A 35 KW AIRBORNE ILLUMINATION SYSTEM (U)

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP70B00584R000100120001-0
• Release Decision: RIFPUB
• Original Classification: C
• Document Page Count: 63
• Document Creation Date: December 15, 2016
• Document Release Date: September 11, 2003
• Sequence Number: 1
• Publication Date: January 1, 1966
• Content Type: REPORT

Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
CONFIDENTIAL
A 35 kw AIRBORNE ILLUMINATION SYSTEM (U)
R. C. Eschenbach
R. J. Sarlitto
H. H. Troue
"This material contains information affecting the
national defense of the United States with in the
meaning of the espionage laws. Title 18, U. S. C.
Secs. 793 and 794, the transmission or revelation
of which in any manner to an unauthorized person
as prohibited by law."
This document consists of----_38 ------pages;
Copy No.--P
----of---?k--Copies.
This document has 25 attachments.
CONFIDENTIAL
Union Carbide Corporation
Linde Division
USAF review(s) completed.
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/1 4uNTI&00584R000100120001-0
ARPA Order No.:
Program Code No.:
Name of Contractor:
Date of Contract:
Contract No.:
Project Director:
Title of Work:
5G50 (22)
Union Carbide Corporation
Linde Division
January 1, 1966
AF 33(615)-3437
D. A. Bryson
Services and Materials Necessary
to Furnish an Illumination Source (U)
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PniurinrUT
 Approved For Release 2003/1 cmfaNTI&00584R000100120001-0
FOREWORD
This report was prepared by Union Carbide Corporation, Linde Division,
Speedway Laboratories, Indianapolis, Indiana under USAF Contract No.
AF 33(615)-3437. This work was administered under the Air Force Avionics
Laboratory by Mr. H. R. Gedling and Lt. James W. Mayo III.
This report describes the 35 kw airborne illumination system designed,
built and tested January 1, 1966-May 15, 1967 at the Speedway Research Laboratory,
Linde Division, Union Carbide Corporation, Indianapolis, Indiana.
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PAUCIt1CUT1A
 Section
Approved For Release 2003/1
NF00584R000100120001-0
PnI&
0101
TABLE OF CONTENTS
Title
List of Figures (2 pages)
Page
1.0 INTRODUCTION AND SUMMARY . . . . . . . . . . . . . 1
Li The Illumination Pattern . . . . . . . . . . . . . . . . 1
1.2 Systems . . . . . . . . . . . . . . . . . . . . . . . . 2
1. 3 Summary and Recommendations . . . . . . . . . . . . . 3
2.0 35 kw RADIATION SOURCE . . . . . . . . . . . . . . . 4
2. 1 General Description . . . . . . . . . . . . . . . . . . 5
2. 2 Range of Performance . . . . . . . . . . . . . . . . . 6
2. 3 Assembly Procedure . . . . . . . . . . . . . . . . . . 8
2. 3. 1 Anode.Electrode Assembly . . . . . . . . . . . . 8
2. 3. 2 Cathode, Electrode Assembly . . . . . . . . . . . 9
2. 3. 3 Maintenance . . . . . . . . . . . . . . . . . . . 10
3.0 OPTICAL SYSTEM . . . . . . . . . . . . . . . . . . . 11
3.1 General Description of Reflective and Absorptive Elements . 12
3.2 Evaluation of the Beam Pattern . . . . . . . . . . . . . 15
3. 3 Assembly and Installation Procedure for Optical System 17
3.4 Maintenance . . . . . . . . . . . . . . . . . . . . . . 19
4.0 AUXILIARY SYSTEMS . . . . . . . . . . . . . . . . . 20
4. 1 Power Supply . . . . . . . . . . . . . . . . . . . . . 20
4. 2 Control System . . . . . . . . . . . . . . . . . . . . 21
4. 3 Gas Delivery System . . . . . . . . . . . . . . . . . . 21
4.4 Coolant System . . . . . . . . . . . . . . . . . . . . 22
5.0 SYSTEM PREPARATION PROCEDURE . . . . . . . . . . 22
5. 1 Cooling System . . . . . . . . . . . . . . . . . . . . . 22
5.1.1 Required Equipment . . . . . . . . . . . . . . . 22
5.1.2 Purging and Filling the Coolant System . . . . . . 23
5.1.3 Coolant System Pressurization . . . . . . . . . . 24
5. 2 Gas Supply System . . . . . . . . . . . . . . . . . . . 24
5. 2. 1 Filling the Liquid Argon Vessel . . . . . . . . . . 24
5. 2. 2 Check of Internal Temperature . . . . . . . . . . 25
5.2.3 Electrical and Control Systems . . . . . . . . . . 25
5.2.4 Removal of Optical System Shield . . . . . . . . . 26
6.0 OPERATING. PROCEDURE - AIRBORNE OPERATION . . . 26
6.1 Starting Sequence . . . . . . . . . . . . . . . . . . . . 26
6. 2 Beam Intensity Adjustment . . . . . . . . . . . . . . . 27
6. 3 Intermittent Operation . . . . . . . . . . . . . . . . . 27
6. 4 Altitude and Flight Velocity Limitations . . . . . . . . . 27
6. 5 Operating Time and Shut-Down Procedure. . . . . . . 28
iii
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnhuflnftuTIAI
 Approved For Release 2003/1I&00584R000100120001-0
Section Title
Page
7.0 SECURING SYSTEM AFTER OPERATION . . . . . . . 29
7.1 Replace Optical System Shield . . . . . . . . . . . . . . 29
7.2 Vent Unused Argon . . . . . . . . . . . . . . . . . . . 29
7. 3 Purge Coolant for Low Temperature Storage of System , . 29
8.0 SAFETY CONSIDERATIONS . . . . . . . . . . . . . . . 29
8.1 Personnel Exposure to the Radiation Beam . . . . . . . . 29
8.2 Electrical Hazard . . . . . . . . . . . . . . . . . . . 30
8.3 Liquid Argon Handling and Pressure Vessel Precautions. . 30
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnurtnrITIAI
 Approved For Release 2003/1BONFIDENTILOO584R000100120001-0
LIST OF FIGURES
Figure 1 35 kw Illumination System and Pilot's Control Box
Figure 2 Schematic of 35 kw Radiation Source
Figure 3 Radiation Spectra at Minimum System Output
Figure 4 Radiation Spectra at Maximum System Output
Figure 5 Anode.Electrode Assembly for 35 kw Radiation Source
Figure 6 Anode, 'Electrode Subassembly for 35 kw Radiation Source
Figure 7 Cathode. Electrode Assembly for 35 kw Radiation Source
Figure 8 Cathode, 'Electrode Subassembly for 35 kw Radiation Source
Figure 9 Schematic of Reflective-Absorptive Optical System for the 35 kw
Illumination System
Figure 10 Illuminated Area Lateral Distribution Achieved with a 4? x 40?
Prototype Optical System
Figure 11 Reflector Assembly for 35 kw Illumination System
Figure 12 Input kva to the Illumination System versus Input Power to the
Radiation Source
Figure 13 35 kw Illumination System Power Supply Elements
Figure 14 Wiring Diagram for 35 kw Power Supply and Pilot's Control Box
Figure 15 Pilot's Control Box for 35 kw Illumination System
Figure 16 Functional Schematic of Pilot's Control Box for 35 kw
Illumination System
Figure 17 Wiring Diagram for Sensor Elements in Control System for 35 kw
Illumination System
Figure 18 Wiring Diagram for Main Power Distribution Box for 35 kw
Illumination System
Figure 19 35 kw Illumination System Gas Supply Elements
Figure 20 Flow Schematic for the Gas and Coolant Systems for 35 kw
Illumination System
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
Pn11CInr11TIAI
 Approved For Release 2003/1CONF &00584R000100120001-0
Figure 21 35 kw Illumination System Coolant Loop Elements
Figure 22 35 kw Illumination System Liquid Argon and Coolant Fill Panel
Figure 23 Coolant System Service Box
Figure 24 35 kw Radiation Source in Illumination System
Figure 25 Aircraft Altitude Velocity Envelope for 35 kw Illumination System
Operating at Maximum Power
vi
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
Pnhlflnf11TIA
 Approved For Release 2003/1 IKNJIA00584R000100120001-0
A 35 kw AIRBORNE ILLUMINATION SYSTEM
1.0 INTRODUCTION AND SUMMARY
Results of a program to establish feasibility, fabricate and deliver
an ultraviolet airborne illuminator are reported. The work, on Contract
AF 33(615)-3437, has resulted in a flight weight package which has been satis-
factorily operated in the laboratory at input powers of 20-35 kilowatts, in both
the covert and visible modes. Succeeding sections of this report will discuss in
detail the radiation source, optical system, auxiliaries, operating procedure and
safety considerations.
The overall system is shown in Figure 1. Power from an aircraft
three-phase, 400-cycle generator is supplied to the package. The small pilot's
control box, also shown in Figure 1, enables the pilot to control illumination in-
tensity and duration. Heat rejection is to ambient air, using a movable scoop.
Internal sequencing and interlocking provide for fail-safe operation and automatic
occurrence of starting and stoping procedures. The beam has a fixed 2? x 40? and
can be varied spectrally by inserting filters (on the ground).
1. 1 The Illumination Pattern
The radiation source has a 1. 5 inch long are and a reflector sys-
tem which forms a fan-shaped beam of variable spectral characteristics. It has
been found that filters for optimum ultraviolet but minimum visible transmission
also permit a significant degree of infrared transmission. Thus, the filters pro-
vide both ultraviolet and infrared while removing over 99. 9% of the visually
-1-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
RUMUTA1
 Approved For Release 2003/1OWKUJ 00584R000100120001-0
effective radiation. In addition to demonstration of design point operation with
filters, operation with filters removed has permitted a large visible output,
estimated as over 0. 5 million lumens in the same fan-shaped beam, An alternate
set of filters, optimized for infrared transmission with effective removal of both
visible and ultraviolet light, is included with the package. The infrared power can
be increased by a factor of over 4 over that available with the UV-IR filters if
the alternate filters are used.
The reflector system used with the line radiation source forms a
beam narrower in the fore-and-aft direction than the originally specifided 4 degrees.
Analysis has indicated that a reduction in the spread would be desirable in order
to reduce exposure time and image motion. This was achieved without increased
size and weight. The reflector has an aperture about 6 inches by 14 inches, and
our laboratory tests have indicated that approximately 90% of the light is within
a 2-degree spread. The 40-degree pattern is close to the desired uniform illumi-
nation on a flat plane.
1.2 Systems
The package uses automatic sequencing elements to reduce the num-
ber of operating controls to a minimum while assuring safe operation (or termina-
tion of operation in the case of malfunctions). The pilot's control (a small, separate
control box) consists of a make-ready switch and indicator, an are start switch
and indicator, and an intensity control. The illumination package measures
30 x 36 x 40 inches and has a complete cover, lifting lugs, and power factor
correction condensers. These elements, added to the original specifications, have
-2-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
MUCIITA
 Approved For Release 2003/1W W=JL00584R000100120001-0
increased the weight slightly over the 400-pound goal to 470 pounds. The system,
as originally specified, weighs 402 pounds.
The radiation is generated in an arc inside a quartz envelope, with
flowing argon gas constricting the are to a narrow column raising its temperature
and inducing intense radiation. The argon is supplied from a cryogenic liquid
container. Heaters in the container boil off liquid at the desired rate. The gas is
then heated to near room temperature before flowing into the device, being heated
by the are, cooled somewhat in a water exchanger, and then discarded along with
the cooling air. A closed-loop water system removes heat from the arc electrodes,
the reflector and the are gas, and then rejects the heat to ambient ram air ingested
by a scoop. Power, three-phase, 400-cycle, 120/208 volt, is conditioned by a
saturable reactor controlled by the pilot's intensity control, a transformer to in-
crease the voltage and a silicon rectifier stack to convert the alternating current
to direct current. By this means, the operating voltage of 300-315 volts can be
achieved at the desired current of 70-110 amperes. Because an arc power supply
tends to have a relatively low power factor, a modification was requested by AFAL
to permit operation from generators of lower capacity than those originally speci-
fied. Power factor correction capacitors have been included which reduce the
total kva demand to about 43 kva for operating everything in the device (except for
a minor amount of 28 volt dc control power).
1.3 Summary and Recommendations
The package has been operated in the laboratory using a blower to
simulate ram air for the cooling scoop. Satisfactory operation of the assembled
-3-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnucinflTIAI
 Approved For Release 2003/lCONF1D JALB00584R000100120001-0
system has been encountered during many starts and a total of about 5 hours of
running. Equally reliable operation is expected after installation in an aircraft.
Since the amount of air needed varies little with altitude and de-
pends only on the heat to be rejected while the air actually ingested by a scoop of
fixed design varies significantly with altitude and velocity, the rejection of heat
to ambient air requires close integration with aircraft performance. For this
reason, the source is suitable only for certain altitudes and velocities with the
scoop supplied. A more flexible scoop or a scoop designed for a specific aircraft
would be needed to cover a wide range of operating conditions.
A desirable change for potential, improved models would be to have
a closed-cycle gas system rather than open-cycle. At the time the work was
initiated, an open-cycle system was the most assured of success and was weight-
competitive. Since that time, development work has shown a good probability of
obtaining a satisfactory diaphragm recirculation compressor which would permit
indefinite running times as well as operation with gases like krypton or xenon
which are more effective in generating infrared and visible radiation than is argon.
Information generated from the course of the work shows significant
growth potential for this approach in power, efficiency and performance. Use of
reflectors to provide different shape beams, such as 40? square or 450 cone,
could be cone with relatively simple changes to result in expanded areas of
application.
2.0 35 kw RADIATION SOURCE
The function of the 35 kw radiation source is to establish a. small
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PRUMf'NTAI
 Approved For Release 2003/1 =HA00584R000100120001-0
diameter, long, intensely radiating, electric are between two non-consumable
electrodes. Since the arc is cooled by flowing gas, maintaining a specified
current results in a high current density and high temperature core. The com-
bination of high current density and high temperature produces intense radiant
energy.
2.1 General Description
The radiation source is shown schematically in Figure 2. The
source is composed of two electrodes aligned axially within a pair of cylindrical
quartz envelopes. The quartz envelopes are also concentric and axially aligned.
The quartz envelopes transmit the radiation and provide pressurization and con-
tainment for the swirling flow which constricts and maintains the line arc.
The anode electrode is hollow allowing the gas to exit after it has
passed through the arc column. The arc terminates on the interior of and rotates
about the circumference of the hollow electrode. The cathode electrode assembly
is a movable, recessed stick. The are attaches to the tip of the stick which is re-
cessed in a tungsten shroud, Because of electron emission cooling, the stick is
capable of operating for extended periods as the arc termination point. The cathode
assembly has a built-in gas piston so that the stick electrode may be advanced
across the 1. 5" arc gap to contact the anode and withdraw the are. The gas supply
for the starter piston is the same as that for the arc chamber. Withdrawal of the
piston is automatically controlled by a current-sensitive relay which senses the
initiation of the arc.
The anode and cathode bodies are axially positioned by the end walls
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnhflnfUTIA
 Approved For Release 2003/1 UNUMM00584ROO01
of the optical system which serve as mounting fixtures for the are source. The
envelope seals are O-rings at each end of the quartz envelopes. The inner en-
velope is sealed on the I. D. , and the outer envelope is sealed on the 0. D. The
electrode assemblies are cylindrical and fit into the bodies which provide align-
ment and fluid flow passages.
The arc gas passes through the annulus between the two quartz
envelopes, enters the anode electrode assembly, is injected into the arc chamber
as a swirling flow, exits the arc chamber after having passed through the arc, and
passes through a heat exchanger to be cooled to less than 500?F before being
dunnped overboard.
All the seals of major components are of the O-ring type to
facilitate assembly and disassembly. Thus, the electrodes and quartz envelopes
are readily accessible for inspection.
2.2 Range of Performance
The design goal was to produce a radiation source capable of
operating at variable input power so that the radiation in the 2400 A to 4000 A range
could be varied by a factor of 2. The most readily controlled variable in the radia-
tion source is the current at which the source is operated. With fixed flow and
geometry, the current defines the chamber pressure and the operating voltage for
the radiation source. It is of interest to note that the efficiency with which the
radiation source converts electrical energy into radiant energy increases as the
current to the radiation source increases. Consequently, to obtain a factor of 2
variation in radiant output requires less than a factor of 2 variation in operating
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
nhUNTIA
 Approved For Release 2003/1CNIFMNTI00584R000100120001-0
current. To obtain the desired variation in radiation output, the current to the
radiation source is controlled by a saturable core reactor over a range from
72 to 110 amperes dc.
Figures 3 and 4 show spectra obtained at the minimum and maximum
operating conditions. The minimum operating condition corresponds to a gas flow
of 550 scfh of argon yielding a chamber pressure of 300 psig at a current of
70 amperes and a voltage of 315 volts with a conversion efficiency of 27%. The
maximum operating condition corresponds to a gas flow of 550 scfh of argon yield-
ing a chamber pressure of 310 psig at a current of 110 amperes and a voltage of
310 volts with a conversion efficiency of 30%. The stated flows,. pressures, volt-
ages, and efficiencies are average values.
It can be noted for the spectral distributions that &. 6% of the radiated
energy is between 2600 A and 4000 A, 34. 6% from 4000 A to 7000 A, 31. 8% from
0 0 0 0
7000 A to 9000 A and the remaining 25% between 9000 A and 25, 000 A. Corre-
sponding to each unfiltered spectrum is a spectrum obtained with the radiation
passed through a Corning 7-54 filter which is used to tailor the spectral output from
the radiation source. In the ultraviolet region from 2400 A to 4000 A, the 7-54
filter passes approximately 67. 5% of the incident radiation, and in the range from
7000 A to 9000 A the filter passes 22. 5% of the incident radiation. These spectral
ranges are useful for ultraviolet- or infrared-sensitive films.
These spectral distributions are also useful to determine the portion
of the visible radiant energy, defined as the 4000 A to 7000 A region, which is re-
moved. It can be noted that the 7-54 filter passes 1. 5% of the incident radiation
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
nflJTIAl
 Approved For Release 2003/'CUNF IIAL00584R000100120001-0
in this region. This radiation is passed at the extreme ends of this spectral
O O O
region; some passes from 4000 A to 4400 A and the rest passes from 6800 A to
7000 A. These spectral regions represent extremely non-sensitive portions of a
human eye's spectral response. As a result, the transmitted radiation, given in
terms of luminosity, has a luminosity of 0. 02% of the unfiltered luminosity, mean-
ing that more than 99 9% of the luminous output of the arc radiation is removed by
the 7-54 filter.
2.3 Assembly Procedure
The assembly of the radiation source can be divided into two parts
which will be described separately: the anode electrode assembly and the cathode
electrode assembly.
2.3.1 Anode Electrode Assembly
The anode electrode assembly, shown in Figure 5, consists
of several major components: the anode body which contains the fluid passages
and is used to align the source in the optics' structural mount, a gas-to-liquid
heat exchanger and fitting flange assembly, an electrode nut, a water divider, a
gas manifold and an electrode. The assembly procedure (see Figure 6) is most
easily started with the gas manifold. Install the front O-ring with the O-ring in-
serter provided. Insert the water divider into the gas manifold from the rear.
Insert the electrode from the front with the electrode flange projecting into the
angular front O-ring slot of the gas manifold. The electrode nut can then be
screwed onto the electrode and tightened to hold the entire electrode assembly
together. Initiate the tightening process by hand, tightening the nut so that the
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnuflnruTIAI
 Approved For Release 2003/'F I&00584R000100120001-0
electrode touches the front O-ring. Then further tighten the nut one-third turn.
This is adequate to seal the fluids and allows for differential expansion of the
metal parts when the source is operated at high temperatures. Tools are pro-
vided for holding the electrode and turning the electrode nut. Once this assembly
has been completed, O-rings can be inserted on the gas manifold, water divider
and electrode nut circumferences. Then insert this assembly into the aluminum
body. Once this has been done, the O-rings can be installed on the heat exchanger
assembly. Insert this assembly into the aluminum body to complete the assembly
of the primary anode components. Thp anode electrode assembly can be attached
to the optical system and held in place by the four bolts shown with this assembly.
2.3.2 Cathode Electrode Assembly
The primary components of the cathode assembly shown in
Figure 7 are the cathode body, the gas manifold, the piston cylinder wall, the
electrode housing, the electrode and flow tube, the stop nut, the spring, the gas
piston, and the fitting flange. The first step (see Figure 8) in assembling the
cathode is to install all the O-rings. Screw the electrode and flow tube together
and insert this assembly into the electrode housing. Then insert the resulting
assembly into the gas manifold. Position the stop nut over the tubular section
of the electrode housing and tighten the set screws. Position the spring at the
back of the stop nut and push the gas piston over the flow tube to compress the
spring. The compression should be adjusted so that the electrode extends out of
the electrode housing 0. 2" when the piston is in the forwardmost position. Once
this adjustment has been made, lock the gas piston into place by the four set
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
lITIAI
 Approved For Release 2003/CONF UB00584R000100120001-0
screws. Then place the piston cylinder wall over the gas piston. This assembly
can then be inserted in the insulator. The last component to be assembled is the
fitting flange. Slide it over the flow tube and insert it into the rear of the in-
sulator. The cathode electrode assembly can be attached to the optical system
and held in place by the four bolts shown.
2.3.3 Maintenance
Little maintenance of the radiation source should be re-
quired. In the anode electrode assembly, the only component which can deteriorate
is the electrode. This can be determined by looking at the external electrode
surface, or by removing the electrode from the assembly. It is important that if
the electrode is replaced, the O-rings associated with the electrode also be replaced.
The electrode is the most likely part of the cathode assembly
to deteriorate. If this electrode is replaced, the entire electrode and flow tube
assembly should be replaced by disassembling the electrode assembly.
It should also be noted that since the cathode electrode
assembly is designed to move during starting, it is necessary that the piston O-rings
have lubrication. It is also important that the lubrication be applied with restraint
so that it does not get into the gas stream and contaminate the quartz envelopes.
A silicone O-ring grease, such as Stopcock grease by Dow-Corning, is recom-
mended. The need for lubrication of this piston assembly will be indicated by slug-
gishness of the piston action during the starting process.
It might also be noted that, as is true for all O-ring seal
devices, the O-rings have a finite life and are subject to accelerated deterioration
-10-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnucinflT
 Approved For Release 2003/1CONF IIAL00584R000100120001-0
at high temperature. Consequently, if the source is to be stored for a long
period (greater than 2 months), it would be advisable to replace the 0-rings
prior to renewed use to avoid possible leaks.
Maintenance will be required infrequently; but when neces-
sary, the procedures outlined in the foregoing paragraphs should be followed ex-
actly, and great emphasis should be placed upon care'and cleanliness.
3.0 OPTICAL SYSTEM
The primary purpose of the optical system is to produce a narrow
fan of radiation so as to illuminate a narrow rectangular pattern at some dis-
tance from the optical system. The fan is determined by two angles of di-
vergence which give the beam divergence in two planes oriented perpendicular
to each other from a common point (the exit opening of the optical system).
The narrow beam divergence angle (in the flight direction) is specified to be 40
or less. The wide divergence beam angle (transverse to the flight direction)
is specified to be 40?. The size of the illumination pattern is determined by the
distance of the illuminated area from the exit plane of the optical system.
In addition to the required angular coverage, it is necessary that
the illumination be more intense at the periphery of the rectangular pattern so as
to account for the cosine4 fall-off with a camera lens. This requires that the
illumination on the ground be more intense at the edges by the sec4 of the lateral
half-angle. The optical system has been designed to direct radiation more strongly
toward the periphery so that the entire film plane will have a uniform density to
provide high contrast and resolution over the ground area.
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PAUC UNTIA1
 Approved For Release 2003/10ONFIDENTIL00584R000100120001-0
A 2? x 40? optical system has been designed for the prototype. The
400 divergence is considered adequate to provide the maximum angular coverage
for a single lens of reasonable f-number. Although a 4? divergence was specified
as the upper limit for the beam divergence, measurements of the prototype illumi-
nation pattern have indicated that 80% to 90% of the radiation is with a 2? beam.
The 2? beam spread is more desirable than the 4? beam for minimizing film
blurring and image motion compensation requirements.
3. 1 General Description of Reflective and Absorptive Elements
The reflective optical system components shown schematically in
Figure 9 can best be described by listing some of the pertinent general features:
1. The optical system makes extensive use of cylindrical re-
flector optical elements. The cylindrical elements are utilized to complement
the long line cylindrical arc source.
2. A cylindrical mirror concentric with the axis of the arc column
is used to return radiation through the optically thin arc to the primary optical
surfaces.
3. Optical surface elements which would normally be blocked by
the are and the concentric mirror accompanying the arc are positioned in such a
way as to direct radiation past the arc, allowing the radiation to exit the optical
system in an area that is free from blockage. These blockage-eliminating optical
surfaces are designed to yield a theoretical 100% utilization of the arc radiation
in the plane perpendicular to the arc axis.
4. To obtain the small divergence beam, cylindrically parabolic
-12-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnurinflTIAI
 Approved For Release 2003/1 CONF L00584R000100120001-0
optics are used with the axis of the arc column being at the focal point of the
cylindrical parabola. The maximum divergence angle of the exiting light beam
is determined by the angle subtended by the arc diameter at the primary focal
length of the optical system. It should also be noted that cylindrically parabolic
surfaces can be approximated over short segments by circularly cylindrical
elements, and this has been done in various parts of the optical system.
5. End walls used with the cylindrically parabolic surfaces are
flat and perpendicular to the axis of the are column and the cylindrical optics from
the arc axis to the apex of the optics. Contoured end walls, used to control the
beam divergence in a direction transverse to the narrow beam direction, are used
from the arc axis to the optics aperture. The contoured end walls are located be-
tween the arc axis and the optics opening so that the radiation striking these end
walls has already been focused by the parabolic surfaces and is "in the beam" in
the narrow divergence plane.
6. Beam spreaders are small, flat mirrors located at the opening
of the optical system. There are two such flats located at the outer edges of the
parabola opening to take exiting radiation which has already been put into the narrow
beam and redirect it into the wide beam direction.
In addition to directing the radiation into the desired beam with
the prescribed distribution, it has also been required that the radiation be spec-
trally tailored to eliminate the visible portion of the spectrum, allowing only the
ultraviolet and infrared radiation to exit the optics. Two filtering elements shown
schematically in Figure 9 are used to remove unwanted radiation:
-13-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnucinrMTIAl
 Approved For Release 2003/1CONF 00584R000100120001-0
1. Dichroic or interference filters are used at the wings of the
optical system to remove unwanted radiation by allowing it to pass through the
quartz elements on which dichroic is coated and be absorbed by blackbody ab-
sorbers located behind the elements. Only the ultraviolet radiation is reflected
from these elements.
2. Numerous absorption filters located in the optics exit aperture
are used to remove unwanted radiation by absorbing the energy within the filter
material. The absorbed energy is removed by air cooling of the filter elements.
The initial concept called for utilizing commercially available
Corning 7-54 filters to remove the 4000 A to 7000 A visible radiation allowing the
ultraviolet and infrared portions of the spectrum to be transmitted. The Corning
7-54 filters do remove the required energy as shown in the spectra included with
the previous section of this report. Preliminary tests indicated that, at the high
energy removal rates of 80 to 100 watts per square inch required with the optical
design, the filters would be unable to sustain the associated temperatures and
thermal stress conditions. The 7-54 filters are composed of two separate dyes,
each removing a portion of the visible spectrum. Two sets of filters were acquired,
each removing a different portion of the visible spectrum, so that the loading on each
filter could be significantly reduced. In addition, very thin and long filter strips
are used to reduce the temperature gradients and associated thermal stresses.
Tests with the optical system have indicated that with sufficient air
cooling the filter strips generally survive. Occasionally, the strips crack at maximum
-14-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PAIJr111r11TA1
 Approved For Release 2003/1 RMLOO584R000100120001-0
power from the extreme loading and temperature gradients. To remove any
possibility of a cracked filter disrupting the coolant air flow and causing de-
struction of all the surrounding filters resulting in a loss of covertness, metal
H-bar grids are used to hold the filters in position even should they crack. Con-
sequently, the optical system strip filters are held on all sides by grooves so that
any broken filters will remain properly oriented in the system and accomplish the
job of filtration until the end of the mission. This arrangement assures that
breaking of the filters will represent only an occasional operational cost, but will
in no way hinder proper operation of the filter system.
During the testing phase of the program, the optical system was
assembled element by element and the durability of each element evaluated. The
metallic reflective elements are capable of sustaining the radiant loads using the
prescribed cooling. The wing dichroic filter elements are capable of sustaining
the loading associated with removing the unwanted radiation. The assembled
optical system has been operated in the laboratory for more than five hours at
power levels ranging from 20 to 35 kw and has been shown capable of providing the
required filtering and beam control.
3. 2 Evaluation of the Beam Pattern
Determination of the narrow beam divergence has shown the beam
to have a maximum divergence of 2. 3? as determined by viewing backwards into
the optical system until all the elements become inactive. This implies that 80% to
90% power point in the beam is considerably less than 2. 3?, most likely being of
the order of 2?.
-15-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PTA1
 Approved For Release 2003/'Mgwwam"F IIAL00584R000100120001-0
A prototype optical system using a 500-watt, quartz-iodine lamp
was constructed prior to building the actual system, and was used to determine
the beam control to be accomplished in the 40? direction. Figure 10 shows the
illumination on a flat area achieved with the prototype. At the ? 20? points, the
illumination drops to 52% of the peak value. Allowing the illumination to drop
off at the edges greatly reduces spillage outside the ? 20? limits.
The total power output from the optical system has not been quanti-
tatively determined, but indications are that the optical system directivity effi-
ciency is in the range of 60% to 70%. This value has been partially confirmed by
measurement of the heat absorbed in the optical system elements. Some energy
tends to be conducted and reradiated away from the optical system so that any
heat balance determination is not totally accurate. In addition to the power lost
outside the desired beam or absorbed by the optical surfaces, considerable energy
is removed in the filtering process. Only about 15% of the energy that would exit
the optical system and be in the beam if it were used in the visible mode passes
through the filters. This yields a total output in the beam of less than 900 watts
divided between the ultraviolet and infrared spectral regions. It might also be noted
that by using the wing dichroics which reflect only light in the ultraviolet region,
some of the infrared energy is removed. The wing dichroics handle 24.4% of the
radiant energy emitted by the arc so that the IR is reduced to 75. 6% of that avail-
able if the absorption filters were utilized alone.
'Typical calculated values of the available beam power with the dichroic
and absorption filters in place are listed as follows for several wavelength regions
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
mirinrlTlAl
 Approved For Release 2003/1CDNFIDENIIAL00584R000100120001-0
0
3400
- 4000 A
260 watts at max. power
3400
- 4000 A
140 watts at min. power
7000
a
- 9000 A
360 watts at max. power
0
7000
- 9000 A
230 watts at min. power
3.3 Assembly and Installation Procedure for Optical System
The primary structural components of the optical system shown in
Figure 11 are the two mirrored end walls which are positioned and held by an
aluminum cross-member (saddle). This saddle provides structural strength
alignment and mounting for the concentric mirror. Once the two end walls and
saddle have been assembled, the concentric mirror can be placed in position and
bolted down.
The next step is installation of the arc source. Insert the cathode
electrode assembly previously described into the positioning hole on either side of
the optical system and screw the bolts into the tapped holes in the end wall of the
optical system. The quartz envelopes can then be assembled. The only lubricant
to be used for the O-rings sealing the quartz envelopes is distilled water, and
this should be used in moderation. Insert the quartz envelopes through the optical
system from the side opposite the cathode assembly. Then insert the anode
assembly into the quartz tubes with the optical system support hole providing align-
ment. Push the anode assembly forward while rotating clockwise. Once the anode
assembly has advanced until the optical system stops further forward motion, the
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
AV[111[1IT1A1
 Approved For Release 2003/1 R100584R000100120001-0
assembly is complete. The anode assembly can then be bolted into place. In
order that the distilled water not be spread over the interior of the quartz envel-
opes by the gas, vacuum pump through the source heat exchanger while sealing
the gas inlet and pressure tap until the water is evaporated. This completes
assembly of the source into the optical system.
Once the source is in place, the two saddle mirrors at the top of
the optical system can be attached. Then install the parabolic mirrors which are
held in place on the optical system by the trellis networks. Use heat sink com-
pound between the cooled trellis networks and the parabolic surfaces to assure
good thermal contact. Then install the two 23-degree dichroic mirrors and two
18-degree beam splitter mirrors on either end as shown.
Grooved guides are used to hold the filters in the optical system.
Position the filter guides in the mirrored end walls as shown and insert the
filters from each end. An aluminum H-beam which acts to support the edge of the
filters is used between each filter. Seven filters must be inserted into each of
three layers on either side of the saddle support. The light yellow colored filters
must be positioned closest to the. source, then the blue colored filters and the dark-
est-colored filters nearest the outside, as shown in Figure 9
In the reflector, the water flows through three parallel loops which
are all interconnected. The first loop goes through the sidewall, into the saddle,
through the concentric mirror, out the saddle, and through the sidewall. The other
two loops start at the saddle mirrors, go through the trellis networks and then go
through the absorbers for the dichroic elements.,
-18-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
innurIncuTIAI
 Approved For Release 2003/1COHF&00584R000100120001-0
Air cooling is provided for the filter network. Fittings on either
side of the optics provide attachment for 2" diameter, flexible hoses. These
hoses take air from the scoop and thrust the air into the optical system so
that it may move along the surfaces of the filters to provide cooling. After the
optical system is mounted in the package on the four shock mount points, the
2" diameter air ducts, water coolant loops for the source and optics, and power
cables should be attached. This completes installation of the illumination source-
reflector assembly.
3.4 Maintenance
The primary maintenance requirement for the optical system is
cleanliness, It is important that the optical surfaces remain free of water, dust,
oil and other contaminants. The reflector surfaces can be cleaned with a window
cleaner such as Windex and a soft cloth.
The absorption filters require special attention since they are quite
delicate and easily broken, After hours of operation, it is likely that some of the
filters will be cracked. Although this does not affect the operation of the illumina-
tion system, once disassembled, the broken filters cannot be readily reassembled.
This means that new filters should be installed to replace the cracked filters after
every complete disassembly.
The quartz envelopes, should they become contaminated, will re-
quire cleaning. The most advisable procedure is to remove the two saddle mirrors
so as to provide visual access. Unbolting either electrode assembly allows the
envelopes to be removed from that end of the optical system. There is provided
-19-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
AV[In[11TIA1
 Approved For Release 2003/ICON I1AL00584R000100120001-0
a separate structural mount into which source ends can be inserted once they are
both removed from the optics so as to enable holding the envelopes to pull them off
the O-rings which tend to become vulcanized from the high temperature. The
source should be reassembled into the optical system as previously described
and the two saddle mirrors replaced. Removing the saddle mirrors also provides
a rapid visual check on the condition of the quartz envelopes after extended operation.
4.0 AUXILIARY SYSTEMS
4.1 Power Supply
The radiation source system requires an external supply of 400 cps,
208 v, 3-phase, alternating current. The input kva requirement versus radiation
source input power is shown in Figure 12. Approximately 3. 5 amperes of 28 v
dc power are required. The location of the power input connections is shown in
Figure 1.
The illumination system power supply elements include a main con-
tactor consisting of a power relay in each phase, a saturable core reactor, a
transformer, a rectifier and capacitors for power factor correction, as shown in
Figure 13. The power supply circuitry is shown schematically in Figure 14.
Three power relays within the main power distribution box switch power to the
reactor/transformer automatically upon signal from the control system. dc
current is supplied to the reactor control winding from a dc control circuit located
in the pilot's control box. After rectification, power having the do volt-ampere
characteristic shown in the insert of Figure 14 is delivered to the are electrodes.
-20-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rfur111r11TA1
 Approved For Release 2003/12cONp 1AL00584R000100120001-0
4.2 Control System
The function of the control system is to operate the system safely
with minimum demand upon the operator's attention. The control system of the
airborne light source regulates the distribution of electrical power to the auxiliary
systems and the are power supply. The control system initiates the functions re-
quired before the are starts and monitors the operation of the auxiliary systems
during arc operation. The starting point of the control system is the pilot's
control box. As shown in Figure 15, the manual operations required of the pilot
are few. The "ready switch" prepares the auxiliary systems for operation of the
light source. The "arc on switch" turns on the light source. Two signal lights
indicate the "ready" or "on" status of the 35 kw illumination system. The
"intensity control" provides means for presetting or adjusting the intensity of the
light output. Figure 16 diagrams the control functions which automatically result
from actions taken by the pilot. Elements in the control system are detailed in
Figures 14, 17 and 18.
4.3 Gas Delivery System
The gas delivery system shown in Figure 19 comprises a liquid
argon storage vessel and heaters for vaporizing the argon at a controlled rate.
A flow schematic of the gas delivery system is included in Figure 20. The storage
vessle is a vacuum-insulated, spherical container which holds 22 liters (approxi-
mately 67 pounds) of liquid argon. Immersion heaters inside the vessel vaporize
argon to raise the internal pressure to 500 psig. Pressurization from atmospheric
pressure to 500 psig requires approximately 8 minutes' operation of the immersion
Approved For Release 2003/12/09 CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/1=F IMLO0584R000100120001-0
heaters. Additional superheaters are located externally to further warm the argon
gas being delivered. The delivery tube is finned to raise the argon gas to ambient
temperature before it enters the radiation source. Instructions for filling the argon
vessel are included in Section 5. 2.
4.4 Coolant System
The airborne radiation source coolant system.shown in Figure 21 uses
distilled or demineralized water in a recirculating loop to cool the arc electrodes
and the optical system. The water in turn is cooled by passing through a liquid-to-
air heat exchanger. A ram air scoop directs ambient air through the heat ex-
changer. The scoop is sized to ingest approximately 170 pounds per minute of
ram air at a flight velocity of 150 knots. The scoop is retracted by hydraulic
actuators when the radiation source is turned off. The ingested air leaves the compart-
ment via two exhaust ducts located in the floor of the compartment. These exhaust
ducts are permanently open.
5.0 SYSTEM PREPARATION PROCEDURE
Cooling System
Required Equipment:
1) A source of argon gas with regulated pressure
up to 50 psig for purging and pressurizing the
coolant system.
2) A vacuum pump to evacuate the system before
filling with liquid.
3) A coolant system service box, which includes the
-22-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
P=1UtTIAI
 Approved For Release 2003/1 F IIAL00584R000100120001-0
necessary valves, connection hoses and
pressure-indicating gauge. This is included
with the illumination system.
Removing the access. panel from the top of the system en-
closure (see Figure 1) reveals the water fill connection to the coolant system, as
shown in Figure 22. This connection is used for purging, system evacuation,
filling and pressurizing.
To purge the coolant system with gas, connect the water
transfer tube of the coolant system service box shown in Figure 23 to the water
fill connection. Then open the coolant fill valve above the water fill connection by
turning the handle 90? counterclockwise. Connect argon gas to be used for purging
to valve A of the service box. Then open the coolant drain valve (see Figure 24).
Introduce gas to the coolant system by opening valve A of the coolant system
service box. Do not allow the gas pressure introduced to the system to exceed
20 psig as indicated by the pressure gauge attached to the service box. The gas
will purge the system of most of the remaining liquid in 1-2 minutes. After
purging, the coolant system must be evacuated to remove trapped air and water
vapor in the system. To do this, connect a vacuum pump to valve B of the service
box (see Figure 23). With the vacuum pump operating, close valve A, close the
coolant drain valve (Figure 24) and open valve B. Allow the vacuum pump to draw
the vacuum to 28" Hg or more and remain operating for at least 30 minutes. This
will draw all air and water vapor pockets out of the closed system. At the end of
-23-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rn rIUMTIAl
 Approved For Release 2003/1NTI1L00584R000100120001-0
this period, close valve B and turn off the vacuum pump. If the coolant system
is leak-tight, the vacuum will not decrease and the system is ready for filling.
Disconnet the vacuum tube from valve B.
Connect the transfer tube from a distilled water container
(Figure 23) to valve B and open valve B. The vacuum will draw approximately
three quarts of water into the system. Disconnect the transfer tube from valve
B, leaving the valve open. Next, to assure proper liquid level in the system,
open the coolant overflow valve (Figure 24). Water will drain from this valve
until the proper level is reached. Close the overflow valve, close valve B and
the system is properly filled.
5.1.3 Coolant System Pressurization
With argon gas connected to valve A of the coolant system
service box (Figure 23), raise the gas pressure to 11 psig. Then open valve A
allowing the gas to enter and pressurize the coolant system to 11 psig. Close
valve B. Read the proper pressur on service box gauge. Close the coolant fill
valve (Figure 22) and disconnect the transfer tube from the water fill connection.
The coolant system is now filled, pressurized and ready to operate. It need not
be refilled unless pressurization is lost or coolant line is disconnected, allowing
trapped air into the system. System pressurization may be checked periodically
by attaching the service box to the fill port, opening the coolant fill valve and
reading system pressure on the service box gauge.
Gas Supply System
5. 2.1 Filling the Liquid Argon Vessel
The liquid argon fill connection to the liquid argon vessel
-24-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnufinflTIAI
 Approved For Release 2003/1
F I1AL00584R000100120001-0
WVTWM
is located under the access panel shown in Figure 1. Removing this panel re-
veals the liquid argon fill connection and the converter vent valve as shown in
Figure 22. Open the vent valve to atmosphere by turning its handle 900 counter-
clockwise. If the vessel is pressurized at the time, gas will vent through the
right side exhaust duct shown in Figure 24. Attach the fill line to the gas fill
connection after removing its protective cap. Begin filling and continue until the
vent line begins to vent liquid argon at a constant rate from the right side exhaust
duct. This indicates that the vessel is filled to the proper level (approximately
22 liters). Close the vent valve. Disconnect the fill line from the fill connection.
Replace the protective cap.
5. 2. 2 Check of Internal Temperature
The gas temperature inside the liquid argon vessel is used
as a control signal to indicate when the vessel is empty of liquid. The internal
temperature is indirectly indicated on the gas thermometer pressure gauge shown
in Figure 22. After filling the vessel with liquid argon, this pressure should be
checked. The proper reading is 15 psig ? 1. 0 prig. If the reading is outside this
range, it should be adjusted. Adjustment is made with the method used to pres-
surize the coolant system (see section 5.1. 3). Connect the argon line to the gas
thermometer port shown in Figure 22. Open the gas thermometer valve and ad-
just the pressure to the proper reading.
5.2.3 Electrical and Control Systems
Preparing the electrical and control systems for operation
involves connecting electrical power to the proper input terminals and connecting
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnluclnlIT1A1
 Approved For Release 2003/1 ETUL00584R000100120001-0
the control box cable to its receptacle. Figure 1 shows the locations of these
terminals. Three-phase, 400-cycle ac power should be connected in the phase
sequence denoted on the terminals. The voltage required is 208 v phase-to-phase
(120 v phase-to-neutral). The dc voltage required for internal control equip-
ment is connected to the two terminals designated dc with the proper polarity
shown. The required dc voltage is 28 v dc. Power consumption is approximately
120 watts.
5. 2.4 Removal of Optical System Shield
The radiation source enclosure incorporates an aluminum
panel which slides in to protect the optical system (see Figure 24). This shield
is marked "Remove Before Operating". This must be observed or severe damage
to the optical system will result.
6.0 OPERATING PROCEDURE - AIRBORNE OPERATION
The following procedure relates directly to operation in a forward
moving aircraft. For static operation either aloft or at ground level, an auxiliary
source of forced cooling air must be supplied to the air scoop. This air require-
ment is 2600 cfm at a static pressure (gauge) of 14" of water. This pressure
corresponds to ram pressure in sea level flight at 150 knots.
6.1 Starting Sequence
All operational control functions originate at the pilot's control
box (Figure 15). To initiate the starting sequence, the "ready switch" is first
turned on. This begins pressurization of the liquid argon storage vessel and checks
that the coolant system and transformer are ready to function. Pressurization of
-26-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnICinWITIAI
 Approved For Release 2003/1 00584R000100120001-0
the gas system requires approximately 8 minutes. When the gas pressure reaches
a preset level, the ready light on the control box lights. At this point it is recom-
mended that the "ready switch" be turned off until actual operation is desired if
there is to be a delay of more than ten minutes before starting the radiation
source. The "ready switch" must be on before the radiation source can be
started, however.
Ignition of the radiation source is accomplished by turning on the
"arc on switch" shown in Figure 15. This switch triggers a series of automatic
start functions which delay the start of the light source by ten seconds.
6. 2 Beam Intensity Adjustment
The dial at the top of the control box (Figure 15) controls the in-
tensity of the radiation output. Turning the knob clockwise increases intensity.
The desired position of the intensity control when starting the are is at the mini-
mum stop. The intensity control setting may be changed at any time during
operation.
6. 3 Intermittent Operation
The radiation source may be operated for short periods inter-
mittently by using the "arc on switch". The system will standby in the ready con-
dition between operating periods. The ten-second delay to start is repeated each
time the light source is turned on. Rapid cycling of the on-off switch is not recom-
mended.
6.4 Altitude and Flight Velocity Limitations
The operating altitude and flight velocity limits of the illumination
-27-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
r_nurlnrlTl
 Approved For Release 2003/1 MH00584R000100120001-0
system are fixed by the requirements of the ram air system. At low velocity and
high altitude, insufficient ram air is available for cooling, while at high velocity
and low altitude ram drag exceeds the structural design limit of the ram air scoop.
The estimated operating envelope is illustrated in Figure 25. This range of
operation may, of course, be extended by tailoring the air scoop design to a
specified aircraft and mission.
6. 5
Operating Time and Shut-Down Procedure
The maximum continuous operating period of the light source system
is fixed by the capacity of the liquid argon vessel. With a 22 liter fill, the vessel
will supply argon for sixty minutes' operation. At the end of this period, depletion
of gas pressure will automatically turn the radiation source off. When this occurs,
the "arc on" indicator light on the pilot's control box (Figure 15) will extinguish.
As soon as possible after this indication, the pilot should shut down the system
auxiliaries by:
1) First turning off the "arc on switch",
2) Then turning off the "ready switch".
This sequence of switching will allow the ram air scoop to close
and lock properly.
If the radiation source is to be turned off after less than sixty
minutes' operation, the two switches should be turned off in the same sequence as
above.
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnucinrMTIAl
 Approved For Release 2003/1 CL00584R000100120001-0
7.0 SECURING SYSTEM AFTER OPERATION
7.1 Replace Optical System Shield
7.2 Vent Unused Argon
If all of the argon has not been used it may be vented so as to de-
pressurize the argon vessel. This is accomplished by gaining access to the gas
vent valve (Figure 1) and opening it as described in the filling procedure, Section
5.
2.
1.
This will exhaust the remaining gas through the right side exhaust duct.
7.
3
Purge Coolant for Low Temperature Storage of System
If the illumination source system is to remain idle in an enviorn-
ment below 32?F, the coolant system should be purged by the procedure given in
Section 5.1.2.
8.0 SAFETY CONSIDERATIONS
The illumination system incorporates a high pressure gas system,
a source of light intense enough to injure, and voltages high enough to be lethal.
Although every effort has been made to make the system fail-safe, the presence
of these factors demands prudence and caution in the handling and operation of the
equipment. The following precautions are included here in the interest of foster-
ing this prudence.
8. 1 Personnel Exposure to the Radiation Beam
Exposure to the radiation should be as brief and as seldom as
possible. Direct viewing into the optics aperture should be done only with welding
glass of G 14 or greater density and from a distance of 100 feet or greater. Ex-
posture of the skin to the direct radiation beam should be limited to a distance of
-29-
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnunMAI
 Approved For Release 2003/1cONF 00584R000100120001-0
at least 100 feet and a time of no more than one minute. Obviously, personnel
sensitive to sunlight should not expose themselves to the direct radiation beam. It
is suggested that a distance of 10 feet be maintained from the optics aperture for
exposure to the diffuse randomly reflected radiation from the beam and that such
exposure be limited to five minutes. In general, exposure to/or viewing of the
radiation beam should be accorded the same precautions given to viewing the sun
on a bright day. It should also be noted that because the visible radiation is
mostly removed, there will be a natural tendency to underestimate the harmful
ultraviolet energy present. It should always be remembered that it is the invisible
ultraviolet that can cause sunburn and serious eye damage.
All equipment installed in the illumination source package is elec-
trically grounded to the framework. The frame is connected to the neutral
terminal of the input power. This terminal should be connected to a local ground
to avoid the frame assuming voltage.
Several exposed electrical cables and terminals within the system
enclosure acquire lethal potentials during normal operation. For this reason, it
is imperative that personnel not work within the system enclosure whenever power
is connected.
8. 3 Liquid Argon Handling and Pressure Vessel Precautions
Servicing the liquid argon vessel requires the normal precautions
in handling cryogenic liquids. Cryogenic liquids produce an effect on the skin
similar to a burn. The very cold gas issuing from the liquid can also produce
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnhC1nrMTIAl
 Approved For Release 2003/'IP-M
FRDItB00584R000100120001-0
these "burns". Delicate tissues, such as thos of the eyes, can be damaged by an
exposure to the cold gas which may be too brief to affect the skin of the hands or
face. No unprotected part of the body should be allowed to touch uninsulated tubes
containing liquid argon. The extremely cold metal may stick to the flesh and tear
it when withdrawn. Loose fitting leather or asbestos gloves and a shield or
safety goggles should be worn.
The argon pressure vessel becomes pressurized to 500 psig for
operation of the radiation source. Once the vessel has been filled and the vent valve
closed, the small heat leak from its surroundings will gradually build up the in-
ternal pressure by evaporation of some liquid. For these reasons, whenever the
vessel contains some liquid and is not vented to atmosphere, it should be re-
garded as being pressurized.
Approved For Release 2003/12/09 : CI2 RDP70B00584R000100120001-0
rnmrinrITIMM
 Approved For Release 2003/1faU1 a"00584R000100120001-0
[(;lil;F: I ::ii kw 1ili1rni.nn.tion ;;ystcrn Wm(l Pilot'.: Control Rox
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
r_nKfinflTiai
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
CDIEIDENTIAL
"nis material contains information affecting the
national defense of the United States with in the
meaning of the espionage laws. Title 18, U. S. C.
Secs. 793 and 794, the transmission or revelation
of which in any manner to an unauthorized person.
is prohibited by law." ,
INLET TO
SOURCE
IAN LET TO ARC
CHAMBER
ARC COLUMN
-%-- I N LET TO
COOLANT AN P'
PRESS. BALANCE'
C4lAML ER
`- QUARTZ ENVELOPE
HEAT EXCHANC1ER
EXHAUST TO ATMOSPHERE
FIGURE 2 Schematic of 35 kw Radiation Source
Approved For Release 20
P70B00584R000100120001-0
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
l _V001 ?lS 2,W'a ~I.l`dM,'J~N'd la~d~! 1`d~ll73dS -1V W'klQN 3 N1-a N'S
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
W 9 0(
tL 11
~U g Z J
z
0- go
nc- 4 00
8
\~ S
N 54 __ N OO
It 2 Ti
~_~ool ,_~SZ.w~ S11VM- 'a~N`dlab-~i "1'd~11D3dS '1'JL ~ON 3h1I1~i31N33
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/11ONF00584R000100120001-0
00 "14
w
Approved For Release 2003/ 2 nz A DI G m t 1 d'P1!
nnurlnruTIA1
 Approved For Release 2003/19NF00584R000100120001-0
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
nniurinr&T
 Approved For Release 2003/1cUNF IIAL00584R000100120001-0
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnurinrlTI
 Approved For Release 2003/iDNFM B00584R000100120001-0
o ;r
00
p ;?+ c000
O
N
00
00
a z
cJ
N
00
0
N
N
R
z
c0 C- 00 m O
GO
O
nr c rr i
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
rnuflmITIAI
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
d1
-ij
M
cc it
^I 04 +
O
Q ? a t
O o U b
a W~
a a~
0 ;.4 0 :0
P% o, ra 5 4-4
14 P 'C c~ N ?' O
Cd Q U 'd 4 4a
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
CONFIDENTIAL
I I I I I I I, I I I I I I I 1 I_ I
Z? 18 IG 14 IZ '10 6 Co 4 Z c Z 4 Co 6 10 - IZ 14 IG I8 20
PECZ1IZEES FROM AK 1'5 OF
OPTICAL SYSTEM
"This material contains information affecting the
national defense of the United States with in the
meaning of the espionage laws. Title 18, U. S. C.
Secs. 793 and 794, the transmission or revelation
of which in any manner to an unauthorized person
is prohibited by law."
FIGURE 10 Illuminated Area Lateral Distribution Achieved with a
4? x 40? Prototype Optical System
Approved For Release 20030 l 10B00584R000100120001-0
 Approved For Release 2003/1CUNFIIA60584R000100120001-0
1.
Mirrored end wall.
7.
Trellis networks.
2.
Saddle.
8.
23-degree dichroic mirror position.
3.
Concentric mirror.
9.
18-degree beam-splitter mirrors,
4.
Electrode assembly positioning hole.
10.
Grooved filter guides.
5.
Saddle mirrors.
11.
Air duct connections.
6.
Location of parabolic mirrors.
Approv Y e4gas e 03/t1o2r/OA9ssemb1RyDfo~ q 1 u0minatio00 ysq
em
rnucinflTII
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
This material contains information affecting the
national defense of the United States with in the
meaning of the espionage laws. Title 18, U. S. C.
Secs. 793 and 794, the transmission or revelation
of which in any manner to an unauthorized person
is prohibited by law."
(V t\* LnrJNI W31515 N?,jLvN1Wf nni
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/1NTII&00584R000100120001-0
1. Main power distribution box. 3. Transformer. 5. Power factor correction capacitors.
2. Saturable core reactor 4. Rectifier.
r~am.a~namare~~~r
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
"~~ Q
Qj Ob
(
~v'
~ r
z
,
'
j ? q U d d; m to W n ~.
O 1C 4 4 ~v ~^ s sr x F o n ~1 F a
Lzj
I~~I'III1~~I?Iu?AcIIaIIUI?I'Nlaml_~I alo
tn0
J O ~
W,
z i
pWLJ
o3-
0.N
1
N
UI
N
J
J
.~
r?
J
u_
i.
i.
--
tr
_v
O
Q
p
J
m
'
v
0
x
Y
,
u
u
J
u
n
u
th
'~
ff
Q
O
O
4
u
z,
tr
J
. J
y
J
i
~
l
d
t~
t7
z
V
U
aP~
$
an
(i
a
?
d
Q
?
in
_
N
a
n
4
f
u
a
Q
tl
i
N
In
m
N
c~
In
k
m
m
0
N
m
d
in
'o
00
0)
O
N
rl
t
N
N
Ih
to
(n
4n
R-
0
rn
m
m
+
d
d
d
d
cr
d
d
V
to
in
_FV
} 3 O R F E W ii K s W
0G tai ~ u~ ~ 1,? m
I
41.
IF
T
aosnd ?M el 'C9 Pa glgo'd et
po!neon ae oq i uu w AM Ut t M Jo
UMV#aa> >o ao!scnmuest 091 UL Ptm #6L '4"S
z 's 'n '8 t aP!.L *entel a8>;no!dsa ath Jo eutueauu
atfi Ut tp!M satets P?l!un a%P JO osuopP leuoqun
9%( 8ugoa9e uogeuuoM "UO (e saietu e:U.:
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 00584R000100120001-0
Approved For Release 2003/I ON.F
FIGURE 15 Pilot's Control Box for 35 kw Illumination System
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
CNFIFNTIAI
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
c''
d,ol
1
z
_ 3
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
CONFIDENTIAL
iii
0
E
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
6-467NHVN
I
~
 Approved For Release 2003/12/09: CIA-RDP70B005 1-0
"true material' contains information affecting the V I M,
/.wnayV
1JW~YIY
fh Uid Sh ih
national defense o tentetates witn te
meaning of the espionage laws. Title 18, U. S. C.
Secs. 793 and 794,?the .transmission or revelation
of which in any manner to an unauthorized-person
is prohibited by law:'
f 'If
saas
CONFIDENTIAL
ft-!.
Sn'
N -4
l - - proved-For Release 2003/12/09: CIA-RDP70B00584R100i00'120001.0~
 Approved For Release 2003/ALB00584R000100120001-0
o
W
Way
0
cd
rn
~cd!}
T
0
u~
N N
> C1
cd Cd
. 0
0,
I
0 0
b
N b~-4A
^Ci
cd
Approved For Release 2003/ clA
7. t
rnurItlfwITIA1
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
0
~m
~r
4J
aW
Fa
-{IN
-91* It- I'?1,01-1RI=IV I.It I i I T
'Thin material contains information affecting the
national defense' of the United States with in the
meaning' of the espionage laws. Tide 18, U. S. C.
Secs. 793 and 794, the transmission or revelation
of which in any manner to an unauthorized person
s prohibited by law."
~IOwl INI IS
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
 Approved For Release 2003/2 F IIAL00584R000100120001-0
Approved?For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnurinrNTIAI
 Approved For Release 2003/11~~D00584R000100120001-0
rnNrInrNTIAI
 Approved For Release 2003/1 gFRI600584R000100120001-0
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
PnmrinrNTA
 Approved For Release 2003/1cUNFUAL00584R000100120001-0
Appi%ved For Release-2003/12/09` 1A-RDR7O S'$4ROO0100120001-0
f
PnurlnrlTIA
 Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0
ALTITUDE (FEET)
5 to Is 'A
Approved For Release 2003/12/09 : CIA-RDP70B00584R000100120001-0