# Presentation: 531987

## Section 9

_***Section 9***_
***Subsystem Status***

## Attitude Control System

*** ******. . . Paul Sanneman***
*ACS Lead*

## Changes Since S/C Thermal Vacuum

***Changes Since S/C Thermal Vacuum***

***ACS Components***
***AST removed and X-rayed; subsequent removal/replacement of EMI Filter with additional clearance between part and PWB (1/00)***
*Debris found under EMI Filter and removed during repair*
***AST removed and opened for addition of stiffener on the lid of Interpoint DC/DC  converter (5/00); reintegrated in flight orientation (6/00)***
***Removed IRU to prevent helium exposure during MAP testing (2/00); re-integrated with upgraded purge (5/00)***
***ACE Software***
***ACE RSN SW update to A/D conversion implementation (3/00?)***
***ACE RSN SW update for IRAM2 checksum protection and removal of high rate event message (6/00)***

## Changes Since S/C Thermal Vacuum (continued)

***Changes Since S/C Thermal Vacuum ****(continued)*

***ACS Software***
***Ephemeris epoch time changes from MET to UT to improve navigation propagation accuracy (M5 clock drift) (12/99)***
***Modified Warm restart logic to ensure consistent recovery time (3/00)***
***ACS table parameters updated via STOL procedures (5/00)***
*Table 78 X-band Theta angle limit increase from 60 to 65 deg*
*Table 90 Disable autonomous re-entry into Delta-V mode*
*Table 53 Increase pitch attitude FDC count from 30 to 80 sec*
*Table 87 Adjust solar array FDC limits to avoid trips during normal slew maneuver operations*

## ACS Summary

***ACS Summary***

***Trending data to be collected using same procedure as T/V I***
***ACS trends from T/V I available for reference***
***IRU PDV has remained stable***
***RWA runup/rundown in vacuum to be measured***
***Open Problem Reports***
***468-20-4  IRU Parametric Drive Voltage***
***Star Tracker temperature trends to be monitored/controlled closely with thermal engineering as in T/V I***
***Thermal limits in database have been reviewed***
***Special ACS steps during T/V II have been coordinated***
***RWA Overspeed, AST TEC, ACE MTB Pwr Supply, GPS Ant feeds***

## IRU PDV Processed Trend

***IRU PDV Processed Trend***

## IRU PDV Data Trend

***IRU PDV Data Trend***

## ACS

***ACS***

***Coarse Sun Sensors 1, 2 and 3 remain in non-flight configuration of the SAD test bracket until after T/V II test***

***Attitude Control Subsystem is ready for T/V II test.***

## Attitude Control & Determination Subsystem (ACDS)

*** ******. . . Steve Schumacher***
*Swales ACDS Lead*

*** ******. . . Philip Luers***
*GSFC ACDS Lead*

## ACDS Readiness

***ACDS Readiness***

***ACDS hardware is in Final Flight Configuration***
***Hardware modification since last T/V test:***
***Stiffeners added to Interpoint power converters on ACE I/O and C&DH LVPC boards***
***Ceramic barrels on 1773 bulkhead connectors replaced with Phosphor-Bronze***
***Powered vibration (workmanship) performed on 1 axis***
***Re-integration was nominal***
***No Open Problem Reports***

## ACDS Plans

***ACDS Plans***

***Trending Plans (exactly like last T/V test)***
***4 voltages, 4 currents, 4 temperatures recorded every 5 minutes, graphed and analyzed for correlation with temperature***
***Confirm oscillator drift measurements made during last T/V test***
*Correlates spacecraft time adjustments with temperature*
***No work required before pump down***
***Critical limits in database confirmed***
***Procedures have been reviewed***

## Power

*** ******. . . Allan Billings***
*Power System Lead*

## Status of Flight Hardware/Software

***Status of Flight Hardware/Software***

***PSE in Final Configuration including Software***
***Changes since Thermal Vacuum***
*SOFTWARE: The new PSE version ( "8.00" ) was loaded, with the 8 wait states + modified A/D read routine. NO significant increases in the execution time of the control loop was observable, i.e, execution time = 1.6 msec. *
*SOFTWARE: All PSE RSN Commands verified*
*HARDWARE: LVPC switched service #9 abandoned due to damage caused by short during last thermal vacuum test. Added new thermal wiring and rerouted.*
*HARDWARE: Fuse plugs added to all PSE LVPC outputs (non-essential services)*

## Status of Flight Hardware/Software

***Status of Flight Hardware/Software***

***Battery---In Storage, Ready for Flight***
***Solar Array---After Integration of Solar Array to the Spacecraft, the Solar Array Will Be in Final Flight Configuration***
***Changes since last thermal vacuum***
*LAPSS Test performed on Array at Goddard at beginning of this year---Measured string current agreed with Tecstar values within 4%. Open circuit voltage of strings agreed with Tecstar values within 100mV. All string V/I curves were smooth.*

## Open Problem Reports

***Open Problem Reports***

***PR837-20-1 (RFA 33 4/12)***
***Anomaly---***
***PLVPCLDI2 telemetry went to FF (Maximum value) with no active spacecraft activity.**** PLVPCLDI2 reports the total load current magnitude for the PSE LVPC. FF would correspond to 19.275A. *
***This anomaly never occurred before and never happened again.***
***The anomaly lasted only for one sample.**** If this was a valid out of tolerance current indication, the pulse width lasted less than 533uS since the anomaly did not trip the LVPC over current protection circuit. *
***The spacecraft configuration was set to load the software into the housekeeping RSN.**** It is possible that something in this configuration contributed to this anomaly (unknown at this time). This configuration is a ground configuration and will not be used in flight.*

## Open Problem Reports

***Open Problem Reports***

***Investigations***
***Analyzed PSE LVPC timing**** as a possible source of the Anomaly. If one assumes worst case timing for all the individual IC’s we still have positive margin from the time the LVPC places data on the bus until the RSN reads the data. However the margin appeared to be less than adequate and the MAP ETU PSE LVPC was tested to measure actual (not theoretical) timing margin. The margin measured on MAP was adequate. *
***The spacecraft harness was examined**** by quality control (EO1-WOA-963) and found to pass visual inspection.*
***The FEDS data system was analyzed**** to determine if it was the source of the anomaly. The conclusion was that the telemetry (PLVPCLDI2)reported down from the spacecraft had FF. This was not a FEDS problem.*

## Open Problem Reports

***Open Problem Reports***

***Disposition***
***A fault tree analysis was performed**** as a result of RFA 4/12 and no credible source of the failure other than the spacecraft configuration was found. It is speculated that the spacecraft configuration may have been responsible and this configuration will not be used in flight.*
***If a similar (benign) anomaly is generated on orbit**** (PLVPCLDI2=FF for one sample) a red limit violation would occur and this would be observed in ground data. No other spacecraft consequences would accrue.*
***We will continue to monitor for this anomaly throughout all spacecraft testing.***

## Trending Plans/Critical Limits/Additional Work before Pump down 

***Trending Plans/Critical Limits/******Additional Work before Pump down ***

***Trending Plans***
***Trending requirements passed on to MOC***
***MOC is utilizing a heritage data collection and trending system from TRACE (DTAS) ***
***Trending procedures are currently being implemented. Completion expected soon after Thermal Vacuum Test.***
***Critical Limits***
***Critical Limits have been placed in ASIST work stations. All other limits undergoing thorough review.***
***Additional Work Before Thermal Vacuum***
***The test battery will be reconditioned before Thermal Vacuum***

## RF Communications

***. . . Bill Jupin / Pete Young / Ken Perko***
*EO-1 RF Comm Team*

## RF Communications

***RF Communications***

***Entire Subsystem in Final Flight Configuration***
***X-Band Hat Coupler repaired***
***No Open Problem Reports***
***Automatic Trending Script has been updated***
***No further work required before Pump Down***
***Helping with GPS GSE Configuration and Setup***
***Critical limits in the ASIST Database are being reviewed***
***Procedures almost identical to TVAC 1***
***Only remaining item to verify during TVAC 2***
***Must see X-Band Antenna Track and Dump Data to Various Ground Stations During Orbits.  Want to Witness Entire Process During TVAC (ACS commanding, Phase Shifters Changing State in Antenna, RF Activation, etc).***

## Wideband Advanced Recorder Processor (WARP)

*** ******. . . Terry Smith***
*WARP Lead Engineer*

## Status

***Status***

***Hardware is in its final flight configuration***
***Software is in its final flight configuration***
***There are no open problem reports***
***No work is required before pump down***

## Changes Since Last Thermal Vacuum Test

***Changes Since Last Thermal Vacuum Test***

***A voltage reference part failed (open) on the WARP LVPC on 1/4/00***
***The failure produced a high voltage within the LVPC***
***Numerous parts were over-stressed***
***The entire LVPC piggyback card was replaced***
***The WARP successfully completed an extensive re-qualification program***
***The WARP was operated over 400 hours prior to re-integration on the S/C***

## Trending Plans

***Trending Plans***

***The following parameters will be monitored each day:***
***Mode of operation***
***Primary input power voltage***
***All secondary voltages***
***The temperature of the front and back of every card***
***RF Exciter Power Output***

## Critical Limits & Procedures

***Critical Limits & Procedures***

***The Processor Card Mongoose V Temperature sometimes reaches the yellow limit during the hot plateau***
***The heater mode procedure must be run prior to a memory card cold start.  If the WARP fails to power up the memory cards, no harm is done.  ***

## Flight Software

*** ******. . . Ray Whitley***
*EO-1 Flight Software Systems Manager*

## Flight Software Readiness

***Flight Software Readiness***

***No T/V II Concerns/Liens***
***There are no know leans against or issues with the flight software at this time.  (What a difference 7 months makes!)***
*Code Walk-throughs have been conducted for the HSK and X-Band RSNs since TV-I*
*Code 300 ran code analyzer s/w against most of EO-1’s FSW with very positive results*
*FSW testbed has been re-located to GSFC from Swales & an ACE ETU fabrication is in progress*
*Thanks to Tom Feild & Emory Stagmer, all TSMs & RTSs are incorporated and tested at the spacecraft*
*ESN A/D converter wait state timing issues understood & resolved (compliments of MAP h/w and s/w engineers).   EO-1 fix installed and tested*
*1773 Bus Controller s/w hardened against possible failure mode*

## Flight Software Readiness

***Flight Software Readiness***

***No T/V II Concerns/Liens***
***There are no open software PTRs that require software change in any of the flight processors.  EO-1 PTRs generated over the last year have been analyzed for severity, and the results indicate a very positive trend toward zero(0) make-play changes.***
***PTRs have been cross-checked against the MAP problem database***
***There are no open PARs/PRs in the S/C I&T database that require software change in any of the flight processors ***

## Flight Software Readiness

***Flight Software Readiness***

***Have Been Ready To Go for Several Months***

## Reaction Control System

*** ******. . . Mike McCullough***
*RCS Lead Engineer*

## Reaction Control System

***Reaction Control System***

***Configuration for Test***
***Pressurized to 40 PSIG w/ GN******2 ******(Long Term Leak Check)***
***Enable Plug Test Set (EPTS) Installed***
*Thrusters Valves Will Not Be Actuated*
***Components & Functions to be Tested***
***Thruster Drive Voltage Recorded on Strip Chard via EPTS***
***Catalyst Bed Heaters Enabled via EPTS***
***Thermal Control Heaters (Primary & Redundant)***
***Pressure Transducer & Temperature Telemetry***
***Latch Valve Function (Part of CPT5)***

## Reaction Control System

***Reaction Control System***

***Additional Testing for T/V II***
***RCS Secondary Heaters Will Be Exercised ***
*Primary Heaters Function & Sizing Verified During T/V I*
*Secondary Heaters Will Control System 12-18C*
***No Open Problem Records***
***RCS is ready for Thermal Vacuum testing***

## Mechanical

*** ******. . . Pete Alea***
*Mechanical Systems Engineer*

## Satellite 

**Satellite **
**Support Stand**

## EO-1 Satellite Test Configuration

**EO-1 Satellite Test Configuration**

- Chamber 225

## Chamber Configuration

**Chamber Configuration**

**Chamber 225**

**Satellite Test Stand**

## Test Readiness

***Two open problem records - WOA 1028, Event 50 & 80***
***Insufficient gas flow rate from purge cart to support both IRU and SI***
***Purge cart modifications in progress to replace regulator and flow meter to provide increase flow rate.  MIT/LL has approved required changes***
***Test fixture and support hardware has been completed and is ready to support T/V test***
***Satellite handling procedures ready and WOA is in place***
***There are no outstanding mechanical PRs or liens against the S/C which may delay testing***

## Global Positioning System

*** ******. . . David Quinn***
*GPS Lead*

## Global Positioning System

***Global Positioning System***

***Entire Subsystem in Final Flight Configuration***
***Stiffener ‘hat’ added to PCU Interpoint DC/DC Converter***
***1-axis Vibration***
***Successfully Reintegrated into S/C ***
***Ground System Command Interfaces Online***
***RF GSE Upgraded from TVAC-1***
***Hat Coupler Gaps Reduced***
***Noisy RG-142 RF Cables Removed***
***Rooftop Antenna Relocated***
***Low Noise Belden 9913 Cable Runs - Reduced in Length Over TVAC-1***
***No Open Problem Reports***
***Temperature Trends to be Monitored as Part of TVAC-2***
***RF GSE Testing Required Before Pump Down***
***Limits Reviewed Prior to TVAC-1 - Valid and Unchanged. ***
***Procedures Almost Identical to TVAC-1***
***More Attention Given to Signal Levels From All Four Antennas ***

## TVAC II Setup