CORPORATION 

A

E

R

OSP

ACE 

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GOODYEAR AEROSPACE 

CORPORATION 

AKRON, OHIO 

7E-CtiNICAL PROPOSAL 

RFP 15't 

GAP-50.17 

eir-048/001--211-68 

HANDLE VIA BYEMAN 

ONTROL 

-ad/D 

28 June 1968 
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1 

Copy —1 of a 

Conqi sts of 59 Pages 

TL ViNICAL PROPOSAL 

RFP 15"1 

ei P-048/001-2311-68 

GAP-5037 28 June 1968 

MI6 12 1968 

HANDLE VIA BYEMAN 

:ONTROL SYSTEM ONLY 

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TABLE OF CONTENTS 

1.0 BACKGROUND 

1.1 BETA Subsystem General Description 

1.2 Origin and Background of Proposed Design 

Including a Discussion of Development 

Work to Date 

1.3 Part 0 Design Status 

Page 

5 

5 

7 

9 

2.0 ANALYSIS OF.DESIGN AND TEST REQUIREMENTS 11 

2.1 Design 11 

2.2 Test 13 

3.0 DESCRIPTION OF POSSIBLE SUBSYSTEM IMPROVEMENTS 15 

3.1 General 15 

3.2 CORRELATRON Modifications 15 

3.3 Mechanization Changes 15 

3.3.1 Variable Amplitude Nutation 15 

3.3.2 Variable Exposure Control • • • 16 

3.3.3 Magnetic Zoom 16 

4.0 SPECIFICATION REVIEW 17 

5.0 ANALYSIS AND TRADE-OFFS 29 

5.1 General 29 

5.2 Design Effort Support Studies 29 

5.2.1 Center of Power Effects 29 

5.2.2 Illumination Spectrum Effects 30 

5.2.3 Output Spectral Density Investigation 30 

5.2.4. Dynamic Response Investigation 30 

5.3 Trade-Off Studies 30 

5.3.1 Dynamic Range Vs Accuracy 30 

5.3.2 Dynamic Response Vs Accuracy 30 

5.3.3 Linearity Vs Accuracy 31 

5.3.4 Power Vs Weight Vs Accuracy 31 

5.3.5 High and Low Frequency Time Share of Light 

with the Visual Optics Vs Accuracy 31 

5.3.6 Accuracy Vs Image Luminance 31 

5.4 Error Analysis 31 

5.5 Dynamic Performance Model Studies 32 

5.6 Cloud Obscuration Study 34 

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6.0 DESIGN APPROACH 

6.1 General Description 

6.2 Block Diagram and Theory of Operation 

6.3 Equipment Characteristics 

6.3.1 Size6.3.2 Weight 

6.3.2.1 IVS System 

6.3.2.2 Sensor Weight Breakdown 43 

6.3.2.3 Electronics Control Assembly Weight 

Breakdown 44 

6.3.3 Power 45 

6.3.3.1 IVS System 45 

6.3.3.2 Sensor Power Breakdown 46 

6.3.3.3 Electronics Control Assembly Power 

Breakdown 46 

6.3.4 Reliability 46 

6.3.5 Diagnostic Monitoring 47 

7.0 HIGH RISK TECHNICAL PROBLEMS AND PROPOSED 

SOLUTIONS 48 

7.1 General 48 

7.2 A/D Converter Incorporation 48 

7.3 Saturation - 0.1 Second Recovery Time 49 

7.4 IVS Frequency Response Vs Output Power 

Spectral Density 49 

7.5 Reliability 49 

7.6 Power Dissipation . 49 

7.7 Weight 50 

7.8 Electromagnetic Interference 50 

8.0 MAINTAINABILITY CONSIDERATIONS 51 

9.0 SAFETY CONSIDERATIONS 52 

10.0 RELIABILITY CONSIDERATIONS 53 

11.0 THERMAL CONSIDERATIONS 55 

12.0 ON-BOARD SELF TEST DESCRIPTION AND BUDGETARY 

ESTIMATE 57 

12.1 General 57 

12.2 Concept Description 57 

13.0 ADAPTER BUDGETARY ESTIMATE 58 

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36 

37 

43 

43 

43 

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LIST OF ILLUSTRATIONS 

Page 

1-1 Image Motion Sensor Function Diagram 6 

4-1 Electronic Control Assembly 24 

6-1 Block Diagram of the IVS System 38 

13-1 Adapter 59 

Applicable Drawings - previously submitted 

1 Sensor Assembly, 623A500-101 

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1.0 BACKGROUND 

1.1 BETA Subsystem General Description 

The BETA Subsystem consists of a Sensor package containing an 

optics system which images the 2.8 inches diameter input image on the 

photocathode of the CORRELATRON* and the peripheral electrical items 

which must be in close proximity with the CORRELATRON, and an Electronics Control Assembly which contains the remaining electronics 

required by the Subsystem. The Electronics Control Assembly accepts 

the system Input power and commands, provides the system output signals 

and supplies and receives the Sensor power and signals during system 

operation. The Sensor and Electronics Control Assembly are interconnected by a single cable. 

In order to obtain image rate information the IVS uses the 

CORRELATRON in a closed loop as shown in Figure 1. The electron 

image in the CORRELATRON is nutated by magnetic deflection fields 

from the orthogonal a and 6,(a and a are the correlation variables) 

deflection system. Quadrature nutation signals are provided by a 

nutation oscillator to the deflection system and as reference signals 

to the phase discriminators. The resulting CORRELATRON output signal 

at the nutation frequency is amplified and phase-discriminated with 

respect to each quadrature nutation reference. The outputs of the 

phase discriminators are the derivatives of the correlation function 

with respect to a and a and thus equal zero at the maximum of the 

correlation; i.e., the position of best correlation. The discriminator 

output signal is used to close the loop around the CORRELATRON through 

an integrator and deflection system in each axis. This causes the 

electron image to be deflected to the position of best correlation. 

The outputs of the integrators are, therefore, proportional to 

a and a and thus the inputs to the integrators are the derivatives of 

a and B with respect to time. By definition of the correlation 

da da 

t function, TE and -- are proportional to the image rates on the face d 

of the CORRELATRON. 

Trademark, Goodyeai Aerospace Corporation, Akron, Ohio 44315. 
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Y 

Deflection: Integra-14..Phase fir 

S stem for Discriminator 

A 

Error 

CORRELATRON Amplifier 

da 

dt 

Optics 

Nutation 

Oscillator 

Deflec- tion 

System 

Integra 

for 

Phase 

tor 

.4111r■-• 

Pic!ure-1-1 Image Motion Sensor Function Diagram 

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The preceding discussion presents a very much simplified 

description of the IVS performance and does not attempt to describe 

the actual mechanization which will be discussed later. The 

discussion serves only as an introduction to the IVS theory of 

performance. 

1.2 Origin and Background of Proposed Design Including a Discussion 

of Development Work to Date 

In 1947, GAC began the development of the MX-778 ATRAN* guidance 

system for the TM-76A Mace Missile. This system used an automatic 

image correlation technique to register a real-time radar display with 

synthesized reference images. This contract effort continued through.= 

out the 1950's and was supported by Corporate R&D programs to develop 

improved correlation implementations. One approach consisted of a 

vidicon optical sensor and an electrical storage tube correlator, 

which led to the award of Contract AF33(657)-8811 in April 1962 from 

Wright-Patterson Air Force Base, Dayton, Ohio. This contract was 

for the development of a high accuracy passive V/H sensor, which 

could control the motion of a film platen of an aerial camera in order 

to minimize image smear during exposure. 

Evaluations of this type of correlator, which sequentially 

examined the image parameters by a line-by-line scanning spot process,. 

indicated that heavy smoothing of the output signal was required in 

order to achieve a signal-to-noise ratio which approached that 

obtainable from optical projection correlators which simultaneously 

accommodated all the image parameters contained in the field-of-view. 

Accordingly, GAC initiated a Corporate R&D program to develop an 

electronic implementation of the optical correlator. This initial 

work utilized an ITTIL Model 231 Storage Image Tube, and led to the 

filing of patent 3,290,546 in October 1962. This patent discloses 

a sensor tube containing a photocathode for converting the optical 

input image to a corresponding electron image, a storage technique 

for temporarily recording the geometric and contrast parameters of 

an initial input image,, a deflection technique for electronically 

displacing a later input image with respect to the initial stored 

input image, an electron modulation technique to simulate image 

multiplication, and a signal collection technique to simulate integration. 

Trademark, Goodyear Aerospace Corporation, Akron, Ohio 44315. 

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In May 1963, GAC received Contract AF33(657)-11090 from 

Wright-Patterson AFB, Dayton, Ohio to develop a Night-Velocity 

Over Altitude Ratio. Sensor. This program demonstrated that a fast 

response passive image motion sensor was feasible for low illumination level applications, by utilizing the improved S/N available 

from electronic simultaneous area correlation. Concurrent with this 

contract effort, GAC Corporate R&D funds were provided to ITTIL, 

Ft. Wayne, Indiana, to develop a practical tube configuration. The 

first such tube was delivered in February 1965, and was designated 

the CORRELATRON. 

Also in February 1965, GAC received Contract AF33(615)-2404 

from Wright-Patterson AFB, Dayton, Ohio, to develop a CORRELATRON 

sensor capable of automatically controlling the image motion compensation, the focus, and the exposure of an aerial camera. During 

this same' period, GAC was engaged in discussions with SAFSP, Los 

Angeles, California, concerning an application for a very high accuracy 

image motion sensor. This application required that the sensor be 

an integral component of a Navigation and Control Subsystem, and 

that it senses light diverted from an image on a film platen of a 

camera to generate viewer image rate correction signals for an Optical 

Tracking Mirror Drive. These discussions indicated that the allelectronic CORRELATRON area correlator employing an internal closed 

integrator feedback loop was particularly well suited to the system 

requirements for: Low image rates, low image illumination, low 

image contrast, fast dynamic response, insensitivity to image changes, 

low power, low weight, high reliability, and long life. Accordingly, 

GAC received RFP 04-695-66-148 in September 1965, and was awarded' 

Contract AF04(695)-914 in October 1965. This program required the 

demonstration of the feasibility of a frame mode closed loop IMC 

(Image Motion Compensation) device using the CORRELATRON. It consisted of an analysis of the IMC requirements for strip and frame 

mode cameras, and the design, fabrication, and demonstration of a 

laboratory simulator and IMC breadboard. 

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Following the successful demonstration of feasibility, GAC 

received Contract AF18(600)-2967 in July 1966. This contract continued until January 1968, and consisted of the further development 

of IVS techniques and implementations, and included: Coordination 

with Air Force/Aerospace and with GE; system analysis; component 

review, selection, and experimental evaluation; IVS breadboard 

fabrication; test and improvement; simulator improvement modifications; 

and system experimental evaluation. 

On 8 September 1967, GAC received the subcontract 029B25006 

from GE. This contract consisted of providing the IVS breadboard 

system fabricated under Contract AF18(600)-2967 for GE evaluation, 

provide field test support and develop, design, fabricate, assemble, 

test and deliver one IVS engineering prototype evaluation model for 

GE evaluation. This contract is still in effect and continues 

until the latter part of this year. Initial evaluations of the IVS 

breadboard have been completed and the prototype is presently being 

assembled. 

1..3 Part 0 Design Status 

The design of the Part 0 Engineering Prototype Evaluation Model 

(EPEM) is essentially complete and the fabrication and assembly 

phases are presently underway. The EPEM is a second generation bread-' 

board or can be considered a first generation IVS which has design 

objectives to satisfy the space, weight, power and performance required of the subsequently designed IVS systems as defined by EC701A, 

Rev. 5. Testing of the IVS breadboard at GE indicated several areas 

of performance require improvement. Presently a model improvement 

program on the EPEM is underway in order to satisfy the performance 

requirements of the specification. 

The Part 0 program also includes a study phase which is presently 

engaged in (1) evaluating possible trade-offs in performance, (2) 

analyzing possible methods applicable to image specification techniques, (3) math modeling to aid in performance prediction of the 

IVS, and (4) investigating cloud detection techniques and the effects 

of ground obscurations on the IVS performance. These studies 

represent the first phases of the study programs required for the 

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proposed efort. Significant progress has been made in the aforementioned areas but much remains to be done before the results of 

the studies can significantly improve the IVS design. 
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2.0 ANALYSIS OF DESIGN AND TEST REQUIREMENTS 

2.1 Design 

The primary objective of the IVS design and development program, 

defined in the Work Statement WS 701E, dated 27 May 1968, is to 

satisfy the performance requirements of the specification EC701 

Rev. 6. The second most important design consideration is reliability 1 

and thirdly, safety. Of course, it is difficult to separate these 

latter two areas of effort, but if a trade-off must be made between 

these two areas it must be made in favor of reliability with all 

other considerations being equal. All other areas of design such as 

producibility, maintainability, logistics, schedule, etc., are 

subordinate to the above three mentioned areas. This does not mean 

to say that these subordinate areas of endeavor are not essential to 

the program but it does mean that performance, reliability and safety 

will be given primary consideration in performing all the subordinate 

tasks of the program. 

It goes without saying, of course, that the single most critical 

item to be considered, and "followed to the letter", is security. 

Although this is usually not a part of a design effort, on this 

program it must be used as a guide and sometimes as a hindrance to 

a desired progress in order to control and restrict contacts with 

uncleared individuals. The cleared individuals on the program must 

constantly be aware of their responsibilities to the program from a 

security point of view and no breach of security must occur regardless 

of the seemingly urgency of the problem. This stringent security 

requirement is a restriction on the operation of the program personnel 

which is not normally placed on them and which must be constantly reemphasized to them to keep all personnel alert to their responsibilities. 

It must be noted that the security imposed on this program places the 

entire responsibility for maintaining security on the individual, 

hence, the proper education of the individual in this area is imperative. 

The IVS design task is one of developing and designing the 

next genekation hardware of the Part 0 BETA Subsystem. The Part 0 

hardware is scheduled for delivery 30 September 1968. The proposed 

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IVS system will be an improvement over the Part 0 system in the 

areas of performance, circuitry and packaging including the incorporation of a CFE A/D converter. Reliability, safety, weights, 

maintainability, power, etc. which were design objectives of the 

Part 0 program become design requirements on the proposed program 

and, therefore, a much more extensive effort is required in these 

areas. This additional effort will impose more restrictions on the 

design and development engineers with regard to these items than the 

previous program did which will result in a better system as far as 

the secondary program requirements are concerned. The defined 

program disciplines associated with the secondary objective& of the 

program, such as weights, power, reliability, etc., analysis and 

reports will assure compliance with the requirements for the areas 

of concern. 

A study program is proposed to support the IVS design effort. 

This study program is a continuation of the Part 0 program studies 

in the areas of (1) Image Specification Techniques, (2) Performance 

Prediction Techniques, and (3) Cloud Obscuration Effects. This. 

Tatter task was the cloud detection techniques study of Part O. 

Cloud detection is no longer a requirement, however, the effects of 

ground obscurations on the IVS performance must be known in order to ' 

determine the IVS performance under all anticipated operating conditions. 

Updating and continuations of the Part 0 studies for design 

support are required in the areas of null accuracy, illuminance 

effects, center of power effects, theoretical system response and 

dynamic response, dynamic range and linearity versus accuracy. In 

addition, an error analysis task has been included in the proposed 

program which was not included in the Part 0 program. The results 

of the studies will serve to either verify or provide information 

for improving the IVS system performance. 

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2.2 Test 

A development test program is required to support the IVS 

design eflort. This test program will include the operation of the 

Part 0 EPEM breadboard and a GAC engineering model of the MAMO 

configuration as the deliverable engineering models when it is 

available. The GAC engineering model will be used as a manufacturing 

tool after its performance has been verified. It will be used for 

checkout and verification testing of the acceptance tester, qualification tester and the deliverable test setup. Also, it will be used 

as a "standard" for comparison purposes with the test results 

obtained from the deliverable units. The GAC engineering model will 

be continuously updated to reflect the latest IVS design so its 

performance will be compatible with the hardware being delivered. 

The development test program will also include the evaluation 

of various circuit configurations proposed for use in the IVS. ,The 

testing will include circuit performance evaluations under the 

temperature conditions and input power conditions stipulated in the 

specification EC-701A, Rev. 6. Special consideration will be given 

to minimizing power dissipation and defining the proper heat sink 

techniques to be employed for each component. 

Hard testers will be obtained to support the proposed program 

IVS fabrication. These testers will include units for testing 

incoming components including the CFE A/D converter, electronic 

subassemblies such as multilayer boards, focus coils and power 

supplies, and IVS assemblies of the sensor and the electronics control 

assembly. The testers will be suitably designed so that subassembly 

and assembly trouble-shooting and repair can be accomplished with 

relative ease. 

The qualification tester will be an acceptance tester with 

additional accessories required to operate the IVS during testing 

under the various required environments. System operation is required during such environmental tests as temperature cycling, and 

EMI. Performance evaluation testing of each IVS under test is 

required after exposure to each of the environmental conditions. 

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The IVS performance tests will be performed to the acceptance 

test procedure. 

The qualification test procedure will define the power and 

scene input conditions to be used in operating the IVS during the 

exposure to the various environments. The critical performance 

parameters will be measured during these tests and an evaluation 

of the system performance made. Quick look reports will be forwarded 

to GE upon completion of test phase which will be after the IVS has 

been performance evaluated to the acceptance test procedure. GE 

will also be notified of any malfunction of the IVS detected during 

these tests. 

Two IVS systems will be fabricated especially for the qualification test program because of schedule considerations. The qualification test required time span and the specified end date necessitate 

starting the test on 1 September 1969. Hard tooling and prime 

equipment processing and procedures will be used to fabricate these 

systems. Prior to starting the qualification testing, the units 

will be acceptance tested. The acceptance test will be performed 

on the prime equipment acceptance tester and will include the operability assurance tests defined in DR1100. Therefore, the qualification test program will be conducted on prime IVS units which have 

been accepted for delivery. Also, all test data accumulated during 

the qualification testing will be relatable to the original acceptance 

test data since the compatibility of the acceptance and qualification testers will be established prior to the start of testing. 

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3.0 DESCRIPTION OF POSSIBLE SUBSYSTEM IMPROVEMENTS 

3.1 General 

Several improvements to the IVS are presently under investigation and evaluation on the Part 0 program. These system changes 

are primarily concerned with improving the system performance in 

the areas of low light level, low scene contrast and scene scale 

changes due to changes in line-of-sight. The changes under consideration are 

(1) CORRELATRON modifications, 

(2) variable amplitude nutation, 

(3) variable exposure control, 

(4) magnetic zoom. 

3.2 CORRELATRON Modifications 

The modifications to the CORRELATRON which are presently 

under investigation are the incorporation of (1) a coarse collector 

mesh, and (2) a thicker dielectric storage mesh. The coarse 

collector mesh will increase the electron transmission of the 

CORRELATRON by approximately a factor of two (2). The incorporation 

of the thicker dielectric storage mesh will allow at least twice a 

given charge to be stored with the same exposure conditions used 

for the present CORRELATRONs. Both of these changes will reduce 

the minimum light level required for satisfactory IVS performance 

and will also reduce the write and erase times of the IVS for the 

present range of operation. It should be noted that the present 

write time will be required to obtain satisfactory subsystem 

performance for say one-quarter of the present minimum illumination 

required for satisfactory performance, therefore, trade-offs in the 

IVS performance can be made in order to obtain acceptable overall 

system performance. 

3.3 Mechanization Changes 

3.3.1 Variable Amplitude Nutation 

- Incorporation of a variable amplitude nutation capability 

in the IVS will enable the system to select the appropriate nutation amplitude to maximize the sensor output for a given scene. .- 

This, will maximize the system signal-to-noise ratio for a given 

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scene and will allow the IVS to remain locked on a marginal scene 

for a longer period of time than is presently possible. The 

optimum nutation for a given scene is a function of the correlation 

function of that scene. The TVS circuitry will optimize the nutation amplitude based on the CORRELATRON output signal which is a 

function of the scene correlation function. 

if3.3.2 Variable Exposure Control 

p) r; f ( 

The incorporation of a variable write exposure control 

will improve the IVS performance for high illumination, low contrast 

scene inputs. This modification will allow the scene modulation 

enhancement capability inherent in the CORRELATRON to be used to 

the ultimate in obtaining satisfactory system performance under the 

aforementioned adverse operating conditions. Extensive changes 

to the present IVS electronics will be required to incorporate this 

...**.orow.*.areosor 

change. 

3.3.3 Magnetic Zoom 

Changes in the line-of-sight while tracking a grounl 

scene, produce significant scale changes in the live image with 

respect to the stored image. This scale change rapidly degrades the 

correlation function, as sensed by the CORRELATRON, at the larger 

tracking angles. The introduction of a magnetic zoom capability 

in the IVS will compensate for the scene scale changes and improve 

the system performance while tracking a ground scene. The magnetic 

zoom will be accomplished by electronically controlling tha sensor 

magnetic focus field as a function of look angle. 

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4.0 SPECIFICATION REVIEW 

Following are the GAC comments on the specification EC-701A, 

Rev. 6, Engineering Critical Component Specification Performance/ 

Design and Product Configuration Requirements for Image Velocity 

Sensor, 4 June 1968. Every numbered section is commented on. 

The comment "comply" indicates that GAC considers the requirement 

reasonable and that the requirement can be satisfied by the IVS. 

This does not mean to imply that there are no technical problems 

in complying to the requirement or that the present design necessarily 

satisfies the requirement. 

1.0 Scope - Comply 

2.1 Applicable Documents 

(1) EC1602 High Frequency A/D Converter 

This document was not included in the bid package, however, 

the following information was forwarded and taken into consideration 

in preparing the proposal. 

1. A reference voltage of +5 VDC -1% to be supplied by 

analog source at 10 ma. Output impedance to equal to or 

less than 0.1 ohms. 

2. Input power - provided by the analog data source 

+4 VDC -5% 0.7W 

+12 VDC -5% 0.15W 

-12 VDC -5% 0.15W 

3. Size - To be less than 1.5" x 3" x 4" 

4. Weight - Shall not exceed 1 pound. 

(2) DP1690A Electromagnetic Compatibility Requirements 

AN1 through 3 for Equipments and Subsystems, Specification 

of 

This document was not forwarded with the bid package and 

only AN1 and 2 were included. The GAC proposal is based on DP1690, 

Rev. 1 dated 11 November 1966 and AN1 and 2 to DP1690A. 

(3) -GE-711-03013 Space Envelope 

Rev. 1 Available for IVS (14/A) 

This drawing, revision A, was available at GAC for use 
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in preparing the proposal. Significant comments on this drawing 

were forwarded to GE on 6 March 1968; M2197, Drawing Comments, and 

no reply has been received to date. The response to the aforementioned comments has a direct bearing on the IVS sensor design 

effort defined by WS701E, 27 May 1968. The proposal includes the 

effort to redesign the sensor to satisfy the space requirements of 

GE-711-03013. 

(4) GE-711-03059 Electrical Schematic 

Preliminary copies of 711-03059 were made available 

for review. There appears to be no problem with complying with 

this drawing when it is finalized, however, it should be noted that 

only five connectors are shown on the IVS electronics. The soecification indicates there should be six connectors. 

(5) TBD Space Envelope Available for IVS (A) 

GAC has no information pertaining to this drawing, therefore, no consideration was given to its effect on the program in 

the proposal. It is assumed that all the required pertinent design 

information is contained in GE-711-03013. 

3.0 Requirements(title) 

3.1 Performance (title) 

3.1.1 Functional Characteristics - Comply 

3.1.1.1 Primary Performance Characteristics (title) 

3.1.1.1.1 Image Velocity Output Signals 

Comply, however, for the proposal GAC assumed that the 

5 VDC reference voltage source was capable of supplying a 10 ma 

maximum current. 

3.1.1.1.1.A Dynamic Range - Comply 

3.1.1.1.1.B Signal Linearity - Comply 

3.1.1.1.1.B.1 Large Signal Region - Comply 

3.1.1.1.1.8.2 Null Region - Comply 

3.1.1.1.1.0 IVS Noise and Bias - Comply 

3.1.1.1.1.C.1 Noise Definition - Comply 

3.1.1.1.1.C.2 Bias Definition - Comply 

3.1.1.1.1.C.3 Requirements in Large Signal Region - Comply 

3.1.1.1.1.C.4 Requirements in Null Region - Comply 
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3.1.1.1.1.C.5 Determining Value of Periodic Noise Components - Comply 

3.1.1.1.1.0.6 Determining Value of Random Noise Component - Comply 

3.1.1.1.1.C.6.A Comply 

3.1.1.1.1.C.6.B Comply 

3.1.1.1.1.C.6.0 Comply if the Figures 7-A through 7-E are in 

reality 5-A through 5-E of the specification. 

3.1.1.1.1.C.6.D Comply 

3.1.1.1.1.D Saturation 

The IVS can comply with the 0.5 sec. recovery time, 

but can only partially comply with the 0.1 sec. recovery time. The 

lock-on time of the IVS varies from approximately 0.16 sec. to 0.3 

sec., and is dependent on many factors, several of which are beyond 

the control of the IVS. The erase cycle is presently 0.065 sec., 

but may be reduced depending on the outcome of future trade-off 

studies. The write-cycle varies from approximately 0.01 to 0.015 

sec., depending on scene brightness. There is an additional 0.080 

sec., approximately, required for lock-on stabilization. 

When a disable signal is not supplied to the IVS, but 

it is saturated, the IVS will continuously recycle until it locks-on. 

If the image velocity falls below the dynamic range of the IVS 

during the last 0.1 sec. of the cycle, the requirement for 0.1 sec. 

recovery will be met. If the image velocity falls below the dynamic 

range of the IVS during the rest of the lock-on cycle, the recovery 

time will be greater than 0.1 sec. 

There will also be times when the IVS will lock-on for 

image velocities above 0.3 in/sec. If the tracking-mirror can 

respond fast enough to prevent the live image from reaching the edge 

of the stored image, the recovery time of 0.1 sec. can be achieved. 

Presentlyi model improvements to the CORRELATRON are 

under investigation which will probably significantly reduce the 

erase and write times. There is a good possibility that these 

changes and some circuitry changes to reduce the settling time will 

allow the 0.1 sec. recovery time to be satisfied. The CORRELATRON 

improvement program should be complete within the next three months. 

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3.1.1.1.1.E Frequency Response 

The IVS frequency response is related to the output 

power spectral density (PSD) requirement. Each of the requirements 

for frequency response and Pgii can be satisfied independently, 

however, trade-offs between these two areas will probably be required 

in order to obtain satisfactory system performance. Close collaboration between GE and GAC engineers will be required to obtain satisfactory trade-offs related to these two areas. 

3.1.1.1.2 Lock-On Signal - Comply 

3.1.1.1.3 Operational Readiness Signal 

It is felt that GAC can comply with this requirement, 

however, close coordination with GE engineering will be required 

in order to arrive at a mechanization which will be approved by GE. 

3.1.1.1.4 Diagnostic Monitoring Signals - Comply 

3.1.1.1.5 Sub-threshold Irradiance Signal 

Comply, however, when the threshold energy spectrum 

defined in this section is convolved with the CORRELATRON photocathode response of the IVS, the resulting cathode current is greater 

than the current resulting from the use of curve 2 of Figure 11. 

3.1.1.2 Secondary Performance Characteristics - Comply 

3.1.2 Operability (title) 

3.1.2.1 Reliability 

GAC can comply with the 10,000 hour MTBF requirement 

exclusive of the CFE A/D Converter. It is assumed that the 

reliability of the converter will be a GE responsibility and the MTBF 

will be compatible with the IVS requirements. 

3.1.2.2 Maintainability - Comply 

3.1.2.2.1 Maintenance and Repair Cycles - Comply 

3.1.2.2.2 Service and Access - Comply 

3.1.2.3 Useful Life - Comply 

3.1.2.4 Environmental - Comply 

A clarification of the orientation of the electronics 

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assembly with respect to the vehicle coordinate axes shown in 

GE 711-03013, Rev. 1 is desired so a rigorous dynamic load and 

stress analysis can be made. 

3.1.2.4.1 Steady State Load Factors (N)(title) 

3.1.2.4.1.1 Head- Comply 

3.1.2.4.1.2 Electronics Box - Comply 

3.1.2.4.2 Dynamic Environment (title) 

3.1.2.4.2.1 Acceleration- Comply 

3.1.2.4.2.2 Vibration- Comply 

3.1.2.4.3 Pressure- Comply 

3.1.2.5. Transportability- Comply 

3.1.2.6 Human Performance- Not Applicable 

3.1.2.7 Safety - Comply 

3.1.2.7.1 Flight Safety - Comply 

3.1.2.7.2 Ground Safety - Comply 

3.1.2.7.3 Nuclear Safety - Not Applicable 

3.1.2.7.4 Personnel Safety - Comply 

3.1.2.7.5 Explosive and/or Ordnance Safety - Not Applicable 

3.2 Component Definition (title) 

3.2.1 Interface Requirements - Comply 

3.2.1.1 Schematic Arrangement (title) 

3.2.1.1.A Mechanical - see comments under 2.1 (5) 

3.2.1.1.B Electrical - see comments under 2.1 (4) 

3.2.1.2 Detailed Interface Definition (title) 

3.2.1.2.1 Input Power Interface - Comply 

3.2.1.2.1.1 Normal Conditions (title) 

3.2.1.2.1.1.A Operating Voltage - Comply 

3.2.1.2.1:1.B Ripple - Comply 

3.2.1.2.1.1.0 Transient Level and Duration - Comply 

3.2.1.2.1.1.D Ripple and Transients - Comply 

3.2.1.2.1.1.E Transient Energy Content - Comply 
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3.2.1.2.1.1.F Power Dissipation 

Comply, except that no allowance is made in this 

section for the power supply inefficiencies or additional circuitry 

power requirements resulting from the incorporation of the CFE A/D 

Converter. The maximum average power requirement should be changed 

to 28 watts for the input voltage and operating times specified. 

3.2.1.2.1.2 Abnormal Conditions (title) 

3.2.1.2.1.2.A Applied Voltage - Comply 

3.2.1.2.1.2.B Power Interrupt - Comply 

3.2.1.2.2 Signal Interface (title) 

3.2.1.2.2.1 A/D Converter 

GAC feels that the requirements of this section can be 

complied with. However, further definition of the mechanical, 

structural, thermal and electronic requirements of the converter 

are required. Also see comments under 2.1 (1). 

3.2.1.2.2.2 Telemetry Multiplexer - Comply 

3.2.1.2.2.3 Monitor and Alarm Subsystem - Comply 

3.2.1.2.3 Mechanical Interface (title) 

3.2.1.2.3.1 Mounting 

Compliance with the requirements of this section is 

contingent upon the GE drawing - TBD - not changing the clearance 

within the adapter used by the IVS or the sensor mounting arrangement• 

as defined on GE drawing 711-03013. The comments under 2.1 (3) & (5) 

are also pertinent to this section. 

3.2.1.2.3.2 Space Envelopes 

GAC can comply with the sensor space allocation defined 

in GE 711-03013 although it requires a redesign of the Part 0 configuration, see comments under 2.1 (3). 

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Compliance with the electronics space allocation defined 

in EC-701A, Rev. 6 can be attained. However, compliance cannot be 

attained with the 711-03013 drawing space allocation with the A/D 

converter incorporated. It is assumed that the 711-03013 drawing 

will be revised to reflect the space allocation of EC-701A, Rev. 6. 

Figure 4-1 shows the GAC interpretation of the maximum allowable 

size for the electronics enclosure. 

3.2.1.2.3.3 Weight • 

GAC can comply with the maximum weight allowed for 

the sensor but cannot comply with the IVS total weight of 23 pounds 

maximum. The estimated system weight is 25.6 pounds based on the 

new requirements of incorporating the CFE A/D converter, providing 

three (3) additional connectors on the electronics and providing 

the associated additional support structure, mounting hardware and 

wiring. The weight estimate will have to be adjusted when the GE 

drawing 711-03059 and the GE specification EC1602 are available for 

review and evaluation. 

3.2.1.2.3.4 Alignment 

GAC feels that compliance with the requirements of 

this section can be attained, however, the comments under 3.2.1.2.3.1 

apply. 

3.2.1.2.4 Optical Interface (title) 

3.2.1.2.4.1 Optical Alignment - see comments under 3.2.1.2.3,4 

3.2.1.2.4.2 Characteristics of IVS Input Images - Comply 

3.2.1.2.4.2.A Image Format - Comply 

3.2.1.2.4.2.B Image Dynamic Effects - Comply 

3.2.1.2.4.2.0 Location of IVS Image Plane - Comply 

3.2.1.2.4.2.D Average Irradiance in IVS Image - Comply 

3.2.1.2.4.2.E Abnormally High Image Irradiance 

GAC can comply with the requirements of this section 

providing the IVS does not have to perform to the requirements of 

the specification EC-701A, Rev. 6 during the periods of exposure. 

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3.2.1.2.4.2.F Image Contrast and Spatial Frequency Distribution 

Comment on this section must be reserved until the - 

TBD - items are defined. 

3.2.1.2.4.2.G Uniformity of Image Irradiance - Comply 

3.2.1.2.4.2.H Polarization - Comply 

3.2.1.2.5 Thermal Interface (title) 

3.2.1.2.5.1 Electronics Box 

GAC can comply with the requirements of this section 

providing the Console Envelope Reference Drawing - TBD - does not 

change any of the presently stated requirements. 

3.2.1.2.5.2 Sensor Head 

The power dissipation within the sensor shall be held 

to a minimum but the design goal of 3 watts maximum cannot be 

satisfied. Presently the estimated sensor power dissipation is nine 

(9) watts. Some reduction in total sensor power dissipation is 

possible but certain trade-offs will have to be agreed upon during 

the course of the program. Also, it is assumed that section 4.4.3.2-A 

of DR1100,to be definedl will only change the temperature monitoring 

interval which should have no effect on the proposal. 

3.2.2 Component Identification - Not Applicable 

3.3 Design and Construction (title) 

3.3.1 General Design Features (title) 

3.3.1.1 Dimensions 

See comments under 3.2.1.2.3.2 

3.3.1.2 Weight 

See comments under 3.2.1.2.3.3 `(specification ref. error) 

3.3.1.3 Wiring - Comply 

3.3.1.3.1 Cabling and Connectors - Comply 
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3.3.1.4 Dielectric Strength 

Compliance with 

based on the assumption that 

and insultion resistance is 

4.1.3.4.1.1 which allows for 

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and Insulation Resistance 

the requirements of this section is 

the testing of the dielectric strength 

performed in accordance with section 

protecting certain electronic devices. 

3.3.1.5 Emissivity - Comply 

3.3.1.6 Colors - Comply 

3.3.1.7 Cleanliness - Comply, however, GAC assumes that since both 

of the IVS packages are hermetically sealed no special cleaning is 

required for any parts installed within the packages. Also, it is 

assumed that no special cleaning of the external surfaces is required 

by GAC, however, the external surfaces must be such that they can 

be cleaned satisfactorily. No special considerations were given to 

the cleaning of the components in preparing the proposal. 

3.3.1.8 Grounding- Comply 

3.3.1.9 Hermetic Sealing 

The maximum leak rate of 10-8 atmospheric cubic centimeters per second is difficult to achieve on the packages of the 

IVS. It is recommended that a design requirement of the maximum 

leak rate be 10-6 atmospheric cubic centimeters per second with a 

design objective of 10-8 atmospheric cubic centimeters per second. 

3.3.1.9.1 Component Seal - Comply 

3.3.2 Selection of Specifications and Standards - Comply 

3.3.3 Material, Parts and Processes - Comply 

3.3.4 Standard and Commercial Parts - Comply 

3.3.5 Moisture and Fungus Resistance - Comply 

3.3.6 Corrosion of Metal Parts (title) 

3.3.6.1 Electrolytic Corrosion- Comply 

3.3.6.2 Stress Corrosion- Comply 

3.3.6.3 Protective Treatment - Comply 

3.3.7 Interchangeability and Replacement - Comply 

3.3.8 Workmanship- Comply 
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3.3.9 Electromagnetic Interference 

GAC feels compliance with the requirements of this 

section can be attained but there is a potential problem area involving the optical window of the sensor. It is assumed that 

deviations will be granted, on a closely controlled and selective 

basis, to the electromagnetic interference requirements if it becomes 

apparent that these requirements cannot be met because of the use 

of the optical window in the sensor. The application of coatings 

or other types of EMI suppression to this window would effect light 

transmission and seriously degrade the low light level performance 

of the device. 

3.3.10 Identification and Marking - Comply 

3.3.11 Storage - Comply 

3.3.12 Vibration (title) 

3.3.12.1 Sensor Generated Vibration - Comply 

3.3.12.2 Resonance - Comply 

3.3.12.3 Sensor Generated Noise (Acoustic) - Comply 

4.0 Quality-Assurance Provisions (title) 

4.1 Category I Test (title) 

4.1.1 Engineering Test and Evaluation - Comply 

4.1.2 Preliminary Qualification Tests - Not Applicable 

4.1.3 Formal Qualification Tests - Comply 

4.1.3.1 Inspection - Comply 

4.1.3.2 Analysis - Comply 

4.1.3.3 Demonstrations - Not Applicable 

4.1.3.4 Tests - Comply 

4.1.3.4.1 Preliminary Tests (title) 

4.1.3.4.1.1 Dielectric Strength and Insulation Resistance - Comply 

4.1.3.4.1.2 Continuity-Test - Comply 

4.1.3.4.1%3 Performance Test - Comply 

4.1.3.4.1.4 Interface Test - Comply 

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4.1.3.4.1.5 Corona and Arcing Test - Comply 

4.1.3.4.2 Operability-Assurance Test - Comply 

4.1.3.4.3 Qualification Environmental Tests 

Comply with the understanding that for 

(1) item B, the higher curve of Figure 8 of EC-701A, 

Rev. 6 defines the test requirements aid paragraph 4.4.3.5 of DR1100 defines the test 

procedure. 

(2) item J, paragraph 4.2.4 of DP1690 accepts the 

use of the interference meter, Fairchild EMC-10, 

in performing the conducted interference test. 

This meter has a bandwidth of 50 Hz while DP1690 

specifies the measurement should be made with a 

60 Hz bandwidth. Therefore, a deviation is requested to make the measurement with a 50 Hz 

bandwidth. Also, there is some doubt about the 

availability of the McDonnel Electronics Equipment 

Model 35G001 transient generator. An equivalent 

unit which satisfies the requirements of DP1690 

has not been found. Deviation is requested for 

performing the conducted transient test with a 

pulse width of 200 microseconds if a suitable 

generator cannot be obtained. 

(3) item M is not applicable. 

(4) item N applies but will be defined later. 

4.1.4 Reliability Test and Analysis - Comply 

4.1.5 Engineering Critical Part Qualification - Not Applicable 

4.2 Category II Test Program - Not Applicable 

6.0 Notes - Not Applicable 

10.0 Appendix - Not Applicable 

Figures - Comply 
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5.0 ANALYSIS AND TRADE-OFFS 

5.1 Genera,. 

The proposed program includes a study effort which will 

provide analysis of the IVS performance and evaluate trade-offs 

to be made involving the IVS design. Proposed studies that 

directly support the IVS design effort are the following: 

(1) Center of Power Effects, 

(2) Illumination Spectrum Effects, 

(3) Output Power Spectral Density Investigation, 

(4) Dynamic Response Investigations. 

Studies which involve the evaluation of trade-offs in the IVS 

design are the following: 

(1) Dynamic Range vs. Accuracy, 

(2) Dynamic Response vs. Accuracy, 

(3) Linearity vs. Accuracy, 

(4) Power vs. Weight vs. Accuracy, 

(5) High and Low Frequency Time Share of Light with the 

Visual Optics vs. Accuracy, 

(6) Accuracy. vs. Image Luminance. 

An Error Analysis study will be performed on the IVS. Also, 

Dynamic Performance Model studies and a Cloud Obscuration study 

will be conducted. 

5.2 Design Effort Support Studies 

5.2.1 Center of Power Effects 

A preliminary effort on the Center of Power Effects 

study has been started on the Part 0 program. Basic concepts and 

a basic understanding of the effects of the image center of power 

effects on the IVS performance as a function of look angle will 

be gained during the Part 0 progiam. Refinements of the basic 

concepts and a complete evaluation of the image center of power 

effects on the IVS determination of the velocity at the center of 

format remain to be completed during the proposed program. This 

study will involve analytical and experimental investigations of 

the effects of various scenes, with known centers of power, on the 

IVS performance. 

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5.2.2 Illumination Spectrum Effects 

The Illumination Spectrum Effects study will involve 

experimental and analytical evaluations in order to determine the 

effects of the revised illumination spectrum defined in EC-701A, 

Rev. 6 on she IVS performance. This study will include the determination of the effects of different atmospheric conditions as well 

as various sun angle and look angle effects on the IVS performance 

with respect to the illumination spectrum. 

5.2.3 Output Power Spectral Density Investigation 

This investigation will analytically and experimentally 

evaluate the IVS output power spectral density with respect to the 

revised requirements of EC-701A, Rev. 6. The task is a continuation 

of the one started in the Part 0 program. The effort on the proposed program in this area is to update the PSD computer program to 

be compatible with the revised specification and evaluate the updated IVS design when it is available. Collaboration with GE 

engineering will be required to properly update the computer program. 

5.2.4 Dynamic Response Investigation 

The Dynamic Response Investigation effort consists of 

developing the analytical transfer functions for the various 

functional blocks within the IVS. A comparison of the theoretical 

block diagram with experimentally obtained data will be made in order 

to verify the theoretical work. The results of this study will aid 

in understanding and possibly improving the IVS system. 

5.3 Trade-Off Studies 

5.3.1 Dynamic Range vs. Accuracy 

The Dynamic Range vs. Accuracy study will be primarily 

interested in defining and evaluating the trade-offs involved in 

changing the IVS dynamic range to improve the accuracy of the 

system. Revised requirements for scaling and hence the dynamic 

range of the IVS appear in EC-701A, Rev. 6. These requirements will 

be evaluated and then the trade-off portion of the study will follow. 

5.3.2 Dynamic Response vs. Accuracy 

This study will evaluate the revised requirements of 

EC-701A, Rev. 6 with regard to the IVS response and identify and 

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evaluate 1,, trade-offs involved in improving the system accuracy 

by modify n.7; the IVS dynamic response. Experimental support for 

this stud: will be provided by the operation of an IVS breadboard 

on the GA(' simulator. 

5.3.3 LThearity vs. Accuracy 

The trade-offs involved in improving the IVS accuracy. 

at the expense of linearity will be identified and evaluated during 

the courso! of this study. Experimental evaluations of the possible 

trz.--offs will be included. 

5.3.4 Power vs. Weight vs. Accuracy 

A trade-off study will be conducted to identify and 

evaluate methods of improving the IVS accuracy by possible increases 

in subsystem weight and power. Experimental evaluations of the 

recommended trade-offs will be made, as well as analytical evaluations. 

5.3.5 High and Low Frequency Time Share of Light with the Visual 

Optics vs. Accuracy 

The improvement in system accuracy will be investigated 

with respect to obtaining a higher input illumination level by time 

sharing the light made available to the visual optics. Providing 

additional light during periods of low light level operation clearly 

will improve the IVS performance but possibly this light could be 

provided at a high frequency rate which would not appreciably 

deteriorate the IVS or the observers image and improved performance 

could be obtained without undue compromise of the observer.. A 

complete analytical and experimental investigation of this mode o_ 

operation is planned. 14rt 

5.3.6 Accuracy vs. Image Luminance ,r_ • ' P'sr 

The effects of variations in scene luminance on IVS 

accuracy will be investigated both analytically and experimentally. 

Both uniform and non-uniform luminance variations will be considered 

involving various atmospheric conditions and sun and look angles. 

5.4 Error Analysis 

An error analysis of the IVS will be conducted encompassing all 

error contributors from the input imagery to the output signals. 

Experimental verification of the analytical study will be made 
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where practIcal. 

5.5 Dynamic Performance Model Studies 

The objective of this analytical and experimental study will be 

to complete the development of a math model of the BETA Sensor. 

The model will be implemented in the form of a digital program for 

the IBM 360 (S40) computer, in order to provide an efficient and 

flexible capability to predict the output signal performance characteristics as a function of changes in either the input image 

parameters or in the sensor internal component parameters. 

During the Part 0 program, a separate study was performed to 

develop the techniques required for mathematically specifying the 

input optical image. This preliminary effort primarily concerned 

the evaluation of computer generated synthetic images, to identify 

the scene parameters which significantly influence the sensor 

correlation response. Generally, these special images were mathematically specified by a tabulation of the transmissivity and color 

at each individual point across the entire format. 

Also during the Part 0 program, a separate study was performed 

to develop the techniques required for mathematically specifying the 

performance of the BETA Sensor tube. Emphasis was restricted to 

this particular component of the sensor, since the tube operation 

represents a complex inter-relationship between many individual 

physical responses. This preliminary effort identified the responses 

that were significant to the model, and defined appropriate mathematical 

expressions. Generally, the tube model was formulated on the basis 

of synthetic input imagery that could be specified on a point-bypoint basis. 

During the proposed study effort, these two investigations will 

be continued, but they will be integrated into a single program to 

develop a sensor math model. This reflects the need during this phase 

to provide a marriage between the response function of the sensor 

and the excitation function of the input image. Accordingly, the 

program will primarily concern an effort to specify complex actual 

input imagery in a mathematical form that can be accepted by the 

sensor model, and to adapt the sensor model to insure full accommodation of the input stimulus. To achieve a manageable model, an image 

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specificacLon technique other than a point-by-point tabulation 

will be recaired; i.e., one which can combine all the significant 

image characteristics into a relatively simple mathematical expression. 

To develop such an expression, both analytical and experimental . 

studies wil be performed. The laboratory effort will include the 

scanning of image samples with a microdensitometer to determine the 

spot size (resolution) and the scanning patterns (% coverage) that 

art required for adequate specification. An attempt will be made 

to find suitable combinations wherein the data obtained from 

relatively few scans, or from averages obtained by non-spot aperatures (e.g., slits), is shown to be sufficient. Tests will also be 

performed with coherent and non-coherent optical processors to 

determine whether data extracted from the frequency transform plane 

or from the autocorrelation response will be sufficient. It is 

likely that data obtained from a reasonable combination of these 

various sources will be required for a comprehensive specification 

of the image characteristics, and that machine processing of this 

data will be required to generate the corresponding mathematical 

expression for the model input stimulus. 

The analytical effort concerning image specification will 

provide the equipment and measurement parameters to be examined 

experimentally, based on the image characteristics which are known 

to influence the correlation response. This effort will also provide 

the programming necessary to process the resulting data. The effort 

will not include a specific effort to establish the nominal physical 

characteristics of terrain imagery received at a spaceborne sensor. 

The effort will, however, include a study to determine if these 

nominal characteristics, if available, could be used to adequately 

specify the model input stimulus. Such summary characteristics are 

spatial frequency distribution, spectral distribution, etc. will 

be considered. 

The image specification study will be closely coordinated with 

the development of the sensor model, to insure that the expressions 

for the input stimulus are mechanized in a form that can be readily 

accommodated by the model. Likewise, the prediction performance 

that results from trial exercising of the model will be evaluated to 

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identify deficiencies in the image specification and to conceive 

necessary improvements or allowable simplifications. 

The effort to develop a mathematical model of the BETA Sensor 

will, as previously mentioned, include modification of the model 

form in order to accept input expressions that fully describe complex 

actual terrain images. In addition to this, the study will include 

the general improvement and refinement of the expressions used to 

describe the individual physical responses and their inter-actions 

within the sensor tube. The model will also be expanded to include 

the electronics external to the tube, as required to fully describe 

the output signal characteristics under null and dynamic conditions. 

Expressions for noise and non-linear responses will also be included. 

During the proposed program, a significant effort will be 

expended to program the 360 computer as defined by the math model, 

and then to exercise the computer in such a manner as to isolate 

the deficiencies. For this evaluation, actual sensor output signal 

characteristics will be generated from comparison with the model 

results by performing appropriate tests with the Princess Sensor 

and Laboratory Simulator. 

5.6 Cloud Obscuration Study 

The objective of this analytical and experimental study will 

be to determine how specific cloud and terrain parameters influence 

the intended performance of the BETA Sensor, and to determine the 

characteristics of sensor signals that are selected as indicative 

of cloud obscuration. This will be a logical continuation of a 

corresponding effort initiated during the Part 0 program. As such, 

the proposed effort will primarily concern the refinement of image 

parameters, obscuration simulation, test procedures, and data 

evaluation. 

The study will include a continued evaluation of engineering 

data concerning typical cloud characteristics that is available 

from this and other programs. This information will be used to' 

develop obscuration simulation techniques which provide more 

realistic parameters. The servo-driven image fixture, the BETA 

Sensor, and the Laboratory Simulator will be used to experimentally 

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determine which obscuration models prohibit "in-spec" performance 

when used in conjunction with a variety of typical terrain scenes. 

This data will be compiled in a form to show the probability of 

successful performance as a function of the type and degree of 

obscuraticn. 

Also as part of these tests, selected signal points within the 

sensor will be monitored. This data will be evaluated to determine 

the nominal characteristics of these signals as a function of the 

obscuration parameters. These characteristics will be analyzed, 

in turn, to develop computer processing techniques capable of automatically indicating the type and degree of obscuration. Analysis 

or trial computer runs will be performed to identify obscuration 

conditions which can result in ambiguous indications, or in errors 

of commission or omission. 

' Refinements in signal measurement techniques and/or alternate 

processing techniques will be evaluated, as required to minimize 

these deficiencies. 

At the conclusion of the proposed program, it is anticipated 

that the obscuration conditions which can prohibit satisfactory 

performance of the BETA Sensor will be specified. Likewise, the 

signal measurement and signal processing techniques required for an 

automatic indication of obscuration conditions will be defined in 

sufficient detail to adequately determine the influence of this 

capability on the mission effectiveness. 

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6.0 DESIGN APPROACH 

6.1 General Description 

The IVS system is composed of two subassemblies, a sensor 

and an aloetronica control assembly and one interconnecting cable. 

A test cable is delivered with each IVS. However, GAC must only 

define the requirements of the interconnecting cable in the final 

installation. 

The sensor is a hermetically sealed unit containing the 

CORRELATRON, focus and deflection coils, erase lights and the sensor 

electronics. Hermetic sealing of this unit is required to protect. 

the CORRELATRON, which is a vacuum tube with a glass envelope, 

from the helium environment. It has been demonstrated that helium 

gas readily penetrates the glass envelope of the CORRELATRON and 

reduces the vacuum inside the tube to an unacceptable level in a 

relatively short period of. time. It has also been demonstrated, 

that an enclosure approximating the sensor housing size and construction can adequately protect the CORRELATRON from the helium 

environment for the proposed application. The sensor will be 

purged and filled with 0.5 atmospheres of dry nitrogen after the 

seals have been made. A pressure sensor will be installed to allow 

The sensor electronics consists of six individual potted 

modules including the high voltage supply, high voltage control 

and focus current regulator. It should be noted that all of the 

high voltage connections are contained within the hermetically 

sealed sensor package. This is a primary consideration with respect 

to personnel safety. 

The electronics control assembly is also a hermetically 

sealed assembly, filled with 0.5 atmospheres of dry nitrogen and 

contains a pressure sensor. Multilayer board construction is 

used for mounting the integrated circuits and associated discrete 

components. Components with high power dissipations are mounted on 

heat sinks with good thermal conducting paths to base. The unit 

.... 

. 

for the evaluation of the seal integrity throughout the life of 

the unit. 
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will be d,3igned to operate mounted on a heat sink. The case will 

be painted to give a thermal emissivity of 0.85 or greater. All 

heavy components are mounted near the base for mechanical stress 

considerations. The CFE A/D converter will also be contained in 

this assembly. All electrical connections to the electronics assembly are made through six hermetically sealed connectors mounted 

on the surface opposite the mounting surface. 

6.2 Block Diagram and Theory of Operation 

Figure 6-1 is.a block diagram of the IVS system. Following 

is a discussion of the operation of the IVS system. 

In order to obtain image rate information the IVS uses the 

CORRELATRON in a closed loop system. To function properly, the 

CORRELATRON requires three modes of operation: 

(a) A "write" mode,, wherein the initial image position is 

stored as a two-dimension charge pattern, and during 

which the IVS output is inhibited. 

(b) A "read" mode, wherein correlation of the input image 

and the previously stored reference is performed, and 

during which the sensor output is enabled. 

(c) An "erase" mode, wherein the previously stored reference 

charge pattern is removed from the storage mesh, and 

during which the sensor output is inhibited. 

During the write mode, an optical image is stored within the 

CORRELATRON by electron secondary emission of the storage mesh. 

During the read mode, a switching sequence is enabled to the 

tube elements to reduce the electron velocity so a non-destruct 

readout can be performed; Thus, for the single write sequence many 

non-destructive comparisons can be made before signal degradation 

occurs and a new write sequence is required. Before a new image is 

stored an erase signal actuates the "erase lights" and biases the 

CORRELATRON so that the storage mesh, stored image, is flooded 

with a uniform electron bundle and a "clean slate" is prepared to 

receive the write signal. 

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NRO APPROVED FOR 

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The data stored in the CORRELATRON is fixed on an x-y 

plane. The incoming optical image produces an electron bundle 

within the CORRELATRON which is nutated a small amount by field 

modulation in the coils around the CORRELATRON and an area match 

yields a maximum output when the input and stored images are superimposed. Closed loop characteristics of the IVS maintain the image 

superposition as the subject moves by displacing the field around 

the CORRELATRON and deflecting the image signal. 

The input is nutated in x and y by a one kilohertz sine wave. 

The x deflection is activated for one cycle, while the y is blanked 

and then the y is activated for one cycle while the x is blanked. 

The output data is thus a complex, multiplexed signal which will be 

synchronously demodulated to separate x and y. During a closed 

loop match condition, this signal appears as a full wave rectified 

sine wave. Under normal conditions this signal may vary from one 

millivolt peak-to-peak to 150 millivolts peak-to-peak depending on 

the image and it is riding on a 2,000 VDC level. 

The "buffer amplifier" is an AC coupled high impedance 

amplifier and converts the signal from the high voltage, current 

source, CORRELATRON to a ground level, low output impedance source. 

The low level "buffer amplifier" signal is amplified and 

AGC'd to provide a three volt peak-to-peak replica of the error 

signal without distortion or phase shift. To accomplish this, the 

three error amplifiers provide a common bandpass well in excess 

of an order of magnitude above and below the 1K Hz full wave 

rectified sine wave. Since the signals are multiplexed, only the 

single channel of gain is required. However, to properly AGC the 

separate x and y data there are two separate AGC amplifiers that 

are multiplexed synchronously into the feedback loop for the three 

stages. Each of the two AGC circuits employ a single lead-single 

lag network that is tuned to the 2K Hz ripple of the match signal 

to control the AGC operation. 

The fixed amplitude wave is then passed through the phase 

discriminator which reconstructs the match signal in a manner to 

obtain the least DC output for the best match. When the CORRELATRON 

LECRET 0 
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senses drift of the input image by distortion of the full wave 

rectified signals "form factor", the phase discriminator determines 

magnitude and direction to correct the loop, and maintain the 

proper form factor. 

The correction signal, still multiplexed, is now separated 

by synchronous demodulation and sent to separate x and y filters 

for processing. Each filter is designed to produce a double 

break at 34 Hz. The signal separation is accomplished prior to 

these filters to avoid smearing the x and y data. 

Each of the nutation summing amplifiers has a DC input which 

is controlled by the output of an integrator. The input to each 

of the two integrators is the output from one of the 34 Hz filters. 

By summing the nutation signal and the integrator output, the incoming image is deflected across the stored image maintaining the 

match signal. When the incoming image is displaced away from the 

centroid far enough that the integrator cannot force the deflection 

to match, then the "saturation limiters" force an erase-rewrite 

mode. The new write will start with the stored image of the CORRELATRON centered and both integrators zeroed. 

To maintain the closed loop condition, the small nutation must 

be maintained to generate a match signal. To maintain "lock-on" 

the integrators must slew to properly energize the coils, and 

deflect the incoming image from its present position on the CORRELATRON photocathode face to its originally stored position. The 

position saturation monitors control the limit of the slewing for 

both x and y in both directions. A verification circuit monitors 

the match signal from the third error amplifier to determine the 

condition of operation after write. The verify circuit compares 

the amount of 2K Hz ripple to the amount of 1K Hz in the error signal. 

The closed loop response maintains the optimum position match 

between the drifted image, somewhere on the CORRELATRON photocathode, 

to the stored image. The integrator that maintains "position " 

must, by definition, have "rate" as its input. Rate inputs to the 

r " 
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integrators, IVS output rates, are filtered by a 3.5 Hz filter 

and this relative DC output is scaled to provide the proper range 

of voltages for the input image rates encountered. This output is 

converted to provide a zero to plus five volt output with a polarity 

bit for negative excursions. The purpose of this is to provide a 

bounded zero volt to plus five volt input to the Analog to Digital 

converter. The polarity bit will be used with the digital readout 

for negative excursions. 

The operating sequence is implemented in the following 

manner: 

1. A six second warm-up interlock is enabled when power is 

applied. 

2. At the end of warm-up, and if the input scene illumination level is in excess of minimum requirements, the 

system steps into the "standby" mode which indicates 

operational readiness. 

3. If a "track command" is available the system will step 

from standby without delay. Without a "track command" 

it will remain in the operational ready or "standby 

mode". Given the three primary"initial conditions": 

the six second warm-up, satisfactory illumination and 

a track command the system will initiate an initial 

erase to prepare the CORRELATRON and establish all initial 

conditions in the operating sequence. 

4. The next sequence step is a "write" cycle which is 

dynamic with light intensity such that a low light causes 

a longer write period. The maximum write time is clocked 

to force an erase and rewrite if the write time exceeds 

some predetermined value. 

5. When the write mode is satisfied, the CORRELATRON is 

switched to the "read mode". For about the first 80 

milliseconds of the read mode, a stabilization and 

verification period is established. After approximately 
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40 milliseconds of stabilization, the 3.5 cycle filter 

inputs are enabled to permit their initializing before 

being placed "on line". The verification circuit is 

also enabled to permit an evaluation of the match. The 

"verification" consists of comparing the 2K Hz "match" 

signal to the 1K Hz "lost" signal. At the end of the 

stabilization and verification period, after switching to 

"match", the logic "enables" the output of the verification circuit and "enables" the position and saturation 

monitors. Two clock pulses at a 2K Hz clock rate are 

permitted before the "lock-on" signal and output data 

are released to permit verify or saturation to operate 

prior to "lock-on". 

6. "Lock-on" consists of passing the verify test without 

limiting on the position or deflection coil drives. 

Otherwise an erase mode is activated and a new cycle 

begun. A rate saturation is read out but does not force 

a recycle. During "lock-on" the verification makes a 

continuous monitor of the quality of the match. Once in 

the "lock-on" mode the system will stabilize and "match" 

the image until the deflection coils reach a limit or 

the verification indicates a degraded match signal. The 

system will cycle and erase and rewrite continuously until 

the "track command" is removed or low input illumination 

is encountered. 

7. There are two operational modes that will stop the system 

with track command on, one is low input illumination, 

the second loss of power. 

(a) If low illumination is encountered a low light 

indicator is activated to produce an IVS output 

indication and the system continues in lock-on 

until the next recycle. Recycle can be initiated 

41. by either the track verify circuit or an input 

command to the IVS. At that point the IVS enters 

the erase mode and erases and stops the clock. 
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When light again becomes available and if 

the track command is still on, it will erase 

again to clear the system and then continue 

cycling. 

(b) If power is dropped for less than one second 

the system will not go through warm-up. It 

will erase as the first step when power comes 

back on. If power loss is longer in duration, 

the system will "warm-up" for two seconds, 

erase and then continue operation. 

6.3 Equipment Characteristics 

6.3.1 Size 

Figures 4-1 and I show the outline dimensions of the proposed electronics control assembly and sensor of the IVS. The 

sensor length must be reduced by about 0.25 inches in order to 

comply with the space allocation of GE drawing 711-03013. 

6.3.2 Weight 

6.3.2.1 IVS System 

The estimated weight of the IVS system is approximately 

25.6 pounds. This exceeds the specified maximum weight by 2.6 

pounds. The increased weight is required to accommodate the new 

requirements for mounting the CFE A/D converter, increasing the 

electronics assembly package size for the converter, adding three 

additional connectors on the electronics assembly and providing the 

additional wiring needed. 

6.3.2.2 Sensor Weight Breakdown 

Following is a tabulation of the measured component weights 

for the Part 0 sensor. 
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Measured 

Weight 

(pounds) 

End Cap 0.31 

Cover 0.30 

bolder 0.01 

Field Lens Lock Ring 0.03 

Field Lens Assembly 0.32 

Relay Lens Lock Ring 0.02 

Relay Lens Assembly 0.23 

Window Retaining Ring 0.03 

Window 0.02 

CORRELATRON Assembly 1.38 

Coil and Light Assembly 4.47 

Sensor Body 6.20 

Connector Assembly 0.05 

Exhaust Tube 0.03 

Component Board Assembly 0.07 

X&Y Deflection Control Assembly 0.14 

2 KV Filter Assembly 0.25 

Chopper and Rectifier 0.29 

Terminal Board Assembly 0.08 

Wiring 0.03 

H.V. Component Assembly 0.26 

Focus and Light Control 0.13 

H.V. Control Assembly 0.14 

Total 14.79 

The required sensor weight of 14 pounds maximum can be 

met by some redesign primarily in the area of the sensor housing. 

This will be accomplished during the proposed program. No problem 

is anticipated in satisfying the sensor weight requirement. 

6.3.2.3 Electronics Control Assembly Weight Breakdown 

Following is a tabulation of the electronics control 

assembly component parts weights. Measured values are shown where 

possible and are indicated as such. 

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Part Name 

Part 0 

Growth 

Part 0 

Growth 

Part 0 

Growth 

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Weight 

(pounds) 

(actual) 

(estimate) 

(estimate) 

(estimate) 

(actual) 

(estimate) 

Base Housing: 

Outer Case: 

cover 

Assembly: 

1.80 

1.35 

0.20 

0.07 

0.55 

0.43 

Connector Mounting Part 0 0.75 (actual) 

Assembly: Growth 0.18 (actual) 

Wire and Part 0 0.10 (estimate) 

Hardware Growth 0.10 (estimate) 

Toroid Part 0 1.57 '(actual) 

Mounting Assembly: Growth U.50 (estimate) 

CFE A/D Converter 1.00 (specified) 

Shim 0.01 (estimate) 

Spacer 0.01 (estimate) 

Al P.C. Assembly 0.46 (actual) 

A2 P.C. Assembly 0.30 (estimate) 

A3 P.C. Assembly 0.30 (estimate) 

A4 P.C. Assembly 0.30 (estimate) 

A5 P.C. Assembly 0.30 (estimate) ' 

Ground Bus Assembly 0.03 (actual) 

Total 10.31 

Growth in the above table indicates the additional weight 

required to satisfy the revised requirements of EC-701A, Rev. 6. 

The total estimated increase in weight is 3.63 pounds including the 

CFE A/D converter specified weight of one pound. Taking into 

account the tabulated weights and allowing for growth during the 

IVS design phase, GAC feels a reasonable system weight requirement 

is 25.6 pounds maximum. 

6.3.3 Power 

6.3.3.1 IVS System 

The total IVS system power estimate for the Part 0 unit 

is about 25.6 watts. Addition of the CFE A/D converter requires 

one additional watt. Taking into account the IVS power supply inefficiencies, 28 watts maximum appears to be a reasonable IVS 

power requirement for inclusion of the CFE A/D converter. Presently, 

the proposed system power estimate totals about 27.7 watts. 
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6.3.3.2 Sensor. Power Breakdown 

The following is a tabulation of the current estimate of the 

sensor average power for an operating duty cycle of 20 minutes on 

and 70 minutes off. 

Circuit Power (watts) 

CORRELATRON 0.120 

Buffer Amplifier 0.042 

Deflection Control (X&Y) 1.310 

Deflection Coil 0.049 

Focus Coil 4.453 

Erase Light Control 0.081 

High Voltage Control 0.730 

Erase Lamps and Ballast 0.080 

Cathode Monitor 0.042 

H-V Power Supply 0.550 

Focus Control 1.435 

Total 8.942 

6.3.3.3 Electronics Control Assembly Power Breakdown 

Following is a tabulation of the current power estimate for 

the electronics control assembly. 

Circuit Power (watts) 

Error Amplifier and AGC 

Phase Discriminator Filter 

& Feedback Filter (X&Y) 

Output Filter, Polarity 

& Sense (X&Y) 

Reference Nutation & Multiplex Generator 

Programmer and Track Verify 

Diagnostic Monitoring 

Obscuration Detector 

CFE A/D Converter 

L-V Power Supply 

Total 

0.324 

0.466 

0.300 

0.084 

6.190 

0.336 

0.196 

1.000 

9.850 

18.746 

6.3.4 Reliability 

The present MTBF estimate for the IVS is in excess of 11,000 

hours. The additional requirements implied by the GE drawing 

711-03059 will undoubtedly have an adverse effect upon the estimated 

MTBF. No allowance has been made for the added CFE A/D converter 

since this item is a GE responsibility. 

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All IVS drawings will be approved by Reliability as a 

normal release procedure on this program, although it is not a 

normal company policy. It is the opinion of GAC that reliability 

of the ivs is second in importance only to system performance. All 

incoming narts will be functionally tested, reliability tested on 

a lot sample basis and stored in a bonded area until required for 

fabrication of the IVS. Strict adherence to approved procedures 

will be enforced so the component reliability will not be degraded. 

6.3.5 Diagnostic Monitoring Signals 

The proposed IVS will provide the following analog output 

signals for monitoring the performance of the system. 

1. Buffer Amplifier output 

2. Error Amplifier output 

3. X position 

4. Y position 

5. X velocity 

6. Y velocity 

7. Cathode current 

8. Write voltage 

These signals allow the IVS performance to be evaluated by providing 

an indication of the average input illumination (cathode current) 

and monitors several points in the forward path, the outputs and 

the feedback paths. Also, the write mode voltage pedestal .is 

measured. Each of these signals are buffer isolated from the IVS 

primary signal components for reliability considerations and will 

be scaled to be compatible with the telemetry requirements. The 

diagnostic monitoring points are indicated on the IVS block diagram, 

Figure 
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7.0 HIGH il3 SK TECHNICAL PROBLEMS AND PROPOSED SOLUTIONS 

7.1 Gene 

The ollowing items are considered technical risk items on the 

proposed rogram. Each item is subsequently discussed in detail including the approach to be taken in minimizing the risk. 

1. VD converter incorporation 

2. Saturation - 0.1 second recovery time 

3. IVS frequency response vs. output power spectral density 

4. Reliability 

5. Power dissipation 

6. Weight 

7. Electromagnetic Interference 

7.2 A/D Converter. Incorporation 

The following items concerning the CFE A/D converter are 

critical to the satisfactory completion of the proposed program. 

1. Delivery to GAC 

2. Thermal requirements 

3. Physical characteristics 

Following are the required dates for receipt of the CFE A/D converters at GAC to support the IVS program. One unit is required by each 

date indicated. 

1968 1 Nov, 1 Dec 

1969 1 Feb, 1 Mar, 1 Apr, 1 May, 15 May, 1 June, 15 June, 

15 Sept 

1970 1 Jan, 15 Jan, 15 Apr, 15 Aug, 15 Nov, 15 Dec 

1971 15 Mar, 15 Apr 

Spares will have to be provided in addition to the above required 

:,.sits to support the fabrication and repair phases of the program. 

Me definition of the thermal requirements and the physical characeristics of the converter will be needed by 15 September 1968 to 

support the IVS design effort. Close coordination between GAC, GE, 

and the A/D converter vendor will be required in order to provide the 

aforementioned information and hardware to support the program schedule. 

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7.3 Saturation - 0.1 Second Recovery Time 

Presently, the IVS cannot meet the 0.1 second recovery time 

under all operating conditions as discussed under section 3.1.1.1.D 

of the comments on the specification. CORRELATRON modifications 

(re. 3.2) and IVS electronic mechanization changes are presently 

under evaluation in the Part 0 program which will allow the IVS to more 

nearly satisfy the 0.1 second recovery time requirement. Coordination with GE engineering during the proposed program should give a 

better understanding of the performance of the system utilizing the 

IVS and satisfactory IVS performance of the IVS with regard to this 

requirement should result. 

7.4 IVS Frequency Response Vs Output Power Spectral Density 

The IVS performance will satisfy the requirements for frequency 

response and power spectral density of the output independently. 

However, certain trade-offs will be required in order for the system to satisfy both requirements simultaneously. Coordination with 

GE engineering, in evaluating the trade-offs when more IVS performance data is available, will enable the system to satisfactorily 

perform in the final application. 

7.5 Reliability 

The present IVS estimated MTBF is in excess of 11,000 hours. 

Addition of selected, redundant circuits will increase this number. 

However, the addition of the circuitry required by incorporating the 

A/D converter and GE drawing 711-03059 will have an adverse effect 

upon the MTBF. These effects will have to be evaluated when better 

circuit definition is available. Close collaboration between GE and 

GAC engineering should assure compliance with the MTBF requirement 

of 10,000 hours. 

7.6 Power Dissipation 

The present specification pertaining to the maximum IVS power 

dissipation makes no allowance for the required increases resulting 

from the addition of the A/D converter and the circuitry implied in 

GE drawing 711-03059. A 1-watt power increase was allowed for the 

A/D converter but no allowance was made for any required peripheral ' 

electronics or power supply inefficiencies. Likewise, no allowance 
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was made for any additional circuits or power supplies required to 

satisfy the 711-03059 drawing. Engineering contact between GE and 

GAC engineers is required to arrive at a satisfactory IVS power value 

considering performance, reliability, and safety trade-offs. 

7.7 Weight 

The revision 6 specification included a weight increase equal 

to the weight of the CFE A/D converter which must be incorporated 

into the IVS. No allowance was made for mounting hardware, bracketry, or the outer housing size increase of the electronics control 

assembly. Also, no allowance was made for the additional connectors, 

wiring and circuitry and associated hardware required by the GE 

drawing 711-03059. Collaboration between GE and GAC engineering 

will result in a satisfactory IVS weight once the requirements of 

the aforementioned items are completely defined. 

7.8 Electromagnetic Interference 

There is a potential problem area involved in satisfying the 

specified EMI requirements. The sensor must have a window installed 

in order to admit the input image. This window cannot have any EMI 

corrective fixes applied which will reduce the illumination level or 

the quality of the input image. It is assumed that deviations to 

the specification, if required, will be granted on selected, closely 

controlled basis. 
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8.0 MAINTAINABILITY CONSIDERATIONS 

Both units of the IVS are hermetically sealed making field 

maintenance difficult. It is understood that all IVS repair will 

be made at the factory. 

The IVS design will take into account the requirement of 

effecting a repair of any malfunction without adversely affecting 

the reliability of any component not involved in the repair. 

Modular construction is to be used wherever practical so complete 

subassemblies may be replaced. All subassemblies and components 

will be made as accessible as possible once the hermetic seal is 

broken and the cover removed. The test points available at the 

subassembly interface allow for a thorough evaluation of any repair 

upon completion. 
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9.0 SAFETY CONSIDERATIONS 

The design of the IVS is such that few safety hazards will 

be involved. The design, being all electronic, incorporates few 

sources of energy which could present hazards to the crew or overall 

system. Hydraulics, pneumatics, explosives or propellants are not 

required in the design. Potentially toxic or fire producing 

material has been minimized by material selection and packaging 

approach; the two subassemblies of the system are hermetically 

sealed inert gas filled (dry nitrogen) at 0.5 atmospheres. High 

voltage, 2000 VDC, is employed in the system but its use is completely internal to the sensor. Electrical shorts, should they 

occur in the IVS, will be isolated from the overall system by fusing 

provided by the vehicle electrical system. 

The structure used to house and hermetically seal the two 

packages making up the IVS, is rugged with no sharp edges and 

corners which could prove hazardous to the crew. 

There is no known combination of materials in the design 

which could provide any substantial source of chemical energy that 

would present a hazard to the crew or to the overall system. 
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10.0 RELIABILITY CONSIDERATIONS 

Listed below are the reliability tasks and considerations 

to be applied to the proposed program. 

1. All parts will be burned-in for 168 hours at maximum 

rated power and/or voltage at maximum rated temperature. 

This is intended to weed out incipient failures and 

localize any potential reliability problems. 

2. A worst case circuit design analysis utilizing the 

ECAP (computer aided design analysis technique) system. 

The data obtained from this analysis will be used'to 

establish the application failure rate of each component 

part, and the subsequent MTBF for the system. 

3. A preliminary reliability prediction will be made for 

the IVS. The data from this prediction will be used in 

the system and/or subassembly redundancy studies and as 

a guide in determining and identifying critical parts. 

The failure rates to be used on this program are based 

on MIL-HNBK-217A, FARADA, or other approved sources. 

4. A complete systems reliability analysis will be conducted. . 

This analysis will include probabilities of failure during 

or immediately following Qualification testing, storage, 

actual mission and transportation to a test site. 

5. A failure modes and effects analysis will be conducted. 

This data will be used to evaluate parts selection, 

reliability problem areas and the need for redundancy. 

6. A closed loop failure analysis system will be used to 

maintain control of vended parts and pinpoint any potential. 

reliability problems that have not been observed in the 

normal screening and testing results. 
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7. Operating time logs will become a part of every system 

or subsystem test specification. This data is used to 

maintain control of operating hours or equipment, used 

in the observed system reliability analysis, and as 

observed data in any failure analysis. 

8. A parts evaluation program will be initiated for the IVS. 

This program enables reliability to maintain control of 

quality workmanship '(internal and external), process uniformity, and materials that go into the fabrication of 

the parts. 

9. The parts that are not listed on the SPL will be 

specified as non-standard and selected in the order of 

procedure as shown below. 

(a) Qualified Established Reliability Specifications 

Parts 

(b) Qualified JAN Parts 

(c) Company Specification Control Drawings 
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11.0 THERMAL CONSIDERATIONS 

The specifications for having a surface finish with an 

emittance greater than 0.85 does not create any design problem. 

Many paints will meet this requirement. A gloss paint which is 

easier to clean would be marginal, 0.8 < 6 < 0.85, but semi-gloss 

or flat paints would meet the requirements. The finish would 

be obtained by following an approved painting specification. The 

emittance would either be accepted on published test data or it 

would be verified by measurements. There are two ways of measuring 

the emittance, either by a reflectometer or an emissometer. Most 

measurements made in the past at GAC were done with the reflectometer 

where the spectral reflectance, or energy E(X) between 2 and 22 

microns are measured and the emittance calculated for some temperature T by use of the equation 

X=22 

f

E(x)dx 

6(T) - =2 X=22 

j EB(x) dX 

X=2 

where EB is the black body spectral energy. 

This type of analysis has been automated and is programmed 

for data reduction on the IBM360 digital computer. Most of the 

future measurements will be done with an emissometer. Obtaining an 

LRC Emissometer, Model 25B (Lion Research Corp.) is presently in 

process. It is a portable unit and enables the measurements to be 

made on the finished items. 

The cooling of the electrical box will be accomplished by 

limiting the heat into the contact area of the base plate, AB, 

so that the base plate heat flux, qB, meets the requirements of 

handling the generated heat load Q within the following limits 

0.9 Q • 

< (ID< 1.0 watts/sq. in. A

B 

Ms 0 
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The sensor head cooling will be more difficult to distribute 

properly. The heat generated will result in some average temperatures from 

F

E VA c(T

avg 

+ CM (Tavg - T ) 

where 

FA = Radiatign area factor 

F = Effective emittance factor 

T

E = Enclosure temperature 

T

B = Base temperature 

CM = Conductance of the mounting 

The heat loss distribution can be obtained once all the 

variables are defined. 111e one that will be most difficult to 

specify will be the contact heat transfer at the base mount. The 

conductance C would have to be determined by testing. M 

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12.0 ON-BOARD SELF TEST DESCRIPTION AND BUDGETARY ESTIMATE 

12.1 General 

The GE letter, Request for Proposal-RFP 159, dated 3 June 1968, 

requests that the technical proposal include a description and a 

budgetary cost estimate for an on-board self tester to be included 

in the IVS. Including the self tester in the IVS design results in 

certain penalties in design areas such as weight, power, and reliability. A self tester separate from the IVS which could be disconnected during the mission should be considered in order to minimize 

the penalties imposed on the IVS by the self test capability. 

12.2 Concept Description 

Testing of the IVS requires introducing a moving image to the 

photocathode of the CORRELATRON and evaluating the resulting electrical outputs of the system. It appears that all of the desired 

self test electrical outputs are presently available in the form of 

diagnostic monitoring signals. Comparator and condition indicating 

circuitry will have to be added or made available to the IVS to implement the self test capability. 

The most practical technique for projecting a moving image on 

the CORRELATRON photocathode appears to be accomplished by installing 

a set of miniature incandescent lights, within the hermetically 

sealed sensor, near the erase lights. By controlling individual 

lights the uniformity of the illumination falling on the photocathode can be controlled and the center of power of the input image 

can be varied. This results in an indicated scene positional change 

sensed by the IVS. The turn-on and turn-off illumination increase 

and decay of the individual bulbs result in an apparent velocity as 

the scene center of power moves from one position to another. The 

electronics required to evaluate the IVS performance could be installed in the electronics control assembly. 

The budgetary estimate of the cost for implementing the aforementioned on-board self test capability within the IVS is $250,000. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

e / D 

BIF-048/001-2311-68 

58 

13.0 ADAPTER BUDGETARY ESTIMATE 

On 26 June 1968, GAC was requested to include a ROM in the 

technical proposal for providing the adapter, which supports the 

sensor. Figure 13-1 shows the GAC understanding of the physical 

size of the adapter. Mechanical and thermal properties of the 

adapter remain to be defined by GE. 

It is assumed that a precision spacer is required for each 

installation to compensate for the +0.25 inch tolerance on the IVS 

image plane position. The spacer is considered as being of the 

same material as the adapter and having comparable surface finishes. 

Properly choosing the adapter, spacer, sensor, and the main optics 

mounting surface finishes should result in light- and dust-tight 

seals that are adequate for the IVS application. It should be noted 

that the sensor mounting flange is large enough to accommodate an 

0-ring seal, if required, while the main optics mounting flange is 

too small for 0-ring usage. A gasket is not recommended for this 

application because of environmental considerations. This latter 

consideration necessitates the close control of the adapter and the 

associated mounting surface finishes. 

For estimating purposes, it was assumed that no parts would 

protrude into the area allocated for the adapter defined on GE drawing 711-03013 and that alignment of the sensor to the main optics 

would be accomplished by dowels,. 

The budgetary estimate for providing the adapters and spacers 

required for the deliverable hardware during the proposed program 

is $10,220. 
648/601 

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