of the instrument quenched the optical pumping process,
26

a nylon and fiberglass construction was used throughout the payload

along with a telescoping device which moved the magnetometer away
from current loops in the payload electronics.

W. Whitaker

calculated the largest eddy current loop allowable (at a position
70 inches from the electronic boxes) in order that the gradient in
the magnetic field stay below 10-5 gauss per centimeter for large
dB/dt.

The frequency response of this system allowed field changes

of 104 gauss per second to be measured.

27

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39
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40

CELAPTER 3
RESULTS
3.1

STAR FISH
3.1.1

Star Fish Instrument Positions.

Figure 2.1 shows

the rocket trajectories in the magnetic meridian through Johnston
The rockets are labeled

Island at the time of the Star Fish event.
as P-2, F-3, ?-4,

P-6, and P-7, and their positions at H-0 time are

den'oted by the initial part of a short, heavy line along the trajectory path.

heavy line represents the rocket position

This short,

during the thirty seconds that the high-frequency data was stored
in the tape recorder imediately following the burst.

The launch

-

azimuths were chosen so that the trajectories wouid follow the magnetic meridian through Jchnston Island.

Projections of these

trajectories upon the earth's surface are shown in Figure 2.2.

The

five islands which had receivinge sites for Project 6.7 rockets are
also shown in Figure 2.2, and positions at H-0 time are denoted, by
Because rocket pairs P-7,

_nr "X" along each trajectory.

P-2 and

P-4 and P-3 were launched with identical azi,.uth settings,
separation is not resolvable in Figure 2.2.

ther

The PF blackout data

and real-time radiation fluxes are eval',,ted by using the altitude
vs.

time plot which is

shown in Figure 2.3, s-nd the exact distances

at H-0 time which are given in Table 4.l.
grarn•ed to be 100, 200,

400,

througl t,.e burst at H-'

time.

The rockets were pro-

and 800 km across the field lines
These distances, basel on crevicusl.
41

.'

mentioned calculations,

were chosen so that debris ionization

the Rocket P-7

For eiample,

percentages could be measured.

should be near the stopping radius point if the material were only
10%

ionizeI and Rocket P-6 if it were only 1% ionized.
Payload P-6 was located

Position P-6 Measurements.

3.1.2

117 km down and across the field lines from the burst point.

Measure-

ments obtained from the instruments at times from H-0 to H+30 seconds

are shown in Fig. 3.1.

Proceeding from the top to the bottom of

Figure 3.1, the five plots represent the outputs of the following
instruments:

(1)

Faraday cup thick collector

(2)

The 1-radl

(3)

Solid-state beta detector

(h)

Solid-state ga.-ma-neutron detector

(5)

Rubidium vapor magnetometer

Faraday cup foil

"

4

The top graph in Figure 3.1 gives the resul.s from one of the
three Faraday cup foils located aboard Pyload P-6.
located behind a grounded grid

This foil was

and a grid bi."ed at -300 volts to

keep out the low-energy plasma electrons and allow measurements of

only positively charged heavy particles.

The instrument was capable

of measuring ion fluxes from plus and minus 105 to 10l
cme/sec/ster.

The fir'st downward deflection was caused by the tra=-

sient radiation effect from the prompt gammas.
negative charges,

to 10-

measured from 10-

due to electrons with energies
second,

charges per

The subsequent
second,

greater than 300 ev.

are probably
At H+0.755

the Faraday cup foil goes from a negative current reading

42

!

to a large positive current reading.

This is

interpreted to be the:

arrival time of those positively charged heavy debris ions, which

%

traveled with a velocity of

'The second graph from the top in Figure 3.1 gives the results
of one of the three thick Faraday cup electron detectors

located

aboard Payload P-6.

The ordinate has the units of charge times

2.47 cm 2 /sec/ster.

The abscissas,

3.1,

cosmon to all graph%. in Fig-are

are times in seconds after H-O.

located behind the thin foil in

The thick aluminum collector

the Faraday cup was designed to measure

'he high-energy fission product beta particles.

The electrometer

used to measure the current from this thick collector also ex-erienced a severe transient radiation effect and did not recover until
I+.002 second.

At H+51 milliseconds,

large negative current in

the Faraday cup detected a

the thick collector which is

to be the arrival of the high-energy beta particles.
there was a sharp decrease
the

intensity is

in

interpreted
At

.+13

ccondZ,

intensity of these beta particles, and

modulated in time at twice the spin rate cf the

vehicle.
Th.e third graph from the top in

Figure 3.1 represents

the out-

put of one of six lithium ion drifted solid-state beta detectors
aboard Payload P-6

iTe amolifier in this instrument also experienced

transient radiatiou effects until H+1 millisecond.

I

At this time the

electronics recover-d and was able to measure the l-1m.ev fusion
,'1

neutrons which arrived
gammas.

after the prompt

The solid-state detector then measured the lower enerpr- fission

neutrons and delayed gamr-nas until

at .- ich tine

43

. d

*.

r'", S r

.

...

I..

a high flux of beta particles arrived at the P-6 position.
the center graph in Figure 3.1, it

From

is evident that the beta particles

were expanding outvard in the form of a shell traveling with an
p..

averagc velopity of
At H+16.7 seconds the beta detector output was intensity modulated
at twice the spin rate of the vehicle (Figure 3.11).

This modula-

tion is due to the beta particles being trapped in the magnetic
field which is orthogonal to the vehicle spin axis.
The fourth graph from tne top in Figure 3.1 gives the result
of the ganna-neutron detector on board Payload P-6.

The results

are plotted aA R/second deposited in eilicon vs. time.

.7

Prompt gamas

from the bomb caused the first peak to occur at about H+2 milliseconds.

It was delayed in time because the telemetry frequency

response was slower than a millisecond.

At H+1.85 milliseconds, lU-

Mev fusion neutrons arrived and caused a larger increase in R per
second than the prompt gamas.

The difference between the arrival

times of the prompt gammas and the 14-Mev fusion neutrons made possible
a comparison between the distance from the burst point as measured
by radar and the distance as measured by neutron time-of-flight.
Using the relativistic kinetic energy of the 14.5-Mev neutrons to be
K

- 939.526

(-V 2 /C2)-1/ 2-1'

-- 1

where V is the velocity of the neutrons and C the velocity of light.
The distance from the burst point to the payload in given by the

.,

following expression:
d =ty-no Vn o(l-V no/C)IO

..-

44

where t y-n

is the time between the arrival of the prompt ga""The flux deposited in the gamma neutron detector

and the neutrons.

'

following the lh-Mev neutrons was due to lower energy fusion neutrons
-

and (telayed gammas from the radioactive fission debris.
The bottom graph in Figure 3.1 gives the results of the Rb85
magnetometer.

The magnetic field remained constant at the ambient

value of 0.29 gauss until H+51 milliseconds at which time the transient radiation effect rendered the instrument inoperable.

At

H+2.5 seconds the instrument recovered and proceeded to Veasure
the magnetic field until H+25 seconds.

The field rapidly returned

toward the ambient value at H+16 seconds and simultaneously the
beta intensity was modulated at twice the 2.5-cycle/sec vehicle
spin rate,
field.

indicating that the betas were trapped in the maxnetic

The angular distribution of beta particles,

by the six orthogonal beta detectors,

as measured

was isotropic inside the

expa.ndling plasma bubble.
Figure 3.2 shows the outputs of the Faraday cup foil and the
high-energy beta detector for the entire flight of the Taylcad.
top graph in Figure 3.2, showing the Faraday cup foil output,

The

indicates

that th4e payload passed through a rerion of maxim.ri ionization at
300 km.

Immediately following the detonation, it

of expanding positive ions,

measured the shell

and then for the remainder of the flight,

measured more negative than positive charges.

The beta detector

saw a sharp increase in beta intensity i-ntediately following the
detonation and gradually fell off in

intensity af.ter the fission

debris shell had passed beyond the payload.

45

.-

.

x.

.

:j

...

.

.

-

.

.

.

.- -.

. , .

3.1.3

Position ?-3 Measurements.

Payload P-3 was located

205 kilometers down and across the field lines from the burst point.
Mea~surement~s obtained from the instruments at times from H-C to H+30
seconds are showrn in Figure 3.3.

Proceeding from the top to the

F

bottom of Figure 3.3, the five plots represent the outputs of the
following instruments:
(1)

Faraday cup thick collector

(2)

The Faraday cup foil

(3)

Solid-state beta detector

(4) Solid-state gamna-neutron detector
(5)

Rubidium vapor magnetometer

Ihe top graph in Figure 3.3 gives the results of one of the
three Faraday cup foils located aboard P-3.

This foil was located

behind the grounded grid and a grid biased at -300

volts; thus, it

kept out low-energy plasma electrons and measured only positively
charged, heav7r particles.

The instrument was capable of measuring

ion fluxes from plus and minus 10

to 10

charges per cm2/sec/ster.

The negative current measured during the first 20 milliseconds
after H-0 was probably caused by Compton electrons, and the first
positively charged materia~l was due to the ionized air.

At

H+6

seconds, the Faraday cup foil detected positive particles in one
direction and negative charges in another direction.

This was

probably due to high-enerEr betas that penetrated the plasma sheaths
surrounding the vehicle.
The second graph from the top in Figure 3.3 gives the results
from one of the three thick Faraday cup electron detectors located

46

W4

L-

aboard V~yload P-3.

This thick aluminum collector wva

located

behind the thin foil in the Faraa•y cup and was designed to detect
and stop the high-energy fission beta particles below 7 Mev.

L

The third graph from the top in Figure 3.3 represents the
output from one of the six lithium drifted solid-state detectors
aboard Payload P-3.

The first peak at about 8 x 10

-4

second

was due to the prompt gammas from the device, while the peak
3.18 milliseconds later was due to the lh-Mev fusion neutrons.
The energy deposited by the delayed gamma rays and lower energy

neutrons fell off to the detector threshold value at

I

second.

At H+2. 57 seconds the beta detector measured a flux of high-energy
be!ta particles which were trapped in the magnetic field as shown
ir..
Figure 3.11.

seconds, a

This flux lasted for 1.3 seconds.

4-second

*

At H+5.27

duration flux of trapped beta particles

*iwý detected, and later at H+13.5 seconds the rocket entered the
plasma bubble.

This penetration occurred when the rocket was at

an t.ltitude of 271 kilometers and the flux decreased sharply within
17 seconds as seen in Figure 3.4.

This corresponded to an altitude

of 301 kilometers.
1he fourth graph from the top of Figure 3.3 gives the results
from the gamma-neutron detector for Payload P-3.

The results are

plotted as R per second deposited in silicon vs.

time.

peak from prompt gaxmasat about H+2 milliseconds, "es

The first
delayed

since the telemetry channel signal response was limited tc I
millisecond.

At !4+3.18

and were followed

milliseconds, the lh-Mev neutrons &rrived

immediately by the lower energy fission neutrons
47

N

At about H+lO seconds another increase

and delayed gammas.

gamma

in

flux was measured during rocket penetration of the radioactive debris.

'I'

The bottom graph in Figure 3.3 gives the results of the Rb 8 5
magnetometer.

The magnetic field remained constant at its

ambient

gauss until H+l.0 second; thena transient

value of about .31

radiation effect turned off the magnetometer.

At H+3 seconds,

instrument recovered and measured the magnetic

field until H+25

The magnetometer output frequency,

seconds.

telemetry receiver,
values.
ment,

the

as measured by the

could represent one of three magnetic field

During the time of thb,

dead zone in

the magnetometer measure-

information was lost which would have allowed a unique deter-

mination of the magnetic field value represented by the measured
frequency.

Thus,

the bottom graph in Figure 3.3 could represen-t. an

increase rather than a decrease

in the magnetic field.

Figure 3.4 shows the output of the Faraday cup foil and the
high-energy beta detector for the entire flight of the payload.

top graph in Figure 3.4, showing the Faraday cup foil output,

The

indicates

that the payload passed through a layer of ionized material which
was probably caused by the debris stopped on top of the ionosphere;

subsequently, a negative charge was detected due to high'-energy
electrons.

This is

The lower graph in

similar to measurements

Figure 3.4 shows that the payload passed through

a region containing high-energy beta particles

to H+30 3econds.
kilometers

j

taken aboard Payload P-6.

from H+13.5 seconds

These times correspond to rocket altitudes of 271

and 301 kilometers, which can be interpreted as being a

layer of stopped radioactive debris.

48

'

3.1.4

Position P-7 Measurements.

Payload P-7 was located

414 kilometers up and across the field line from the burst point.
.,¶easurements obtained from the instruments from H-0 to H+50 seconds
are ýflown in Figure 3.5.

Proceeding from the top to the bottom of

Figure 3.5, the five plots represent the outputs of the following
instruments:
(1)

The Faraday cup heavy-particle detector

(2)

Faraday cup high-energy electron collector

(3)

Solid-state beta detector

(h)

Solid-state gara-neutron detector

(5)

Rubidium vapor magnetometer

The top graph in Figure 3.5 gives the results from one of the
three Faraday cup foils located aboard P-7.

Thne foil was designed

to measure ion fluxes from plus and minus 105 to
2
cm /secster.

0l1

charges per

T'he foil measured a large flux of positive ions which

started at about H+!.20 seconds and continued for 4OO seconds.

T-_he

arrival time inolied an average velocity of 3h5 kilometers per
second for the positively charged debris.

The dotted line starting

at H+I.T seconds in the top graph of Figure 3.5 is the envelope of
the high-energy betas modulated at the spin rate of the payload.
The second graph from the top in Figure 3.5 gives the results
of one of the three high-energy electron Faraday cup detectors located
aboard Payload ?-7.

This thick al•minum detector,

located behind the

.

thin -oil in the Faraday cup, measured a large flux of electrons
starting about H.+O.140 second.

49

'.

7.

,

---

The third graph from the top in Figure 3.5 represents the
output from one of the six lithium drifted solid-state detectors
aboard Payload P-3.

The first peak at about 5 x 10

second

was

due to the prompt gama=s from the device, and the peak intensity

6.57 milliseconds later was due to the lI&-Mev fusion neutrons.
At H+480 milliseconds a sharp increase in beta flux intensity was
measured which subsequently fell "

apidly at 4.3 seconds.

The

betas meavured after 4. 3 secon

c trapped by the magnetic

field as indicated in Figure 3.11.

This occurred simultaneously

with the recovery of the magnetic field.

The arrival time of high-

energy beta particles at H+480 milliseconds implies an average
expansion velocity of 862 kilometers per second for the shell of
high-energy betas.
The fourth graph from the top of Figre 3.5 gives the results
from the ga=a neutron detector for Payload P-T.

The first peak

which occurred at about H+2 milliseconds was due to the prompt gammas
from the bomb.

A second peak occurred 6.57 milliseconds later and

was due to the lh-Mev fusion neutrons.

A -,hell of radioactive debris

ions caused a third peak in gamma intensity at F+0.2 second.
The bottom graph in Figure 3.5 shows the output of the Rb8 5
magnetometer on Payload P-7.

A timer malfunction caused data to be

lost from H-0 to H+2.9 seconds.

The ambient field of 0.27 gauss at

H-0 time is denoted by a dot in the upper left hand corner of this
plot.

The bottom graph shows that the magnetic field returned

toward anbient value at 4.3 seconds.

50

Simultaneously with this return

,'

field,

toward the ambient magnetic

the high-energy beta particles

The radioactive shell of

were trapped as shown in Figure 3.6.

delayed gamma emitters had passed the payload as shown in

the gamma

detector measurement.
Position P-2 Measurements.

3.1.5

807 kilometers up and across the magnctic
point.

Measurements

obtained as a

are shown in Figure 3.7.
in

Figure 3.7,

Payload P-2 was located
field lines from the burst

function of time after detonation

Proceeding from the top to the bottom

the thrze plots represent the outputs of the following

instruments:

(1)

Faraday cup foil

(2)

Solid-state beta detector

(3)

Rubidium vapor magnetometer

The top graph of Figure 3.7,
particle detector results,

which shows the Faraday cup foil heavy-

was noisy from H-O to

i÷0.6 second.

The

information at 0.6 second shows the positive ion density to be
substantially increased over ambient conditions.
beta detector results,

shown in

The high-enerr"

the center graph of Figure 3.7,

cate a large flux of beta particles arriving at H+19.9 seconds.
bet& particles detected by Payload ?-2 were trapped in

field.

All

the geomagnetic

The bottom graph in Figure 3.7 shows the magnetic

measured by the Rb8 5 magnetometer.

indi-

field as

.h"ne magnetometer experienced

no transient radiation effects, since the payload was far removed
from the detonation point.

in value at H+4 seconds.

The magnetic field started to increase

This increase in ma•rnetic

field at the

51-

.

"

"-

Pyload P-2 position indicates that a diamagnetic bubble was formed
and subsequently decayed without having the plasma boundary pass
the P-2 payload position.

Figure 3.8 shows the real-time beta and

ion flux at the P-2 payload position for the total duration of the
flight.

The Faraday cup ion detector measu~red the highly ionized

region at 320 kilometers.

After passing through this region a net

negative current was measured until the detonation of the weapon,
at which time a net positive charge was measured until the rocket
shown

re-entered the atmosphere.

The high-energy beta detector,

in the lower graph of Figure

3.8, measured a high flux of beta

particles starting at H+19 seconds and rapidly fell off in intensity at 11+60 seconds.

The flux of beta particles then slowly

decayed below the threshold value of the detector at H+200 seconds.
These beta particles were 1001 trapped in the magnetic field, since
the beta intensity was modulated at twice the spin rate of the
vehicle.

Position P-4 Measurements.

3.1.6

Payload P-4 was located

1025 kilometers along the field line from the burst point.

Measurements

obtained from the instruments on this paylodd for thirty seconds
following H-0 are shown in Figure 3.9.

J

Proceeding from the top to

the bottom of Figure 3.9, the five plots represent the outputs of
the following instruments:

(1)

Faraday cup heavy-particle detector

(2)

Faraday cup high-energy electron detector

(3)

Solid-state beta detector

5J

-52°

•• .

(4)

Solid-state

(5)

Rubidium vapor magnetometer

gamma-neutron detector

The top graph in Figure 3.9 gives the results from one of the
three Faraday cup foils located in Payload P-h.

This foil measured

a large flux of electrons with energies greater than 300 ev at 4+0.2
second.

At H÷1.55 seconds the foil

tive ions.

detected a large flux of posi-

The dotted line represents the envelope of the nagatively

charged particle measurements which Vere intensity modulated at the
spin rate of the v-phicle.

The arrival time of positive ions at

1.55 seconds indicates an average velocity of 662 kilometers per
second for this expanding material.
The second graph from the top in Figure 3.9 gives the results
from one of the three high-energy electron Faraday cup detectors.
This detector measured a large flux of high-energy electrons

starting

at 455 milliseconds.

The center graph in Figure 3.9 gives the results from one of
the six solid state beta detectors aboard Payload P-4.

The first two

peaks represent the arrival ef the prompt gammas and the l4Mev
fusion neutrons,

respectively.

measured a sharp increase in
arrival indicates

At H+.455 second,

the beta detector

high energy beta flux.

This time of

an average velocity of 2203 kilometers

for the expanding shell of high energy betas.

per second

These beta particles

were modulated at the spin rate of the vehicle from H÷0. 4 55 second
to H+2.29 seconds at which time the intensity modulation changed from
2.5 cycles per second to 5 cycles per second as shown in

53

Figure 3.11.

The 5-cycle/sec intensity modulation of the beta particles
occurred simultaneously with the reco" -y of the magnetic field and
has been interpreted to indicate the s art of electron trapping.
The fokrth graph from the top of Figure 3.9 gives the results
from the gaoa neutron detector for Payload P-4.
the first and second peaks is

The time between

16.26 aLilliseconds and represents

the flight time of the lU-Mev fusion neutrons.

The resultant

increase in gamma flux a 1h+455 milliseconds has been interpreted
as the arrival of the radioactive shell of debris ions.
The bottom graph in Figure 3.9 shows the output of tie Rb85
magnetometer on Payload P-4.

The magnetic field remained at the

ambient value of 0.22 gauss until H+0.68 second.

At this time the

gamma flux was high enough to cause transient radiation effects in
the rubidium magnetometer electronics.

The magnetometer recovered

from these effects at H+l second and measured a decrease in the
magnetic field followed by an increase toward ambient conditions at
H+2.4 seconds.

Simultaneously with this magnetic field recovery,

the angular distribution of high-energy beta particles changed
from isotropic to anisotropic and peaked at 900 to the magnetic
field lines.
Figure 3.10 shows the results from the Faraday cup foil and
the high-energy beta detector during the entire flight of Payload
P-4.

The faraday cup foil first measured the ions in the region

centered about 320 kilometers and subsequently measured a large
increa•se

-

in positive ions which followed the detonation of the

54

".rn

The high-energy beta detector first measured an expanding

weapon.

shell of beta particles which was traveling at 2,253 kilometers
per second and then a flux of beta particles which slowl.y decreased
in

ihtensity as the rocket proceeded along the field line.

The

slogW decrease in trapped beta intensity was probably due to the
collapse of the magnetic field which allowed the high-energy betas
to escape through the neck of the magnetic bottle along the field
line.

The time his*tory of the intensity of the beta flux was

strongly dependent upon tne trajectory of the rccketlbecause the
rocket did not follow the field line to the southern1 conjugate point.
Hall Effect Magnetometer Measurements.

3.1.7

The Hall

effect magnetometer measuredi the vector component of the magnetic
field along the spin axis of each rocket.

This magnetometer had a

range from plus and minus 0.03 .ýo 4 gauss with an overload catability
of + 6 gauss.

Thne early time results from the! li'all mnappetormeter

weasureýments are shown in Figure 3.12.

The large changes near H1-0

are caused by the transient radiation effect!: on the amplifier lased
in *this device.

A cursory look at the

sagrnetometer 5ikrials indicates

that significant field changes were measured only by PaylIoad P-6.
Tnis field occ.urred simultaneously with the arrival of the highanergy beta rarticles at H1+51 seconds and lasted for 12 inilliseconas.

This may be a magnetic shock, but it

i3.also p~ozsibl'e

that the pulse was caused by the transient radiation effect in the
amplifier.

Although this magnetometer has been calibrated in a

radiation en,,-ronment,
3..IJcnnston

the data is still in tne reduction Ucrcess.
TS?.and M.aznetý,et,ýr.
55

~.s:are 3a-load wjas

operated on Johnston Island during the Star Fish event.

Fifteen

minutes of rubidium vapor magnetometer information was recorded

starting 7.5, minutes before H-O and ending 7.5 minutes after H-0.
Figure 3.13-1hows the magnetic field measured on Johnston Island as
a .runction of time after the Star Fish burst.
was not accurate,

the EMP.

the first

Though the amplitude

large increase at time H-0 was due to

The next increase from the ambient field of 0.3425

gauss to O.3440 gauss occurred at H.3.6 seconds.

This was followed

by a second increase to 0.3454 gauss which peaked at H+25 seconds.
A slow decrease in field to 0.3355 gauss at H + 65 seconds was subsequently
followed by a return to the ambient field at H + 400 seconds.

The last large

decrease of 700 gamma occurred at H + 65 seconds and can be correlated
with the Edgerton, Germeshausen, and Grier, Inc., (EG&G) measurements
on Check Mate and King Fish (Reference 12). The magnetometer signals
measured on Johnston Island had approximately the same shape, but the
amplitudes anid times were strong functions of bomb altitude and yield.

In

all three cases, the field had two increases followed by a slow
decrease and subsequent recovery to ambient conditions.

be fortuitous,

It

may

but the last slow decrease in field for the three

highest altitude shots was directly proportional to the yield
of the devices.Q
-. 4

3.1.9

R.F Attenuation Measurements.

Receiving sites for

the Star Fish event were located on Johnston, Oahu, Hawaii, Tern, and Canton

56

,.

Islands.

These sites are shown in Figure 2.2 along with the

rocket trajectories projected onto the earth't

surface.

Frequencies

trnsimitted by the payloads were as follows:

P-2

247.3 Megacycles

P-3

237.0

P-4

229.0

P-6

221.5

F-7

216.5

"

Figure 3.14 shows the signal strength records received at

Jonnston Island from H-I to H4l00 seconds.

The receiving system

on Johnston Island had a 30-db dynamic range and used an antenna
with a 13-dbm gain.

This system was designed for payload check-

out and was used only as a backup for payload reception.

The

signal strength measured at Johnston Island decreased to receiver
noise levels immediately at H-0 and recovered at about H+7 seconds.
The signal strength as measured from outlying sites on Star
Fish are shown in Figure 3.15.
l-to

28-dbm gain antennas,

at Johnston Island.

Since these receiving sites used

blackout was not as severe as experienced

The RF signals were all blacked out at H-0 but

recovered in about a half a second to levels high enough to obtain
good data.

The blackout duration and recovery time was a strong

function of the relative position of the signal. transmission path
and the ionized regions produced by the bomb.
3.2

CHECK MATE
3.2.1

Check M'te Instrument Positions.

Two rockets were

used on Check H.ate to position Payloads P-1 azid P-5 at 101 kilometers
57

7

along the field line from the burst and at 112 kilometers above
the burst at H-0 time,

respectively.

These payloads were dupli-

cates of those used for the Star Fish event and the trajectories
are shown it Figure 3.16.

This represents a slice in the magnetic

meridian through Johnston Island) and the extra heavy solid line
indicates the position of the payloads at time H-O.
of the trajectories onto the earth's surface is

A projection

shown in Figure

3.17, and the positions of the payloads at H-0 are denoted by an
"X" along the flight path.

Figure 3.17 also depicts the islands

that were used as receiving sites for the two payloads.
vs.

altitude curve is

The time

shown in Figure 3.18 with H-0 time occurring

at 30,60C seconds.
3.2.2

Position P-I Measurements.

Payload P-I was located

101 kilometers along the field line and up from the burst point.
Flux measurements obtained as a function of time from the instruments in this payload are shown in Figure 3.19.

Proceeding from

the top to the bottom of Figure 3.19, the five plots represent the
outputs of the following instruments:
(1) Faraday cup thick collector
(2)

The

l-rail Faraday cup foil

(3)

Solid-state beta detector

(M) Solid-state gamma-neutron detector
(5)

Rubidium vapor magnetometer

The top graph in Figure 3.19 shows the results from one of the
three Faraday cup foils located in Payload P-1.

This foil measured
-

-

58

""WI
i~~i-,

.

T./_-..L
.~~~ .. . ......

.

.-.

i...

i,.

,.

-.....

... •.....,....2.

....

....

-

.

S-

.

-•*~*-,t.v.-.-

--

-

-

..

-••

.r-_

- •-.

•

T••

•_.

.

•

--

•--

a large flux of electrons with energies greater than 300 ev
immediately following H-0,

and at H+20 milliseconds the foil

started to detect a large flux of positive ions.
charted flux was

measured

This positively

until 11+0.l second at which time

a large flux of negative particles was measured.

This negative

flux could be due to Compton electrons which were detected as
the Faraday cup turned and faced the nuclear fireball.

The angular

".

coordinates with respect to the fireball origin were not determined
in the initial phase of data reduction.

The next large flux of

positive ions occurred at H+.25 second which indicated an average
ion velocity of 400 kilometers per second over the flight path of
101 kilometers.
The second graph from the top on Figure 3.19 shows the results
from one of the three high-energy electron Faraday cup detectors.
This thick collector detected a negatively charged flux at H+0.01
second and continued to measure this flux until a decrease occurred
at H÷20 seconds.

The center graph Figure 3.19 shows the results from

one of the six solid-state beta detectors located in Payload P-1.

4.-

At H+6
seconds this distribution changed to an anisotropic angular distribution with the flux values peaked at 900 with respect to the magneticRa
field lines,
39

Ja

The fourth graph from the top in

Figure 3.19 shows the results

frmthe gamma-neutron detector located behind the nylon bremsstra~hlung shield,

The two peaks represent the arrival of the prompt

gammas and-the lU-hev fusion neutrons,

respectively.

The bottom graph in Figure 3.19 shows results from the Rb8 5
magnetometer.

The magnetic field started to decrease at the same

time that the high-energy betas arrived at the payload position,
and continued to decrease until a minimum was reached at H+0.455
second.

The magnetic field then recovered to its ambient value

at H+1.25 seconds.
2.19, is

The subsequent decrease,

as shown in Figure

due to the rocket traveling out to lower values of the

earth's magnetic field.
The results from the Faraday cup ion detector and the solid
state high energy beta detector are shown in Figure 3.20 as a

function of time for the entire flight of the payload.

1he top

graph of Figure 3.20 shows that the Faradey cup foil measured a.

I

large flux of positive ions immediately following the detonation
for about 500 seconds.

The beta detector results,

bottom graph of Figure 3.20,

shown in the

indicate that the large flux of beta

particles which started at H+63 milliseconds dropped i=nediately

-. 71

to near ambient values at H÷2 seconds.
3.2.3

Position P-5 Measurements.

Payload P-5 was located

112 kilometers directly above the burst point.

Measurements obtained

from the instruments in this payload for a period of thirty seconds
following H-0 axe shown in

Figure 3.21.

Proceeding from the top

to the bottom of Figure 3.21, the five plots represent the out60

puts of the follcvwng instruments:
(1)

1'arsday cup thick collector

(2)

The

(7)

Solid-state beta detector

1--mil

.b

Faraday cup foil

.)

•;olid-st•,te

( .)

Iubidium vapor magnetometer

L.

gamma-neutron detector

The top graph in Figure 3.21 shows the output of the Faraday cup
foil heavy icn detector.

There was an increase in positive ion

flux at H+0.14 se!cond, and this ion intensity was modulated at the
spin rate of the vehicle.

The second graph from the top of Figure

3.21 gives the re!sults from one of the three high-energy Faraday
cup detectors.

"he thick collector located behind the Faraday cu.

foil measured th:-ee peaks of the positive ion current at H+2,
and 20 milliseconds.

8,

The center graph in Figure 3.21 gives the out-

put of the high-,tnergy solid-state beta detector.

This detector

measured the arr:.val of the prompt gammas which was followed 1.84
millisecouds late~r by the 114-Mey fusion neutrons.

No beta flux was

measured by this detector.
The results from, the geamm-neutron detector are showun on the
fourth graph frorn the top in Figure 3.21.

This detector measured

a time separe.tiol, of l.8h milliseconds between the arrival of the
prompt gamma and the fusion neutrons.

No gamma ray flux intensity

exceeded the inst;rument threshold after passage of the 11 4-Mev
fusion neutrons.
The bottom gTaph in Figure 3.21 shows the results from the Rb 5
magnetometer measurements.

The vehicle experien. ed an R
61.

droz-off

"

in muagetic field intensity as it

proceeded out from the earth's

reduction in

field has not been subtracted,

Since R

surface.

the

lower graph in Figure 3.21 may contain some very low perturbed
field infor'Mation after H-0.

Figur'

3.22 shows the output of the Faraday cup foil and beta

detector as a function of time during the entire flight of the
payload.

The high-energy beta particle flux did not exceed the

threshold of the beta detector at any time during the flight of
Payload P-5.
3.22,

The ion intensity,

shown in

the top graph of Figure

increased in positive value following H-0.

decreased due to an increase
measurements shown in

It

subsequently

in negatively charged ion flux.

The

--

Figure 3.21 indicate that the radioactive

bomb debris did not reach this payload during the flight time.
3.2.4
transmitted
respectively.

RF Attenuation Measurements.
10

Payloads P-1 and P-5

watts of RF energy at 229.9 and 231.9 megacycles,
Receiviag sites were located at Canton,

Tern, and Oahu Islands during the Check Mate event.

Johnston,

Figures 3.23

and 3.24 show the signal strength records as measured on Johnston
and Tern Islands fromH-i to H+100 seconds.
fromPaylcad P-1,

The signal strength

as measured on Johnston Island,

decreased sharply

at iH+l second when the ionized plasma expanded into the line-ofsight path from the antenna to the payload.

62
Vages 63 through R6 deleted.
•

-1..

..

...-.

r.

,.

,

.rr .r

AN

CRAPTER 4"
DISCUSSION

4.1

STAR FISH DEBRIS HISTORY
Table 4.l is a synopsis of the time-dependent quantities

measured by Project 6.7 instrumentation.

"

-

These measurements

indicate that the debris expanded unimpeded along the field lines

for thousands of kilometers,but that this debris was drastically
slowed as it traversed across the field lines.

The debris was

probably stopped at an altitude between 500 to 800 kilometers above
the burst point and 270 kilometers below the burst point.

Figure

4.1 shows the rocket trajectory and also an estimate of the plasma
bubble surface at H+0.051 second

and H+0.480 second.

probably expanded for approximately

1

This bubble

second and subsequently

collapsed, squirting the ionized material and high-energy beta
particles down along the field lines toward the northern and southern magnetic conjugate regions.

Previous estimates made in Section 1.3

indicate that the percentage of debris ionized was between 10 and 100%.
The radioactive debris particles injected betas at high enough L values
(Reference 13)

to take the high-energy electrons over the southern

magnetic anomaly

and produced a long-lasting belt of electrons

around the earth.

Figure h.2 shows the center of this artifiCial

belt as measured by Van Allen (Reference 14) from satellite LNUJ1N I
detectors.

-

" ".

Approximately 5 to 10% of the total high-energy beta

particles were injected at high enough L values to pass this magnetic
87

r -,. .- -

field anomaly.

Satellite measurements placed the center of the long-

lived artificial belt at an L value of 1.2.

*

Most of the high-energy

betas injected along the field line through the burst point were
deposited in the atmosphere at the northern and southern magnetie

L

conjugate regions.
It

is

recommended that more rocket payloads be used in

future

experiments involving asymetric veapon expansions.
4.2 CHECK MATE DEBRIS HISTORY
Table 4.2 is a synopsis of the Check Mate debris expansion.
4.3 DATA REDUCTION
The information on magnetic tapes as received by the telemetry
sites was reduced by a digitized process which used an Astro Data
Most of this data is

included

Detailed reactor calibration data which is

presently

A/D converter and a CDC 160 4 computer.
in this report.

being reduced will allow a more accurate determination of the flux,
energy, and angular distributions of the debris parameters.

This

voluminous calibration data and more detailed flux information will
appear in a future report.

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REFERENCES
1. A.L. Latter, and R.E. LeLevier; "The Pancake Shot (U)"; RM-2361,
April 1959; The RAND Corporation, Santa Monica, California; Secret
Restricted Data.
2. H.L. Brode; "Theoretical Description of the Blast and Fireball for a
Sea Level Megaton Explosion (U)"; RM-2248, September 1959; The RAND Corporation, Santa Monica, California; Secret Restricted Data.
3. C. L. Longmire; "Notes on Debris-Air-Magnetic Interaction"; RM-3386PR, January 1963; The RAND Corporation. Santa Monica, California; Unclassified.
4. T.G. Cowling; "Magnetohydrodynamics";
New York, New York.

Intersctence Publishers,

1956;

5. D.I. Pxickett; "Selected Fish Bowl Operational Measurements (U)"; FC/
01640270, January 1964; Headquarters Field Command, Defense Atomic Support
Agency, Sandia Base, New Mexico; Secret Restricted Data.
6, R.D. Cowan, et al; "Calculations on the Early Phases of the Star Fish,
Blue Gill, and Urraca Explosions (U)"; LAMS-2749, March 1962; Los Alamos
Scientific Laboratory, Los .Aamos, New; Mexico; Secret Restricted Data.
7. R.W. Hendrick, R.H. Christian, and P..G. Fisher; "Operation Fish Bowl
Theoretical Estimates o, Expected Phenomena (U)"; RM 62TMP-36, May 1962;
General Electric Company, Santa Barbara, Californira Secret Restricted Data.
8. W.A. Lokke; "The Radiated Flux and Debris Angular Distribution of
Star Fish Prime (U("; UCMD-4551, January 1963; Lawrence Radiation Laboratory,
Livermore, Zalifornia; Secret Restricted Data.
9. M. P. Shuler, et al; DASA Review Symposium Fish Bowl 1, 22 (1963),
DASA 1449; Defense Atomic Support Agency, Washington,ID. C.; Secret Restricted
Data.
10. D.C. Jensen, and J. C. Cain, Unpublished, presented at April 1962
American Geophysical Union Meeting, Washington, D.C.
11. H. I. West; "The Beta Ray Spectrum of the Fission Products of U2 5 at
1 to 300 Seconds After Fission"; UCRL-6123, August 1960; Lawrence Radiation
Laboratory, Livermore, California.
12. R. O'Rourke; "ELF, VLF, and Magnetic Measurements (U)"; DASA 1383,
June 1963; Defense Atomic Support Agency, W•ashington, D.C.; Secret Restricted
Data..4pq
92

13. C.E. McIlwain; "Coordinates for Mapping the Distribution of Magnetically Txapped Particles"; Journal of Geophysical Research, 66, 3681-3691, 1961.
14.

J. A. Van Allen. et al; "Satellite Obser-vations oi the Artificial Radiation

Belt of Juliy 1962"; Journal of Geophysical Research, 68, -619-627, 1963.

93

94

ages

and

Fdel eted.

.

-