# Presentation: 122107

## Carbon-Carbon Radiator (CCR)

## Carbon-Carbon Radiator (CCR)

***Carbon-Carbon Radiator (CCR)***

***Equipment panel composed of carbon-carbon facesheets and an aluminum honeycomb core***
***Flight unit and spare***
***No changes since CDR***

## Qualification Testing (Completed)

***Qualification Testing (Completed)***

***Thermal Vacuum/Balance***
***Vibration***
***Mass Properties (Flight unit only)***
***Non-destructive examination (radiography) conducted before start of qualification testing and after completion of thermal testing and of vibration testing***

## Thermal Vacuum / Balance Testing(TV / TB)

***Thermal Vacuum / Balance Testing******(TV / TB)***

***Test Frame simulated S/C***
***Mockups of LEISA and PSE baseplates***
***Two strain gauges on the test frame***
***Four thermal cycles with four-hour soaks at 50C and -10C***
***Thermal balance testing for (8) various conditions***
***Survival heaters tested with four different voltages***
***Thermal cycling loads were half those predicted, indicating that finite element model (FEM) results are conservative***
***Non destructive examination (NDE) indicated no structural damage***

## Vibration Testing

***Vibration Testing***

***Test frame simulated S/C***
***Mass mockups of LEISA and PSE***
***Two tri-axial accelerometers***
***Sine burst to 1.25 x limit load (15g) in each axis***
***Low-level sine sweep before and after each sine burst test***
***Sine sweep tests and NDE indicated no structural damage***
***First frequency 89 Hz, less than 5% below the 93 Hz predicted (indicating that the FEM is reliable)***

## Mass Properties Testing

***Mass Properties Testing***

***Conducted with TRIDYNE model 200***
***Measured weight and cg in x- and y-axes***
***Calculated cg in z-axis and moi about x-, y-, and z-axes***
***Weight 6.87 lb. (3.12 kg)***
_***STRUCTURAL ANALYSIS***_
***Report completed June 2, 1998 ***
***All margins of safety positive (inertial and thermal loading)***
***First frequency predicted to be 112 Hz, above the 100 Hz requirement***

## Status/Issues

***Status/Issues***

***Flight unit damaged during integration with S/C***
***Flight unit will be replaced with spare before Observatory-level environmental  testing***
***Spare unit  meets all subsystem-level environmental requirements***
***Ready for Observatory-level integration and testing***

## GPS

## GPS Subsystem

***Off the shelf GPS receiver, pre-amp and antennas from Loral Tensor***
***In-house power conditioning unit built in-house***
***Provides orbital navigation and time information for C&DH and ACS/EFF applications.***

## GPS -- Scope of Box-Level Testing

***GPS -- Scope of Box-Level Testing***

***Contract Acceptance Testing***
*Random vibration, thermal vacuum, EMI/EMC and acceptance tests on receiver, preamp and antennas performed by Loral Tensor*
***PCU Environmental testing***
*Random vibration and temperature cycling on in-house built power conditioning unit.  EMI/EMC waived..*
***Detailed Characterization at GSFC ***
*Performed three month characterization of entire GPS subsystem using GPS constellation simulator to understand operation and optimize operational configuration.*
***Provided results of all above in detailed acceptance package to Swales before handover of unit.  ***

## Lightweight Flexible Solar Array (LFSA)

## Lightweight Flexible Solar Array (LFSA) Functional Testing

***Lightweight Flexible Solar Array (LFSA) Functional Testing***

***Launch Restraint Release and Deployment***
*Verifies working of shape memory release mechanism and panel hinges*
***CIS Solar Panel I-V Curve Sweep***
*Verifies working of photovoltaic arry*

## LFSA Test Flow

## X-Band Phased Array Antenna (XPAA)

## X-Band Phased Array Antenna (XPAA)

***X-Band Phased Array Antenna (XPAA)***

***Designed and built by Boeing for NMP Communications IPDT under fixed price contract with GSFC.***
***Validates electronically scanned antenna technology for future missions.***
***Provides 105 Mbps QPSK primary science downlink.***

## XPAA Hardware Changes Since Delivery

***XPAA Hardware Changes Since Delivery***

***Change:***
*Replaced 1773 interface connector (1 of 4).*
***Reason:***
*During pre-integration inspection and test this connector was found to have an internal ceramic sleeve which was broken.*
***Action:***
*Antenna was partially disassembled and connector was replaced at GSFC FOIL.*
***Result of the Modification:***
*After repair and workmanship vibration, end-to-end 1773 and RF performance was verified with GSE and Near-Field Scanner at Swales.*

## XPAA -- Scope of Box-Level Testing

***XPAA -- Scope of Box-Level Testing***

***Contract Acceptance Testing***
*Random vibration, thermal vacuum, EMI/EMC, 1773, and RF functional tests using hat coupler, near-field scanner and anechoic chamber.  Levels determined by Swales. Provided results of all above in detailed acceptance package to Swales before hand over of unit.  No technical issues.*
***Bench Testing***
*RF and 1773 functional tests using a hat coupler to absorb and sample the RF output.  Results compared with contractor supplied acceptance data.*
***Near-Field Scanning***
*Verifies antenna beam characteristics and pointing performance, does not require an anechoic chamber. Results compared with contractor supplied acceptance data.*

## XPAA Test Flow

## Pulse Plasma Thruster (PPT)

## PPT Testing

***PPT Testing***

***Qualification/Acceptance Tests***
*Benchtop Functional*
*Verified internal charging functionality  *
*Verified command and telemetry *
*Vacuum Functional*
*Verified discharge of PPT in vacuum*
- Both sides operated at levels encompassing on-orbit commanding
- Charge/Discharge characteristics verified
*Vibration*
*Random vibration of  PPT to proto-qualification levels in three axis*
*Performance*
*Measurement of Impulse bit as a function of commanded charge time*
*Measurement of Off-Axis thrust to determine thrust vector*
*Thermal Vacuum*
*Four thermal cycles*
*Verified  functionality at high and low temperature plateaus*
*EMI*
*Verified conducted and radiated susceptibility requirements*
*Measure conducted and radiated emissions per S/C specifications*
*Life/Contamination*
*Verified minimum mission requirement cycle life (100,000 cycles each side)*
*Measure contamination on MLI, radiator, and X-band material samples*

## PPT Testing (Continued)

***PPT Testing ****(Continued)*

***Spacecraft Level Tests***
*Functional Testing (Firing through Load Box)*
*Verified PPT charging characteristics and sparkplug discharge*
*Verify PPT command polarity and telemetry*
*Close loop ACS control of PPT can be verified during CPTs *
*Firing in Bell Jar Vacuum Integration Test*
*Verified PPT discharge functionality with s/c commands*
*Verified benign effect of PPT discharge on s/c bus (without instruments)*
***Proposed Additional S/C Level Tests***
*PPT Thermal Vacuum Firing*
*To verify begin PPT  discharge interaction with entire integrated s/c*
*Plume covers over PPT horns to be used to prevent plume contamination of s/c *

## PPT Test Flow

## PPT Test Flow

## Atmospheric Corrector (AC)

**NMP / EO-1 ****	****PRE-ENVIRONMENTAL REVIEW**

*** ******Mark Matsumura***
***LEISA AC Lead Engineer, NASA/GSFC Code 553_x0008_***

## Pre-Environmental Functional Testing

***Pre-Environmental Functional Testing***

***Performance tests/Operations at ambient conditions ***
*Housekeeping mode*
*Science Modes (30 Hz/60 Hz)*
*ThermoElectric Coolers were disabled.  *
*GSE limited the amount of science data collected.*

## Vibration Test Status

***Vibration Test Status***

***Modal Frequency Verification (Low Level Sine Sweep)***
***Strength Tests (Sine Burst, Protoflight levels)***
***Random Vibration (Protoflight levels)***
***Performed on 3 orthogonal axes, one normal to mounting surface***
***Tests were performed on each box separately.***
***Harness was connected to the optics module.***
***Due to NCRs LAC 002, and 003, the Optics Module was fully vibration tested a second time to protoflight levels.***
***Due to NCR LAC 001, the Electronics Box was random vibration tested a second time to acceptance levels.   ***

## Mass Properties Test Status

***Mass Properties Test Status***

***Measured weight of instrument.  ***
***Measured center of gravity of Optics Module and Electronics box (No moment of inertia measurement). ***
***Mass properties were measured in the Code 549 Mass Properties Test Facility***

## Thermal Vacuum Test Plan

***Thermal Vacuum Test Plan***

***Overall Plan***
*-10°C to +50°C survival range*
*0°C to +30°C operating range*
*4 cycles/ 25 Degrees per hour maximum*
*Minimum 2-hour soak times*
*Demonstrate turn on at both operational temperature extremes*
*Demonstrate operation through temperature transitions*
*Demonstration of ThermoElectric Coolers*
***Thermal testing was performed in the B7 Code 549 Thermal Vacuum Facility, Chamber 281 as per “EO-1 Spacecraft to LEISA AC ICD,” SAI-ICD-021, and “EO-1 Verification Plan and Environmental Specification,” SAI-SPEC-158.  ***
***Window in chamber provided for detector testing/calibration tests***

## Thermal Vacuum Testing - Profile

*** ***

- Ambient

- +30OC

- 0OC

- -10OC

- 1st Cycle

- 2nd Cycle

- 3rd Cycle

- 4th Cycle

- +40OC

## Thermal Vacuum Testing(Individual Test Descriptions)

***Thermal Vacuum Testing****(Individual Test Descriptions)*

***Cold Start Test ***
***Warm Start Test ***
***Housekeeping ***
***Science Operations/Calibration tests***
*Detector Temperature set points*
*Frame Rate Operations*
*Calibration at varying temperatures and set points*
***1773 Fiber Optics Trending Test***
***NCRs LAC 004 and 005 were from Thermal Vac testing.  ***

## EMI / EMC Test Status

***EMI / EMC Test Status***

***Conducted Emissions***
*Steady-State (CE01, CE03)*
***Radiated Emissions (RE01, RE02)***
***Radiated Susceptibility (RS03)***
***All EMI/EMC tests were performed in the B7 Code 549 facility as per “System Level Electrical Requirements, EO-1” AM-149-0002(155), SAI-SPEC-159.  ***
***Tests were run during housekeeping and science modes.***
***Thermoelectric Coolers were disabled during the tests. ***
***NCRs LAC 006 and 007 were from EMI Testing.   ***

## Interface Summary

***Interface Summary***

***WARP interface tests***
***Spacecraft interface (with Optics Module Simulator)***
*Mechanical*
*Power*
*Fiber Optics/Commanding*

## Non-Conformance Records

***Non-Conformance Records***

***LAC 001 - Fiber optic ceramic connector feed through sleeve cracked during electronics vibration.  ***
*Resolution: Disassembled e-box and replaced connector which is on the digital board fiber optic bracket. Revibrated e-box to acceptance levels (Random). Status: Closed *
***LAC 002 - ******Detector #1 was saturated at post vibration functional test on the optics module (OM).  Partially disassembled OM to investigate failure.  Visual investigation showed that bond wires had sheared from the chip carrier of the detector.***
*Resolution: Fully disassembled OM and rebond the bond wires.  Examined detector. Thoroughly checked the bond wires of the other detectors.  Rebonded the detector bond wires and retested.  Check all three detector assemblies for proper spacing. Fully Re-vib to Protoflight levels. Status: Closed*

## Non-Conformance Records

***Non-Conformance Records***

***LAC 003 - ******Lens of the optics module rotated from its fixed position during vib. testing.***
*Resolution: Fully disassemble OM and uralane all three lens assemblies. Fully re-vib OM to Protoflight levels. Status: Closed. *
***LAC 004 - Instrument was not powering up properly during set-up for T/V testing******.***
*Resolution: Replace GSE power supply with a power supply with greater capacity. Status: Closed. *
***LAC 005 - ******Detector #3 was not cooling down at the same rate as the other two detectors during T/V testing.***
*Resolution: Use as is.  Does not pose a danger to mission success. Status: Closed.*

## Non-Conformance Records

***Non-Conformance Records***

***LAC 006 - Current draw of the instrument did not ramp up as designed. Test set up for Conducted Susceptibility  CS01 has a risk of damaging instruments.  The audio power amp must be powered before any other equipment is powered up, or the power amp acts as an isolation transformer. ***
*Resolution: Make strong recommendation to add a warning to the test procedure. Status: Open   *
***LAC 007 - Instrument is not meeting conducted emissions or radiated emissions test requirements.  ***
*Resolution: Investigate options such as applying for a waiver.  Status: Open.    *

## WARP

## WARP Design Changes Since Delta-CDR

## Pre-Environmental Functional Testing

***Pre-Environmental Functional Testing***

***Fiber-Optics Baseline Test***
*Establishes Pre-Environmental Baseline for Transmitter Output Power and Receiver Sensitivity*
***Power Variation Test***
*Verifies WARP Operation (Record/Playback) at Bus Voltage Limits (35V, 24V)*
***Limited Performance Test***
*Briefly Verifies End-to-End WARP Data Flow*
*Performs Record/Playback via X-Band and S-Band*
***Memory Test***
*Performs Memory Card Built-In Test to Verify All Memory Locations*
*Record/Playback Test Pattern to Assess Memory EDAC Characteristics*

## Pre-Environmental Functional Testing

***Pre-Environmental Functional Testing***

***Comprehensive Performance Test***
*Provides Comprehensive Verification of All WARP Functions and Data Paths*
*Record Large Data Set (Fill Memory) and Playback via X-Band *
*Record Smaller Data Set and Playback via S-Band*
*Verify WARP Processor Memory Scrubbing*
*Verify WARP Processor and RSN Watchdog Operation*
*Verify WARP Special Command Operation*
***Normal Operations Test***
*Emulates Typical On-Orbit WARP Operations (Multiple Record/Playback Iterations) Over an Extended Period*

## EMI / EMC Tests

***EMI / EMC Tests***

***Performed Conducted Susceptibility Tests***
*CS01/02 Steady-State Susceptibility*
*CS06 Transient Susceptibility*
***Will Perform Conducted Emissions Tests***
*CE01/03 Steady-State Emissions*
***Will Perform Radiated Emissions Tests***
*RE01/03 Steady-State Emissions*
***Radiated Susceptibility Tests are TBD***
***Test Limits Defined As Per “System Level Electrical Requirements, EO-1” AM 149-0020 (155)***

## Vibration Test

***Vibration Test***

***Performed Sine-Sweep and Random Vibration in Each Axis ***
***Tested to Protoflight Levels As Per “EO-1 Verification Plan and Environmental Specification” SAI-SPEC-158 Sections 3.7, 3.9***
***WARP Was Not Powered During Vibration Testing***

## Mass Properties Test

***Mass Properties Test***

***Mass Properties Test Shall Measure WARP Weight and Center of Gravity***
***To Be Performed Immediately Prior to Delivery to Spacecraft***

## Thermal Cycling Test

***Thermal Cycling Test***

***Survival Soaks (Powered Off) Performed at +60******O******C and -15******O******C***
***Six Cycles from at +55******O******C and -15******O******C Performed at Ambient Pressure, As Per SAI-SPEC-158 Section 3.11***
***Functional Tests Performed During Cycling***
*Power Variation Test*
*Fiber-Optics Trending Test*
*Limited Performance Test*
*Comprehensive Performance Test*
*Memory Test*
*Long Duration Storage Test*
*Normal Operations Test*

## Post-Environmental Functional Testing

***Post-Environmental Functional Testing***

***Final Fiber-Optics Test***
*Verifies that 1773 Transceivers Were Not Damaged During Environmental Testing*
***Will Perform Comprehensive Performance Test***
*Verifies that WARP Record/Playback Was Not Degraded During Environmental Testing*
***Will Perform Memory Test***
*Verifies that Bulk Memory Was Not Damaged During Environmental Testing*

## WARP Test/Anomaly Status

## WARP Test/Anomaly Status

## Open Items

***Open Items***

***WARP Thermistor Errors Due to RF Exciter Thermistors***
*Characterize Thermistor Errors at Cold Temperatures (Where Errors are Worst)*
*Possibly Install New WARP Harness Eliminating Connection to RF Exciter Thermistors*
***WARP Std Ops Mode Transition Anomaly at Cold Temperatures***
*Determine Via Testing the Coldest Temperature at Which Std Ops Mode Transition Reliably Occurs at a 24V Bus Voltage*
*Determine Work-Around Approach, Possibilities Include:*
*Bias WARP Warm*
*Remain in Std Ops Mode as the Default WARP Mode*
*Perform Retries When Std Ops Mode Transition Fails*
*Fully Document Anomaly and Submit a Request for Waiver *

## Open Items

***Open Items***

***Conducted Susceptibility EMI/EMC Anomalies***
*Compile List of Anomalies and Submit a Request for Waiver*
***Conducted/Radiated Emissions Testing***
*Perform Emissions Tests Prior to Delivery to Spacecraft*
***Mass Properties Testing***
*Perform Mass Properties Tests Prior to Delivery to Spacecraft*
***Radiated Susceptibility Testing ***
*Perform Abbreviated Radiated Susceptibility Test If Spacecraft I&T Schedule Permits*
***Re-Integrate Onto Spacecraft***