# Presentation: 692673

## Section 6

_***Section 6***_
***Chamber / Facilities Status***

*** ******. . . Ray Trunzo***
*EO-1 Thermal Engineer*

## Agenda

***Agenda***

***Chamber #225***
***Test Equipment***
***T/V EGSE Layout***
***Status of Documentation***
***T/V #2 Preparation Flow***

## Chamber #225

***Chamber #225***

## Test Equipment

***Test Equipment***

***Control Panel #1, designated Bay #1 Cryo-panel, will provide a radiative sink temperature simulation for the ALI FPA radiator.  The ALI FPA radiator is approximately 24" x 27".  This cryo-panel size is 36" x 36" & shall be positioned vertically within 5 inches of the ALI FPA radiator.  The temperature of the panel shall be independently controllable from -110************C to +90************C using a GN2 (or LN2) TCU. (ALI FPA Cryo-panel to be capable of controlling FPA radiator to -73°C (200K) during the entire TV test including hot & cold temperature plateaus).  The S/C viewing side of the panel shall have a coating with an emittance of no less than 0.85 & the chamber viewing side of the panel shall be covered with aluminized Kapton.***
***Control Panel #2, designated ALI FPE cryo-panel, will provide a radiative sink temperature simulation for the ALI FPE radiator.  The radiator size is approximately 7" x 7".  This panel size is 12" x 12" & shall be positioned vertically within 5 inches of the ALI top radiator.  The temperature of the panel shall be independently controllable from -110************C to +90************C using a GN2 (or LN2) TCU.  (ALI FPE heater plate shall be capable of controlling FPE to within its qualification temperature range of -20°C to + 40°C during the entire TV test including hot & cold temperature plateaus).  The ALI FPE viewing side of the panel shall have a coating with an emittance of no less than 0.85.***

## Test Equipment (CONTINUED)

***Test Equipment ******(CONTINUED)***

***Control Panel #3, designated ALI heater-panel, will provide a radiative sink temperature simulation for the S/C Nadir (+Z) facing components.  The panel size is approximately 22" x 22".  This panel shall be positioned horizontally within 12 inches of the ALI aperture Door Motor.  The temperature of the panel shall be independently controllable from -50************C to +90************C using the chamber shroud & heaters.  The S/C viewing side of the panel shall have a coating with an emittance of no less than 0.85.***
***Control Panel #4, designated HSA heater-panel, will provide a radiative sink temperature simulation for Hyperion HSA Nadir (+Z) facing components.  The panel size is approximately 18" x 30".  This panel shall be positioned horizontally within 8 inches of the HSA Door Motor Cover.  The temperature of the panel shall be independently controllable from -50************C to +90************C using the chamber shroud & heaters.  The S/C viewing side of the panel shall have a coating with an emittance of no less than 0.85.***
***Control Panel #5, designated Atmospheric Corrector (AC) heater-panel, will provide a radiative sink temperature simulation for AC Nadir (+Z) facing components.  The panel size is approximately 12" x 16".  This panel shall be positioned horizontally within 6 inches of the X-Band Antenna (w/Hat Coupler).  The temperature of the panel shall be independently controllable from -50************C to +90************C using the chamber shroud & heaters.  The S/C viewing side of the panel shall have a coating with an emittance of no less than 0.85.***

## Test Equipment (CONTINUED)

***Test Equipment ******(CONTINUED)***

***Zero-Q heaters will be used on spacecraft-to-support stand interfaces to minimize conductive heat flow from the S/C to the support stand.  They will be controlled by thermocouple temperature data.  The control set point will be determined based on the ************T measured by thermocouples across the interface.  The stand heaters can also be used to help speed up hot transitions.  The support structure as much as possible is to be covered in MLI.***
***Two Thermoelectric Quartz Crystal Microbalances (TQCMs) shall be located directed by the contamination control engineer (with lead thermal engineer’s approval)***
***Four Scavenger Plates will be required.  Two plates will be placed near the bottom of the S/C & closed out to it with MLI blanketing to trap outgassing from the interior. A third plate will be placed above the S/C to the side with a shroud of clear Kapton to direct venting of the ALI, to protect the instrument from cross contamination, & to isolate TQCM measurements.  The fourth scavenger plate will be placed above the S/C to the side with a shroud of clear Kapton to direct venting from the interior of Hyperion, protect the instrument from cross contamination, & to isolate TCQM measurements.  It shall be operate at the chamber shroud temperature of –90 °C.***

## Test Equipment (CONTINUED)

***Test Equipment ******(CONTINUED)***

***A cold finger shall be operated for at least eight (8) consecutive hours at the end of the final thermal vacuum hot soak. Once the test is completed, the cold finger shall be handled in accordance with ASTM-E-834-81 ************Determining Vacuum Chamber Environment Using a Cold Finger************.***
***A Residual Gas Analyzer (RGA)***
***Chamber pressure and temperature indication shall be provided.  This data shall be continuously recorded autonomously by the Data Acquisition System or strip chart recorder.  Plots of these parameters shall be made available upon request.***

## T/V EGSE Layout

***T/V EGSE Layout***

## T/V EGSE Layout (CONTINUED)

***T/V EGSE Layout ******(CONTINUED)***

## T/V EGSE Layout (CONTINUED)

## Status of Documentation

***Status of Documentation***

***SAI-PLAN-412  EO-1 Spacecraft T/V Test #2 Plan***
***In signoff***
***SAI-PROC-867  EO-1 Spacecraft T/V and T/B Test #2 Procedure***
***Profile complete (N. Speciale)***
***Test Script complete***
***Procedure out for first review***

## T/V II Preparation Flow

## Slide 13

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