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Electromagnetic CompatibilityTest Plan____________________________________________________

INTERNATIONAL EXTREME ULTRAVIOLETHITCHHIKER -3 (IEH-3)

FinalFebruary 1998

NASA

National Aeronautics andSpace Administration

Special Payloads DivisionGoddard Space Flight CenterGreenbelt, Maryland

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TABLE OF CONTENTS

LIST OF FIGURES............................................................................................... 5

LIST OF ACRONYMS .......................................................................................... 6

1.0 PURPOSE...................................................................................................... 7

1.1 Applicable Documents............................................................................ 7

1.2 Equipment Testing.................................................................................. 7

2.0 TEST FACILITIES .......................................................................................... 8

3.0 SAFETY REQUIREMENTS DURING EM RADIATION TESTING ................. 8

4.0 TEST LIMITS.................................................................................................. 8

5.0 TEST METHODS ........................................................................................... 9

6.0 TEST CONFIGURATION ............................................................................. 10

6.1 Payload Configuration .......................................................................... 10

6.2 Payload Special Requirements............................................................. 10

6.3 Hitchhiker Ground Support Equipment Configuration........................... 10

7.0 CONDUCTED EMISSIONS TESTS (CE01 /CE03 /CE07) ........................... 15

7.1 Narrowband Conducted Emissions Tests (CE01 /CE03) .................. ...15

7.1.1 Payload Operational Mode ........................................................ 15

7.2 Voltage Spikes on Power Lines Test (CE07)........................................ 17

8.0 RADIATED EMISSIONS TESTS (RE02 /RE04)........................................... 21

8.1 Narrowband and Broadband Radiated Emission Measurements (RE02)...21

8.1.1 Payload Operational Mode .................................................... ....21

8.2 Magnetic Field Radiated Emissions Measurements (RE04)..................24

8.2.1 Payload Operational Mode .................................................... ....24

9.0 CONDUCTED SUSCEPTIBILITY TESTS (CS01 /CS02 /CS06 /HCP)......... 25

9.1 Power Line Conducted Susceptibility Tests (CS01 /CS02) .................. 25


9.2 Power Line Transient Test (CS06) ....................................................... 27


9.3 Power line Transients Caused by STS Hydraulic Circulation Pump (HCP)...28

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10.0 RADIATED SUSCEPTIBILITY TEST (RS03) ............................................. 30

10.1 Susceptibility from Unintentional Orbiter Produced Emissions ............ 30

10.1.1 Payload Operational Mode ...................................................... 30

11.0 PRELIMINARY TEST RESULTS................................................................ 34

12.0 RESPONSIBILITY ASSIGNMENTS ........................................................... 34

12.1 Responsibilities of Code 568 .............................................................. 34

12.2 Responsibility of EMC Test Group Code 754.2 .................................. 34

12.3 Responsibility of Code 300 Flight Assurance Office ........................... 35

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TABLE OF FIGURES

Figure 6-1 IEH-3 Payload Test Configuration ................................................... 12

Figure 6-2 IEH-3 Cable Connections................................................................. 13

Figure 6-3 IEH-3 GSE Layout............................................................................ 14

Figure 7-1 Narrowband Conducted-Emission on Payload Power Leads ........... 16

Figure 7-2 Limits on Payload Produced Spikes (Line-to-Line) on DC Power

Levels ................................................................................................................. 18

Figure 7-3 STS DC Power Line Impedance ...................................................... 19

Figure 7-4 Network Schematic for Simulating Impedance of Orbiter Power System....20

Figure 8-1 Unintentional Radiated Narrowband Limits for Electric Field Emission......22

Figure 8-2 Unintentional Radiated Broadband Limits for Electric Field Emission........23

Figure 8-3 Limits of Radiated AC Magnetic Field at 1 Meter from Orbiter Payload......24

Figure 9-1 Transient Voltage on the Primary PL Bus Produced by Operation of the

Hydraulic Circulation Pump ................................................................................ 29

Figure 10-1 Orbiter Produced Radiated Narrowband Emissions....................... 32

Figure 10-2 Orbiter Produced Radiated Broadband Emissions......................... 33

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LIST OF ACRONYMS

AC Alternating CurrentACCESS Advanced Carrier Customer Equipment Support SystemANSI American National Standards InstituteCGSE Customer Ground Support EquipmentCONCAP Consortium for Materials Development in Space Complex

Autonomous PayloaddB DecibelDC Direct CurrentEGSE Electrical Ground Support EquipmentEM ElectromagneticEMC Electromagnetic CompatibilityEMI Electromagnetic InterferenceGEVS General Environmental Verification SpecificationGSE Ground Support EquipmentGSFC Goddard Space Flight CenterHCP Hydraulic Circulation PumpHH HitchhikerHz HertzICD Interface Control DocumentIEH International Extreme Ultraviolet HitchhikerMIL MilitaryMG Marshall/ GoddardMRDM Medium Rate De-MultiplexerOSR Orbiter Simulation RackPANSAT Petite Amateur Navy SatellitePL PayloadRF Radio FrequencySCA Spacecraft AssemblySEH Solar Extreme Ultraviolet HitchhikerSOLCON Solar Constant ExperimentSTAR-LITE Spectrograph/Telescope for Astronomical ResearchSTD StandardSTS Space Transportation SystemTBD To Be DeterminedUVSTAR Ultraviolet Spectrograph Telescope for Astronomical Research

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1.0 PURPOSE

The purpose of this test plan is to verify that the IEH-3 Payload meets the

specifications stated in the Shuttle Orbiter-to-IEH-3 Interface Control Document

(ICD). The IEH-3 ICD contains the same electromagnetic compatibility

requirements as those specified in the STS core ICD, ICD-2-19001. Those

requirements are not necessarily identical to the ones in the GSFC-GEVS-STS, as

the IEH-3 ICD is the controlling document.

1.1 Applicable Documents

1. ICD-2-19001, Shuttle Orbiter / Cargo Standard Interfaces, JSC 07700

Volume XIV Rev. K (IRN 383 Ref A02673).

2. GEVS-STS, General Environmental Verification Specification for STS

and ELV Payloads, Subsystems and Components, January 1990.

3. GMI 5310.1A, GSFC Malfunction Reporting System.

4. GSFC-303-PROC-002, Procedure for the Documentation and

Disposition of Discrepancies (741 CM #741-PROC-0041).

5. GSFC-303-PROC-001, The GSFC Certification Log (741 CM #741-

PROC-0021).

6. MIL-STD-461C, Electromagnetic Interference Characteristics,

Requirements for Equipment.

7. MIL-STD-462, Electromagnetic Interference Characteristics,

Measurement of, as amended by Notice 1.

8. MIL-STD-463A, Definitions and Systems of Units, Electromagnetic

Interference and Electromagnetic Compatibility Technology.

9. ICD-A-21257, Shuttle Orbiter-to-IEH-3 Interface Control

Document.

1.2 Equipment Testing

The equipment to be tested is the IEH-3 payload. This payload consists of

the CONCAP-IV, SEH, SOLCON, STAR-LITE and UVSTAR experiments and

the PANSAT ejectable.

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2.0 TEST FACILITIES

The test program will be performed in the Spacecraft Assembly (SCA) shielded

room located in building 7 at GSFC. This facility is a Class 10,000 clean room.

Clean room procedures will be adhered to while in this facility. Code 568

representatives shall be responsible for the setup and operation of the IEH-3

payload during the preparation and operation of this test. Code 754 and its

representatives shall be responsible for the setup and operation of the required

test equipment listed in section 12.2. The Fairchild battery cart is required to be

recharged every evening throughout EMC testing. The test duration is expected

to be two weeks.

3.0 SAFETY REQUIREMENTS DURING EM RADIATION TESTING

American National Standards Institute (ANSI) requirements specified in Document

No. 95.1-1982, regarding Safety Levels for Human Exposure to Radio Frequency

Electromagnetic Fields 300 kHz to 100 GHz, will be adhered to throughout the

test to prevent overexposure to personnel. During the radiation susceptibility

portion of the test, no personnel will be permitted near the transmitting antennas.

Although NSI’s will already be installed, no safety hazard to personnel exists since

they will be contained within the bolt cutter assemblies. However, to prevent

inadvertent firing, all personnel in contact with flight hardware shall wear anti-static

gloves and wrist stats.

4.0 TEST LIMITS

The test limits are the applicable test limits of the Shuttle Orbiter / IEH-3 ICD

and are defined herein. The IEH-3 ICD limits are not necessarily identical to the

GSFC-GEVS-STS limits; in some cases they are wider. All of the figures in this

document are for illustrative purposes only. For actual limits, refer to the Shuttle

Orbiter / IEH-3 ICD.

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5.0 TEST METHODS

The tests will be conducted in accordance with the test methods and requirements

of MIL-STD-461 / 462 except for those tests for which special test methods and

are defined herein.

Several EMI tests require the experiments to operate in a noisy and noise

sensitive mode. These modes are described as follows:

Payload Most Noisy Noise Sensitive

CONCAP-IV Oven Operations Data Accumulation

PANSAT N/A (Unpowered) HESE Powered

SEH HMDA Open/Gas Valves HMDA Open/Data

/FW Motor/HV On Data Accumulation

SOLCON Shutter Operations Sensor Voltage Readout

STAR-LITE Scan Platform Ops Data/Video Accumulation

UVSTAR Scan Platform Ops Data/Video Accumulation

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6.0 TEST CONFIGURATION

6.1 Payload Configuration

The IEH-3 payload test configuration is shown in Figure 6-1. Figure 6-2

illustrates the cable connections of the test configuration. Additional cabling

between the experiment electronics is not shown. Only those harnesses

required for this EMI test are shown. The flight harness shall be installed

in a flight configuration. The payload structure shall be grounded to the

facility. Figure 6-3 shows the GSE layout outside the SCA room. During all

conducted tests, the payload shall be battery powered via a code 754

supplied +28 +/ - 4 VDC battery cart. For radiated tests, a lab power supply

may be used. 0 AWG power lines will be required to simulate actual flight

interfaces.

During the susceptibility tests, Ground Support Equipment (GSE) will be

connected to the payload and operating. A unique power harness must be

installed between the HH avionics and the battery in order to perform the

conducted emissions and susceptibility tests.

6.2 Payload Special Requirements

The PANSAT ejectable is mounted to a Hitchhiker provided ejection system

which contains pyrotechnic devices. In order to test these systems in the

most efficient manner, special configurations will be used during EMC testing.

The flight pyrotechnic devices will be part of the integrated system and

armed throughout the test. However, since these will be considered category

B explosives, no potential harm to personnel will exist.

6.3 Hitchhiker Ground Support Equipment Configuration

The Hitchhiker Avionics Electrical GSE includes an OSR and ACCESS. The

OSR provides the necessary Orbiter electrical interfaces to the HH avionics

and will be located outside the SCA clean room in Bldg. 7, room 010. The

ACCESS will be located next to the OSR rack. All cables entering the Radio

Frequency (RF) shield room will be covered with aluminum foil and

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grounded. The HH avionics will be mounted to an Experiment Mounting

Plate (EMP) attached to the bridge (upper truss). The upper truss will be

rolled into the RF clean room.

Customer Ground Support Equipment (CGSE) shall also be used to

control / monitor the payload. The CGSE will interface with the ACCESS.

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Figure 6-1 Payload Test Configuration

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BATTERY CART

AVIONICSGSE RACK

120 VAC SINGLE PHASE

208 VAC THREE PHASE

AREA OUTSIDE SCACLEAN ROOM

GSE RF

GSE ML

GSE HO

TEST CHAMBER WALL

EMITESTBOX

FOR CONDUCTEDEMISSIONS ONLY

HH AVIONICS

P001

J001

P006

J006

P007

J007

P008

J008

FEED THROUGHS

SEE GE1556028 FOR SPECIFICCABLING DETAILS

Figure 6-2 IEH-3 Cable Connections

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RFI ROOM

CABLES TOHH AVIONICS

OSRACCESS

3’ x 3’

CONCAPTABLE

SEHTABLE

SOLCONTABLE

STAR-LITETABLE

UVSTARTABLE

PANSATTABLE

4’ x 6’

Figure 6-3 IEH-3 GSE Layout

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7.0 CONDUCTED EMISSIONS TESTS (CE01 / CE03 / CE07)

The following conducted emissions measurements will be performed on the +28

volt lead to the payload and on the power return lead. The nominal power supply

voltage level shall be maintained at 28 volts.

During the narrowband conducted emissions tests, the payload shall be operated

in its mode that produces the highest levels of noise on the power leads. It may be

necessary to repeat the tests one or more times in order to verify the noise level

requirements or to more completely define conducted emission characteristics of

the HH avionics.

Conducted emissions produced by the CONCAP, STAR-LITE and UVSTAR

experiments will be measured. The test modes shall be determined by Code 568

in conjunction with the experiment representatives.

7.1 Narrowband Conducted Emissions Tests (CE01 / CE03)

Narrowband conducted emissions shall be measured on the supply and

return leads of the power conductors at frequencies between 30 Hz and 50

MHz. Acceptable emission levels are shown in Figure 7-1.

7.1.1 Payload Operational Mode

All Narrowband Conducted Emissions Test measurements shall be taken

between power and return lines of the HH avionics power port (J 001) and the

test batteries. The narrowband and broadband emissions tests shall be

conducted during the following operations modes:

A. Payload and HH GSE unpowered.

B. Payload unpowered, HH GSE powered. Only the minimum

amount of GSE required to operate the experiments will be

enabled.

C. Payload, CGSE and HH ACCESS powered.

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10 100 1k 10k 100k 1M 100M 100M

FREQUENCY (Hz)

dB µ

A

140

120

100

80

60

40

20

0

Payload Bay

Crew Compartment

Figure 7-1 Narrowband Conducted-Emission on Payload Power Leads

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7.2 Voltage Spikes on Power Lines Test (CE07)

Voltage spikes produced by the payload on the Orbiter power line shall be

within the limits defined by Figure 7-2. This includes turn-on / turn-off spikes

and payload switching. Rise and fall times shall be > 1.0 microseconds.

Voltage spikes across the power leads will be measured using a memory

oscilloscope with a bandwidth greater than 50 MHz. A triggered sweep rate of

approximately 20 nanoseconds will be required. Spikes produced by the

CONCAP, STAR-LITE and UVSTAR experiments will be measured.

This test shall be conducted with the simulated power source impedance

defined in Figure 7-3. A shuttle power line simulator with a schematic shown

in Figure 7-4 will be provided by the EMC test facility to meet this

requirement.

All CE07 test measurements shall be taken between the HH avionics power

port (J 001) and the test batteries. Voltage spikes will be measured during

the following scenarios:

A. STAR-LITE power on, K4

B. CONCAP power on, K5

C. UVSTAR power on, K6

D. UVSTAR power on, K7

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DURATION - SECONDS

DC

VO

LTA

GE

60

50

40

20

0

30

10

-10

1x10-6

10-5

10-4

10-3

10-2

100

101

10-1

Figure 7-2 Limits on Payload Produced Spikes (Line-to-Line) on DC Power Levels

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100 1K 10K 100K 1M 10M

FREQUENCY (HZ)

Z (

OH

MS

)

100

10

1.0

0.1

0.01

Figure 7-3 STS DC Power Line Impedance

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+

-

C1INPUT

POWER

L1 R1

R3

R4

L2 R2

Z TEST SAMPLE

R1, R2 = 0.25 ohm* R3, R4 = 25 ohm C1 L1, L2 = 4 µH

= 19,000 µF (75 V ELECTROLYTIC)

* Value of resistors may be reduced to 0.025 ohms or lower for hardware requiring high levels of power currents

Figure 7-4 Network Schematic for Orbiter Simulation of Impedance

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8.0 RADIATED EMISSIONS TESTS (RE02 / RE04)

Radiated emission test measurements are to be made using a Hewlett Packard

8566B equivalent spectrum analyzer to ensure proper measurements at high

frequency; specifically, radiated emissions in the S band notch shown in Figure 8-

1. It is presumed that the highest level of radiation will occur in the area of cable

entry into the HH avionics. Multiple antenna positions are to be used to capture all

potential payloads radiated emissions.

During the radiated emissions tests, the payload shall be operated in its mode that

produces the highest levels of noise on the power leads. It may be necessary to

repeat the tests one or more times in order to verify the noise level requirements or

to more completely define radiated emission characteristics of the HH avionics.

Radiated emissions produced by the STAR-LITE, UVSTAR and GAS experiments

will be measured. The test modes shall be determined by Code 568 in conjunction

with the experiment representatives.

8.1 Narrowband and Broadband Radiated Emission Measurements (RE02)

Narrowband and Broadband radiated emission measurements shall be made

from 14 kHz to 18 GHz, and performed in accordance with MIL-STD-462.

Acceptable limits are defined by the limit curves for payloads in Figures 8-1

and 8-2. This test meets the requirements set by ICD-2-19001.


The Narrowband and Broadband Radiated Emission Tests shall be run in

three sequences. The first sequence will be an ambient test; the GSE and

payload will be off. The second sequence will consist of the GSE on, payload

off. The third sequence will consist of the GSE and payload on. Acceptable

limits are defined by the limit curves in Figure 8-1 and 8-2.

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10k 100k 1M 10M 100M 1G 10G 100G

FREQUENCY (Hz)

Ele

ctric

Fie

ld In

tens

ity

(dB

µv/m

)

70

60

50

40

30

90

80

NOTCH FROM 1.77 GHZ TO 2.30 GHZ

NOTCH FROM 259.2 MHz TO 297.3 MHz

COMPOSITE PAYLOAD (PAYLOAD BAY)

INDIVIDUAL EQUIPMENT ITEMS

LOCATED IN CREW COMPARTMENT

14 kHz

18 GHz

14 kHz

18 GHz

Figure 8-1 Unintentional Radiated Narrowband Limits for Electric Field Emission

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120

110

100

90

80

70

60

dB µ

v/m

/MH

z

FREQUENCY (Hz)

10k 100k 1M 10M 100M 1G 10G 100G

18 GHz

14 kHz

14 kHz

18 GHz

NOTCH FROM 1.77 GHz TO 2.30 GHz

COMPOSITE PAYLOAD IN PAYLOAD BAY

INDIVIDUAL EQUIPMENT ITEM

S LOCATED IN CREW COM

PARTMENT

Figure 8-2 Unintentional Radiated Broadband Limits for Electric Field Emission

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8.2 Magnetic Field Radiated Emissions Measurements (RE04)

Magnetic field radiated emissions measurements shall be made in the range

of 30 Hz to 50 kHz in accordance with the test procedures of MIL-STD-462.

Acceptable limits are defined by the limit curve in Figure 8-3.


The Radiated Emission Tests shall be run in three sequences. The first

sequence will be an ambient test; the GSE and payload will be off. The

second sequence will consist of the GSE on, payload off. The third sequence

will consist of the GSE and payload on. Acceptable limits are defined by the

limit curve in Figure 8-3.

10 100 1k 10k 100k

FREQUENCY (Hz)

AC

MA

GN

ET

IC F

IELD

, dß

AB

OV

E 1

PIC

OT

ES

LA

140

120

100

80

60

20 Hz 2 kHz

50 kHz

Figure 8-3 Limits of Radiated AC Magnetic Field at 1 Meter from Orbiter Payload

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9.0 CONDUCTED SUSCEPTIBILITY TESTS (CS01 / CS02 / CS06 / HCP)

The payload shall be operated in the most noise sensitive modes during the

conducted susceptibility tests. It may be necessary to repeat the conducted

susceptibility tests one or more times in order to ensure the most noise-sensitive

measurement or to more completely define the conducted susceptibility

characteristics of the HH payload. The test modes shall be determined by Code

568 in conjunction with the CONCAP, SEH, SOLCON, STAR-LITE and UVSTAR

experiment representatives.

9.1 Power Line Conducted Susceptibility Tests (CS01 / CS02)

Inflight DC power bus ripple at the interface shall not exceed 0.9 volts peak-

to-peak narrowband (30 Hz to 7 kHz), falling 10 dB per decade to 0.28 volts

peak-to-peak at 70 kHz. Thereafter inflight DC power bus ripple at the

interface shall remain a constant 0.28 volts peak-to-peak at 70 kHz to 400

MHz.

The momentary coincidence of 2 or more signals at any one frequency shall

not exceed the envelope defined as 1.6 volts peak-to-peak (30 Hz to 7 kHz),

falling 10 dB per decade to 0.5 volts peak-to-peak at 70 kHz. Thereafter

momentary coincidence of 2 or more signals at any one frequency shall

remain a constant 0.5 volts peak-to-peak at 70 kHz to 400 MHz.

If a malfunction or degradation of performance is observed, the injected test

signal level shall be decreased in small increments to determine the payload’s

threshold of susceptibility.

The injected test signal shall be monitored on the test item side of the

coupling capacitor for the higher frequency ranges where the test signal is

applied through a coupling capacitor.


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During the Power Line Conducted Susceptibility Test, the payload shall be in

a fully operational mode. The GSE shall also be operational during this test.

Acceptable performance is defined as follows:

HH avionics: Avionics telemetry received at

ACCESS within nominal limits.

CONCAP: Telemetry received at CONCAP

CGSE within nominal limits.

Nominal limits shall be defined by

CONCAP Electrical Engineer.

SEH: Telemetry received at SEH CGSE

within nominal limits. Nominal limits

shall be defined by SEH Electrical

Engineer.

SOLCON: Telemetry received at SOLCON



SOLCON Electrical Engineer.

STAR-LITE: Telemetry received at STAR-LITE



STAR-LITE Electrical Engineer.

UVSTAR: Telemetry received at UVSTAR



UVSTAR Electrical Engineer.

PANSAT HESE: Ordnance (NSI’s) remain unfired.

(verified post test)

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9.2 Power Line Transient Test (CS06)

A transient signal shall be applied across the input power lines in accordance

with the procedures of MIL-STD-461C and 462. According to GEVS, the

applied test transient shall be equal to the power line voltage of 28 volts. The

resulting peak voltage of this transient will be +28 ±28 volts, i.e. +56 volts and

0 volts. However, since the payload (and all other STS payloads sharing the

power bus with IEH-3) can emit turn-on transients of +28 ±30 volts (ICD-2-

19001, 10.7.3.1), the peak voltage of this transient shall be +28 ±30 volts, i.e.

+58 volts and -2 volts. This will provide a 0 dB EMC margin.

The transient shall be applied with a pulse width of 10 micro-seconds at a

variable duty cycle (ICD-2-19001, Figure 7.3.7.2-1).

Due to the sensitive nature of the payload, this transient signal will be applied

in a ramping manner for both peak voltage and repetition rate. When

degraded performance is observed in CONCAP, SEH, SOLCON, STAR-LITE

or UVSTAR that experiment may be turned off while the remaining test

sequence continues. The decision to turn off an experiment or continue with

the test sequence will be made by the IEH-3 test conductor in conjunction

with the EMI Facility operator and the experiments Lead Electrical Engineers.

The test sequence is as follows. Increase the peak voltage offset from +28

volts in 6 increments of 5 volts i.e. ± 5, 10, 15, 20, 25 and 30. At each voltage

level, increase the pulse repetition rate in 6 steps of 10 pulses i.e. 10, 20, 30,

40, 50, and 60. Each pulse rate shall last one minute for a total of six minutes

per each voltage level polarity. Total test duration, excluding equipment or

test set-up and problem resolution, shall be 72 minutes.


During the Power Line Transient Test, the payload shall be in a fully

operational mode. The GSE shall also be operational during this test.

Acceptable performance is defined as follows:

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Engineer.















9.3 Power line Transients Caused by STS Hydraulic Circulation Pump (HCP)

There is a special test requirement to perform a conducted susceptibility

test to determine the payloads vulnerability to transients generated by

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the Orbiter HCP. The test signal to be applied across the power leads is

called out in GEVS 2.5.3.1a (see Figure 9-1), and is as follows:

Saw-toothed transient oscillation

4 volts peak-to-peak

Base frequency 500-700 Hz

Offset from +28 volts to produce +1.5 and -2.5 volt excursions

If a suitable offset cannot be achieved, a signal centered around 2volts

with a peak-to-peak value of 5 volts producing offsets of +/ - 2.5 volts may be

used.

-100 0 100 200 300

TR

AN

SIE

NT

VO

LTA

GE

LIM

ITS

(D

C V

OLT

S)

2.0

1.5

1.0

0.5

0

-0.5

-1.0

-1.5

-2.0

-2.5

-3.0

400 500

0.4v Composite Ripple

Interface Nominal Voltage

Spike Width 1 Millisecond

Figure 9-1 Transient Voltage on the Primary PL Bus Produced by Operation of the

Hydraulic Circulation Pump

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10.0 RADIATED SUSCEPTIBILITY TEST (RS03)

Radiated susceptibility tests shall be performed at each of the two antenna test

positions used for the radiated emission measurements. The power voltage shall

be maintained at 28 Volts.

During the radiated susceptibility tests, the payload shall be operated in its most

noise sensitive modes. It may be necessary to repeat the tests one or more times

in order to ensure the most noise sensitive measurement or to more completely

define radiated susceptibility characteristics of the HH payload. The test modes

shall be determined by Code 568 in conjunction with the CONCAP, SEH,

SOLCON, STAR-LITE and UVSTAR experiment representatives.

10.1 Susceptibility from Unintentional Orbiter Produced Emissions

The payload shall be tested to determine susceptibility to unintentional

Orbiter emissions. The test shall be performed in accordance with RS03.

The test signal antenna shall be located to simulate the configuration of the

Orbiter’s antenna with respect to the payload. The payload shall be tested to

the E-field specified in Figures 10-1 and 10-2 for narrowband and broadband

Orbiter emissions.


During the Susceptibility from Unintentional Orbiter Produced Emissions

Test, the payload shall be in a fully operational mode. The GSE shall also be

operational during this test. Acceptable performance is defined as follows:







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Engineer.















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32

dB µ

v/m

FREQUENCY (Hz)

10k 100k 1M 10M 100M 1G 10G

14.0 kHz

600.0 MHz

80

75

70

65

60

55

50

45

40

35

30

25

20

Figure 10-1 Orbiter Produced Radiated Narrowband Emissions

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FREQUENCY (Hz)

10k 100k 1M 10M 100M 1G 10G

14.0 kHz

300.0 MHz

dB µ

v/m

/MH

z

130

125

120

115

110

105

100

95

90

85

80

75

70

Figure 10-2 Orbiter Produced Radiated Broadband Emissions

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11.0 PRELIMINARY TEST RESULTS

During the EMI testing, Code 754 shall provide preliminary test data to the test

conductor. If during emissions testing, an exceedance occurs, additional testing

may be performed to isolate the cause of the exceedance. If during the

susceptibility testing, the avionics or the experiments do not perform within

nominal limits, additional testing may be performed to isolate the cause of the

anomaly.

12.0 RESPONSIBILITY ASSIGNMENTS

12.1 Responsibilities of Code 568

A. Preparation and setup of the test item.

B. Transportation and handling of the test items.

C. Provide cabling from the ground support equipment needed to

operate and monitor the test item during the test program.

D. Provide cabling from the ground support equipment to the test items.

1. One set of cables are needed with breakout box power leads in

order to apply current probes for conducted emission testing and to

insert a secondary transformer for conducted susceptibility testing.

2. One set of flight cabling is needed for radiated emission and

susceptibility testing.

E. Provide ground support equipment for control monitoring of test items.

F. Operation of instrument during testing.

G. Participation in Data Analysis.

H. Documentation of all malfunctions using GSFC malfunction report

system as defined in GMI-5310.1 All procedures and problems shall be

maintained in certification logs per GSFC-303-PROC-001.

12.2 Responsibility of EMC Test Group Code 754.2

A. Operation of EMC Test Equipment.

B. Conduct tests in accordance with test procedures and good MIL-STD-

461 / 462 test practices.

SSPP-PLAN-015

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C. Calibration of EMC Test Equipment.

D. Documentation of tests including Polaroid pictures (black & white) of the

test setups.

E. Generation of formal EMI test report; 2 duplexed copies to M. Wright

/568, within one month of test completion.

F. Provide Fairchild battery cart to power test items. Battery cart recharging

is required every evening throughout EMC testing.

12.3 Responsibility of Code 300 Flight Assurance Office

A. Verify EMI test equipment is in calibration.

B. Verify item under test configuration.

C. Witness test as required.