# Presentation: 476250

## Test & Evaluation(T&E)Overview

## T&E Overview

***T&E Overview***

***Facilities***
***Safety***
***T&E Flow***

## EGSE Layout in the Clean Tents at GSFC

***EGSE Layout in the Clean Tents at GSFC***

## T&E Facilities

***T&E Facilities***

***Clean Tents:******	******SPOT Tents #1 and #3***
***Acoustics:******	******Acoustics Chamber, Bldg. 10***
***Vibration:******	******Test Cell 036, Bldg. 7***
***EMI/EMC:******	******Large EMI/EMC facility (first floor of Bldg. 7)***
***Thermal-Vacuum:******	******Thermal-Vac Chamber 238***
***Office Space:******	******Bldg. 7, Rm. 188***
***No conflicts exist with facilities usage at this time ***

## EGSE Configuration Requirements at GSFC

***EGSE Configuration Requirements at GSFC***

**C (Data Flow)**

**GN2**

**Purge**

**Cart**

**UPS**

**S-RF**

**RACK**

**UMBIL**

**Console**

**X-RF**

**RACK**

**BATT**

**GSE1**

**APTS**

**ASIST**

**PWS**

**ASIST**

**AWS**

**PDU**

**BATT**

**GSE2**

**UPS**

**A/C**

**UNIT**

**ALI**

**SBX**

**ACDS**

**WARP**

**BERB**

**BATT**

**Hyper**

**AC**

**Skin**

**Conn**

**/CSS**

**/Star**

**Stim**

**DDS**

**Cmd**

**CIU**

**Bit**

**Sync**

**I&T FEDS**

- Purge Line

- S-Band

- Hat Coupler CMD/TLM RF

- TLM Hardline

- X-Band

- RF Hat Coupler

- Cool Air Duct

- Ethernet

- Stimulus & Monitor Signals

- CMD Hardline

- 400 Vac

**ASIST**

**AWS**

**ASIST**

**AWS**

**ASIST**

**AWS**

**Bus**

**Monitor**

- 1773 Mon/VSat

- 110 Vac to EGSE racks

**MOC FEDS**

**    ****(DPS)**

**LZP**

**HDF files**

***AMPEX**

**WB TR**

**ALI**

**EGSE 1**

- Ethernet

- 52.5 Mb I/Q Real Time

**EO-1**

**Spacecraft**

**208 3**

****

** ****Vac**

***Required Near S/C***

***S/C Operations Area***

- May 24, 1999

- EGSEsetp2a.doc

**Roof GPS**

**Antenna**

- <150 feet

**  **

**HUB**

**T1 to EO-1 MOC**

**Laser**

**Printer**

**Event**

**Printer**

**PSE**

- DPC/SAS Pwr/Monitor

- APTS PC

- S/W Load

- Composite I&Q P/B

- 105 Mb composite

-  W/Strip Chart

- * TLM

- * CMD

-  *TLM

-  *CMD

- Patch

- Panel I/F

- Local Link only

- 110 Vac

- *RS422  TRI-AX

- Ethernet

- Voice

- Lines

- Head

- Sets

- Head

- Sets

**HUB**

- HUB

- Located with I&T OPS

- provided by GSFC MOC

- RS422

- REC

- Playback

**APTS**

**PC 1**

**GSFC MOC**

***ALI and Hyperion Data Lines***

- Ethernet

- S-Band 2Mbps

- WARP files ftp

**ASIST**

**AWS**

**ASIST**

**AWS**

*HYP/AC*

*ACS*

*PWR*

*Therm*

*ALI*

*ELEC*

*COMM*

*Systems*

- X-Term

*TC*

- Ethernet

**Hyperion**

**PC**

- PC

**PROP**

**Monitor**

- Intelligent

- Bridge

**HUB**

**ASIST**

**W/S**

**ASIST**

**W/S**

**ASIST**

**W/S**

**MOC**

**FEDS**

**Data Lines to Wallops**

**and/or tracking**

**stations**

- *Portable

- Links required

- between facilities

- Ethernet

**GPS**

## T&E Communication Requirements

***T&E Communication Requirements***

***T1 line to clean tents (from MOC)***
***Ethernet connections to each facility from clean tents***
***RS-422 Tri-Ax (via fiber optic lines) to each facility from clean tents ***
***VDS/SCAMA circuits between clean tents, each facility, and MOC***
***Bldg. 7 internal Telex system between clean tents and each facility***
***Bldg. 7 internal CCTV system at Acoustics and Vibration***
***Administrative LAN (Engineering LAN) at clean tents and in office***
***These items are completed or being worked***

## GSFC Safety

***GSFC Safety***

***All hazardous items have been identified and resolved ***
*Mechanical*
*S/C lifting procedure complete*
*MGSE analysis/testing complete*
*RF*
*S-band and X-band RF systems analysis complete.  Approved for operation at GSFC*
*Pyro (Boeing)*
*Test procedure reviewed by GSFC Safety*
*Pyro delivery and storage coordinated with GSFC Safety*

## I&T Activities at GSFC Prior to Environmental Test

***Unpack, setup (EGSE & S/C), power up and run aliveness test***
***Remove CCR panel 4 and reintegrate PSE to new CCR panel***
***Remove panel 1, mount WARP and reintegrate WARP to S/C***
***Mount and integrate Atmospheric Corrector***
***Mount and integrate X-Band Phased Array (XPAA)***
***Mount and integrate 2 S-Band omni antennas***
***Verify ALI and AC science data flow through WARP***
***Receive and integrate AST (star tracker)***
***Complete LFSA electrical integration and deploy***
***Close out liens against ACDS integration***
***Load and test updated M5 S/W***
***Remove S/A and re-integrate Hyperion STM***
***Install S/A and complete Bay closeout***
***Move S/C to Mass Properties***

## Top Level Test Flow at GSFC

***START FLOW AT GSFC***
*1) **	**Receive, unpack, and inspect.  Move GSE and spacecraft to predetermined locations,*
*2) **	**Move S/C and EGSE to Building 7 Clean Tent (CT) area,*
*3) **	**Setup GSE and spacecraft in CT and perform reintegration and functional tests,*
*4)**	**Move to Building 15 and perform 1st Mass properties with the Hyperion STM, *
*5)**	**Move to VIB and perform 3-axes sine sweep at protoflight levels (functional tests before and aliveness tests between axis) and clamp band pyro shock test, *
*6)**	**Move to CT, *
*7)**	**Solar array release,*

*8)**	**Alignment measurement,*
*9)**	**Post-Vib Functional test,  *
*10)**	**Remove solar array,*
*11)**	**Setup and perform RF Compatibility test,*
*12)**	**Receive Hyperion in CT and conduct Instrument off-line test,*
*13)**	**Integrate the flight Hyperion Instrument and perform alignment measurement,*
*14)**	**Run 2nd CPT & MOC Sims with flight Hyperion Instrument,*
*15)**	**Install S/A,*
*16)**	**Move to Bldg 15 and perform 2nd mass properties with the flight Hyperion instrument,*
*17)**	**Move to Acoustic and conduct acoustic test and 2nd pyro shock test,  run Functional,*

## Top Level Test Flow at GSFC

*18)**	**Move to CT, conduct S/A Pop & Catch,*
*19)**	**Remove S/A and perform compressed functional,*
*20)**	**Move to EMC facility and perform EMI/EMC,*
*21)**	**Move to T/V Chamber and setup for T/B,*
*22)**	**Perform thermal balance test, *
*23)**	**Break vacuum and setup for T/V and Radiometric test,*
*24)**	**Perform thermal vacuum (CPT and MOC Sims),*
*25)**	**Perform Radiometric Test in vacuum,*
*26)**	**Post T/V functional test (ambient) *

*27)**	**Move to CT and conduct a post environmental 3rd CPT & MOC Sims,*
*28)**	**Mount S/C on Ransom Table and move to stable floor area,*
*29)**	**Conduct Focal Plane End to End Test at Ambient*
*30)**	**Move to CT and perform Alignment Measurement, *
*31)**	**Closeout S/C bays and reinstall S/A,*
*32)**	**Pack and prepare for shipment to the Launch Site.  *
***END FLOW AT GSFC***

## Environmental Test Summary(with Hyperion STM)

***Mass Properties ***
***Vibration (3-axis sine sweep)***
***Clamp Band Pyro Shock***
***S/C RF Compatibility Test with Tracking stations (RF Test Van)***

## Environmental Test Summary(with Flight Hyperion)

***Baseline CPT***
***Acoustic Test***
***Clamp Band Pyro Shock***
***Satellite EMI/EMC***
***Thermal Balance***
***Thermal Vac (4 cycles)***
***Post Environmental CPT***
***Ambient Focal Plane End-to-End Test***
***Post Environmental Alignment Measurement***

## Environmental Test

***Supporting Documents***
*EO-1 I&T Plan (SAI-PLAN-130)*
*EO-1 Verification Plan & Environmental Specification (SAI-SPEC-158) *
*EO-1 Satellite GSFC Environmental Facilities Requirements Doc (SAI-SPEC-684)*
***Environmental Test Plans***
*EO-1 Satellite Mass Properties Test Plan (SAI-PLAN-319)*
*EO-1 Satellite Structural Vibration Test Plan (SAI-PLAN-307)*
*EO-1 Satellite Acoustics Test Plan (SAI-PLAN-320)*
*EO-1 EMI/EMC Test Plan (SAI-PLAN-322)*
*EO-1 S/C Thermal Vacuum and Thermal Balance Test Plan (SAI-PLAN-273)*
*End-to-End Imaging Test (SAI-PLAN-321)*

## EO-1 Daily I&T Schedule

## Slide 15

## Slide 16

## Slide 17

## Slide 18

## Slide 19

## Slide 20

## Slide 21

## Slide 22

## Mission Operations Control (MOC)

## MOC Status & Plans

***MOC Status & Plans***

***MOC is in building 14 room N285***
*1 Front End Data System (FEDS) and 2 ASIST workstations*
*Other FEDS loaned to I&T*
*1 Mission Operations Planning and Scheduling System (MOPSS)/Flight Dynamics Support System (FDSS)*
*3 PC’s for X-terminals, FDSS and VirtualSat support*
*2 PC’s for Mongoose simulator and Spacecraft Emergency Response System (SERS)*
*12 X-Terminals*
*Expect to get additional 3-6 ASIST workstations by June 30 *
***Software***
*ASIST 7.1in MOC, ASIST 7.2 launch release due July*
*FEDS 7.0 in MOC, FEDS 8.0 launch release due July*
*MOPSS 3.0 in MOC, launch release is MOPSS 4.0*
*FDSS 4.0, FDSS 5.0 launch release due July*
*DPS 1.0, DPS 2.0 launch release due end of June*

## MOC Status & Plans

***MOC Status & Plans***

***Tests***
*Mission Readiness Test T1, Basic command and telemetry completed 4/99*
*Mission Readiness Test T2, FDSS-MOPSS-CMS-ASIST-Mongoose board completed 4/99*
*Mission Readiness Test T3, FDSS-MOPSS-CMS-ASIST-S/C-Hyperion/AC/ALI-WARP-DPS-TRW/Lincoln Lab/D. Reuter, Science Data Flow, partially completed 5/99 during 1st CPT*
*Plan to run complete test during the second CPT*
*Mission Readiness Test T4, RF Compatibility, planned for last week in June*
*Mission Readiness Test T5, Ground stations and networks test**	*
*Wallops to FEDS IP interface test on open network completed 4/99*
*Wallops command loop back test on open network completed 5/99*
*Tracking test using COBE using open network completed 5/99*
*Interface with S/N for telemetry flow completed 4/99*
*SAFS test - not completed*
*Planning and scheduling test with WOTIS completed 4/99*
*Complete integrated T5 test using closed side of network scheduled for end of June*
*T6 MOC - WTR interface still to be run*
*T7 fully integrated end-to-end*
*Y2K end-to-end still to be run*

## MOC Status & Plans

***MOC Status & Plans***

***Plans for 2nd CPT 2***
*Run portions of 2nd CPT out of  MOC- CPT 1 and CPT 11; agreements still to be finalized*
***1st Launch Simulation July 12 after 2nd CPT***
*Completed 3rd cut of mission sequence*
*Completed 1st cut of top level mission script*
*Working on selecting necessary procedures and ascertaining whether they are:*
*Total reuse*
*Modified*
*New*
*Assessing work required to get to Sim*

## Flight Assurance

*** ******Nick Virmani***
***EO-1 Lead Quality Assurance***
***Swales Aerospace***

## Quality Program Objectives

***Provide support in the implementation of NMD/EO1 GSFC-426-EO1 mission assurance requirements***
***Quality program places major emphasis on the prevention of defects and provides insight and control through all phases of the program i.e., manufacturing, integration, environmental testing and launch***
***Quality program is based on Integrated Product Teams (IPT) consisting of the system and subsystem engineers, and QA which includes Nick Virmani, De Hinton, Art Martinez (Swales), Mike Kelly, Larry Moore, Brenda Parkinson (GSFC Code 300), and Carl Powell (Unisys)***
***Quality program assures that quality requirements are determined and specified throughout all phases of the program***

## Quality Program Objectives (CONTINUED)

***Since the start of the EO1 program, Swales was audited by GSFC, and ISO 9000 auditors***
***We successfully met the requirements of GSFC and ISO 9000 audit and now Swales is qualified to ISO 9000***
***Awareness and Training: All employees involved in hardware fabrication, integration and testing are trained to NHB5300.4(3L) ESD requirement, clean room requirement, and other related training***
***Quality program assures that all products and equipment will meet the requirements specified by our customers through the appropriate controlled documents and procedures***
***The controls and documentation include: Reviews, Incoming/Receiving Acceptance of Hardware, Test Plans and Procedures, Work Order Authorization (WOA), Problem Records (PR), Problem Action Report (PAR), Logs, Closed Work Orders, Test Reports, etc.***

## Quality Program Objectives (CONTINUED)

***All work performed prior to I&T was performed on Cert Log and discrepancies were documented and closed on problem record/MRB***
***Prior to spacecraft integration all cert logs were reviewed and problem records were closed***
***All work done on the spacecraft integration is performed on Work Order Authorization (WOA). WOA are generated and controlled by a computer system and must be approved by I&T Managers, System Lead, and Quality Assurance.***
***WOA system is a Microsoft Access database which will be used until the spacecraft is launched***
***Problem records are also generated using WOA system. WOA cannot be closed with open PRs***

## Quality Program Objectives (CONTINUED)

***QA functions on the WOA are: Signature of approval on the WOA to perform the work/test, Maintain WOA status, Sign-off on WOA closeout, Maintain the WOA problem record status. This system is a closed loop system.***
***Visibility and access to WOA system is available to the customer for their input and comments***
***QA IPT team will continue to support environmental testing***
*at GSFC:*
*Nick Virmani / Art Martinez / Brenda Parkinson - 1st Shift*
*Carl Powell / Nick Virmani / De Hinton - 2nd Shift*
*De Hinton / Nick Virmani / Carl Powell - 3rd Shift (if required)*

## Quality Program Objectives (CONTINUED)

*at Launch:*
*Nick Virmani - 1st shift*
*Carl Powell - 2nd shift*
*Extended shift support will be provided when required.*
*Mike Kelly/Brenda Parkinson will also be available for support during environmental testing and at launch if required.*
***Discuss Problem Action Report Status***
*Dual Payload Attach Fitting (DPAF):**	**	**	**gapping issue - closed*
*Carbon Carbon Radiator (CCR):**	**	**panel damage being investigated*

## Contamination

*** ******Dave Hughes***
***EO-1 Contamination Control Lead***
***Swales Aerospace***

## Agenda

***Requirements Summary***
***Transportation / Testing***
***Thermal Vacuum/Bakeout***

## Requirements Summary

***Visibly Clean Sensitive, Level B***
***Instruments Require GN2 Purge***
*Near continuous purge (1 hr interruption per 24 hours)*
*Grade B Nitrogen*
*10 scfh *
***Instrument Apertures Closed:***
*Class 100,000 Cleanroom*
*Smock, Bouffant Cap, Shoe Covers, Gloves, Beard Cover, Wrist Strap*
***Instrument Apertures Open:***
*Class 10,000 Cleanroom*
*Coverall, Hood, Booties, Gloves, Face Mask, Wrist Strap*

## Transportation / Testing

***Transportation Controls***
*Double bag EO1*
*Purge instruments*
***Testing Controls***
*Double bag if outside clean tent*
*Cut access panels in bags for accelerometers, etc*
*Purge instruments*

## Thermal Vacuum /Bakeout

- Pump

- ALI

***Thermal Vacuum /******Bakeout***

***Chamber 238***
***Operate as Class 100,000 Clean Tent***
***3 Scavenger Plates***
***Outgassing from interior trapped by mylar shield and 1 scavenger plate***
***ALI interior protected from cross contamination by mylar shield and 1 scavenger plate***
***3 QCMs required to measure outgassing sources***

## System Testing forEarth Observer 1

*** ******Mark Perry***
***EO-1 Lead Systems Engineer***
***Swales Aerospace***

## Agenda

***System Testing Topics***
***Overview of System Tests***
***Details of Aliveness Test***
***Development of the EO-1 CPT***
***Details of Functional Test***
***EO-1 CPT Design***
*CPT Sections*
*Highlights of the First CPT*
*Overview of Successful Tests from the First CPT*
*Omissions During the First CPT*
*Problems During Execution*
***Problems during Execution***
***Status of System-Level Testing***
***Objectives of First CPT***
***Summary***

## System Testing Topics

***Description of system tests***
***Detailed description of comprehensive performance test***
***Results of first comprehensive performance test***
***Plans for system testing through launch***

## Overview of System Tests

***Aliveness***
*Verifies that each subsystem and payload operates, including basic functionality; mechanical motion, (configuration or life time limited)*
*Used when system configuration or time limitations prevents a full functional test *
*Quick verification of satellite health after a move*
*After each axis of vibration*
*Prior to acoustics test*
*During launch countdown and during countdown simulations*
***Functional***
*Verify every interface, command, telemetry point, and function*
*Uses EGSE as stimulus and to test systems more fully than aliveness test*
*Performed after vibration and acoustic tests, and on the LV*

## Overview of System Tests (CONTINUED)

***Comprehensive Performance Test (CPT)***
*Measures performance of each subsystem, and EO-1 as a system*
*Dry-run of the CPT performed at Swales in May; baseline in July*
*Three other CPTs: during thermal-vacuum test, after environmental tests, and at the launch site*
***Special tests. These tests need special support equipment, or are conducted only a single time. Some FDC tests are special tests. ***
*Some examples of special tests*
*RCS high-pressure test (tank has limited permissible high-pressure cycles)*
*High/low-voltage test (single-time verification of function)*
*Exhaustive command permutation test (not necessary every CPT)*
*1773 SEU test (requires special GSE)*
*Inserted into the schedule when procedures and equipment available*

## Details of Aliveness Test

***Every component, subsystem, instrument, and payload is turned on***
*Nominal telemetry provides initial state-of-health verification*
***Includes imaging and end-to-end data flow which is extensive test of ALI, Hyperion, AC, WARP, and X-band***
***ACS modes and components tested***
***All power-system functions tested***
***All C&DH tasks tested***
***All downlink rates tested, S-band and X-band***

## Development of the EO-1 CPT

***Based on Spacecraft Test & Operating Language (STOL) Procedures as much as possible***
*Automatic command verification and limit checking*
*Executes quickly*
*Can repeat with precision*
*Procedures are directly transportable to operations team*
*Can check STOL procedures before running first CPT*
***Bottoms-up, modular approach***
*Using tests developed for box testing and integration*
*Some tests also used in aliveness and functional tests*
*Each subsystem’s tests verify all subsystem functions and requirements. These tests are listed and cross-referenced to CPT sections.*
***Where possible, conduct tests of different subsystems in parallel to shorten the duration of the CPT***
***TRMM and XTE CPTs used for reference***

## Details of Functional Test

***Same as the CPT with the following exceptions:***
*Performance-only tests are eliminated, such as the long (spin-down) RWA test *
*The launch and B-dot timelines are shortened *
*Specialized instrument tests eliminated, because they are fully tested in a max-data-rate, end-to-end test *
*LFSA deployment has a limited number of cycles, so its test is eliminated *
*EFF test is shortened to a few cycles *
*Multiple-permutation test of s/a release redundancy eliminated (redundant side still tested) *
*Dedicated s/a drive test eliminated, since the s/a drive is continuously tested in the background *
*Orbit tests are eliminated *
***The total duration is about 24 hours, instead of the 48-72 hours needed for the CPT***
***As in the CPT, much of the system & subsystem health, function, & performance is confirmed and determined from nominal telemetry***

## EO-1 CPT Design

***Three general phases with 11 sections***
*Begin with a launch, ascent, deployment, and sun-acquisition simulation to verify the most critical timelines on the mission and to stress the power system*
*Follow with a series of tests to verify all satellite functions and to measure system performance*
*End with several real-time, nominal orbit-cycle tests*
***The CPT is designed for ambient testing, with the solar arrays un-mounted and all the instruments and payloads integrated***
*Modified for first CPT (without Hyperion)*
*Modified for thermal-vacuum testing (Hyperion cryocooler operations, PPT firing, and RCS pressurization will be different)*
*Modified for launch site (solar arrays will be mounted)*
***Data used to begin subsystem trending of key parameters***

## CPT Sections

***CPT0: Launch configuration. The S/C is turned on & configured as for launch. Nominal performance is verified through telemetry***
***CPT1: Ascent through sun acquisition. From switch to internal power, through launch, ascent, separation, deployment, rate nulling, & sun acquisition following a worst-case timeline. Real time enables assessment of ACS timers & the power system. During the coast phase, additional subsystem tests gain experience in operating the S/C with 2kb/s telemetry.***
***CPT2: ACS & nominal S/C operations. Nominal configuration, except instruments, payloads, & WARP are off. Timeline driven by ACS tests: phasing, sensor stimulation, actuator operation, GPS, & coupling. Power, S-Band, & M5 tests conducted in parallel. S-Band requires some dedicated time.***
***CPT3: Instrument turn-on, including payloads & WARP. Verify health of instrument & most functions excluding imaging.***

## CPT Sections (CONTINUED)

***CPT4: Comprehensive instrument & payload tests. Each payload performs exhaustive testing, including image data, where possible***
*CPT4A: ALI. Dark images, cal lamps, heater functions, FDC, mechanisms, processor loads, timers.*
*CPT4B: Hyperion. Dark images, cal lamps, heaters, cryocooler, mechanism, timers, FDC.*
*CPT4C: AC. Dark images, lab image, gain variations, temperature control*
*CPT4D: LFSA. Launch release, deploy, current/voltage*
*CPT4E: PPT. Single & multiple firings, both tubes, long & short pulses*
*CPT4F: EFF*
***CPT5: Comprehensive ACS testing. Complete performance testing of ACS S/W & component functions. RCS testing.***

## CPT Sections (CONTINUED)

***CPT6: Solar-array drive. Orbit rate, ramp up, ramp down, open loop test, blind acquisition of index, min/max travel limits, rewind, potentiometers, glitch test.***
***CPT7: WARP/RF. Correct image data through X-Band, correct data through MSSP to X-Band at 2 Mb/s (compare X- and S-Band data), correct pointing of X-Band.***
***CPT8: End-to-end tests & maximum rate. Correct data from instruments, through WARP & X-Band to ground storage. Test maximum data ingest: all instruments operating at the same time for 60 seconds.***
***CPT9: Safemode & load shed. Transition to safemode, ACS, all subsystems put into correct configuration. Safemode recovery***
***CPT10: Special command. Test each special command: reset processors & switch to alternate PROMs. ***
***CPT11: Orbit-cycles. As a minimum: data-collection orbit with downlink, lunar-calibration orbit, & delta-V orbit.***

## Highlights of the First CPT

***The first iteration of the CPT took about 72 hours. Most tests were successful***
***Tests with the most problems during the first execution were re-run on the fourth day, with success. These tests were CPT0, CPT1 (launch), and some ACS tests from CPT2.***
***There were 36 problem records (PRs), which represent hardware or software anomalies. Most are resolved. ***
***There were about 100 discrepancies in the CPT procedures, most of which had not been tested previously. Most of the deviations caused test delays. Most of the deviations have been incorporated into new versions of the procedures. ***
***The FOT developed orbital timelines, which were tested successfully and resulted in improved command sequences***

## Overview of Successful Tests from the First CPT

***ALI comprehensive Health & Safety and imaging***
***All WARP functions, performance and evaluation***
***Power system: solar-array drive, power switching, and battery-charge management***
***ACS: End-to-end open loop phasing of all major ACS modes of operation were performed. Completed a full performance test of RWAs, IRU, & MTBs***
***C&DH: all thirteen of the M5 C&DH tasks performed without error***
***GPS update of spacecraft time tested***
***Command sequence (ATS and RTS) tested***
***RCS: thruster valves and flow tested***

## Overview of Successful Tests from the First CPT (CONTINUED)

***Some contingency and FDC tested: ***
*HOP (solar-array release) redundancy and backup activation*
*ACS timers to delay transitions*
*Transition to safemode*
*1773 redundancy*
*Watchdog timers, special commands, and re-starts.*
***EFF loaded and executed***

## Omissions During the First CPT

***Hyperion, Atmospheric Corrector, LFSA and Autonomous Star Tracker were not integrated. (AST I/F and interaction with the ACS was tested & verified.)***
***Due to ALI concerns, the PPT was not tested***
***Most FDC was not tested (exceptions stated above)***
***C&DH: uplink-error tests not performed. (Tested at box-level.)***
***RF: The S-band RF not tested (GSE Transmitter in repair RF was tested during integration.) ***
***RF: X-band not tested (critical X-band tlm not calibrated). X-Band passed all performance tests during integration***
***Solar-array drive: redundant drive and encoder, orbital-motion control by M5 ACS FSW, including imaging profile***

## Omissions (CONTINUED)

***ACS use of GPS position and velocity vectors (tested previously during integration)***
***Since the ACE software is just completing development, ACE safehold control of the actuators (MTB, RWA, SAD) not tested***
***End-to-end phasing for the M5 ACS B-dot control mode***
***Thermal: thermostatically-controlled heaters will not draw power unless the temperature is below 4 to 8 Celsius***
***Since the ACDS required some software patches, we did not perform some M5-reset tests (for example, memory-scrub errors), which requires re-loading the patches. The re-sets were tested during integration and at the box level.***
***Comprehensive testing of PSE and C&DH commands: Some seldom-used commands not tested***

## Problems during Execution

***About 100 procedure deviations.  Most of these have been incorporated, already, into corrected STOL***
***TSMs did not operate at first. (TSMs were not available for testing prior to the CPT).  The launch TSMs were fixed and re-tested.***
***GPS telemetry had intermittent dropouts, even after new s/w (PTR ___ )***
***The ACE software, version 2.03, contained errors (2.03 had not been tested prior to the CPT).  After using an earlier version of the code for about 24 hours, ACE 2.04 was loaded and used successfully for the remainder of CPT.***
***The magnetic field around the spacecraft was different from the previous TAM calibration: ALI integrated and SAS wiring***
***There is a still-undiagnosed problem using the AST load box (EGSE)***
***EFF hogged the M5 CPU for too long and caused a warm re-start***

## Status of System-Level Testing

***Working on STOL procedures***
*Finish building tests that were omitted from the first CPT due to insufficient preparation.*
*Complete revisions of all existing STOL procedures*
*Perform test-run of all new and revised procedures so that the next CPT executes smoothly*
***Each subsystem working on improving tests***
*Final review of subsystem requirements*
*Complete red and yellow limits for parameters that have limits*
*Yellow limits are just outside nominal or expected operation and permit a controlled response by the TC*
*Red limits indicate impending damage to flight hardware and require immediate action*
***Completed two aliveness tests that were abbreviated due to missing hardware***

## Objectives of First CPT

***Met all objectives of first CPT***
*Perform as much functional and performance testing of EO-1 as is possible*
*Refine our knowledge of operating EO-1*
*Identify problems and additional work necessary before baseline CPT and environmental tests*
*Test the CPT STOL procedures*

## Summary

***First dry run of CPT was successful, but incomplete***
*Successfully tested most of EO-1 but some omissions due to lack of hardware (AST, Hyperion, etc.) and problems with GSE (S-band and X-band)*
*Some testing also reduced due to some incomplete procedures (redundant s/a drive, etc.)*
*Demonstrates that smooth CPT can be completed within 72 hours*
*Missing procedures are nearly complete*
***All components and payloads will be mounted for the baseline CPT***
***Nearly all Problem Records have been resolved; only Category “C” issues remaining***
*Telemetry filter tables for 2 kb/s downlink rate*
*AST interface?*
*FEDS crash*
*Anomalous warm starts (intermittent problem with probable causes based on configuration; do not expect during baseline CPT)*

## Spacecraft Testing

## Agenda

***Mechanical Alignment***
***Vibration Testing***
***Shock Testing***
***Mass Properties***
***Acoustic Testing***

## Mechanical Alignment

***Satellite ground alignment plan (SAI-PLAN-206) establishes system requirements***
***The following alignment measurements shall be performed to establish the spacecraft primary reference frame***
*S/C MRC to S/C datums*
*S/C SRC to MRC*
***IRU SRC will be mapped to the S/C MRC & star tracker reference cube***
***ALI & HSA reference cubes will be mapped to the S/C MRC***
***ALI & ACI Optics Module shall be co-aligned to within 2 arc-mins.  Bushings have been fabricated to allow adjustment in the position of the ACI OM.***

## Mechanical Alignment Flow

***Baseline measurements shall be performed after all flight components have been installed***
***Alignment measurements shall be performed of the IRU and star tracker to S/C MRC prior to vibration testing.  Post vibration measurements will be made to verify that alignment has been maintained between components***
***Measurements are taken with one sec accuracy theodolites (Model Wild T2) with autocollomating eyepieces***

## Satellite Vibration Testing

***The Delta 7320-10 launch vehicle payload environment includes sustained sinusoidal vibration as well as quasi-sine transients during the launch phase of flight***
***Three separate and distinct sustained oscillation conditions typically occur, resulting in both lateral and thrust-axis responses.  These conditions, in the order they occur in flight, and the associated frequency bands and sweep rates are:***
*First pre-MECO (Main Engine Cutoff)**25 to 30 Hz**1.5 octaves per minute*
*Second pre-MECO**30 to 35 Hz**1.5 octaves per minute*
*Prior to MECO**15 to 20 Hz**4 octaves per minute*

## Satellite Vibration Testing

***Satellite Sine Vibration Test Plan (SAI-PLAN-307) has been drafted and is in review by project, facility & spacecraft personnel***
***The vibration test shall be run in three axes. The X & Y-axis tests shall be run on the lateral slip table & the Z-Axis test shall be run on the exciter in the vertical configuration with the use of a head expander***
***The launch vehicle contractor shall provide a Test Payload Adapter Fitting for use during this vibration test***
***The MAP S/C vibration test fixture is being used for this test. The fixture assembly consists of three parts, 1) a force ring plate, 2) six multidimensional force transducers, & 3) adapter test plate***

## Satellite Vibration Testing

***Approx. 30 tri-axial accelerometers have been identified on the spacecraft and payload.  These accelerometers were installed at the Swales cleanroom facility, prior to shipment to GSFC***
***The vibration test control instrumentation will consist of three tri-axial accelerometers mounted on the MAP adapter plate.  The average in-axis response of these accelerometers will be used to control the test***
***Three additional accelerometers will also be used to limit the input acceleration level to the spacecraft, ALI & HSA.  A predetermined, Not To Exceed (NTE), level will be specified for each limiting accelerometer and the test input levels shall be automatically adjusted, by the control system, if the NTE level of any of the limiting accelerometers is reached***

## Satellite Vibration Testing

***The following figures shows the proposed accelerometer placements:***

## Satellite Vibration Testing

***Satellite Vibration Testing***

***The test specification is derived from latest flight coupled loads analysis times a 1.25 factor to obtain the protoflight levels below***
***The sweep rates for the sustained oscillations have been selected to approximate the actual flight time it takes to sweep through the frequency bands shown***

## Satellite Vibration Testing

***The following plots are expected responses for the S/C, ALI & HSA***

**<<< Response Plots >>>**

## Satellite Shock Testing

***The satellite shock test procedure will be incorporated within the sine vibration test procedure***
***Two shock tests will be performed at the conclusion of the vibration test***
***The satellite will be lifted, by a crane, approx 3” with the test PAF installed.  A sheet of foam will be placed under the PAF and the clampband shall be released and allowed to drop onto the foam sheet***
***All accelerometer instrumentation used during the vibration test shall remain installed on the satellite and will be recorded during the shock test***

## Satellite Mass Properties

***The satellite mass properties test plan, SAI-PLAN-319, will be created to provide the facility test requirements***
***The satellite center of gravity in the X-Y plane and the moment of inertia about the Z-axis will be measured and compared to the prediction from the CAD solid model***
***This test will be performed prior to vibration testing and again before acoustic test with a fully integrated satellite***
***The test will be preformed on the Miller mass properties table in building 15***
***The satellite will be placed on the thermal vacuum test fixture with the clampband installed***

## Satellite Acoustic Testing

***The maximum acoustic environment for the EO-1 satellite will occur during liftoff and transonic flight.  Liftoff levels are typically higher than transonic levels at the payload location***
***A satellite acoustic test plan, SAI-PLAN-320, will be created to provide the facility test requirements***
***This test will be preformed on a fully integrated satellite in the GSFC acoustic test facility in Building 10***
***A reduced set of accelerometer instrumentation will be installed and recorded during the test***
***The satellite will be lifted off the transportation dolly and raised into the center of the microphones acoustic field***

## Satellite Acoustic Testing

***The predicted EO-1 acoustic environment is a function of the configuration of the launch pad, the vehicle (e.g., 7320 Delta with 3 GEM solid motors), the payload fairing (10-ft. composite, with 3-in. acoustic blankets) and the fill effect due to the satellite and DPAF volume and radial gap to the fairing wall***
***The EO-1 protoflight acoustic levels are shown. The test duration is one minute for protoflight test.  These estimated P95/50 probability levels are based on current McDonnell Douglas Aerospace Delta 7320-10 levels, with an adjustment for the EO-1 fill effect***

## Spacecraft Testing:

***EMI / EMC***

*** ******Bob Vernot***
***EO-1 Electrical Engineer***
***Swales Aerospace***

## Agenda

***EMC Related System Tests to Date***
***Planned System Level EMC Tests***
***Transient Tolerance Testing***
***Power Profile Testing***
***RE02 (NB Radiated Emissions)***
***RE02 (BB Radiated Emissions)***
***Limited Radiated Susceptibility Test***
***Magnetic Survey Plan***
***Issues***

## EMC Related System Tests to Date

***Power Service Current Balance***
***Turn-On/Turn-Off Transients***
***Operational Transients***
***Powered SADA rotation***

## Planned System Level EMC Tests

***S/C Self Compatibility Tests***
*Transient Tolerance Test*
*Power Profile Test*
*RF Compatibility Test*
***Quantitative Testing***
*RE02 Narrowband Radiated Emissions Test*
*RE02 Broadband Radiated Emissions Test*
*Limited Radiated Susceptibility Test*

## Transient Tolerance Testing

***Goal - Demonstrate that worst case EMI from each S/C subsystem has no detrimental effect on any other subsystem***
***Test Description***
*S/C must be in flight like configuration*
*All S/C subsystems begin test in normal on-orbit operational mode considered to be most susceptible to (and/or most indicative of) EMI*
*Each subsystem (individually) is exercised through normal modes of operation considered to produce worst case EMI*
*All other subsystems monitor telemetry and science data for anomalies which may correlate to EMI from other subsystems. Some off-line data evaluation is required*

## Power Profile Testing

***Goal - Provide a Quantitative measure of S/C Conducted Emissions under worst case conditions***
***Test Description***
*S/C must be in flight like configuration*
*S/C Power Bus is instrumented with Oscilloscope and Spectrum Analyzer (accomplished via isolated test point at PSE)*
*All Subsystems are configured for orbital mode of operation creating maximum EMI*
*S/C power bus is monitored for compliance with CE01 and CE03*

## RE02 (NB Radiated Emissions)

***Goal - Demonstrate that EO-1 S/C RE will not interfere with Delta II avionics***
***Test Description***
*S/C will be configured for the worst case mode of operation during launch and ascent*
*RF probe is used to determine locations of worst case RE*
*Biconical test antenna will be placed one meter from these locations and configured at 45 degree angle to the horizontal*
*One sweep (14 KHz - 18 GHz) required for each location identified*

## RE02 (BB Radiated Emissions)

***Goal - Demonstrate that EO-1 S/C RE will not interfere with Delta II avionics***
***Test Description***
*S/C will be configured for the worst case mode of operation during launch and ascent*
*Biconical test antenna will be placed one meter from locations determined previously, and configured at 45 degree angle to the horizontal*
*One sweep (14 KHz - 18 GHz) required for each location identified*

## Limited Radiated Susceptibility Test

***Goal - Demonstrate that S/C is not susceptible to RF energy that it may be exposed to On-Stand***
***Test Description ***
*All S/C subsystems powered On and in most susceptible mode*
*Various test antennae used to emulate RF energy which may result from LV transmitter and launch site specific sources. Test antennae locations are dependent on RF source locations relative to S/C frame of reference on-stand.*
*Test antennae will be powered individually to provide no more than 10 V/m of RF energy at the S/C*
*Telemetry shall be monitored for any anomalous behavior associated with Radiated susceptibility*

## Issues

***Not all components have undergone EMC testing***
*Some qualified by simularity*
***Waivers issued for some components within S-Band Notch***
*ECU*
***Exceedances in broadband emission***

## Magnetic Survey Plan

## Magnetic Survey Plan

***Analysis and ALI STM Magnetic Test indicate magnetic self-combatability is not an issue***
***Clean area magnetically , and evaluate and measure external sources such as lights and filter blowers***
***Perform an un-powered survey with the compass, noting any changes in needle direction when the compass is approximately 6 inches from a potential source***
***For dipoles that may be vertical and/or inaccessible within 6 inches of the source (e.g. ALI), use the test TAM.  Any field change greater than 35 mGauss from 1 foot away is significant, and would equate to a field change greater than 280 mGuass from 6 inches away***
***The center of the dipole (within the box) is best found by aligning one axis of the test TAM along the dipole, and recording the measurements from at least two points along the dipole***
***Repeat on powered spacecraft***

## Spacecraft Testing:

***RF Compatibility***

*** ******Tom Spangler***
***EO-1 RF Engineer***
***Swales Aerospace***

## RF Compatibility Test

***Purpose***
*Testing Ensures EO-1 Communicates with GN & SN*
*Compatibility Test Van utilizes highly calibrated equipment similar to that of ground stations*
*CTV allows end-to-end tests between EO-1 MOC and the S/C*
*Wallops Ground Station*
*White Sands (TDRSS)*
***Test Plan***
*Performance Characterization of S-Band and X-Band*
*Validation of measurements taken by I&T during functional tests*
*Measurements performed by CTV are more accurate*
*Ground Network Tests*
*End-to-End test flowing commands and telemetry*
*MOC Interface with Wallops will be verified*
*TDRSS Special Test*
*End-to-End test flowing telemetry from S/C to the MOC through TDRSS (White Sands)*

## RF Compatibility Test (CONTINUED)

***Configuration***
*Test Procedure and Equipment from Code 540*
*S/C in Bldg 7/10*
*Fiber Optic Cable and Copper Wire provide link from S/C to Bldg 25 (RF Compatibility Lab)*
*Front End Equipment Mated to S/C*
*CTV located in Bldg 25 during test allows more flexibility in CTV schedule*
*Hat Couplers*
*S-Band: NO (CTV connected to antenna harness)*
*X-Band:  YES*

## RF Compatibility Test (CONTINUED)

***Test Results/Review***
*Test Report from Code 540*
*Data Review by EO-1 Communications Engineer and Support*
*Verification of MOC interface with GN*
*Verification of MOC interface with SN*
*Verifies S/C RF signals meet both GN and SN requirements*
*Ground Equipment configuration parameters determined by Compatibility testing will be given to ground stations*

## Spacecraft Testing:

***Thermal Vac / Thermal Balance***

*** ******Nick Teti***
***EO-1 Lead Thermal Engineer***
***Swales Aerospace***

## Agenda

***Requirements***
***Thermal Control System Status***
***Mission Mode Configurations***
***EO-1 Thermal Design***
***Thermal Subsystem Changes Since CDR***
***EO-1 Thermal Verification***
***Thermal Balance / Thermal Vacuum Test Objectives***
***EO-1 Thermal Balance / Thermal Vacuum Test Plan***
***Thermal Balance Test Configuration***
***EO-1 Thermal Vacuum Test Configuration***
***Status***

## TCS Requirements

***Maintain Spacecraft Components and Instruments Within Appropriate Temperature Limits for All Phases of the Mission.***
***Provide Suitable Conductive and Radiative Thermal Interfaces for each Payload Instrument***
***Minimize Heater Power Requirements***
***Maintain Deployable Mechanisms Within Temperature Limits Prior to and During Deployment***
***Provide Telemetry To Adequately Assess Spacecraft Health and Safety***

## Thermal Control System Status

***Thermal Coatings Completed***
***Thermal Blankets ***
*Zenith Deck and Transition Cone Completed*
*Battery Bay Enclosure Completed*
*S-Band Antenna Brackets Completed*
*X-Band Antenna in Fabrication*
*HOPS and S/A Restraints in Fabrication*
*Equipment Panels in Fabrication*
*Atmospheric Corrector Template to be Fit Checked *
*Planned closeouts and modifications prior to TB Testing*
*** ******Passive Radiators***
* **Drawings completed*
* **Silver Teflon Installation prior to TB Test*

## Thermal Control System Status (CONTINUED)

***Heaters, Thermostats***
*Spacecraft Heater Circuits Resistance Checks Completed*
*Replacement CC Radiator Thermal Hardware Installation planned for 6/10, Resistance Check Planned for 6/14*
***Flight / Test Thermistors***
*119 Flight Thermistors*
***Test Thermocouples***
*120 Thermocouples*
*Installed by GSFC Code 549*
***Cryopanels and Heater Panels***
*Supplied by GSFC Code 549*

## Mission  Mode Configurations

***Stowed***
*Ascent*
*Pre Solar Array Deployment*
*** ******Science***
*Data Taking*
*RF Transmission*
*Stand-By*
*** ******Safe Hold***
*Zenith Deck toward Sun*
*Solar Array Fixed*

## Thermal Control System

***Passive Radiators***
*Used on Spacecraft Equipment Panels 1, 2, 4 and 6 to radiate excess heat to space and maintain overall bulk temperature of spacecraft*
*Regulated conductive paths*
*G-10 Isolators between Equipment (Battery) Panel 3 and S/C Structure*
* **Maintain Battery 18±5°C*
*G-10 Isolators between PPT Mounting Plate and Panel 6*
*** ******Louvers***
*Used to Regulate Battery Equipment Panel Temperature*
*TRMM spare with 10°C Design (5°-15°C) - calibrated by OSC*

## Thermal Control System (CONTINUED)

***Multi-Layer Insulation (MLI)***
* **Built by Swales Aerospace*
* **3 mil on Zenith Deck & Equipment Panels*
* **2 mil on Nadir Deck and HEA/CEA boxes*
* **Black Kapton on Nadir Deck below ALI FPA Radiator*
* **Battery Bay Enclosure - Aluminized Kapton*
* **Propulsion Tank*
*** ******Thermal Coatings***
* **Aeroglaze A276 White Paint*
* **Zenith Deck S-Band Antenna and SADA Actuator Cover*
* **Aeroglaze Z306 Black Paint*
* **Used on Nadir Deck S-Band Antenna*

## Thermal Control System (CONTINUED)

***Thermostatically Controlled Survival Heaters***
*Used to maintain components above cold survival limits*
*Primary and Secondary Circuits*
*Redundant Thermostats*
*Heater Sizing*
-  Science Mode: < 5 watts
-  SafeHold Mode:  < 20 watts
***CHOTHERM used between electronic boxes and S/C Equipment Panels***
***High emissivity coatings are used to enhance internal radiation***

## Thermal Control System (CONTINUED)

***ALI***
* **Maintain 200K Passive Radiator for Focal Plane Assembly *
* **Black Kapton On Nadir Deck in Front of FPA Radiator*
* **Passive Radiator for Focal Plane Electronics*
* **ALICE Box Conductively Coupled to Instrument Pallet which is Conductively Coupled to the EO-1 Nadir Deck*
*** ******Hyperion***
* **HSA Conductively Isolated from Spacecraft Nadir Deck*
* **CEA/HEA are Thermally Coupled to the Spacecraft Nadir Deck*
*** ******Atmospheric Corrector***
* **MLI Blanket Provided by Swales*
* **Conductively mounted to Spacecraft Nadir Deck*

## Thermal Control System (CONTINUED)

***Carbon Carbon Radiator***
*Six Thermistors, Heaters and Thermostats installed on 6/10*
*** ******Pulse Plasma Thruster***
*G-10 Isolators between PPT Mounting Plate and Panel 6*
*** ******Lightweight Flexible Solar Array***
*MLI Enclosure Completed with Zenith Deck Blanket*
*** ******Advanced Star Camera***
*Current Modifications incorporated*
*** ******Calorimeters***
*Design Completed*
*Hardware in fabrication*
*Thermistor modification completed*
*** ******Propulsion Tank***
*MLI blanket fabricated and installed*

## EO-1 Thermal Analysis Model

## EO-1 Thermal Analysis Model (CONTINUED)

- Louver

- Bay 4 Radiator

- ALI FPA Radiator

## Changes since CDR

***Star Tracker Tilt***
*Updated Thermal Model*
***Calorimeters***
*Modified two thermistor locations*
***Thermal Louvers***
*Reduce Heater Power for Battery (Bay 3)*

## EO-1 TCS Verification

***Component Level***
*Box Level *_*Thermal Cycle*_* Testing  using GEVS as a guideline to verify the proper function of the component at Qual or Acceptance Level*
*Solar Array TV Testing was completed by Manufacturer*
*8 Cycles of Thermal Vacuum Cycling using GEVS as a guideline to verify the proper function of the component at Qual or Acceptance Level*
*Each component is subjected to a Hot & Cold Turn On*
***Instrument Verification***
*Instrument Components have Component Level Thermal Analysis*
*Instrument Thermal Vacuum Testing was Done at Assembly Level*
*Instruments have Performed Thermal Balance Testing*

## EO-1 TCS Verification (CONTINUED)

***Spacecraft Level***
*EO-1 will have four cycles of Thermal Vacuum Testing*
*EO-1 will also have a Thermal Balance Test in which Hot and Cold Mission Balance Cases will be simulated with as much fidelity as possible*
*Pre-Test Balance Analysis is in progress, Post Test Correlation will be performed. On-Orbit Models will be updated to reflect post test correlation*
***Spacecraft Hardware***
*Thermal Louver calibrated by OSC *
*Heaters are NASA Standard Parts (S-311-79)*
*Thermostats are NASA Standard Parts (S-311-429)*
*Heater/Thermostat Circuits verified using CO2 cold spray*
*Thermistors are NASA Standard Parts (S-311-P18)*
*Telemetry verified with ASSIST*

## EO-1 TV/TB Test Objectives

***The thermal vacuum and thermal balance tests are being performed to accomplish the following objectives:***
*Demonstrate that the payload & spacecraft bus can operate satisfactorily in all functional modes for the mission, at temperatures 10****C beyond the hot and cold extremes predicted on orbit.  For heater controlled components the margin can be reduced to 5****C on the cold extreme.  If thermal balance test results do not agree with analytical predictions, components shall be tested to their qualification limits where appropriate.*
*Demonstrate the ability of the payload & spacecraft bus to operate satisfactorily under safehold conditions and after a cold restart*
*Demonstrate satisfactory operation during and after temperature transition*
*Demonstrate satisfactory operation of the payload thermal control systems.  This shall include checking thermostat set points, thermistor data, heater operation, and heater duty cycles. The heaters are switched services.*

## EO-1 TV/TB Test Objectives (CONTINUED)

***The thermal vacuum and thermal balance tests are being performed to accomplish the following objectives ******(CONTINUED)******:***
*Verify the EO-1 spacecraft meets the contamination requirements*
*Verify the EO-1 spacecraft and instrument thermal models*
*Measure the power dissipation *
*Verify optimal radiator sizes for the equipment panels*
*Demonstrate the workmanship of the EO-1 spacecraft and instrument is thermally and functionally adequate*
*Perform thermal cycling and verify performance using GEVS as a guideline*
*Confirm thermal interface between the instrument and spacecraft*
*Confirm thermal characteristics of calorimeter experiment*

- This test shall be conducted at GSFC in the facility 238 (12’x15’ cryo-pumped chamber), located in building 7.  The chamber shall provide the necessary appurtenances for the test article, cryo-panels, and support hardware.  The chamber shall also be capable of maintaining a minimum vacuum of 1x10-5 torr.  The temperature of the chamber walls shall be selectable in the range of -190C to 75C  2C.  In addition, the necessary number of heaters, thermocouples, and plumbing lines shall be provided.

## EO-1 Thermal Balance / Thermal Vacuum Test

***TVTB Test Plan in Final Review***
***TVTB Test Plan identifies requirements and goals of TVTB Testing***
***TVTB Test Plan Outlines the Method of Simulation & Environmental Levels***
***TVTB Test Plan lists the required hardware, personnel and configuration of the spacecraft***

## Thermal Analysis Cases

***Hot and Cold Thermal Vacuum Test Predicts are compared against worst case analytical predicts***
***Worst Case Analysis has worst case blanket effective emissivity and power dissipations***
***Hot and Cold Thermal Balance Test Predicts are compared against Hot and Cold Analytical Predicts***

## EO-1 Thermal Balance Test Configuration

***Spacecraft is in as close to flight configuration as practical***
***Solar arrays are simulated using Heater Plate provided by GSFC/Code 549***
***Spacecraft sits on G-10 standoffs with ZERO-Q heater control***
***Three cryo-panels, four heater panels and the chamber walls provide the orbital environment simulation***
***All flight MLI blankets, Radiators, and Louvers will be present***
***Connection to spacecraft will be through spacecraft umbilical***

## EO-1 Thermal Balance Test Environment

***EO-1 Thermal Balance Test Environment***

## EO-1 Thermal Balance Test Configuration

## Slide 114

## EO-1 Thermal Vacuum Test Configuration

***Equipment Panel MLI will be removed to allow for faster transition time***
***Chamber walls provide Test Environment***

## EO-1 TV/TB Test Status

***Thermal Vac / Thermal Balance Test Plan in Final Review***
***Facility Requirements Provided to GSFC Code 549***
***Preliminary Pre-Test Thermal Balance and Thermal Vacuum Predictions Completed***
***Currently On Schedule for 8/99 Thermal Balance Test, followed by Thermal Vacuum Test***

## Spacecraft Testing:

***End-to-End Imaging Test***

*** ******Tim Zukowski***
***EO-1 ALI System Engineer***
***Swales Aerospace***

## Agenda

***Objective and Key Points***
***Configuration***
***End-To-End Imaging Test Optical Setup***
***End-to-End Imaging Test GSE***
***End-to-End Imaging Test Optics***
***End-to-End Imaging Test Flow***
***Data Acquisition and Analysis***
***Issues***

## Objective and Key Points

***The purpose of the end-to-end imaging test is to verify that the ALI and Hyperion have not suffered significant imaging performance degradation due to environmental testing.***
***The MIT/LL Focus Test Equipment (FTE) will be used to test both instruments by simulating a ground scene.***
***This test is scheduled for Sept. 1, 1999. Detailed planning will be done late June. Concept is mature, and coordination between GSFC, MIT/LL, and TRW is in place.***
***Ground scene imaging has been (will be) done for both instruments prior to delivery, providing a baseline for comparison.***

## Configuration

***The end-to-end imaging test will be conducted in ambient conditions, therefore only VNIR / MSPAN detectors will be used.***
***The S/C is to be mounted on a rotary tilt table (Ransome), and tilted so that nadir is horizontal. The instruments will be facing the FTE table.***
***Each instrument will be tested separately - the FTE equipment is repositioned for each one.***
***The FTE will project an image of a test pattern (AF bar target). The image will be scanned by the FTE to simulate the moving Earth’s surface. Each instrument will record an image of the bar target.***

## End-To-End Imaging Test Optical Setup

***End-To-End Imaging Test Optical Setup***

- Courtesy of Dr. D. Lencioni, MIT/LL

## End-to-End Imaging Test GSE

***The Focus Test Equipment is to be provided by MIT/LL.  It will require transport, setup and operation support. It is currently clean and ready to go.***
***The FTE will require mechanical GSE to align with the instruments ******(GSFC responsibility)***
***Preparation of the Ransome table for use in a clean area will be required ******(GSFC facilities responsibility)***
***The test requires a stable environment (solid floor, still air, and stable temperature) ******(GSFC responsibility)***
***An interface between the S/C and Ransome table is required; this is already in the current S/C I&T plan ******(Swales responsibility)***

## End-to-End Imaging Test Optics

**Relative Positioning **
**Tolerances:**
**X & Y:****	****± 1 in.**
**Z:****	****± 6 in.**
**Yaw & Roll:****	****± 0.5°**

**3 m from Entrance Pupil**

- Courtesy of Dr. D. Lencioni, MIT/LL

***End-to-End Imaging Test Optics***

## End-to-End Imaging Test Optics

**Beamsplitter**

**Optical Table**

**3' **

- 

** ****9'**

**Field Lens**

**Focal Surface**

**3.25" dia.**

**66182 10-1000 W**

**QTH Lamp**

**Housing**

**Integrating**

**Sphere**

**Condensing**

**Lens**

**3-Axis Slide,**

**6" **

- 

** ****6" **

- 

** ****6"**

**Primary Mirror**

**f = 1.5 m**

- Courtesy of Dr. D. Lencioni, MIT/LL

***End-to-End Imaging Test Optics***

## End-to-End Imaging Test Flow

***Clean and prep the Ransome table***
***In parallel:***
*Receive MIT/LL FTE equipment*
*Set up FTE in test location*
***In parallel:***
*Move Ransome table to test location*
*Attach S/C interface*
***In parallel:***
*Move and setup S/C EGSE*

***In serial:***
*Mount S/C onto Ransome I/F*
*Perform alignment to ALI*
*Take ALI data*
*Perform alignment to Hyperion*
*Take Hyperion data*
*Perform data reductions*
*Review results*
*Deconfigure and goto alignment/packing*

## Data Acquisition and Analysis

***Data will be taken by starting instrument data acquisition, then triggering the FTE image scan.***
***The recorded data will be dumped from the WARP to the DPS FEDS, reviewed by quicklook for validity, then post processed to Level 1 by each instrument team.***
***The Level 1 bar target image will be analyzed for MTF response.***
***A significant degradation from baseline image test results will be cause for investigation of possible optical system damage due to environmental testing.***

## Issues (1)

***GSFC must provide appropriate facility: TBD at this time. (Options shown next slide).***
***Without stable facility conditions, test results may be inconclusive (as shown by MIT/LL’s experience with ALI).***
***GSFC facilities resources needed to prepare and operate the Ransome table — scope of effort is still TBD. ***
***GSE required for positioning the FTE table relative to the Ransome table: Concept for this will require modest mechanical design/layout effort, and details of Ransome table implementation.***

## Issues (2)

***Table of facility choices and issues:***