d0301-014 final engineering f.port for the medium

D0301-014

FINAL ENGINEERING _F.PORT

FOR THE

MEDIUM RESOLUTION INFRA-RED (MRIR) EXPERIMENT

ENGINEERING MODEL DIGITAL ELECTRONICS TELEMETRY UNIT

FOR

NIMBUS "B"

1 November 1965 - 1 April 1966

CONTRACT NO. NAS5-9699

Prepared by

CALIFORNIA COMPUTER PRODUCTS, INC.

305 North Muller Street

Anaheim, California

For

GODDARD SPACE FLIGHT CENTER

Greenbelt, Maryland

D0301-014

SUMMARY

The object of this report is to describe in detail the

overall design aspects of the Engineering Model MRIR

Telemetry Unit, and to present design information onthe Bench Test Equipment which was modified for the

MRIR Telemetry Unit. The Bench Test Equipment was origi-

nally designed and fabricated for the MRIR Telemetry Unit

contained in the NIMBUS "C" Spacecraft.

The final engineering design report is intended to estab-

lish information on the telemetry unit operation, to

define engineering problems uncovered during functional

testing, and to recommend improvements to be incorporated

into succeeding units. Data pertinent to maintaining the

MRIR Telemetry Unit is also presented within this report.

The finished Engineering Model MRIR Telemetry Unit had

slight deviations from the information presented in the

Design Study Report, CalComp Document D0301-013, dated

31 December 1965. The deviations, electrical in nature,

were brought about because of problems uncovered during

fanctional test. These problems involved circuit changes

or logic changes. These were as follows:

a. Noise pulses on the second stage flip-flop

input of the commutation ring counter.

i,_:CELTigG F'F\G E ..........

iii

D0301-014

b. 200-kc input filter network.

c. A/D Converter comparator amplifier compensation.

d. A/D Converter precision operational amplifier

compensation.

e. MOS-FET device failures during functional test.

Solutions and recommendations pertaining to these problems

are explained in the main test of this report.

The initial engineering model design approach was straight-

forward and relatively complete. Except for. necessary

changes to ensure reliable operation, only two recommenda-

tions are made as improvements. One improvement recommenda-

tion is the availability of two MOS-FET devices per analog

input channel (requires two additional TO-5 packages), and

the other improvement is to provide better noise isolation

on the second stage comg.utation ring counter.

The functional test of the Engineering Model MRIR Telemetry

Unit was performed with the aid of the modified NIMBUS "C"

Bench Test Equipment. The BTE provided the input signals

and captured the responses which were processed to provide

visual inspection capability for determining the operation

of the telemetry unit. Inasmuch as the BTE was used to

test the telemetry unit, the very act of its testing capa-

bility provided data which indicated that the BTE was per-

forming in a manner which constituted acceptance of its own

operability. Therefore, the modification to the BTE has

been tested through actual use of the equipment.

iv

D0301-014

In concluding this summary, it is felt that the Engineering

Model MRIR Telemetry Unit and the Bench Test Equipment meet

the requirements of the GSFC-NASA specification for the

Medium Resolution IR (MRIR) Experiment Engineering Model

for the NIMBUS "B" Spacecraft. The design, fabrication,

assembly, and testing of the telemetry unit did not present

any major problems that could not be simply and easily

rectified. The mechanical design is complete and all parts

were assembled without any modifications being required.With the inclusion of the suggested recommendations, pro-

totype and flight model telemetry units may be constructed

and tested in the same manner as the Engineering Model MRIRTelemetry Unit. The BTE and its new modifications have

been checked out and found to be sufficient for testing

the telemetry unit. No further additions or modifications

are to be incorporated into the BTE.

V

D0301-014

TABLE OF CONTENTS

Section Title

l • INTRODUCTION ..............

1.1

1.2

1.3

1.4

Scope ...............

History of Contract NAS5-9699

Engineering Model Telemetry

Unit General Description .....

Bench Test Equipment

General Description ........

i-I

i-i

I-i

1-6

1-7

• ELECTRONIC REVIEW ...........

2.1 Printed Circuit Boards ......

2 .i .i

2.1.2

2.1.3

2 .i .6

Analog Input -25-KC Generator Board

Analog/Digital

Converter Board ......

Analog/Digital

Data Control ........

Encode-Timing Generator

Frame Sync and

Data Output ........

DC/DC Converter

Nos. 1 and 2 ........

2.2 Grounding Scheme and

Voltage Distribution

2-6

2-9

2-11

2-13

2-13

2-13

2-13

v1

D0301-014

TABLE OF CONTENTS (continued)

Section Title

2.3

2.4

2.5

Telemetry Points .......... 2-15

Electrical Precautionary Measures. 2-17

Electronic Design Recommendations. 2-17

o MECHANICAL DESIGN ............ 3-1

3.1 Engineering Model

MRIR Telemetry Unit ......... 3-1

3.1.1 Package Layout ........ 3-1

3.1.2 Physical Parameters ..... 3-3

3.1.3 Center of Gravity ...... 3-5

3.1.4 Mechanical Design

Recommendations ....... 3-5

3.2 Bench Test Equipment ........ 3-7

.

.

SYSTEM TEST AND OPERATION ........ 4-1

4.1 System Temperature Cycle Test .... 4-1

4.2 MRIR Telemetry Unit Interface. . . 4-1

4.3 MRIR Telemetry Timing Diagram. . 4-2

4.4 Interconnection Diagram ...... 4-9

NEW TECHNOLOGY ..............

5.1 Results of Contractor's Review .

vii

D0301-014

TABLE OF CONTENTS (continued)

Section Title

. B IBL I OGRAPHY ..............

6.1 Technical Reports

and Manuals ............

Monthly Progress Reports .....

Functional Test Specifications.

6-1

6-1

6-3

6-4

Appendix Title

n.

So

C •

DQ

MRIR TELEMETRY UNIT

ELECTRICAL SCHEMATICS AND

PRINTED CIRCUIT BOARD ASSEMBLY DRAWINGS

MRIR TELEMETRY UNIT

INTERFACE DESCRIPTION

MRIR TELEMETRY UNIT

MECHANICAL DRAWINGS

MRIR TELEMETRY UNIT

INTERCONNECTING PIN CHART

A-I

B-I

C-I

D-I

viii

D0301-014

LIST OF ILLUSTRATIONS

Figure Title

2-1 Split-Phase Wave form .......... 2-4

2-2 First Stage Input Commutator

(Pre-Functional Test Design) ...... 2-7


(Engineering Model Fix) ......... 2-8

2-4 200KC Input Filter

Pre-Functional Test Design ....... 2-10

2-5 200KC Input Filter Prototype

Flight Model Design .......... 2-10

2-6 200KC Input Filter

Engineering Model Design ........ 2-10

2-7 Frame Sync Inhibit Logic ........ 2-12

2-8 Ground and Power Supply Wiring

MRIR Telemetry Unit .......... 2-14

2-9 Temperature Telemetry Point ...... 2-16

D0301-014

LIST OF ILLUSTRATIONS (continued)

Fiqure Title


(Prototype - Flight Model

Design Recommendation) .......... 2-19

2-i1 Two MOS-FET Per Analog

Input Channel .............. 2-21

3-1 Printed Circuit Board Allocation . . . 3-2

3-2 MRIR Telemetry Unit

Engineering Model Center of Gravity . • 3-6

3-3 Display Console ............. 3-8

3-4 Auxiliary Console ............ 3-9

4-1 Timing Chart NIMBUS "B" MRIR

(Telemetry Unit) ............. 4-6

X

D0301-014

LIST OF TABLES

Table Title Paqe

3-1 Input/Output Connectors ......... 3-4

4-1 MRIR Telemetry Unit Power Supply

Temperature Test at +60°C Ambient .... 4-2

4-2 MRIR Telemetry Unit Power Supply

Temperature Test at -10°C Ambient . 4-3

4-3 MRIR Telemetry Unit Analog/Digital

Conversion at +60oc Ambient Temperature

(Nominal Voltage) ............ 4-4

4-4 MRIR Telemetry unit Analog/Digital

Conversion at -10°C Ambient Temperature

(Nominal Voltage) ............ 4-5

xi

D0301-014

SECTION 1

INTRODUCT ION

The Engineering Model MRIR Telemetry Unit has been designed,

fabricated, functionally tested, and delivered. A final

engineering report covering the history, fabrication, and

testing of the completed subsystem is presented herein.

In addition, this report shall cover the Bench Test Equip-

ment which was modified for the NIMBUS "B" telemetry unit.

1.1 SCOPE

This final report contains the data which is pertinent to

the completed Engineering Model _._IR Telemetry Unit. The

report is intended to cover the electrical, mechanical,

and functional testing aspects of the completed subsystem,

provide recommendations for improvement on following units,

and to provide sufficient data for maintenance purposes.

Also, a functional and physical description of the modified

Bench Test Equipment shall be included in this report.

1.2 HISTORY OF CONTRACT NAS5-9699

A CPIF contract with an incentive clause for cost and

delivery was awarded to California Computer Products, Inc.,

i-i

D0301-014

(CalComp) on 1 November 1965. The overall object of the

contract was to perform a design study on a Medium Re-

solution Infra-red (MRIR) Telemetry Unit which had been

designed by NASA for the NIMBUS "B" Spacecraft, to review

and recommend improvements in the design, and to generate

a pre-prototype engineering model based on the results

presented and agreed to in the design study review. In

addition to the telemetry unit, the contract required that

one set of NIMBUS "C" MRIR-PCM Bench Test Equipment (BTE)

be modified for use with the NIMBUS "B" Telemetry Unit.

Manuals to support the BTE for both operation and mainte-

nance purposes were also required as part of this contract.

The contract called for completion of the hardware fabri-

cation and final delivery on or before 31 March 1966.

The delivery of the Engineering Model MRIR Telemetry Unit

was fulfilled with a final sell-off demonstration test to

an authorized representative of the Government as appointed

by NASA on 1 April 1966.

To aid in the design study of the MRIR Telemetry Unit,

NASA shipped to California Computer Products, a breadboard

version of the design on 9 November 1965. The breadboard

consisted of two major parts, the power supply and the

telemetry unit logic section with associated drawings and

test aids. With the aid of the breadboard, careful analysis

and relying on the past experience of the NIMBUS "C" MRIR

Telemetry Unit, CalComp generated a design study report

which assessed the submitted design for the proposed

1-2

D0301-014

telemetry unit. The design study report pointed out

potential trouble areas, recommended improvements, and

presented a hardware packaging concept with thermal and

mechanical analytical data.

The preliminary design study report was submitted to NASAon 31 December 1965 for their review. On 6 January 1966,

three representatives from NASA consisting of the contract-

ing officer, the technical officer, and the telemetry unit

designer met with CalComp representatives at CalComp to

discuss the recommendations set forth in the design study

report. At this meeting, it was determined what recommen-

dations would be adopted. It was also decided that all

suggested improvements which were adopted were within thescope of the original contract; therefore, no negotiations

were required to receive additional funding for work con-sidered to be beyond the intent of the original contract.

With the formal approval of NASA on 25 February 1966, Cal-

Comp initiated the orders to produce an engineering model

of the MRIR Telemetry Unit. Parts were ordered, artwork

for the printed circuit modules was completed, functional

test specifications were written, and supporting test

equipment was developed and fabricated. The BTE design

was firmed up as a result of the agreement reached on the

MRIR design recommendations.

All parts contained within the Engineering Model MRIR

Telemetry Unit were ordered from vendors with the exception

of the fl_t pack integrated circuits which were Government-

1-3

D0301-014

furnished. The GFE IC's were functionally tested at

CalComp prior to being soldered to the printed circuit

boards.

On 2 March 1966, an interface agreement meeting conducted

by General Electric was held at Goddard Space Flight Center

in Greenbelt, Maryland. In attendance were representatives

from General Electric, Santa Barbara Research, California

Computer Products, Inc., and NASA. The purpose of the

meeting was to establish interface requirements among the

equipment suppliers. Since General Electric has the re-

sponsibility for system integration, General Electric

conducted the meeting. The final results of the meeting

were to be compiled into separate documents specifically

directed to the participating equipment manufacturers.

After the establishment of interface requirements, the

task at hand was to fabricate, assemble, and test the

Engineering Model MRIR Telemetry Unit. The telemetry unit

consists of a magnesium chassis and seven printed circuit

cards. The procurement of parts for the assembly did not

present delivery problems. The IC's were hand soldered to

the printed circuit boards even though a resistive solder-

ing machine was slated to be used for this job. Using the

soldering machine, a sample IC board was prepared with

dummy IC's which were attached to the printed circuit board.

The sample was submitted to NASA for review and tests.

NASA tests showed that the soldering was unsuitable at this

time; however, NASA recommended several improvements in

1-4

D0301-014

using the soldering machine. The NASA laboratory report

indicated that once the right combination of heat, solder

content, solder deposition, and bonding pad area were

determined, the solder bond would be sufficient to fulfill

NASA soldering requirements.

As each printed circuit board was completed, it was sub-

jected to a comprehensive static test to ensure that no

damage occurred to the board or its components during the

assembly. At the completion of the board test, the boards

were inserted into the wire harness connectors contained

in the chassis to perform the system functional test with

the aid of the BTE. The functional test of the boards,

individually as well as combined within the system, un-

covered malfunctions for which corrective action was initi-

ated. The details of the malfunctions and new recommenda-

tions are contained in the main body of this report. Prior

to delivery, the engineering model was subjected to a

thermal cycle test which covered the range from minus 10°C

to plus 60°C. The results of this testing are contained

in Section 4. As it was stated before, the acceptance

test which constituted delivery was performed on 1 April

1966 at the C?iComp facility. On 5 April 1966, the engineer-

ing model was presented to the NASA technical officer at

the Goddard Space Flight Center. Power and input signals

were applied, and the Engineering Model MRIR Telemetry Unit

responded by presenting the correct data.

1-5

D0301-014

From the start of the contract to the hardware delivery

of the Engineering Model MRIR Telemetry Unit, the total

time frame for the design review, fabrication, assembly,

and test of the telemetry unit was five months and one day.

1.3 ENGINEERING MODEL TELEMETRY UNIT GENERAL DESCRIPTION

The NIMBUS "B" MRIR Telemetry Unit interfaces with the

MRIR Radiometer Electronics Unit to convert analog data

to a serialized digital format. The logic circuitry

within the MRIR Telemetry Unit samples in sequence each

of five radiometer output channels. The analog information

is gated to an Analog-to-Digital (A/D) Converter Unit

where 34.7 A/D conversions per second are performed on

each channel input. The A/D conversion is performed with

an accuracy of 1 part in 256 (8 bit accuracy).

The output of the A/D Converter is formatted with a frame

synchronization word to produce a 28.8 millisecond frame

length. The serial bit-stream frame consists of one 8-bit

frame synchronization word (i0111000) and five 8-bit

digitized conversions of the analog radiometer data (one

word for each of the five channels). The formatted data

is transmitted in a split-phase waveform to a satellite

digital recorder at a 1.66-kc bit rate (208 cps data word

rate). The least significant bit for each word is trans-

mitted first.

1-6

D0301-014

1.4 BENCH TEST EQUIPMENT GENERAL DESCRIPTION

The MRIR Telemetry Unit Digital Subsystem Bench Test

Equipment is designed to facilitate the functional testing

of the Engineering Model MRIR Telemetry Unit. The Bench

Test Equipment generates the clock frequencies, analog

voltages, and primary power required by the telemetry unit.

By routing all interface signals through the test point

panel, an evaluation of the various input/output signals

can be made. The primary output of the telemetry unit

subsystem, a split-phase code modulated signal, is decom-

mutated and made available as a visual display.

Additional features, such as current monitoring facilities,

incremental voltage sources, and dummy loads are contained

in the test equipment, minimizing the accessory equipment

required for a thorough test.

The digital electronics contained in the test equipment is

mechanized from basic modules for ease of maintenance and

replacement. To aid in maintaining the test equipment,

miscellaneous remote controls and indicators are brought

to the front panel of the electronics drawer.

The d-c voltages required to operate both the test equipment

and the unit under test are provided by modular power supplies

housed in the test console.

1-7

D0301-014

SECTION 2

ELECTRONICREVIEW

2.1 PRINTED CIRCUIT BOARDS

The final design of the MRIR Telemetry Unit contains seven

(7) printed circuit boards (PCB's). Five of the PCB's con-

tain the electronics to initiate and perform the function

for converting the analog input information into a digital

format. The remaining two PCB's provide the necessary

secondary power levels which are generated from a primary

input voltage source of a nominal minus 24.5 volts. A

brief description of each module and its function is pre-

sented below.

a. Analog Input - 25-kc Generator

This board contains six MOS-FET devices (only

five are used) which gate the analog information

to the A/D Converter. A five flip-flop ring

counter provides the commutating control. In

addition, this board generates a 25-kc clock

signal by using three flip-flops to divide the

200-kc input by eight.

2-1

D0301-014

b. A/D Converter

This board contains the precision voltage supply,

the comparator amplifier, constant current sources,

transistor switches, and a precision resistor-

ladder network to accomplish the analog-to-digital

conversion.

c. A/D Data Control

This board contains two 8-flip-flop registers.

One register retains the data after the A/D

conversion. The other register provides the

control signal to successively turn on each

current source. Depending on whether the analog

voltage is greater than or less than the voltage

generated by the ladder network, will determine

whether a selected current source should be left

on or turned off. This module also contains the

Frame Sync Inhibit logic which changes the least

significant bit to a "one" if analog data is

converted to have the same bit pattern as the

Frame Sync word.

d. Encode - Timing Generator

This board contains nine flip-flops which are

used to provide timing control. Six flip-flops

are used to divide a 10-kc input signal to

1.66 kc (one bit time) and 208 cps (one word

time). A transfer pulse is generated to gate

the converted information from the data register

2-2

D0301-014

e .

f.

on the A/D Data Control board to an output data

shift register on the Frame Sync-Data Output

board. In addition to the transfer pulse, a

second timing pulse (ENCODE pulse) is generated.

The ENCODE pulse clears the A/D data register,

resets the A/D shift register, and starts the

A/D conversion of new input data.

Frame Sync - Data Output

This board generates the Frame Sync word (i0111000)

every sixth word time. The function of the Frame

Sync word is to provide a basis for synchronization

when decommutating the telemetry data transmitted

to a ground station. As was mentioned before, an

8-bit flip-flop shift register is contained on

this board to provide the serial data output to

two redundant data output buffer drivers. The

data is transmitted in a split-phase waveform as

shown in Figure 2-1.

DC/DC Converter No. 1

This board is one of two power supply boards

which provides the secondary voltage levels.

These levels are +3.2v, +6v, -6v, -12v, and -18v.

Contained on this board are the primary power

relay, flux oscillator, power transformer, and

secondary voltage diode rectifiers. The DC/DC

No. 1 board was designed so that all oscillating

signals would be confined on this board and not

be coupled into the wiring harness by sending the

oscillating signals to another board for condition-

ing.

2-3

D0301-014

BINARY NUMBER

BINARY WAVEFORM

SPLIT-PHASE WAVEFORM

1II

OlI

I 0

II

I

I I I

I ' l i I II I i

'' I' ' II lI I i II i l I

t I

tl Ia Il

o I z I.I i

I1I

0I

tI

Ilk;

I_'-_ II NEGATIVE-GOING TRANSISTION REPRESENTS A "ONE"• z___I

Ilt I

POSITIVE-GOING TRANSISTION REPRESENTS A "ZERO"

TIME

FIGURE 2-1

Split-Phase Wave form

2-4

D0301-014

g.DC/DC Converter No. 2

The second half of the two power supply boards

contains the input filter network, voltage

regulator, secondary level output filters, and

the telemetry point circuits.

Test equipment to test the PCB's on an individual basis

was designed and fabricated. To perform as complete a

test as possible on each PCB, functional test specifica-

tions were generated for each PCB with the exception of

the two power supply boards. These two boards are tested

as a unit; therefore, one functional test specification

covers both boards.

While performing the initial functional test on the PCB's,

several problems were uncovered. The necessary action to

solve these problems was initiated and the solutions have

been implemented. The malfunctions spoken of here are the

types which required printed circuit board modifications

and drawing changes. Other discrepancies which have been

found are of such a minor nature that they will not be

discussed. These discrepancies involved wrong value

components, failed parts, term exits on a pin other than

noted on the schematic, etc. The intent here is to review

each PCB type and comment on it. The electrical schematics

and assembly drawings for all PCB's are found in Appendix A.

2-5

D0301-014

2.1.1 ANALOG INPUT - 25-KC GENERATORBOARD

Of the seven PCB's in the MRIR Telemetry Unit, the Analog

Input board presented the most problems. The major problem

was that noise feedback on the output of the first stage

of the commutation ring counter was sufficient to SET thesecond stage 300 microseconds after it was RESET. The

RESET should have been for a time duration of 4.8 milli-

seconds. The circuit showing the situation when the faultyoperation occurred is shown in Figure 2-2. The solution

to this problem for the engineering model is shown in

Figure 2-3. The gate which was contained on the board,

but unused, provided the isolation from the noise feedback

on the "zero" side output, while the collector provided

isolation on the "one" side output. The use of both the

collector output and the emitter-follower output on the

"one" output side is ordinarily not a good practice because

base drive for the emitter-follower output is reduced.However, in this instance, the emitter-follower fan-out

load is only eight. Its maximum fanout is fifteen. Since

the emitter follower is driving half its capacity, the

simultaneous use of the flip-flop collector output does

not divert enough base drive to hamper the emitter-follower

operation.

The second problem area on the Analog Input board was the

transformer isolation input filter network for the 200-kc

clock signal. This network as shown in Figure 2-4 provided

too much attenuation on the input clock, and the reduced

2-6

D0301-014

C6 +3.2v

NOISE

FEEDBACK

C1 C1 +3.2v

C6I

II!!!

!

!--!

CLOCK

l

IlI

75

4 IC

1 *6 i0

5

1

3 7

IC

9 8

CLOCK

*Emitter-Follower Output-

FIGURE 2-2

First Stage Input Commutator

(Pre-Functional Test Design)

2-7

D0301-014

m

Cl Cl RCl

+3.2v +3.2v

7 25

4

i6 i0

9

8

: - OTPI

_E

5 I(

4

18 9

_r

FIGURE 2-3


(Engineering Model Fix)

2-8

D0301-014

voltage was insufficient to drive the IC device. A

review of the NIMBUS "C" MRIR design which had the same

clock input requirement showed that this filter network

was redesigned to that indicated in Figure 2-5. For the

Engineering Model NIMBUS "B" MRIR Telemetry Unit, a com-

promise was made between the filter networks. The design

used on the present MRIR engineering model is shown in

Figure 2-6. However, for the subsequent prototype and

flight model MRIR's, the filter network shown in Figure 2-5

will be included on the board.

2 .1 .2 ANALOG/DIGITAL CONVERTER BOARD

The A/D board required some rework as a result of its

functional test. Because of the accuracies involved,

the A/D design is very sensitive. Extraneous noise was

sufficient to cause the A/D Converter to operate erroneously

To remedy this situation, the board required additional

components to eliminate the noise. One source of noise

was the VLAD test point output term which is directly

coupled through a 4700-ohm resistance to the comparator

input circuit. This integrated circuit has a high impedance

input and a very high gain. Any noise pickup on this line

was coupled to the comparator input and amplified. To

eliminate this action, the 4700-ohm resistor was replaced

with a 100-picofarad capacitor tied to signal ground.

The VLAD test point term has been eliminated and the noise

is now filtered to ground.

2-9

200KC

200KC GRD--

5.1K T1

470pf

C2 47pf III

D0301-014

GATE

FIGURE 2-4

200KC Input Filter Pre-Functional Test Design

1 .OK T1 200pf

il

470pf200KC GRD

i:i _I_

Q Select

FIGURE 2-5

GATE

200KC Input Filter Prototype - Flight Model Design

1 .OK T1

°°200KC GRD

100pf

,,11 GATE

FIGURE 2-6

200KC Input Filter Engineering Model Design

2-10

D0301-014

The comparator amplifier required a frequency compensation

capacitor between IC pins one and eight. When the A/Dboard was laid out, no provisions were provided for this

compensation. Previous to the layout design, breadboard

tests on this IC showed that no frequency compensation

was required; however, when the board was fabricated and

tested, the operational amplifier broke into a 1-megacycle

oscillation when the null point between the actual data

input and the ladder network output were approximately

equal. A 10-picofarad capacitor was inserted between pins

one and eight on the IC comparator amplifier to prevent

this oscillation at the null point.

2.1.3 ANALOG/DIGITAL DATA CONTROL

The A/D Data Control logic board did not have any problems

associated with it during the board test and the subsystem

functional test. Prior to having the board fabricated, a

logic error was found on the Frame Sync Inhibit logic. The

logic was corrected, the artwork was updated, and the board

was fabricated correctly. Figure 2-7 shows the logical

representation for the correct mechanization. This mechani-

zation will change the LSB of the data word to a "one" if

the data word appears exactly as the Frame Sync word

(i0111000).

2-11

D0301-014

D8

D7

D6

D5

D4

D3

IC26

8SN512

D2

D1

SN512

SN514

iC22

IC27

n

D1

FIGURE 2-7

Frame Sync Inhibit Logic

2-12

D0301-014

2.1.4 ENCODE-TIMING GENERATOR

The Encode-Timing Generator board did not require any

changes.

2.1.5 FRAME SYNC AND DATA OUTPUT

The Frame Sync and Data Output boards did not require any

changes.

2.1.6 DC/DC CONVERTER NOS. 1 AND 2

The two boards which provide the secondary voltage levels

did not require any changes.

2.2 GROUNDING SCHEME AND VOLTAGE DISTRIBUTION

Figure 2-8 shows a signal flow diagram which contains the

grounding scheme and voltage distribution. The grounding

scheme in the MRIR was designed to avoid any ground loops.

The power ground and signal grounds are in reality the

same ground, but a difference is shown between the two.

The power ground pertains to the DC/DC Converter boards,

while the signal ground pertains to the other printed cir-

cuit boards. Chassis ground and telemetry ground are not

internally tied to any point within the engineering model.

2-13

D0301-014

However, the telemetry points on the flight models will

have the temperature telemetry point referenced to telemetry

ground. The secondary power distribution is straight-

forward and presented no problems. The voltage distribution

can be determined on the pin chart contained in Appendix D.

2.3 TELEMETRY POINTS

There are only three telemetry points contained within the

Engineering Model MRIR Telemetry Unit. The points are used

to monitor that the primary power relay has switched on

command, that the minus 12 volt secondary level is main -

taining regulation, and what the internal temperature is

at the hottest point. A temperature sensitive component

(Sensistor) is used to monitor the temperature. The output

of the Sensistor as a function of voltage and temperature

is shown in Figure 2-9. This curve can be used for cali-

bration purposes. Appendix B gives the electrical informa-

tion on the other two telemetry point outputs.

2-15

i

og

"\ \\\\

\• \

\ \\

| , ,. _

t)O0

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D0301-014

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2-16

D0301-014

2.4 ELECTRICAL PRECAUTIONARY MEASURES

The use of MOS-FET devices has necessitated that extreme

care be used in their handling. The devices can be easily

damaged by static electricity or high positive voltage

spikes. CalComp used precautionary measures during the

board assembly as well as during functional test of the

printed circuit board, and testing at the completed system

level.

During the PCB assembly, the leads of the MOS devices were

shorted together before, during, and after the assembly.

A special 44-pin shorting plug was wired and attached to

the board to tie all the input leads of the MOS devices

to signal ground on that assembled module. At the system

level, the analog inputs were routed to the J4 Bench Test

connector so that a shorting plug (37-pin) provided pro-

tection when the MRIR telemetry was not connected. The

procedure for system integration or connecting to the BTE

is to install all cables to the other four connectors

before removing the shorting plug to install the last

cable, J4. The reverse procedure is used for cable removal.

2.5 ELECTRONIC DESIGN RECOMMENDATIONS

a . On the Encode-Timing Generator board, a fix

was made to isolate the emitter-follower outputs

from the outputs going to the next stage of the

2-17

D0301-014

b.

commutating ring counter. Instead of simultane-

ously using the collector output and emitter-

follower output on the Cl flip-flop, it is

recommended that a gate be added to eliminate

the use of the collector output. The mechaniza-

tion will then be as shown in Figure 2-10.

During the course of performing the functional

test at the board level and the completed system

level, three failed MOS transistors have been

encountered. The cause and nature of their failure

cannot be explained because other areas of the

board or system were under investigation and not

the MOS devices themselves. When the attention

was turned to the MOS transistors, the failures

were detected. The task of removing a multilead

TO-5 device from the PCB is a very tedious job

and in most cases pads are lifted. In addition,

there is the risk of causing a failure to the

new device being installed. The MOS-FET's used

in the MRIR Telemetry Unit contain two devices

within the same TO-5 can. The failure of any

one MOS device within the package requires that

the package be replaced. The waste here is that

one MOS device within the removed package is

still good but cannot be used elsewhere. Since

these MOS devices can be easily damaged in

handling, it is recommended that one MOS device

per package per analog input channel be used or

2-18

D0301-014

22 X

I0 6 8_ ,_ I'• I

n

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FIGURE 2-10


(Prototype - Flight Model Design Recommendation)

2-19

D0301-014

that the present two MOS devices per package

be used except that the two devices be allocated

for one channel only. For the latter recommenda-

tion, the five analog input channels would each

have two MOS transistors (one package) each.

The interconnection on the PCB could be done so

that each channel input could be hardwired to

use either of the two MOS devices available within

the package. The mechanization for one channel

input is shown in Figure 2-11. In the present

layout, three M0S packages are used, but only

five of the six available MOS-FET devices are

wired into the circuit. The sixth is left hanging.

The proposed scheme requires that only two addi-

tional TO-5 packages be added. This recommenda-

tion provides economy, saves repair time, and

does not subject the PCB to damage which can be

caused during repair.

2-20

D0301-014

ANALOG

OUTPUT

ANALOG

INPUT

-18V

m

-18V

Dotted lines represent shorting wires.

Wire B dotted lines for B MOS-FET.

Wire A dotted lines for A MOS-FET.

NOTE: Only one MOS-FET circuit is wired in at any one time.

FIGURE 2-11

Two MOS-FET Per Analog Input Channel

2-21

D0301-014

SECTION 3

MECHANICAL DESIGN

3.1 ENGINEERING MODEL MRIR TELEMETRY UNIT

3.1.i PACKAGE LAYOUT

The layout of the Engineering Model MRIR Telemetry Unit

was changed from the layout initially presented in the

design study report to the layout shown in Figure 3-1.

The Analog Input - 25-kc Generator board was placed as

close as possible to the input/output connectors to keep

the analog input lines short. Shields were placed between

the analog input board and the input/output connectors to

protect against crosstalk. The shield between the DC/DC

Converter No. 1 board and the remaining logic modules was

to isolate the logic modules from the flux oscillator

circuit. The mechanical drawings containing the actual

design of the Engineering Model MRIR Telemetry Unit are

available in Appendix C.

No mechanical design problems were encountered when the

engineering model MRIR was assembled. The machined

magnesium parts were finished with the DOW 17 protective

coating. All parts fit without modifications. The

3-1

D0301-014

I---1 F---1J[""-_ I i ["--"_ I I J l I !

ANALOG INPUT - 25KC

A/D CONVERTER

A/D DATA CONTROL

ENCODE TIMING

FRAME S YNC - DATA OUTPUT

rllllJlll////lll l //I//l / JJl////I/f /lllll///llJ/I//I//_,_

DC/DC CONVERTER NO. 1

DC/DC CONVERTER NO. 2

SHIELD

SHIELD

FIGURE 3-1

Printed Circuit Board Allocation

3-2

D0301-014

mechanical design drawings pertaining to the chassis parts

are complete. The final package size was 2 over 0 or

6 x 4 x 6.5 inches. The housing contained five input/output

connectors which are labeled Jl through J5, and the type

and function of each connector is indicated in Table 3-1.

Each connector is different to prevent mismatching between

cables and connectors.

Internal to the housing are seven 44-pin printed circuit

board (PCB) connectors which are keyed to match a particular

PCB. The PCB's contain slots corresponding to the keys.

3.1.2 PHYSICAL PARAMETERS

3.1.2.1 Layout

The PCB layout of the Engineering Model MRIR Telemetry Unit

is shown in Figure 3-1.

3.1.2.2 Weiqht

The completed engineering model MRIR weighed 4.3 pounds

(unpotted). This weight included the shorting plug on

connector J4.

3.1.2.3 Power Dissipation

The measured power dissipation of the engineering model

3-3

D0301-014

TABLE 3-1

Input/Output Connectors

Connector Number of Pins Signals

J1 15-pin Plug Power Input and Commands

J2 9-pin Socket Output Signals

J3 15-pin Socket Input Signals

Telemetry and Bench Test

J4 37-pin Socket Equipment Test Point

J5 9-pin Plug Input Clock Signals

3-4

D0301-014

MRIR was 1.7 watts at minus 10°C. This figure represents

the maximum power dissipation.

3.1.3 CENTEROF GRAVITY

The dimensions of measured center of gravity of the

engineering model MRIR are shown in Figure 3-2.

3.1.4 MECHANICALDESIGN RECOMMENDATIONS

The mechanical design is sufficient as it stands for the

engineering model telemetry unit; therefore, prototype

and flight models will be mechanically fabricated in the

same manner as the engineering model.

3-5

D0301-014

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I C.6.

3. ZSS

II

FIGURE 3-2

MRIR Telemetry Unit

Engineering Model Center of Gravity3-6

D0301-014

3.2 BENCH TEST EQUIPMENT

3.2.1 PHYSICAL DESCRIPTION

The MRIR Telemetry Unit Bench Test Equipment is housed in

two single bay racks. One rack, called the display console,

houses the power supply drawer, test point panel, data

display drawer, and a console blower. See Figure 3-3.

The other rack, the auxiliary console, houses the remaining

commercial test equipment, which includes a Tektronix RM45A

oscilloscope, a Non-Linear Systems Model 484A digital volt-

meter, and an Exact Electronics Model 250 function generator.

In addition to a console blower, the latter bay is equipped

with a loose equipment drawer and a writing surface. This

unit is shown in Figure 3-4. A more comprehensive descrip-

tion can be obtained from the Bench Test E%uipment Document

D0106-004 entitled "Maintenance Manual for MRIR-PCM Bench

Test Equipment, NIMBUS B," dated 24 March 1966.

Convenience outlets are available at the power supply drawer

and the rear of the auxiliary console. Both consoles are

designed to be operated from single-phase, ll5-vac power.

The display console is protected by a 10-ampere circuit

breaker in the a-c line, with a 15-ampere breaker protecting

the auxiliary console. In addition, the d-c power supplies

are protected by a line fuse.

3-7

D0301-014

-- .< i

FIGURE 3-3

D i s p l a y Console

3-8

FIGURE: 3-4

Auxiliary Conso le

n n ? n i n i A . lJUdUL-VLY

3- 9

D0301-014

SECTION 4

SYSTEMTEST AND OPERATION

4.1 SYSTEM TEMPERATURE CYCLE TEST

The engineering model was placed into a temperature controlled

oven to test the effects of the unit at +60°C, and at -10°C.

The results of each test on a per channel basis are contained

in Tables 4-1, 4-2, 4-3, and 4-4. In all cases, the MRIR

unit was allowed to temperature soak (no applied power) for

approximately forty-five minutes. The internal temperature

of the unit was determined by monitoring the Sensistor.

4.2 MRIR TELEMETRY UNIT INTERFACE

The interface list for the Engineering Model MRIR Telemetry

Unit is contained in Appendix B. The list provides the

terms on each connector pin plus the equivalent voltages

and impedances on those pins which originate or terminate

on the telemetry unit.

4-1

D0301-014

4.3 MRIR TELEMETRY TIMING DIAGRAM

A timing diagram showing the relationship among the logic

signals within the MRIR Telemetry Unit is presented in

Figure 4-1 on page 4-6.

TABLE 4-1

MRIR Telemetry Unit Power Supply

Temperature Test at +60°C Ambient

Secondary Primary Power Input

Voltage

Levels -24.0 ± 0.02v -24.5 ± 0.02v -25.0 ± 0.02v

+0.23+3.2

-0.i0

+6 + 0.18

-6 = 0.18

-12 ± 0.36

-18 + 0.54

+3.189

+6.128

-6.154

-12.25

-18.42

+3.189

+6.127

-6.154

-12.25

-18.42

+3.189

+6.128

-6.154

-12.25

-18.42

4-2

D0301-014

TABLE 4-2

MRIR Telemetry Unit Power SupplyTemperature Test at -10°C Ambient

Secondary Primary Power InputVoltageLevels -23.5 ± 0.02v -24.5 ± 0.02v -25.5 ± 0.02v

+0.23+3.2 -0.i0

+6 ± 0.18

-6 ± 0.18

-12 ± 0.36

-18 ± 0.54

+3.117 +3.117

+5.907

-5.937

+5.907

-5.938

+3.118

+5.908

-5.939

-11.97

-18.05

4-3

D0301-014

TABLE 4-3

MRIR Telemetry Unit Analog/Digital

Conversion at +60°CAmbient Temperature

(Nominal Voltage)

Bit Channel

Channel 2 Channel 3 Channel 4

20 (25mv)

21 (50mv)

22 (100mv)

23 (200mv)

24 (400mv)

25 (800mv)

26 (1600mv)

27 (3200mv)

All

Bits 6375mv

Channel 1

-18mv

-45

-94

-194

-396

-797

-19mv

-45

-95

-195

-396

-797

-20mv

-45

-95

-195

-396

-797

-20mv

-45

-95

-196

-396

-797

-1596

-3197

-6372

-1596

-3197

-6372

-1596

-3197

-6372

-1596

-3197

-6372

Channel 5

-20mv

-45

-95

-196

-396

-797

-1596

-3197

-6372

4-4

D0301-014

TABLE 4"4

MRIR Telemetry, Unit Analog/Digital

Conversion at -10°C Ambient Temperature

(Nominal Voltage)

Bit Channel

Channel 1 Channel 2 Channel 3 Channel 5

20 -25mv

21 -50my

22 -100mv

32 -200mv

24 -400my

25 -800mv

26 -1600mv

27 -3200mv

-19mv

-44

-94

-194

-396

-796

-1596

-3197

-20mv

-45

-95

-196

-396

-796

-1596

-3197

-20mv

-45

-95

-196

-396

-796

-1596

-3196

-20mv

-45

-95

-196

-396

-796

-1596

-3196

_ll

Bits -6375mv -6372 -6372 -6372 -6372

4 Channel

-20mv

-45

-95

-196

-396

-796

-1596

-3196

-6372

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D0301-014

4.4 INTERCONNECTION DIAGRAM

Appendix D provides a combination wire list and inter-

connecting diagram. The JXXX numbers associated with the

connector terms indicate where the wire is going.

4-9

D0301-014

SECTION 5

NEWTECHNOLOGY

Throughout the performance of the contract NAS5-9699, a

continual review of the work performed was conducted by

a designated committee, including the Project Manager and

the Patent Counsel. The committee met periodically to

discuss all effort performed with a view to ascertaining

reportable items disclosed in performance of the contract,

both by the contractor and all subcontractors.

5.1 RESULTS OF CONTRACTOR'S REVIEW

The following are considered reportable items under the

"New Technology" clause:

a. Reportable Item: Analog-to-Digital Converter

Circuit.

Invention Status: Not reasonably patentable.

Apparent Use: An analog-to-digital converter.

Description: The analog-to-digital converter

for this contract is based

almost entirely on the design

submitted by NASA to the

contractor. The contractor

made some component changes

5-1

D0301-014

bo

in incorporating some new

integrated components which

the contractor bought as off-

the-shelf items from Fairchild

Semiconductor Corporation.

The design of the circuit was

slightly different due to the

requirements of the integrated

components. The complete

circuit is shown in this re-

port as drawing No. D-I0368-502.

Reportable Item: Interface Buffer Circuit.

Invention Status: Not reasonably patentable.

Apparent Use: A data output buffer circuit.

Description: The data output buffer circuit

for the frame sync and data

output is of standard design

utilizing integrated circuit

components. The circuit is

based on the design submitted

to the contractor by NASA.

The circuit is shown in

drawing No. 10354-502.

There were no subcontractors reportable under the "New

Technology" clause.

5-2

D0301-014

SECTION 6

BIBLIOGRAPHY

The following documents are directly related to the design

and development of the Engineering Model MRIR TelemetryUnit.

6.1 TECHNICAL REPORTS AND MANUALS

a. D0201-65/I18 - 21 September 1965

A technical proposal for a Medium Resolution IR

(MRIR) Experiment Engineering Model Digital

Electronics Telemetry Unit for NIMBUS "B."

b. D0301-013 - 31 December 1965

Reliability Assessment and Development Study

Report on MRIR-PCM Subsystem.

D0106-003 - i0 March 1966

Operator's Manual for MRIR-PCM Digital Subsystem

Bench Test Equipment, NIMBUS °'B. "

D0106-004 - 24 March 1966

Maintenance Manual for MRIR-PCM Bench Test

Equipment, NIMBUS "B. "

C •

d .

6-1

D0301-014

e .

f.

g .

h.

i .

j .

k.

i .

20101-01 - 23 November 1965

Engineering Model MRIR Telemetry Unit Telecon

Report.

20101-02 - 7 December 1965


Report.

20101-03 - 9 December 1965


Report.

20101-04 - 14 December 1965

Engineerlng Model MRIR Telemetry Unit DC/DC

Converter Analysis.

20101-05 - 20 December 1965


Report.

20101-07 - 5 January 1966

Engineerlng Model MRIR Telemetry Unit Telecon

Report.

20101-08 - ii January 1966


Report.

20101-09 - 18 January 1966


Report.

6-2

D0301-014

m. 20101-010 - 19 January 1966

Stresses Caused by Module Clamps.

n. 20101-011 - 4 February 1966


Report.

o. 20101-014 - 22 March 1966


Report.

6.2 MONTHLY PROGRESS REPORTS

a. D0513-001 - 14 December 1965

Monthly Progress Report No. 1 for MRIR-PCM

Telemetry Unit, 1 November 1965 - 28 November 1965

b. D0513-002 - ii January 1966


Telemetry Unit, 29 November 1965 - 2 January 1966.

c. D0513-003 -8 February 1966


Telemetry Unit, 2 January 1966 - 31 January 1966.

d. D0513-004 - 7 March 1966


Telemetry Unit, 1 February 1966 - 28 February 1966.

e. D0513-005 - 14 April 1966


Telemetry Unit, 1 March 1966 - 31 March 1966.

6-3

D0301-014

6.3 FUNCTIONAL TEST SPECIFICATIONS

a. A0205-I01 - 29 April 1966

Functional Test Specification for Analog Input

and 25-KC Generator.

b. A0205-I02 - 5 May 1966

Functional Test Specification for Analog-to-

Digital Converter.

c. A0205-I03 - 29 April 1966

Functional Test Specification for Analog-to-

Digital Data Control.

d. A0205-I04 - 29 April 1966

Functional Test Specification for Encode-

Timing Generator.

e. A0205-I05 - 2 May 1966

Functional Test Specification for Frame Sync

and Data Output.

f. A0205-I06 - i0 May 1966

Functional Test Specification for DC-to-DC

Converter No. 1 and No. 2.

g. A0201-019 - 10 March 1966

Functional Test Specification for the MRIR-PCM

Digital Subsystem, NIMBUS "B."

6-4

D0301-014

APPENDIX A

MRIR TELEMETRYUNIT

ELECTRICAL SCHEMATICS

AND

PRINTED CIRCUIT BOARDASSEMBLYDRAWINGS

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D0301-014

APPENDIX B

MRIR TELEMETRY UNIT

INPUT/OUTPUT

INTERFACE SPECIFICAT ION

D0301-014Append ix B

Input Connector Jl

Pin Term

1 Spare

Characteristics

2 -24.5 DRA Connected to the negative terminal

of the satellite primary regulated

supply. To be used by the radio-

meter drive amplifiers.

3 Spare pin

4 OFFCMD 65-ms pulse with a nominal ampli-

tude of +12 volts to the ON-OFF

relay. Input impedance is 160

ohms. Relay is turned off.

5 OFFCMDR Relay OFF command return line

6 Spare pin

7 GRD S MRIR signal ground

8 GRD P Power ground connected to the

positive terminal of the

satellite regulated supply.

B-I


Input Connector Jl Icontinued)

Pin Term Characteristics

9 -24.5 M Connected to the negative terminal


supply.

i0 -24.5 TM Connected to the negative terminal


supply. To be used by the thermistor

Input impedance is nominal 2K ohms.

ii ONCMD 65-ms pulse with a nominal ampli-

tude of +12 volts to the ON-OFF

relay. Input impedance is 160

ohms. Relay is turned on.

12 ONCMDR Relay ON command return line.

13 Spare pin

14 GRD T Telemetry ground

15 GRD C Chassis ground

B-2


Output Connector J2


1 TRO 1 Tape Recorder Output No. 1

amplitude is +6.5 volts to +5.0

volts for the high state and 0

volts ± 0.6 volts for the low

state. Output impedance is 330

ohms.

2 Spare pin

3 GRD TRO 1 Tape Recorder Output No. 1

reference ground

4 GRD TRO 2 Tape Recorder Output No. 2

reference ground

5 GRD P Power ground

6 TRO 2 Tape Recorder Output No. 2

characteristics are same as TRO i,

Pin i.

7 GRD S Signal ground



B-3


input/output Connector J3


1 -24.5 MR Negative terminal of the satellite

primary regulated supply. Primary

power is routed through the MRIR

unit to the radiometer.

2 -24.5 RDA Negative terminal of the satellite

primary regulated supply. Primary

power is routed through the MRIR

unit to the radiometer driver

amplifier.

3 Spare pin

4 CH 1 Radiometer Analog Input No. 1

voltage amplitude is 0 volts to

-6.4 volts at a frequency up to

8 cps. Input impedance is greater

than 150K ohms when the analog

gate is on.


(Same description as Pin 4.)




B-4


Input/Output Connector J3 (continued)

Pin Term

8 GRD P

Characteristics

Power ground connected to positive

terminal of the satellite primary

regulated supply.

9 ioo OA Output Phase A of a 2-phase, 100-cps,

square wave signal which is routed

through the MRIR unit to the radio-

meter. Amplitude is -1.5 k 1.0

volt for the high level and -23.0

± 1.5 volts for the low level.

i0 i00 _B Output Phase B of a 2-phase, 100-cps,

square signal which is routed

through the MRIR unit to the radio-

meter. Phase B leads Phase A by

90 ° . Amplitude same as Phase B.

ii

12 CH 4

13 CH 5

14 GRD T

Spare

Radiometer Analog Input No. 4


Radiometer Analog Input No. 5


Telemetry ground

15 GRD C Chassis ground B-5


Output Connector J4

Pin Term

1 RLY TMP

2 TEM TMP

3

4 -18V TP

5 -12V TP

Characteristics

Relay Telemetry Point Output.

Voltage amplitude for on condition

is 8 + 1.5 volts and 0 + 0.6 volts

for the off condition. Output

impedance is 16.3K ohms.

Temperature Telemetry Point Output.

Voltage amplitude is variable

between -1.3 volts and -3.0 volts

over the temperature range of

-10°C to +65°C. Output impedance

is less than 3K ohms over the

temperature range. The output

voltage is derived from a separate

-24.5 volt supply.

Spare

MRIR -18 volts ±3 percent regu-

lated secondary supply. Provides

4.7K-ohm isolation resistor on

output.

MRIR -12 volts +3 percent regu-

lated secondary supply. Provides

4.7K-ohm isolation resistor on

output.

B-6


Output Connector J4 (continued)


6 -6V TP MRIR -6 volts +-3 percent regulated

secondary supply. Provides a 4.7K-

ohm isolation resistor on output.

7 +6V MRIR +6 volts +-3 percent regulated

secondary supply. Provides 4.7K-

ohm isolation resistor on output.

8 +3.2V MRIR +3.20 (+0.22V, -0.10V)

regulator secondary supply. Pro-

vides a 4.7K-ohm isolation resistor

on output.

Spare

i0 RB4 208-cps symmetrical square wave

output. Amplitude is +0.2 ± 0.i

volts for the 1 state and +2.0 ± 0.5

volts for the 0 state. Output

impedance is greater than 4.7K ohms.

ii RB5 Pulse output that occurs every 4.8

milliseconds. Pulse duration for

1 state (+0.2 ± 0.I volts) is i00

microseconds. For the remainder of

the time, the 0 state is +2.0 ± 0.5

volts. Output impedance is greater

than 4.7K ohms.B-7




12 RB 1 1.66-kc symmetrical square wave

output. Amplitude for 1 state is

+0.2 ± 0.i volt and +2.0 ± 0.5

volts for the 0 state. Output

impedance is greater than 4.7K

ohms.

13 RN4 (ECD) 20-microsecond pulse output which

repeats every 4.8 milliseconds.

Output amplitude is +0.2 ± 0.i

volts for the 1 state and +2.0

± 0.5 volts for the 0 state.

Output impedance is greater than

4.7K ohms.

14 RK4 25-kc symmetrical square wave

output with an amplitude of +2.0

+ 0.5 volts for the high level

and +0.2 ± 0.i volts for the low

level. The output impedance is

greater than 4.7K ohms.

B-8




15 RC6 Pulse output that repeats 33

times per second, pulse duration

is 4.8 milliseconds. Voltage

amplitude is +2.0 ± 0.5 volts

for the 0 level and +0.2 ± 0.i

volts for the 1 level. The out-

put impedance is greater than

4.7K ohms.

16 RCl Pulse output which occurs 30

milliseconds after C6 occurs.

The voltage amplitude and out-

put impedance characteristics

are the same as C6 on Pin 15.

17 CH5 Radiometer Analog Input No. 5.

This pin is provided for a pro-

tective purpose. During shipping

this point is shorted to signal

ground.


B-9




19 GRD P

2 0 -12 TMP

21 CH4

22 RDI

23 RD--/

Power ground connected to the

positive terminal of the satellite

primary regulated supply.

-12 volt telemetry point output.

Nominal voltage output is -6 volts

±4 percent. The output impedance

is 2.8K ohm ±2 percent.

Radiometer Analog Input No. 5.

Same description as Pin 17 on

this connector.

LSB from the A/D data register.

Voltage amplitude is +2.0 ± 0.5

volts for the 0 state and +0.2

± 0.i volts for the 1 state.

Output impedance is greater than

4.7K ohms. Digital value is 2° .

21 Digital bit from the A/D data

register. Voltage and impedance

characteristics are the same as

D1 on Pin 22.

B-10

D0301-014Appendix B



24 RD32

2 Digital bit from the A/D data



D1 on Pin 22.

2 5 RD4 23 Digital bit from the A/D data



D1 on Pin 22.

m

26 RD5 24 Digital bit from the A/D data



D1 on Pin 22.

27 RD6 25 Digital bit from the A/D data



D1 on Pin 22.

28 RD--7 26 Digital bit from the A/D data

register. VQltage and impedance


D1 on Pin 22.

B-II

D0301-014

Append ix B


Pin Term Character is tic s

2 9 RD8 27 Digital bit from the A/D data



D1 on Pin 22.


Same description as Pin 17 on this

connector.

31 COMP OT Comparator output voltage. Voltage

output swings from +3.0 volts for

Vladder <Vinput to -6.0 volts for

Vladder >Vinput. Output impedance

is greater than 4.7K ohms.

32 V PREC Precision voltage output -I0.0

± 0.3 volts. Output impedance is

greater than 4.7K ohms.

33 Spare



this connector.

B-12




35 CHI Radiometer Analog Input No. i.


this connector.



B-13


Input Connector J5


1 i0 KC CLK 10-kc symmetrical square wave

input nominal voltage swing is

0 volts to -6 volts. Input

impedance is 3.3K +2 percent.

Spare

3 200 KC CLK 200-kc symmetrical square wave

input. Nominal voltage swing is

0 volts to -6 volts. Input

impedance is 24.7 ohms +i0 percent.

4 GRD 200 KC Provided as 200-kc input reference

ground.

5 GRD P Power ground connected to the

positive terminal of the satellite

primary regulated supply.

6 i00 _A Input Phase A, I00 cps, square

wave to be used by the radiometer

subsystem. Nominal voltage swing

is same as J3, Pin 9.

B-14

D0301-014

Appendix B

Input Connector J5 (continued)

Pi___n_n Term Char ac ter is tic s

7 zoo Input Phase B, i00 cps, square

wave to be used by the Radiometer

subsystem. Nominal voltage swing

is same as J3, Pin i0. Phase B

leads Phase A by 90 ° .

8 Spare pin


B-15

D0301-014

APPENDIX C

MRIR TELEMETRYUNIT

MECHANICALDRAWINGS

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