####### SIT Thermal Balance Test Plan {#sit-thermal-balance-test-plan .unnumbered}

APPROVED BY:

J. Hawk Date

Thermal Engineer

Lillian Reichenthal Date

STEREO Instrument Manager

David Curtis Date

IMPACT Instrument Manager

Peter Wapole Date

SIT Lead Engineer

#### TABLE OF CONTENTS  {#table-of-contents .unnumbered}

ACRONYMS AND ABBREVIATIONS [4](#acronyms-and-abbreviations)

APPLICABLE DOCUMENTS [5](#applicable-documents)

1.0 INTRODUCTION [5](#introduction)

2.0 TEST OBJECTIVES [5](#test-objectives)

3.0 SUCCESS CRITERIA [5](#success-criteria)

4.0 DESCRIPTION OF TEST HARDWARE [6](#description-of-test-hardware)

4.1 TEST ARTICLE [6](#test-article)

4.2 GSE [6](#gse)

4.2.1 Cryoplate / Heater Plate [7](#cryoplate-heater-plate)

4.2.2 Test Heaters [7](#test-heaters)

5.0 TEST TEAM [7](#test-team)

6.0 TEST PROGRAM [8](#test-program)

6.1 FACILITY DESCRIPTION [8](#facility-description)

6.2 TEST CONFIGURATION [8](#test-configuration)

6.3 TEST SET-UP RESPONSIBILITY [8](#test-set-up-responsibility)

6.4 INSTRUMENTATION [9](#instrumentation)

6.5 TEMPERATURE LIMITS [9](#temperature-limits)

6.6 TEMPERATURE CONTROL [9](#temperature-control)

6.8 CONTAMINATION/ELECTROSTATIC REQUIREMENTS
[10](#contaminationelectrostatic-requirements)

6.8.1 Contamination [10](#contamination)

6.8.2 Electrostatic [10](#electrostatic)

6.9 TEST DESCRIPTION [10](#test-description)

6.9.1 Pre-Test Activities [10](#pre-test-activities)

6.9.2 Test Readiness Review [10](#test-readiness-review)

6.9.3 Pre-Test Check List [11](#pre-test-check-list)

6.9.4 Instrumentation Check [11](#instrumentation-check)

6.9.5 Temperature Rate of Change [11](#temperature-rate-of-change)

6.9.6 Thermal Stabilization Criteria
[11](#thermal-stabilization-criteria)

6.9.7 Test Description [12](#test-description-1)

[Thermal Balance]{.underline} [12](#thermal-balance)

7.0 DOCUMENTATION [14](#documentation)

7.1 CHANGES TO TEST PROCEDURE [14](#changes-to-test-procedure)

7.1.1 During Test [14](#during-test)

7.1.2 Post-Test [14](#post-test)

7.2 TEST DATA [14](#test-data)

7.3 TEST LOG BOOK [14](#test-log-book)

7.4 TEST REPORT [14](#test-report)

7.5 TEST FAILURE AND ANOMALY REPORTS
[15](#test-failure-and-anomaly-reports)

7.5.1 Test Failure Criteria [15](#test-failure-criteria)

7.5.2 Failure Reports [15](#failure-reports)

8.0 QUALITY ASSURANCE [15](#quality-assurance)

9.0 SAFETY [15](#safety)

10.0 TECHNICAL PHOTOGRAPHY [15](#technical-photography)

# ACRONYMS AND ABBREVIATIONS {#acronyms-and-abbreviations .unnumbered}

GSE Ground Support Equipment

GSFC Goddard Space Flight Center

ICD Interface Control Document

I/F Interface

IMPACT In-situ Measurements of Particles and CME Transients

MLI Multi-Layer Insulation

MGSE Mechanical Ground Support Equipment

MHz Megahertz

PRT Platinum Resistance Thermometer

QCM Quartz Crystal Microbalance

RGA Residual Gas Analyzer

S/C Spacecraft

SEPT Solar Electron Proton Telescope

SIT Suprathermal Ion Telescope

STEREO Solar Terrestrial Relations Observatory

TB Thermal Balance

TCU Thermal Control Unit

TD Test Director

TE Test Engineer

T/C Thermocouple

T/M Thermistor

TTC Thermal Test Conductor

TV Thermal Vacuum (cycling)

TVTE Thermal Vacuum Test Engineer

# APPLICABLE DOCUMENTS {#applicable-documents .unnumbered}

-   STEREO Environment Definition, Observatory, Component and Instrument
    Test Requirements Document.

-   STEREO Contamination Control Plan.

-   IMPACT Environmental Test Plan

-   IMPACT Contamination Control Plan

# 1.0 INTRODUCTION {#introduction .unnumbered}

> This document establishes the test conditions, requirements, and
> procedures for the IMPACT Instrument SIT thermal balance test. This
> test will complete the Instrument level thermal balance requirement
> for SIT. The thermal balance test articles will include SIT Ahead
> (FM1). Figure 1 shows the thermal balance test set-up.

# 2.0 TEST OBJECTIVES {#test-objectives .unnumbered}

The primary objectives of this test are to:

1)  Validate the thermal design by subjecting the instruments to thermal
    test environments that conservatively simulate the flight hot and
    cold environments.

[]{.mark}

2)  Gather steady state data in order to correlate the thermal models.

3)  Confirm the thermal interface between the instruments and spacecraft
    via mounting standoffs and cabling.

[]{.mark}

4)  Verify that survival heaters perform as specified. That they
    maintain the hardware within survival limits in the simulated worst
    case flight conditions.

[]{.mark}

5)  Verify that the operational heaters perform as specified. That they
    maintain the hardware within operational limits in the simulated
    worst case flight conditions.

# 3.0 SUCCESS CRITERIA {#success-criteria .unnumbered}

The following compliance matrix illustrates how the Test Objectives will
be achieved during the test:

  ----------------------------------- -----------------------------------
  **Objective**                       **Compliance Criteria**

  Validate the thermal design         Subject the instrument to test
                                      environments outlined in Table 1
                                      that conservatively simulate the
                                      flight hot and cold environments
                                      and verify that all temperatures
                                      are within limits with margin.

  Gather steady state data in order   Thermal Balance to the stability
  to correlate the thermal models.    criteria stated in this test plan
                                      must be achieved at hot and cold
                                      environment conditions and data is
                                      gathered.

  Confirm the thermal interfaces      Temperature gradients across the
  between the instruments and         interfaces should be within 3^o^C
  spacecraft via mounting standoffs   agreement between the test results
  and cabling                         and correlated thermal model.

  Verify that survival heaters        The survival heaters keep all
  perform as specified (100% duty     instrument components above Cold
  cycle at 25V). That they maintain   Survival temperature limits at the
  the hardware within survival limits Cold Survival test environment
  in the simulated worst case flight  settings outlined in Table 1. All
  conditions.                         thermostatically controlled heater
                                      circuits should be tested for
                                      proper function.

  Verify that the operational heaters The operational heaters keep all
  perform as specified (75% duty      instrument components above Cold
  cycle at 30.5V). That they maintain Operational temperature limits at
  the hardware within operational     the Cold Operational test
  limits in the simulated worst case  environment settings outlined in
  flight conditions.                  Table 1. All thermostatically
                                      controlled heater circuits should
                                      be tested for proper function.
  ----------------------------------- -----------------------------------

# 4.0 DESCRIPTION OF TEST HARDWARE {#description-of-test-hardware .unnumbered}

The test hardware consists of the test article and ground support
equipment (GSE). The test article is the flight hardware being tested
including instrument components and test blankets, isolators and
cabling. GSE is any hardware in support of the test but exclusive of the
test article. GSE includes the chamber and its control system,
cryopanel, interface plate, instrument mounted test heaters,
thermocouples, interface cabling, TQCMs, and the thermal data
acquisition system.

## 4.1 TEST ARTICLE {#test-article .unnumbered}

The TB test articles shown in Figure 1 consist of the Ahead SIT (FM1)
electronics, HVPS, and telescope. The electronics box is mounted to the
interface plate using the flight isolators. Flight-like MLI will be
installed in the flight configuration. Radiator surfaces on SIT will be
silver Teflon. Ground straps between the test article and the interface
plate will be configured as flight-like as possible. Flight cables will
be routed and secured to the interface plate as flight-like as possible.
The cables that, in flight, run along the spacecraft deck to other
electronics boxes will be coiled up and attached to the interface plate
under an MLI blanket. GSE cables will run from the flight cables to the
chamber feed-thru connecter and to external GSE.

Flight cables will be coiled up and attached to the interface plate.

## 4.2 GSE {#gse .unnumbered}

The Goddard supplied GSE will include a cryoplate with a hard mounted
interface plate and a heater panel. Project supplied GSE will include
Test article mounted test heaters and any stimulii needed for functional
testing. The functions of the GSE components are described below:

### Cryoplate / Heater Plate

The cryoplate and interface plate to which the test articles mount
simulates the Spacecraft mounting interface in TB, and will be
temperature controlled to values shown in Table 1. The cryoplate must be
controllable and stable to within 2°C of its setpoint. The S/C interface
needs to be controlled between --18°C and +45°C for TB. The cryoplate
will carry an interface plate which will be drilled to mount the test
articles. The S/C interface plate will need an MLI blanket on top for
TB, facing the test article as the spacecraft would be blanketed. The
backside of the heater plate should be blanketed for TB to help isolate
it from the LN2 flooded shroud.

The heater plate will simulate solar heating from the Sun and will be
temperature controlled to values shown in Table 1. The heater plate will
be mounted to the interface plate with thermal isolation and the panel
will have an MLI blanket on the side facing away from the test article.
The power delivered to the heater plate needs to be controllable from
zero to maximum power.

### Test Heaters

Hardware mounted test heaters will be used for TB testing. The heaters
will be used to protect the flight hardware from the cold shroud during
TB in the event of a loss of instrument power or heater plate failure.
The collimator heaters are used to simulate absorbed solar flux. They
will be placed in locations shown in figures 4-5 and will be sized to
provide a maximum of five Watts. Heaters shall be supplied by the
Project, but installation on the test article and wiring to GSE
harnesses shall be done at GSFC.

# 5.0 TEST TEAM {#test-team .unnumbered}

The following personnel or their designated representatives will be
associated with these tests:

Test Directors - John Hawk

Thermal Test Conductor - Amil Mann

> Thermal Vacuum Test Engineer - Mario Martins

Contamination Engineer - Therese Errigo

Product Assurance Engineer - Larry Gibb

**Note**: Additional personnel will provide support as required.

The Test Director (TD) has the overall responsibility for managing the
test. The TD approves all test plans and procedures and has the
responsibility of determining the Instrument is in flight configuration.
The Test Director or a representative is responsible for approving all
major deviations to the test procedure. The TD is also responsible for
assuring all objectives of the thermal test will be satisfied. The TD
will assure that fixtures and all components of the Test Article(s) are
supplied and properly integrated for the test.

The Thermal Test Conductor (TTC) is responsible for coordinating TV Test
Environmental activities. The TTC monitors the thermal test during
actual operation and verifies that all systems are acting correctly and
all test activities are executed. The TTC is responsible for detecting
any out-of-limit temperature conditions of the test components and
taking the necessary steps to correct that condition. The TTC is also
responsible to determine when steady state conditions are achieved to
continue to the next set point or to conclude the test. The TTC shall
have the responsibility to adjust the test condition temperatures based
on test data.

The Thermal Vacuum Test Engineer (TVTE) is responsible for the
verification of the cleanliness of the chamber, fixtures and cables
prior to the initiation of the test. The Thermal Vacuum Test Engineer
also serves as the interface between the Thermal Test Conductor and the
facility operators. The Thermal Vacuum Test Engineer is responsible for
the operation, monitoring and maintenance of the test facility and
auxiliary systems such as fixtures, cold plates, conditioners, etc.

The Contamination Control Engineer is responsible for assuring that the
test is performed in accordance with proper contamination requirements.
This person is also responsible for monitoring the contamination data to
assure that the chamber, fixtures, meet the established contamination
criteria.

The Product Assurance Engineer (PAE) responsibilities are contained in
Section 8.0.

# 6.0 TEST PROGRAM {#test-program .unnumbered}

## 6.1 FACILITY DESCRIPTION {#facility-description .unnumbered}

The thermal balance test will be conducted in a Thermal Vacuum Facility
at GSFC. The thermal shroud within the chamber can be controlled to
temperatures between -180°C (LN2) and +75°C. The facility must be
capable of maintaining the pressure below 5x10^-6^ Torr for this test.
The facility including all GSE internal to the chamber must meet the
following contamination criteria prior to the start of the test:
(300Hz/hr \@100°C on a --20°C Quartz Crystal Microbalance (QCM)). The
facility has the capability to read out (94) test thermocouple sensors.

## TEST CONFIGURATION

The test set-up for the test is shown in Figure 1. The test article
mounts to an interface plate which is hard mounted to a cryoplate and
uses the chamber shroud as the radiative environment. A heater plate is
used to simulate the solar flux upon the Instrument during TB. Test
heaters mounted to the test article(s) will be used for instrument
safety in TB.

## 6.3 TEST SET-UP RESPONSIBILITY {#test-set-up-responsibility .unnumbered}

The Project will provide all materials and equipment pertaining to
operation of the test article including wiring harnesses and ground
support equipment. The Project will provide all feed through connector
plates and electrical harnessing.

[]{.mark}

GSFC Code (545) will provide T/Cs with associated signal conditioning
and recording equipment including computer monitors to display T/C data
in tabular and "real time" plotted format. The project will provide the
EGSE and personnel required to operate and monitor the test article
during powered operation (functional testing).

## 6.4 INSTRUMENTATION {#instrumentation .unnumbered}

There are numerous thermocouple temperature sensors on the test article
and GSE that need to be read out continuously during this test. There
are 23 T/Cs on the test article during TB as listed in Table 2 and shown
in Figure 2.

The test article is equipped with flight thermistor temperature sensors
which are read out by the EGSE, some of which may not be available when
the test article is powered off. A list of all T/M temperature sensors
is included in Table 3.

Test T/Cs can only be mounted on the external surfaces of the
Instruments. Internal component temperatures (with their own test
limits) can only be monitored by the flight telemetry electronics. Test
T/C temperatures will be continuously monitored during the test, but the
red and yellow temperature limits should only be used as a rough
estimate as to internal component temperatures. There could be up to a
15^O^C difference between internal component temperatures and external
thermocouple readings, due to poor heat transfer paths.

6.4.1 Test T/Cs on GSE

There should be two T/Cs placed on the interface plate. The heater panel
should have six T/Cs. GSE T/C temperature sensors are included in Table
2. Detailed locations of the temperature sensors are shown in Figure 2.
The facility shroud should already be equipped with temperature sensors.

## 6.5 TEMPERATURE LIMITS {#temperature-limits .unnumbered}

The temperature limits on the hardware are contained in Tables 2 and 3.
Thermocouple limits are shown in Table 2. Internal component
(thermistor) temperature limits are shown in Table 3 but must be
monitored by flight telemetry electronics and not by test thermocouple
instrumentation.

## 6.6 TEMPERATURE CONTROL {#temperature-control .unnumbered}

The test article mounted T/Cs will be used to determine the test
articles temperature stability. The chamber shroud, platen, heater panel
and test heaters will be used to adjust environmental conditions.
Internal component (thermistor) temperatures shall be monitored as well,
but will use the flight telemetry electronics circuitry.

## 6.8 CONTAMINATION/ELECTROSTATIC REQUIREMENTS  {#contaminationelectrostatic-requirements .unnumbered}

The test article is contamination and Electro-Static Discharge (ESD)
sensitive in the test configuration and the following shall be adhered
to at all times:

### 6.8.1 Contamination {#contamination .unnumbered}

The test article will be double bagged for transportation to the TV
facility. All test fixtures and instrumentation/harnessing will be
cleaned by Contamination Control (CC) prior to use in the TV facility.
Cleanroom uniforms are required during use and handling of hardware
inside the TV facility. A log will be kept to record personnel entering
and exiting the chamber.

The facility must meet the following contamination criteria prior to the
start of the test: (300Hz/hr \@100°C on a --20°C Quartz Crystal
Microbalance (QCM)).

[]{.mark}

One 15 Mhz TQCM shall be placed viewing, and within 3 feet of the test
article. The Contamination Engineer shall verify that TQCMs are properly
placed prior to closing the chamber door. The TQCMs shall be held at -20
C throughout the test, with the exception of the TQCM bake out periods.
The data will be used for evaluation of the cleanliness of the test
article.

[]{.mark}

A bakeout will be performed at the beginning of each phase of the TB
test and will last 12 hours. A bakeout will be performed at the
beginning of the TV test, and will last the duration specified by the
contamination engineer.

### 6.8.2 Electrostatic {#electrostatic .unnumbered}

The test article is ESD sensitive in the test configuration and proper
grounding of the hardware and personnel is required.

## 6.9 TEST DESCRIPTION {#test-description .unnumbered}

### 6.9.1 Pre-Test Activities  {#pre-test-activities .unnumbered}

Pre-operation activities include attaching thermocouples and installing
MLI blanketing on the Instruments. Mount the Instruments and heater
plates to the interface plate and install the assembly in the chamber.

### 6.9.2 Test Readiness Review  {#test-readiness-review .unnumbered}

A test readiness review (TRR) will be conducted prior to the test and
attended by personnel involved in the test. The test procedure and any
other pertinent documentation will be reviewed and discussed to resolve
any problems or discrepancies with regards to safety, test
configuration, facility requirements, and test operations. The test
procedure must be approved prior to the test. An \"as run\" test
procedure will be generated during the test by the TD or designated
representative. Deviations to the test procedure during the test shall
be recorded as red lines to the original procedures and will be approved
by either the TD or designated representative and quality assurance
engineer prior to performing the deviation.

### 6.9.3 Pre-Test Check List  {#pre-test-check-list .unnumbered}

The following is a list of steps required before testing occurs.

1.  Drill holes in the S/C simulator interface plate to the appropriate
    drawings.

2.  Clean interface plate.

3.  Clean and apply ITO Agfep to the SIT Instrument per drawings.

4.  Assemble and fit check heater panel.

5.  Certify cleanliness of chamber with all possible GSE installed.

6.  Test fit SIT Ahead to the interface plate in the TB configuration
    using the flight isolators. Four (4) isolators for SIT Instrument
    isolators will be supplied by the Project.

7.  Install all test T/Cs on the SIT Ahead per Table 2 and Figures 2.

8.  Install two T/Cs onto the top of the interface plate and six T/Cs
    onto the heater panel per Table 2 and Figure 2.

9.  Install and wire the test heaters to the SIT Ahead per Figures 4-5.

10. Attach ground strap to interface plate.

11. Coil flight cables and attach to interface plate.

12. Install MLI blanket to the top of the interface plate and feed
    ground strap and flight cable connecter through access holes in MLI.

13. Mount SIT Ahead to the interface plate in TB configuration using the
    flight isolators. SIT Instrument isolators (4) will be supplied by
    the Project.

14. Attach ground strap to SIT Ahead.

15. Attach proper flight cable connecters to instrument.

16. Install the heater plate with test article and its harnesses into
    the chamber and make all electrical and plumbing connections.

17. Perform functional tests on the heaters and T/Cs to verify nominal
    installation.

18. Perform ambient functional tests on the Instrument to verify nominal
    installation.

19. Close the Chamber

### 6.9.4 Instrumentation Check {#instrumentation-check .unnumbered}

Prior to testing, the test facility will be checked out and verified to
be ready for testing. Installation and checkout of the required
instrumentation will be conducted on the test article prior to closing
the TV chamber door.

### 6.9.5 Temperature Rate of Change {#temperature-rate-of-change .unnumbered}

The chamber shroud shall not exceed a rate of change of 5°C/min. The
bulk Instrument temperature shall not exceed a rate of change of more
than 3°C/min. The SIT Telescope bulk instrument temperature shall not
exceed a rate of change of more than 0.1°C/min when its temperature
reaches 30°C during transition to hot survival TV soak.

### Thermal Stabilization Criteria

Environmental stability will be reached when the Chamber and heater
plates are within 2°C of its setpoint.

Test Article stability for Thermal Balance will be reached when the T/Cs
come to equilibrium at \< (0.1°C/hr) change for at least (1) hours.

### Test Description 

**NOTE: Any functional testing with HVs being turned on requires a
chamber pressure at or below 5.0E-6 torr prior to the HV being turned
on. Perform only limited HV tests if the pressure is any greater than
5.0E-6 torr.**

### [Thermal Balance]{.underline} {#thermal-balance .unnumbered}

Phase

Bakeout

1.  Once the chamber pressure is lower than 5x10^-6^ torr, verify the
    test article is powered off, bring the cryoplate to 45°C at a rate
    not to exceed 5°C/min.

2.  Turn on the test heaters and adjust their power levels to help raise
    the test articles to the Bakeout soak goal temperatures per Table 5
    (45^o^C on the SIT Ebox and 32^o^C on SIT Telescope) at a rate not
    to exceed 3°C/min without surpassing any Survival red temperature
    limits. The SIT Telescope bulk instrument temperature shall not
    exceed a rate of change of more than 0.1°C/min when its temperature
    reaches 30°C during transition to hot survival TV soak.

3.  The shroud is to be transitioned to approximately 30°C but must
    always be 5°C colder than the coldest temperature on the test
    article.

4.  When the soak critera has been met (temperature within 3°C of soak
    goal and rate of change less than 1 °C/hour) declare start of
    Bakeout Soak and take appropriate data snaps.

5.  The Bakeout begins once soak criteria has been met and will not
    conclude until the Contamination Engineer is satisfied that the
    bakeout criteria has been met.

6.  When the Contamination Engineer is satisfied the soak requirements
    have met, declare end of Bakeout Soak and take appropriate data
    snaps.

Cold Survival Balance

7.  When bakeout is completed enable all survival heaters at 25V, bring
    the shroud to LN2 temperature and the cryoplate to -18°C and heater
    plate to 10°C at a rate not to exceed 5°C/min. The shroud is to stay
    flooded for the duration of the Thermal Balance test.

8.  Reduce power to the test heaters to achieve an acceptable transition
    rate on the test article not to exceed 3°C/min.

9.  Transition test article to the survival heater turn-on temperature
    (-26.1°C specified) at the fastest rate not to exceed 3°C/min. Power
    can be applied to the heater plate if necessary to maintain
    transition rate within limits.

10. When leading temperature on test article reaches -16°C(10° from
    heater turn-on) Set the collimator heaters to the Cold Survival
    settings in Table 1. Confirm that test article transition rate
    responds by rolling off to verify the ability to safely stop the
    transition.

11. Decrease survival heater voltage until thermostatically controlled
    heaters operate at 100% duty cycle. Requirement is that survival
    heaters can maintain the instrument within survival limits at 25V
    (IMPACT ICD).

12. Let the balance control T/Cs on the test article come to equilibrium
    at \< 0.1°C/hr change for 1 hour. Soak for four hours after this
    criterion is met. Keep the cryos (shroud and coldplate) within 2
    degrees of their setpoints and the heater plate at the proper
    settings.

13. Take appropriate data snaps. Record survival heater voltage and
    current.

Cold Operational Heater Verification

14. Increase survival heater voltage to 35V (max).

15. Bring the cryoplate to -13°C at a rate not to exceed 5°C/min.

16. Verify that all test environment settings are correct per Table 1
    (Cold Operational ).

17. When all test article temperatures are within operational limits,
    simultaneously turn-on the instrument at 30.5V, enable the
    operational heaters at 30.5V and disable the survival heaters. Do
    not further adjust operational voltage. Verify operational heaters
    are capable of maintaining temperatures within limits Requirement is
    that operational heaters have a 75% duty cycle at 30.5V.

Hot Operational Balance

18. Power the test article on at 35V (max).

19. Bring the cryoplate to +45°C at a rate not to exceed 5°C/min.

20. Set the heater plate and SIT Sunshade test heater powers to the Hot
    Operational settings in Table 1. Verify that all test environment
    settings are correct per Table 1 (Hot Operational).

21. Do not change heater plate or test heater settings unless necessary
    to avoid exceeding any operational red limits on the test article.
    Record any change from those specified.in Table 1.

22. Let the balance control T/Cs on the test article come to equilibrium
    at \< 0.1°C/hr change for 1 hour. Soak for four hours after this
    criterion is met. Keep the cryos (shroud and coldplate) within 2
    degrees of their setpoints and the heater plate at correct
    temperature setting.

23. Take appropriate data snaps. Record operational bus voltage and
    current.

Return to Ambient

24. Keep the test article powered on at 35V.

25. Bring cryos (shroud and cryoplate) to +22°C and reduce test heaters
    to zero power at rates not to exceed 5°C/min on GSE or 3°C/min on
    the test article.

26. Shut down test article when all GSE are at ambient (+22°C), test
    heaters are at zero power and the instrument is at 32°C.

27. Shut off all electronics inside chamber and secure all cryos.

28. Start coldfinger 8 hours before beginning backfill.

29. Once the temperatures are below 28^O^C begin to backfill the chamber
    with dry nitrogen

30. Turn off Cold Finger at 100 Torr

31. Backfill the chamber to 600 torr. **Nitrogen backfilling must occur
    at a reduced rate so not to cause air turbulence near the
    Instrument. Backfill very slowly for the first 20 minutes.
    Backfilling must take at least 90 minutes. Nitrogen must be filtered
    through a 0.5-micron filter before it enters the chamber.**

# 7.0 DOCUMENTATION  {#documentation .unnumbered}

## 7.1 CHANGES TO TEST PROCEDURE {#changes-to-test-procedure .unnumbered}

### 7.1.1 During Test {#during-test .unnumbered}

Deviations to the test procedure during the test shall be recorded in
the chronological test log and approved by both the TD and the PAE prior
to performing the deviation. The deviation number shall be recorded at
the affected line of the "as run" procedure. Procedure errors recorded
during the test shall be incorporated in the test plan prior to testing
subsequent items.

### 7.1.2 Post-Test {#post-test .unnumbered}

Changes that result from either design changes or discrepancies shall be
incorporated as a subsequent revision to the test plan. Other changes
shall be processed as deviations or waivers.

## TEST DATA

The test data will be recorded as required documenting Instrument
performance during testing. Test data and "as run" procedures will be
kept in the test logbook and submitted to the TD by the test engineers
upon completion of the test.

## 7.3 TEST LOG BOOK {#test-log-book .unnumbered}

A chronological log will be kept by the Test Engineer throughout the
testing program. The logbook will contain a copy of the test plans. The
Test Engineer will make daily entries in a brief manner describing the
days testing activities. In addition, the log will record the operating
times of the test as well as significant events such as failures,
damage, or photo records.

[]{.mark}

The thermal test conductor shall also maintain a log.

## 7.4 TEST REPORT {#test-report .unnumbered}

Following completion of the test, a report shall be written in order to
document the results of the tests, including a discussion of data with
conclusions and/or recommendation. The original shall be submitted the
Project within thirty working days after test completion. The Test
Engineer will submit the test report.

## 7.5 TEST FAILURE AND ANOMALY REPORTS {#test-failure-and-anomaly-reports .unnumbered}

### 7.5.1 Test Failure Criteria {#test-failure-criteria .unnumbered}

Either of the following constitutes a failure of the test:

[]{.mark}

1.  Unacceptable operation of the test article during the time that the
    test is being conducted

[]{.mark}

2.  No data is recorded due to failure of the instrumentation or
    recording equipment

### 7.5.2 Failure Reports {#failure-reports .unnumbered}

Malfunction or failure that requires corrective action or re-testing
will result in a Failure Report.

# 8.0 QUALITY ASSURANCE {#quality-assurance .unnumbered}

The performance of this plan will be under the cognizance of the
assigned Product Assurance Engineer (PAE) or a designated
representative. The PAE will verify that the test article is ready for
the test by:

[]{.mark}

1.  Verifying the presence of an approved test procedure

2.  Verifying completion and documentation of all Instrument assemblies
    and inspection operations.

3.  Verifying that all support fixtures are within current proof load
    limits.

4.  Visual inspection of the test article and the test set-up for
    correct configuration and handling/safety constraints.

5.  Verify that the assembly of the test article is per the design.

# 9.0 SAFETY {#safety .unnumbered}

This test shall be conducted in accordance with the GSFC standards of
Safety and Engineering Services Division Safety Manual Rev A, with no
unacceptable risks or hazards to the test article and personnel.

[]{.mark}

Test directors must assure that the test complies with all Occupational
Safety and Health Act (OSHA) regulations and that protective equipment
is used where necessary.

# 10.0 TECHNICAL PHOTOGRAPHY {#technical-photography .unnumbered}

Photographic services will be provided by Code 545. The TD shall arrange
appropriate times to take photographs before closing the TV chamber. The
purpose for using technical photographs is to document the test set-up
and to record any relevant data taken during the test. The test set-up
photographs should capture the test article, instrumentation, and test
equipment. Discrepancies and unusual data should also be photographed.

+---------------+--------+--------------+--------------+--------------+
| **ZONE**      | **Bak  | **Hot        | **Cold       | **Cold       |
|               | eout** | Operation**  | Operation**  | Survival**   |
+---------------+--------+--------------+--------------+--------------+
| Chamber       | +30°C  | -180°C       | -180°C       | -180°C       |
| Shroud        |        |              |              |              |
+---------------+--------+--------------+--------------+--------------+
| Platen        | +45°C  | +45°C        | -13°C        | -18°C        |
+---------------+--------+--------------+--------------+--------------+
| Heater Plate  | +30°C  | +80°C        | +10°C        | +10°C        |
+---------------+--------+--------------+--------------+--------------+
| A_SIT         | As     | Safety Only  | Safety Only  | Safety Only  |
| Telescope     | Needed |              |              |              |
| Heater \#     |        |              |              |              |
+---------------+--------+--------------+--------------+--------------+
| A_SIT EBOX    | As     | Safety Only  | Safety Only  | Safety Only  |
| Heater        | Needed |              |              |              |
|               |        |              |              |              |
| Heater \#     |        |              |              |              |
+---------------+--------+--------------+--------------+--------------+
| A_SIT         | As     | 1.56W        | 1.21W        | 1.21W        |
| Collimator    | Needed |              |              |              |
| Heater \#     |        |              |              |              |
+---------------+--------+--------------+--------------+--------------+
| A_SIT         | As     | 0.35W        | 0.29W        | 0.29W        |
| Collimator    | Needed |              |              |              |
| Heater \#     |        |              |              |              |
+---------------+--------+--------------+--------------+--------------+
| A_SIT         | As     | 0.35W        | 0.29W        | 0.29W        |
| Collimator    | Needed |              |              |              |
| Heater \#     |        |              |              |              |
+---------------+--------+--------------+--------------+--------------+

Table 1: TB Test Environment Settings

+----+-----------------------------+---+------+------+------+------+
| T  | Location                    | F | Ye   | Red  | Ye   | Red  |
| /C |                             | i | llow | Li   | llow | Li   |
|    |                             | g | Li   | mits | Li   | mits |
| \# |                             | \ | mits |      | mits |      |
|    |                             | # |      | (°C) |      | (°C) |
|    |                             |   | (°C) |      | (°C) |      |
+----+-----------------------------+---+------+------+------+------+
|    |                             |   | Ope  |      | Surv |      |
|    |                             |   | rati |      | ival |      |
|    |                             |   | onal |      |      |      |
+----+-----------------------------+---+------+------+------+------+
| 1  | Front of SIT EBOX Ahead     |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 2  | Front of HVPS Ahead         |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 3  | Right Side of SIT EBOX      |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 4  | Right Side of HVPS Ahead    |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 5  | Right Side of SIT Telescope |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 6  | Top of SIT Telescope Ahead  |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 7  | Top Front of SIT Telescope  |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 8  | Top of SIT Collimator Ahead |   | -70  | -75  | -70  | -75  |
|    |                             |   | /+65 | /+70 | /+65 | /+70 |
+----+-----------------------------+---+------+------+------+------+
| 9  | Right Side SIT Collimator   |   | -70  | -75  | -70  | -75  |
|    | Ahead                       |   | /+65 | /+70 | /+65 | /+70 |
+----+-----------------------------+---+------+------+------+------+
| 10 | Front of SIT Telescope      |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 11 | Top of SIT Telescope Ahead  |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 12 | Back of SIT Telescope Ahead |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 13 | Left Side of SIT Telescope  |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 14 | Left Side of HVPS Ahead     |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 15 | Left Side of SIT Telescope  |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 16 | Front of SIT Telescope      |   | -30  | -35  | -35  | -45  |
|    | Ahead                       |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 17 | Back of SIT Telescope Ahead |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+32 | /+35 | /+32 | /+35 |
+----+-----------------------------+---+------+------+------+------+
| 18 | Back of HVPS Ahead          |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 19 | Back of SIT EBOX Ahead      |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 20 | Bottom of SIT EBOX Ahead    |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 21 | Bottom of SIT EBOX Ahead    |   | -30  | -35  | -35  | -45  |
|    |                             |   | /+45 | /+50 | /+50 | /+55 |
+----+-----------------------------+---+------+------+------+------+
| 22 | Under SIT Collimator        |   | -70  | -75  | -70  | -75  |
|    | exterior Ahead              |   | /+65 | /+70 | /+65 | /+70 |
+----+-----------------------------+---+------+------+------+------+
| 23 | Right Side SIT Collimator   |   | -70  | -75  | -70  | -75  |
|    | Ahead                       |   | /+65 | /+70 | /+65 | /+70 |
+----+-----------------------------+---+------+------+------+------+
|    | Heater Plate                |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Heater Plate                |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Heater Plate                | 1 | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Heater Plate                | 1 | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Heater Plate                |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Heater Plate                | 1 | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Mounting Plate              | 1 | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Mounting Plate              | 1 | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Front of Target             |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | Back of Target              |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    | ZeroQ Heater                |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    |                             |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    |                             |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+
|    |                             |   | N/A  | N/A  | N/A  | N/A  |
+----+-----------------------------+---+------+------+------+------+

Table 2: TB Thermocouple Locations

+-----+--------------+------+--------+------+--------+------+------+
| T/M | Location     | Fl   | Opera  | Ope  | Su     | Surv | Mon  |
| Sen |              | ight | tional | rati | rvival | ival | itor |
| sor |              |      | Yellow | onal | Yellow |      |      |
| No. |              | A    | Limit  |      | Limit  | Red  |      |
|     |              | llow |        | Red  |        | L    |      |
|     |              | able | (°C)   | L    | (°C)   | imit |      |
|     |              |      |        | imit |        |      |      |
|     |              | (°C) |        |      |        | (°C) |      |
|     |              |      |        | (°C) |        |      |      |
+-----+--------------+------+--------+------+--------+------+------+
| S1  | SIT A        | -25  | -      | -35  | -      | -45  | S/C  |
|     | motherboard  | /+40 | 30/+45 | /+50 | 35/+50 | /+55 |      |
+-----+--------------+------+--------+------+--------+------+------+
| S2  | SIT A        | -25  | -      | -35  | -      | -45  | In   |
|     | Digital TOF  | /+40 | 30/+45 | /+50 | 35/+50 | /+55 | stru |
|     |              |      |        |      |        |      | ment |
+-----+--------------+------+--------+------+--------+------+------+
| S3  | SIT A        | -25  | -      | -35  | -      | -45  | In   |
|     | telescope,   | /+30 | 30/+32 | /+35 | 40/+32 | /+35 | stru |
|     | inside front |      |        |      |        |      | ment |
+-----+--------------+------+--------+------+--------+------+------+
| S4  | SIT A        | -25  | -      | -35  | -      | -45  | In   |
|     | telescope,   | /+30 | 30/+32 | /+35 | 40/+32 | /+35 | stru |
|     | inside rear  |      |        |      |        |      | ment |
+-----+--------------+------+--------+------+--------+------+------+

Table 3: Internal Component Telemetry (Flight Thermistors)

+------------------------+------------------+-------+-----------------+
| Location               | Heater Circuit   | Size  | Max Power       |
|                        |                  | (i    | (watts)         |
|                        |                  | n^2^) |                 |
+------------------------+------------------+-------+-----------------+
| AHEAD SIT Telescope    |                  | 4     | 12              |
| Heater#                |                  |       |                 |
+------------------------+------------------+-------+-----------------+
| AHEAD SIT EBOX         |                  | 4     | 12              |
|                        |                  |       |                 |
| Heater \#              |                  |       |                 |
+------------------------+------------------+-------+-----------------+
| AHEAD SIT Collimator   |                  | 1     | 3               |
| Heater \#              |                  |       |                 |
+------------------------+------------------+-------+-----------------+
| AHEAD SIT Collimator   |                  | 1     | 3               |
| Heater \#              |                  |       |                 |
+------------------------+------------------+-------+-----------------+
| AHEAD SIT Collimator   |                  | 1     | 3               |
| Heater \#              |                  |       |                 |
+------------------------+------------------+-------+-----------------+

Table 4: Test Heater Maximum Power Table

![](media/image1.png){width="5.010416666666667in"
height="5.114583333333333in"}

Figure 1 SIT TB Test Set-up

![](media/image2.png){width="5.999305555555556in"
height="4.891666666666667in"}

Figure 2: SIT TB T/C Locations

1 = Stabilize, Soak 1Hour and Test Concurrently.

2 = Stabilize, Turn On, Soak 1Hour and Test Concurrently.

![](media/image3.png){width="5.995833333333334in"
height="3.9722222222222223in"} Figure 3: SIT Thermal Balance Test
Temperature Profile

![](media/image4.png)

Figure 4: SIT AHEAD Test Heaters/Thermal Control Surfaces

![](media/image5.png){width="5.957638888888889in"
height="3.042361111111111in"}

Figure 5: SIT AHEAD Test Heaters/Thermal Control Surfaces