mpsrsys- 1 ucb, oct 26, 2006 themis mission pre-ship review systems overview ellen taylor university...

MPSR SYS- 1 UCB, Oct 26, 2006

THEMIS MISSION

PRE-SHIP REVIEW

SYSTEMS OVERVIEWEllen Taylor

University of California - Berkeley


• PSR Overview• Review Purpose and Approach

• Requirement Verification Status• Performance Requirements - MRD Verification Status• Resource Budget Status

• Integration and Test • As-Run Environmental Test Flows• Environmental Test Requirements - ETM Verification Status• Operating Hours

• Current Test Activities • Mission Readiness Testing (Mission Simulations)• Tracking and Trending

• Launch Slip Impact• Mission Design Changes• Impact of Changes

• Problem Failure Reports (PFRs)• PFR Statistics and Status• Open PFRs and discussion• Closed PFRs unverifiable failures, impact to operations and risk list

Overview


Review Purpose and Approach

Mission PSR Review Purpose• Review results of Environmental Test Program• Assess readiness of flight hardware and software for Launch• Assess readiness of Launch Site Plans and Procedures

Review Approach• Instrument Suite and Probe Bus PSRs covered:

• Changes since CDR, problems encountered and close-out• Testing, qualification and performance verification at instrument and subsystem level

• Flight Operations Review covered:• Ground system, flight dynamics system, mission design (maneuver plan, orbit

determination, attitude determination)• Mission simulations, instrument and probe commissioning procedure and testing status

• This review will cover:• Changes since Mission PER, problems encountered and close-out• Testing and performance verification at system level• Test activities since PER, review of upcoming Launch Site activities

• MAIN FOCUS: Environmental Test Report (magnetics, vibration/shock/acoustics, spin balance, alignment and thermal vac) and Flight System Readiness


Performance Verification

Mission Requirements Document (MRD) Verification Matrix• MRD Verification Matrix is available on-line at: ftp://apollo.ssl.berkeley.edu/pub/THEMIS/1

Management/1.3 Systems Engineering/1. Requirements/thm_sys_001J_MRD.xls • 10/26/06 MRD Rev J: Released Verification Matrix for Mission PSR

MRD Recent Revisions• 10/05/06 MRD Rev I.1: Updated Requirements and Verification Matrix for Mission FOR• 06/23/06 MRD Rev I: Released Verification Matrix for Mission PER

Instrument and Probe Subsystem Verification Matrices presented at PSRs• 03/16/06 MRD Rev H: Released Verification Matrix for F2 Probe PER (1st Probe to JPL)• 03/23/06 MRD Rev H.1: Released Verification Matrix for F3 Probe Bus PSR• 05/05/06 MRD Rev H.2: Released Verification Matrix for FM4/FM5 Instrument Suite PSR• 05/04/06 MRD Rev H.3: Released Verification Matrix for F4 Probe Bus PSR• 05/31/06 MRD Rev H.4: Released Verification Matrix for F1 Probe Bus PSR• 06/12/06 MRD Rev H.5: Released Verification Matrix for F5 Probe Bus PSR


Performance Verification

MRD Status• Statistics

• 476 Requirements in MRD, not including Level 1 Science and Programmatic Requirements• 464 Requirements verified (GREEN)• 8 Requirements pending (YELLOW)• 4 Requirements waived (GREY)• 0 Requirements not met (RED)

0

10

20

30

40

50

60

PSRs MPER MPSR On Orbit

Pending

• Pending Requirements • No pending requirements are considered

liens to shipment to the Cape• Verification activities have been planned

for all pending requirements as part of normal course of Launch Site Activities or Mission Readiness Tests (MRTs)


MRD Verification Status

• 6 System (Level 2) Pending Requirements

LEVEL 2 REQUIREMENT STATUS

M-7 Probe Safe-State in any attitude Pending final power analysis in worst-case attitudes with test correlated thermal model to show viable safe-state (thermal, power).

M-8 Failure Detection and Correction Pending final Limit Monitoring (LM) and Real Time Sequence (RTS) verification.

M-33 Electrostatic Cleanliness Pending ESC Survey after all flight close-outs at Launch Site. Components surveyed. Integrated Probes surveyed at various stages of integration.

M-40 Performance Verification Pending completion of MRD Verification Matrix.

M-41 Environments Pending successful completion of Environmental Test Program (PCA Spin Balance) at Launch Site.

M-45 PCA Mass Pending PCA mass measurement and spin balance at Launch Site. Analysis and testing to date shows mass is on track.

• 2 Instrument and Probe Bus (Level 3) Pending Requirements

LEVEL 3 REQUIREMENT STATUS

PB.FSW-3 Code Image identical on all Probes Pending final FSW version and verification prior to launch.

IN.ESA-13 ESA On-orbit Calibration Pending on-orbit calibration, ESA ground cal complete.


MRD Verification Status (cont.)• 4 Requirements have been waived (GREY)

• IN.ESA-08: ESA Dayside Energy Flux

Requirement: The ion ESA geometric factor shall be attenuated in the solar wind to avoid saturation.

Waived: Requirement to measure the solar wind (SW) is met without attenuating the geometric factor. The AMPTEKs count at high enough rate and the angular width is small enough (1/4 and 1/2 of 22.5deg) to measure the SW speed and ion temperature/density without being saturated. The electron detector is also OK because the SW temperature is high enough to not need narrower view.

• IN.DPU-09: Stored Housekeeping Telemetry

Requirement: The IDPU DCB shall not erase instrument housekeeping telemetry from memory unless commanded to do so

Waived: Requirement to not erase instrument housekeeping telemetry in memory until commanded to do so is met by Probe Bus requirement PB.CDH-27. All instrument housekeeping telemetry (APID 404 and 406) is saved in the Probe BAU memory and erased only on command. Therefore, this is not a requirement on the DCB.

• IN.EFI-11: EFI Noise Level

Requirement: The EFI noise level shall be below 1 x 10^-4 mV/m/sqrt(Hz).

Waived: EFI measured noise level is 2 to 3 x 10^-4 mVm/sqrt(Hz). Slightly higher value does not have a significant impact on Level 1 science measurement.

• PC.Mech-1: Probe-to-Probe Static Clearance on Probe Carrier

Requirement: The Probe / Carrier shall accommodate 5 probes of the maximum mass allocation, with a minimum static clearance of 4 inches between adjacent Probes

Waived: Current static clearance is 3.75 inches. From analysis, does not affect dynamic clearance after deployment of 1 inch. See SAI-TM-3048 for MRD Waiver Justification.


Mass Status and History• Mass Status

• Probe Dry Mass is limiting mass resource

• Probe Dry Mass Current Best Estimate (CBE): 77.0 kg

• Measured Probe Dry Mass:

• Measured in flight configuration after Probe Spin Balance, corrected for sep system• < 2% mass deviation between Probes (requirement)

SPACECRAFT MASS

0.00

10.00

20.00

30.00

40.00

50.00

60.00

70.00

80.00

90.00

Ph

ase

A

8/0

3

10

/03

12

/03

2/0

4

4/0

4

6/0

4

8/0

4

10

/04

12

/04

2/0

5

4/0

5

6/0

5

8/0

5

9/0

6

Date

Mas

s (

kg)

Probe Dry Mass NTEProbe Dry Mass CBEProbe Bus CBEInstrument CBE

Corrected P-1 (MB deployed) 78.04 kg





• Mass History• Not to Exceed (NTE): 81.8kg• Mass Margin: 4.7%

(with 100% mass weighed)


Power Status and History• Power Status

• Increase in Probe power (since Probe Bus PSR) was from additional heater power predicted from updated thermal model. Heater power estimate contains most uncertainty, was verified during Probe Thermal Balance Test.

• Increase in capability was based on measured S/A LAPSS performance data coupled with battery time history analysis. Shows an additional 3.5W of continuous load can be supported and still fully recharge the battery.

SPACECRAFT POWER

0.00

5.00

10.00

15.00

20.00

25.00

30.00

35.00

40.00

45.00

PhaseA

8/03 10/03 12/03 2/04 4/04 6/04 8/04 10/04 12/04 2/05 6/05 8/05 10/05 12/05 2/06

Date

Po

wer

(W)

P1 Capability - Daylight Power

P1 Probe CBE

Probe Bus CBE

Instrument CBE

Probe CBE: 36.6 W

Probe Capability: 40.35 W

Probe Margin: 10.2%


F1-5 As-Run Test Flow

F1/2/5 MagneticsTest

Post-Ship LPTsand Pressurization

F1/5 Alignmentsand Spin Balance

• Mission PER: 06/23/06

PCA AcousticsTest

Probe SeparationTests

• thm-mint-proc-019 Probe CPT: 8/15-17/06• thm-mint-proc-033 Instrument CPT: 8/15-17/06• thm-mint-proc-019 SA Illumination: 8/15-17/06

F3/4 MagneticsTest

F1/5 Spin BalanceRe-Test

Post-Vibe LPTsSolar Array Tests

PCA Vibe/Sep Test w/ dummy masses

MissionPER

F3/4 TV Test(4 cycles)

• thm-mint-proc-049 Spin Balance: 7/25-28/06 PFR 209 Spin Balance: OPEN

PCA Vibration(X,Y,Z-axes)

F1/5 TV Test(4 cycles)

• thm-mint-proc-013 Probe LPT: 7/5-7/06• thm-mint-proc-032 Instrument LPT: 7/5-7/06• thm-mint-proc-124 RCS Press.: 7/6/06

F1/5 Alignmentsand Spin Balance

• thm-mint-proc-060 PCA Vibe: 7/7-8/06• thm-mint-proc-070 PCA Sep: 7/7-8/06

• thm-mint-proc-061 PCA Acoustics: 7/18/06 • thm-mint-proc-070 PCA Sep: 7/19-20/06

Post-Env. CPTsSolar Array Tests

• thm-mint-proc-074 PCA Vibe Config• thm-mint-proc-060 PCA Vibe: 7/13-17/06

• JPL Procedure: 8/3-4/06

• JPL Procedure: 7/26-28/06

Mission SimulationsBattery TrendingSpacecraft Health and Status Checks

• thm-mint-proc-013 Probe LPT: 7/20-24/06• thm-mint-proc-032 Instr. LPT: 7/20-24/06• thm-mint-proc-019 SA Illumination: 7/20-22/06

• thm-mint-proc-047 TV Procedure: 7/27-8/2/06• thm-mint-proc-052 TV Functional: 7/27-8/2/06• TV Test Plan and As-Run Log

• thm-mint-proc-049 Spin Balance: 7/27-8/2/06

• thm-mint-proc-047 TV Procedure: 8/4-10/06• thm-mint-proc-052 TV Functional: 8/4-10/06• TV Test Plan and As-Run Log

• thm-mint-proc-049 Spin Balance: 8/15/06 PFR 209 Spin Balance: CLOSED


Environmental Test Verification

Environmental Test Matrix (ETM)• No changes or deviation in test plan since the PER

• All environmental tests are now complete except PCA Spin Balance

• System Level ETM:

NOTES:

A = Analysis Q = Qualification unit only

T = Test I = Inspection

TS = Test on 1st unit only, rest by similarity W = Weigh

TL = Limited Test

OTHER

COMPONENT (ITEM)

QU

AN

TIT

Y

SU

PP

LIE

R

ALI

GN

ME

NT

MO

DA

L S

IGN

AT

UR

E/S

UR

VE

Y

SIN

E B

UR

ST

RA

ND

OM

VIB

RA

TIO

N

SIN

E V

IBR

AT

ION

AC

OU

ST

IC

PR

OO

F T

ES

T

CLA

MP

BA

ND

SH

OC

K

VE

NT

ING

/PR

ES

SU

RE

PR

OF

ILE

MA

SS

PR

OP

ER

TIE

S

ME

CH

IN

TE

RF

AC

E

SP

IN B

ALA

NC

E

INT

ER

FA

CE

VE

RIF

ICA

TIO

N

CO

ND

UC

TE

D E

MIS

SIO

NS

CO

ND

UC

TE

D S

US

CE

PT

IBIL

ITY

RA

DIA

TE

D E

MIS

SIO

NS

RA

DIA

TE

D S

US

CE

PT

IBIL

ITY

TH

ER

MA

L V

AC

UU

M

TH

ER

MA

L B

ALA

NC

E

# O

F T

HE

RM

AL

CY

CLE

S

ES

C A

ND

GR

OU

ND

ING

DC

MA

GN

ET

ICS

AC

MA

GN

ET

ICS

BA

KE

OU

T

RA

DIA

TIO

N

Instrument Suite 6 UCB T TS TS T 6 TS TInstruments and IDPU 1 TUBS T T A T T A W I T T 2 T M T AProbe Subsystems SAI T T A T/A A/T A T Q/A A W I T TS TS TS TS T 8 T M T A Integrated Probe F2 1 UCB T T T T T T W I T T self self T T T T 4 T M T T Integated Probes F1, F3-5 4 UCB T T T T T W I T T self self TS TS T TL 4 T M T TProbe Carrier 1 SAI T T A W IProbe Carrier Assembly 1 SAI T T A W I T

CONTAMINATIONHARDWARE MECHANICAL ELECTRICAL THERMAL

TW I


• Power Log – Hours for Integrated Probe System:

• Components accumulated additional 500-800 hours run time prior to integration. • Failure Free Hours: Hours accumulated on core system after return of transponder and BAU

during mission integration. • Late Instrument Swaps: Spare SST swapped in prior to TVac (>100 hours gained on integrated

system). Spare SCM swapped in early October (>100 hours gained at component level TV prior to integration onto Probe).

• Thermal Vacuum Hours: 120-150 failure free hours were accumulated during TVac

Goal to have 100 failure free hours on Integrated Probes prior to delivery to the Cape has been met

Operating Hours

0

50

100

150

200

250

300

350

400

Hours Failure Free

F1F2F3F4F5


• Flight Probes located at JPL • Probe State of Health Tracking per THM-MINT-PROC-109 JPL Tracking Log

– Visual Check, Purge Flow, Tank Pressure Check

• Probe Trending per THM-MINT-PROC-106 Battery Trending Procedure– Performed approximately every two weeks

• Mission Readiness Testing per THM-SYS-019 Mission Readiness Test Plan– Network connectivity and data path tests between JPL and UCB MOC

– Mission simulations: Maneuver simulations, orbit simulations, commissioning procedures, launch countdown practice

– Training exercises for Flight Operations Team

• FlatSat Environment (Probe Simulator) located at UCB and at Swales• Developed by Swales and Hammers

– Includes BAU EDU, IDPU ETU & Simulator (Instrument Flight Spare can be swapped instead fo Simulator), ITOS Workstation and VirtualSat

• Used extensively (daily) for Mission Readiness Testing since June 2006– Mission simulations prior to being run on flight system– Training exercises, specifically contingency operations– Pre- and Post-launch testing of flight software patches, updated tables and new

procedures

Current Test Activities


MRT Summary

• Mission Readiness Testing (MRT)• Consists of over 230 specific tests• Tracked daily in stand-up meetings with team, weekly summary meetings with GSFC • On track to complete >90% by L-2 months (configuration freeze)

Test Group Completed L - 2 Months L - 1 Month Launch Launch + Total

Ground Systens 10 1 1 0 0 12

Flight Systems 22 2 0 0 0 24

Interfaces and Data Flows 25 3 1 0 0 29

Ground Operations 29 11 1 0 0 41

Launch Operations 5 8 0 0 0 13

Special Operations 13 2 0 0 0 15

Maneuver Operations 32 7 0 0 3 42

Normal Science Operations 12 21 5 0 0 38

Contingency Operations 5 12 0 0 0 17

Operational Readiness (Non Certifications)

0 0 5 1 0 6

Totals 153 67 13 1 3 237

Totals (%) 65% 28% 5% 0% 1%

THEMIS MISSION READINESS TESTS - SUMMARY


Battery Trending

• Battery Capacity Trending• Started trending all flight batteries in June ’06 in response to Probe Bus 1 PSR RFA #7 • All eclipse loads on, discharge for nominal eclipse time of 1 hour• Battery voltage, current and temperature recorded• Voltage set to 32V, voltage drops 0.4V to 0.5V in 1 hour

• Battery Capacity Results to date• Average drop is 0.469V in one hour• Value has been consistent over past 15 weeks• Maximum difference is 50mV from the average• All probes consistent (no outliers)• Indicates all flight batteries are stable, no degradation seen within measurement

capabilities


• Mission Profile, October 19-2006

• Mission Profile, January 20-2006: First tail season targeted for 1 year later

• Mission Profile, February 15-2006: No major change in profile, just shortened Coast Phase.

Launch Slip Impact


• Technical Impact from Change in Mission Profile• EFI Boom Deploy delayed ~ 9 months (L+330d instead of L+63d) on Probes 1 and 5

– THEMIS lifetime test showed no issue: Motor at elevated temperature (50C) for 21 months, worst-case starting current (related to concern of lubrication migration in the gearbox over time) was within expectation

– CLUSTER lifetime tests also relevant and showed no issue

• RCS Re-pressurization delayed about 6 months – No concern over the time on-orbit to recharge, nothing in the sequence is life limited (from

Swales RCS lead)– Cassini waited several years to do the recharge. Other Pyros have been fired after many

years in space and show no signs of loss of performance.

• Radiation environment worse in cruise orbit, affecting total dose prediction– All systems designed with Radiation Design Margin of 2– IRUs were identified as having radiation susceptibility, show a change in bias voltage.

Operational trending will track bias voltage during cruise phase so use during later ascent will not be an issue.

• Power considerations– Much better launch orientation, side solar arrays close to normal, nominal orientation– No change from previous worst-case analyses in number or duration of eclipses (battery

DOD%, battery fade calculations)

• Thermal environment– Bracketed by previous worst-case analyses, updated pass plan still being evaluated for full

run of on-orbit predicts

Launch Slip Impact


PFR Summary

PFR Statistics – 34 PFRs logged since Mission PER (PFR197 – PFR231)


PFR SummaryPFR Statistics - 34 from Environment Test Program: 33 Closed (0 Unverifiable), 1 Open • Open PFR 229

• PROBLEM: SC Event Message: CheckSum (CS) Memory Scrub Failure logged during maneuver simulations on the Probe and FlatSat

• RESOLUTION: Event Message indicates Bulk Memory Scrub failure. Single bit error is found and corrected on-board. No adverse affects have been

noted. Although impact is minor, further investigation into cause on-going. Problem has been recreated a number of times on FlatSat West, seems to be caused by changing filter tables. Swales/Hammers still trying to recreate on FlatSat East.

• PFR is not considered a lien against going to Launch Site


PFR Summary

Closed PFRs - If applicable, closed PFRs are moved to “UCB Watch List” which includes

• Unverifiable Failure List (UVF):• Moved to UVF List when a specific problem can not be reproduced and therefore not

definitively fixed. • Although not proven, a best guess of what occurred is listed, as well as an impact risk

assessment if the problem were to show up at a later date. • Unverifiable failures from Swales have been transferred to UCB system if they require a

“UCB watch.” All Swales unverifiable failures are tracked as risks.

• Operational Impact List: • Moved to the Operational Impact List when a problem is considered minor enough to “fly-

as-is,” but an operational work-around is required. • The work-around can be action the Ops team must take to avoid the problem or simply

knowledge that the issue exists.

• Risk List: • Moved to the Risk List when an problem is closed, but some residual risk remains. • Risk List is provided to Explorers and includes risk statement, impact, mitigation,

probability of occurrence, risk level and status.


BACK-UP

Closed PFR Lists - Unverifiable Failure List

Operational Impact List

Risk List

Mission I&T Procedure List


Unverifiable Failure List

PFR # Problem Description Best Guess Risk AssessmentPFR 039 FGM high telemetry (TMH) showing bit errors due to apparent

misconfiguration. Problem could not be recreated after power cycle.

Probably related to same software issue as 45 and 65: packet minimums not big enough. Problem has not re-occurred since packet minimums were worked out.

LOW: Temporary corruption of FGM data only. As shown in test, FGM data can be recovered after power cycle.

PFR 062 EFI V1 failing Functional Tests during TVAC testing of the FM1 Instrument Suite. Problem could not be recreated in re-test after cables were disconnect cables and inspected.

Most likely cause is that the sphere was being intermittently grounded as seen on Instrument EFI F3 and solved by an additional insulator.

LOW: Affects EFI internal diagnostic test only, not data. Only an issue in initially determining EFI SOH, would not be a problem on orbit after booms are deployed.

PFR 070 FM1 GSE was inadvertently disconnected. IDPU had apparent FSW corruption, after reconnection. Problem could not be recreated after power cycle.

System not designed to operate with all communications are removed and re-established without a reset into a known state.

LOW: Temporary loss of all science and instrument housekeeping data. Communication can be re-established with cold restart to the IDPU.

PFR 074 SST Sensor Channel 2 showed intermittent failure during Hot Cycle TVAC Instrument Suite testing. Problem could not be recreated in re-test.

Most likely caused by low voltage on the FPGA. This problem was solved in response to a later PFR by increasing the voltage from 2.5 to 2.6V.

LOW: Intermittent loss of SST data in only one channel. If indicative of total loss, only one channel of the dual sensor head would be affected.

PFR 108 ETC EEPROM Table did not load correctly in one instance. Problem could not be recreated.

EEPROM not loading correctly has to happen as the DCB is turned off and writes are enabled. Software protection on the EEPROM was not being used, but subsequently will be with procedures to Lock and Unlock.

LOW: Temporary loss of ESA and SST data. As shown in test, EEPROM table can be re-loaded without issue.

PFR 121 (Swales PRB 0097). One instance of an unexpected current draw was seen on the GSE when IDPU enabling plug was installed during the initial safe-to-mate of the IDPU ETU.

Fishbone of possible causes provided in response to Probe Bus PSR RFA #3. If failure occurs again, additional current draw will be obvious. Problem not seen again after numerous installations of the enabling plug.

LOW: Additional current draw was minimal in comparison to overall power budget.

PFR 130 One instance of BAU corrupting an IDPU command was logged during IDPU/BAU reset investigation.

Most probable cause is noise on the line due to break-out configuration. All corrupted commands are identified w/ checksum error reporting in IDPU. Problem not seen with Probes in flight configuration.

LOW: Corrupted command would not.be executed. If seen on orbit, IDPU would report CS error and command would have to be resent.

PFR 131 One instance of IDPU was rejecting all commands send during IDPU/BAU reset investigation.

Most probable cause is memory corruption due to IDPU reset problem. Reset problem fixed, problem not seen again (expected/received command counter used during testing).

LOW: Temporary loss of command capability to IDPU. If seen on orbit, IDPU would report discrepancy between expected and received command counter. As shown in test, IDPU accepted commands after cold restart.

PFR 147 One unexplained BAU reset during IDPU safe-to-mate after BAU reset problem was suppose to have been fixed.

Most probable cause is break-out configuration caused noise on the line. Problem has not been seen again with Probes in flight configuration.

LOW/MED: Cold reset of BAU on orbit would set Probe to known default state. Default state is safe configuration. Low/Medium risk is assigned because operations could be significantly impacted depending on when in mission restart occurred (i.e. during a m


Unverifiable Failure List (cont.)

PFR 161 Intermittent receiver lock was noted during low-level vibration sequence, but started before actual vibe.

All telemetry consistent with receiver actually locking on a signal. Hat coupler was off for vibe, and some signals radiated at JPL are near THEMIS frequency. No other instance was seen throughout JPL testing.

LOW: Intermittent receive capability during launch would not impact mission as no commands are issued.

PFR 172 K1 Battery Relay changed state during EGSE #2 checkout. Not reproduce-able.

No mechanism (command or otherwise) is available to turn on only one of the battery relays and not the other. Therefore, the DaqScan 2000 DAC which controls the switches on the Umbilical Drawer was hypothesized to be the source of the anomaly. By defaul

LOW: Only a monitor problem on the GSE. Battery relay state is redundant. Battery is not actually taken off line.

SAI # Problem Description Best Guess Risk AssessmentSAI PRB 0215

BAU 101 cold restart and command rejection. Not reproducible Commands were processed correctly when DPC current limit (at umbilical rack) was increased to 1.0A. BAU restarts and command rejection was monitored throughout I&T at UCB, problem has not re-occurred.

LOW/MED: Cold reset of BAU on orbit would set Probe to known default state. Default state is safe configuration. Low/Medium risk is assigned because operations could be significantly impacted depending on when in mission restart occurred (i.e. during a m

SAI PRB 0340

Thruster stop times for VirtualSat out of expected range. Attempt to recreate problem unsuccessful.

Verification of stop times will be affected by relative drift of VirtualSat clock, ITOS clock, and BUA clock. Likely that ITOS clock drift was responsible for stop time discrepancy.

LOW: Stop time showed small descrepancy in error, drifted up as test progressed. Such a small error would be noticed in manuever reconstruction and calibration, but would not affect the successful manuever execution.

PFR # Problem Description Best Guess Risk Assessment


Operational Impact ListPFR # Subsystem Problem Description Operational Work-aroundPFR 030 All Probes

ActuatorsPCB FPGA accepts actuator commands only if actuator voltage is present. If SC actuator supply trips off during actuation, PCB will not turn off actuator switch. Thus, actuator will be active when actuator supply voltage is re-enabled.

In the event that the SC Actuator supply trips off during an actuation, the ground must enter a SAFE command prior to re-enabling supply. (SAFE command has IPCB_ACTREST which resets all instruments and states).

PFR 075 All ProbesESA

ESA High Voltage tripped off during Suite Thermal Vacuum testing due to in-rush.

PCB supplies must be forced on during Low Voltage, High Voltage and HV level adjustment. Current trip should be re-enabled after during normal operations.

PFR 164 All ProbesESA

Unloaded ESA supply causes IDPU current oscillation at narrow temperature range around 10degC.

Oscillation would only be seen if ESA was off over narrow temperature range. FOT alerted that condition can be expected and causes no damage.

PFR 183 Probe CEFI

Lower AXB (V6) EFI channel responded anomalously during EFI Functional Test (DC excitation higher amplitude and noisier, AC excitation high-pass filtered).

Not an issue after AXB deploy. Unit still provides sufficient SOH (through anomalous, but consistent DC response) information to make probe assignment decision.

PFR 205 All ProbesRCS/Thermal

A cold spot on the RCS thermal control system causes the RCS line to get colder than specification if only the secondary heater is on (RCS thermostat closes at <3 degrees)

Very serious issue only if Primary Heater fails as fuel freezes at 0 degrees C. Additional operational precautions (such as shadow avoidance maneuvers and achieving bus heating attitudes) must be taken if Primary RCS heater fails.

PFR 206 Probe DEFI

F4 AXB temperature sensor reads incorrectly (1052C). Performance of associated EFI channel not affected.

Temp sensor not critical for operation of the EFI. Failed state of the F4 AXB temp sensor noted by FOT to avoid alarm over condition.

PFR 210 All ProbesFSW

The first pulse of some maneuvers were not being executed due to how the FSW buffers were handling start/stop thrust times.

A critical stop command prior to new thrust commands will clear all registers and always solve this problem. Critical stop should automatically be built into all ATS maneuver loads.

PFR 226 Probe AThermal

Two monitors, BTMPRCSLN1 and BTMPRCSSVC were swapped on F1. RCS Line 1 (LN1) is registering the temperature of the RCS solenoid valve (SVC).

BTMPRCSLN1 and BTMPRCSSVC mnemonics need to be swapped in Probe specific ITOS database, Probe A only.

PFR 230 All Probes FSW

Onboard 20Hz thruster counter not accurate (5-10% off actual) For Spin Up and Attitude Change Maneuvers, sun angle and spin rate should be used as verification instead of counter. For Axial or Side Thrusts, the counter should be used for realtime verification, and can be assumed everything went fine if reads within 5-10% of expected. VC4 data should be used for thruster reconstruction and calibration.

PFR 231 All Probes FSW

Onboard command counter is inaccurate (count rate is 25% too high, and enters long periods of time where it does not increment at all) in FSW Build3.19.

Operations will NOT use the uplink_timer in any Limit Monitoring action. LM09 in FSW 3.19 EEPROM, which uses the counter to enter a “broadcast” mode should be disabled and left that way. The purpose of LM09 was to provide some action if the probe was not heard from in 5 days. Instead of on-board LM, if this condition is see on-orbit, Operations will follow a specific contingency plan to send "hardware" commands from the ground to reset the communications board.

SAI # Subsystem Problem Description Operational Work-aroundSAI PRB 0339

Probe AThermal

IRU measurements out of range for first two samples of each second. Cannot prevent noise in samples, investigating removing first two samples in attitude determination processing.

First two samples of IRU measurements throughout I&T and On-orbit Operations for further degradation.


Risk List


Procedure ListMission Integration and Test Procedures Due DateUCB Harris thm-mint-proc-010 THEMIS Probe Power On/Off Procedure - Released THM_MINT_PROC_010_ProbePwr CompleteUCB Harris thm-mint-proc-011 THEMIS Probe Umbilical Safe-to-Mate C Released THM_MINT_PROC_011C_ProbeSTM CompleteUCB Harris thm-mint-proc-012 THEMIS Probe CPT Procedure C Released THM_MINT_PROC_012C_ProbeCPT CompleteUCB Harris thm-mint-proc-013 THEMIS Probe LPT Procedure F Released THM_MINT_PROC_013F_ProbeLPT CompleteUCB Harris thm-mint-proc-014 THEMIS Probe AT Procedure - Released THM_MINT_PROC_014_ProbeAT CompleteUCB Donakowskithm-mint-proc-015 THEMIS Probe Handling Procedure H Released THM_MINT_PROC_015H Probe handling ProcedureCompleteUCB Berg thm-mint-proc-016 THEMIS Probe EMC/EMI Signatures C Released THM_MINT_PROC_016c_EMI_EMC Signature Complete UCB Taylor thm-mint-proc-017 THEMIS Probe Self Compatibility A Released THM_MINT_PROC_017a_Probe SCT CompleteUCB Turin thm-mint-proc-018 THEMIS Probe Side Solar Array Installation/Removal ProcedureB Released THM_MINT_PROC_018b SIDE SOLAR ARRAY PROCCompleteUCB Curtis thm-mint-proc-019 THEMIS Probe Solar Array Illumination Procedure A Released THM_MINT_PROC_019A_SA Illumination Complete

UCB Turin thm-mint-proc-100 THEMIS BAU Removal Procedure - Released THM_MINT_PROC_100 BAU Removal Procedure CompleteUCB Taylor thm-mint-proc-101 THEMIS PFR Close-out from P2 Initial Integration - Released THM_MINT_PROC_101_F2 PFR Close-out CompleteUCB Taylor thm-mint-proc-102 THEMIS Thermal Vacuum Functional Configuration Test - Released THM_MINT_PROC_102 TVac Configuration CompleteUCB Dalton thm-mint-proc-103 THEMIS Probe Top/Bottom Solar Array Installation/Removal - Released THM_MINT_PROC_103 TOP-BOTTOM SOLAR ARRAY PROCCompleteUCB Plauche thm-mint-proc-104 THEMIS Mag Boom Shim Replacement - Released THM_MINT_PROC_104 Mag Boom Shim ReplacementCompleteUCB Harris thm-mint-proc-105 THEMIS Simulated Pyro Test Procedure B Released THM_MINT_PROC_105B_PyroTest CompleteUCB Harris thm-mint-proc-106 THEMIS Battery Trending Test Procedure A Released THM_MINT_PROC_106a BatteryTrend CompleteUCB Sholl thm-mint-proc-107 THEMIS PPMU Safe-to-Mate Procedure - Released THM_MINT_PROC_107 PPMU_STM CompleteUCB Sholl thm-mint-proc-108 THEMIS PPMU Operations Manual - Released THM_MINT_PROC_108_PPMU operational instructionsCompleteUCB Taylor thm-mint-proc-109 THEMIS JPL Tracking Log - Released THM_MINT_PROC_109 JPLTracking Complete

UCB Scholz thm-mint-proc-020 THEMIS Instrument Harness Installation - Released THM_MINT_PROC_020_THEMIS Flight Harness InstallationCompleteUCB Elliot thm-mint-proc-021 THEMIS IDPU/ESA Mechanical Integration Procedure B Released THM_MINT_PROC_021b IDPU INTEGRATION TO PROBECompleteUCB Turin thm-mint-proc-022 THEMIS SST Mechanical Integration Procedure C Released THM_MINT_PROC_022C SST Mechanical Integration ProcedureCompleteUCB Donakowskithm-mint-proc-023 THEMIS SPB Instrument Mechanical Integration Procedure A Released THM_MINT_PROC_023a SPB_INTEGRATION_PROCEDURECompleteUCB Turin thm-mint-proc-024 THEMIS FGM Sensor Mechanical Integration Procedure A Released THM_MINT_PROC_024A FGM Sensor Mechanical Integration ProcedureCompleteUCB Turin thm-mint-proc-025 THEMIS SCM Sensor Mechanical Integration Procedure A Released THM_MINT_PROC_025A SCM Sensor Mechanical Integration ProcedureCompleteUCB Duck thm-mint-proc-026 THEMIS Mag Boom Mechanical Integration and Alignment A Released THM_MINT_PROC_026a Mag Boom Mechanical Integration ProcedureCompleteUCB Turin thm-mint-proc-027 THEMIS Mag Boom Mechanical Clearance Verification - Released THM_MINT_PROC_027 Mag Boom Mechanical Clearance VerificationCompleteUCB Harris thm-mint-proc-028 THEMIS IDPU Electrical Integration Procedure C Released THM_MINT_PROC_028c_IDPU Integration CompleteUCB Taylor thm-mint-proc-029 THEMIS Particles Electrical Integration Test B Released THM_MINT_PROC_029b_Particles Electrical IntegrationCompleteUCB Taylor thm-mint-proc-030 THEMIS Fields Electrical Integration Test A Released THM_MINT_PROC_030a_Fields Electrical IntegrationCompleteUCB Taylor thm-mint-proc-031 Deleted - THEMIS Deployment Verification Test - covered in LPTN/A N/A N/A N/AUCB Taylor thm-mint-proc-032 THEMIS Instrument LPT Procedure D Released THM_MINT_PROC_032d_Instrument LPT CompleteUCB Taylor thm-mint-proc-033 THEMIS Instrument CPT Procedure B Released THM_MINT_PROC_033b_Instrument CPT CompleteUCB Taylor thm-mint-proc-034 THEMIS Instrument AT Procedure - Released THM_MINT_PROC_034_Instrument AT CompleteUCB Taylor thm-mint-proc-035 THEMIS Closed Loop ACS Test Procedure - Released THM_MINT_PROC_035_ClosedLoopACS CompleteUCB Turin thm-mint-proc-036 THEMIS SST Connector Plate Alignment Procedure A Released THM_MINT_PROC_36A SST Connector Plate Alignment ProcedureCompleteUCB Plauche thm-mint-proc-037 THEMIS Mag Boom Position Calculation Procedure B Released THM_MINT_PROC_037b Mag Boom Position Calculation ProcedureCompleteUCB Plauche thm-mint-proc-038 THEMIS Mag Boom Restow Procedure - Released THM_MINT_PROC_038 Mag Boom Restow ProcedureCompleteUCB Turin thm-mint-proc-039 Deleted - THEMIS Instrument Closeout Procedure - covered in specific close-out proceduresN/A N/A N/A N/AUCB Taylor thm-mint-proc-040 THEMIS Instrument SPB Deploy Procedure - Released THM_MINT_PROC_040_Instrument SPB Deploy Complete


Procedure List (cont.)

UCB Donakowskithm-mint-proc-120 THEMIS Facility and MGSE Magnetic Test Procedures - Released THM_MINT_PROC_120_Magnetics Survey CompleteUCB Ludlam thm-mint-proc-121 THEMIS Component Magnetic Test Procedure - Released THM_MINT_PROC_121_Component Mag CompleteUCB Elliot thm-mint-proc-122 THEMIS ESA/SST Purge Hookup Procedure D Released THM_MINT_PROC_122d Purge Connection ProcedureCompleteUCB Donakowskithm-mint-proc-123 THEMIS ESA/SST Radiation Source Handling Procedure - Released THM-MINT-PLN-123 REV- DRAFT 23JAN06 CompleteUCB Sholl thm-mint-proc-124 THEMIS RCS Recharge to 50psi - Released THM_MINT_PROC_124_RCS low pressure CompleteUCB Bonnell thm-mint-proc-125 THEMIS Probe ESC Closeout Procedure A Released THM_MINT_PROC_125a_ESC Closeout CompleteUCB McCauley thm-mint-proc-126 THEMIS Magnetic Screening and Degaussing Procedure A Released THM_MINT_PROC_126_RA_MAG SCREENING AND DEGAUSSINGCompleteUCB Sholl thm-mint-proc-127 THEMIS RCS Pressurization for Vibration - Released THM_MINT_PROC_127 Vibe Test Pressurization CompleteUCB Donakowskithm-mint-proc-128 THEMIS Handling of Pyrotechnic Devices - Released THM-MINT-PLN-128 PYROTECHNIC HANDLING PLANCompleteUCB Sholl thm-mint-proc-129 THEMIS Pressure Test Panel and Line Proof Test - Released THM_MINT_PROC_129_PressureLineProof CompleteUCB Donakowskithm-mint-proc-130 THEMIS Installation and Removal of Radiation Sources into TVAC chamber - Released THM_MINT_PROC_130_Radiation Sources Instl CompleteUCB Bonnell thm-mint-proc-131 THEMIS MSSS Exposed Insulator Overtapping Procedure - Released CompleteUCB Donakowskithm-mint-proc-132 THEMIS EGSE RACKS Moving Procedure - Released THM_MINT_PROC_132 EGSE RACK PROCEDUREComplete

UCB Curtis thm-mint-proc-041 THEMIS Probe EMC Test Procedure B Released THM_MINT_PROC_041b_Probe EMC Test CompleteUCB Ludlam thm-mint-proc-042 THEMIS Probe Magnetics Test Procedure - replaced by JPL ProcN/A N/A N/AUCB Pankow/Donakowskithm-mint-proc-043 THEMIS Probe Vibration Test Procedure Rev 5 Released THM_MINT_PROC_043_Vibration_Rev5 CompleteUCB Pankow/Donakowskithm-mint-proc-044 Deleted - covered in -043 (THEMIS Probe Pair Vibration Test Procedure)N/A N/A N/AUCB Harris thm-mint-proc-045 THEMIS Probe Vibration Test Electrical Configuration B Released THM_MINT_PROC_045B_VibeConfig CompleteUCB Smith thm-mint-proc-046 THEMIS Probe TV Test Procedure A Released THM_MINT_PROC_046a2_TV Procedure CompleteUCB Smith thm-mint-proc-047 THEMIS Probe Pair TV Test Procedure - Released THM_MINT_PROC_047_ Probe Pair TV CompleteUCB Taylor thm-mint-proc-048 THEMIS Probe TV Functional A Released THM_MINT_PROC_048a T-V Functional CompleteUCB Pankow/Donakowskithm-mint-proc-049 THEMIS Probe Spin Balance Procedure Rev4 Released THM_MINT_PROC_049-Probe_Spin_Balance_rev_4CompleteUCB Bester thm-mint-proc-050 THEMIS Probe CTV RF Compatibility Test Procedure - Released THM_MINT_PROC_050_RFCTP-2nd Draft_9-23-05Complete KSC Davis thm-mint-proc-051 \THEMIS Probe Fueling Procedure (KSC Proc)UCB Harris thm-mint-proc-052 THEMIS Probe-InstrumentThermal Vac LPT - Released THM_MINT_PROC_052_TV-LPT CompleteUCB Taylor thm-mint-proc-053 THEMIS Probe Pre-Launch Closeout Procedure - Released THM_MINT_PROC_053_ProbeCloseOut CompleteUCB Berg thm-mint-proc-054 THEMIS Probe Battery Ops Procedure D Released THM_MINT_PROC_054d Battery Handling Plan CompleteUCB Sholl thm-mint-proc-055 THEMIS Probe RCS Pressure Test and Leak Check B Released THM_MINT_PROC_055b RCS PressureTest CompleteUCB Elliot thm-mint-proc-056 THEMIS Probe Rollover Procedure - Released THM_MINT_PROC_056- Complete UCB Turin thm-mint-proc-057 Deleted N/A N/A N/AUCB Elliot thm-mint-proc-058 THEMIS Probe Lift in Rollover Fixture Procedure - Released THM_MINT_PROC_058- Complete UCB Elliot thm-mint-proc-059 THEMIS Probe Thermal Vac Chamber Loading Procedure - Released THM_MINT_PROC_059- Complete

UCB Smith thm-mint-proc-140 THEMIS Probe Thermal Closeout Procedure A Released THM_MINT_PROC_140a_Thermal Closeout CompleteUCB Dalton thm-mint-proc-141 THEMIS Separation System Stow Procedure A Released THM_MINT_PROC_141a SEPSYS STOW Complete


Procedure List (cont.)

UCB Pankow/Donakowskithm-mint-proc-060 THEMIS PCA Vibration Test Procedure R6 Released THM_MINT_PROC_060_PCA_Vibration_rev_6 CompleteUCB Pankow/Donakowskithm-mint-proc-061 THEMIS PCA Acoustics Test Procedure - Released THM_MINT_PROC_061_PCA_Acoustics CompleteUCB Turin thm-mint-proc-062 THEMIS PCA LV Mate Procedure D Released THM_MINT_PROC_062D PCA LV Mate ProcedureCompleteUCB Taylor/Harristhm-mint-proc-063 THEMIS PCA Electrical Test Procedure Draft Released THM_MINT_PROC_063_draft_PCAElectrical CompleteUCB Harris thm-mint-proc-064 Deleted N/A N/A N/AUCB Taylor/Harristhm-mint-proc-065 THEMIS PCA Launch Tower Electrical Test Procedure (at Block House)Draft In Progress L-55 daysUCB Taylor thm-mint-proc-066 THEMIS PCA Pre Launch Closeout Proc Draft In Progress L-55 daysUCB Pankow/Donakowskithm-mint-proc-067 THEMIS PCA Spin Balance Procedure Draft In Progress L-55 daysUCB Dalton thm-mint-proc-068 THEMIS PCA Lifting and Handling Procedure - Released THM_MINT_PROC_068_PCA Lifting-Handling ProcCompleteUCB Dalton thm-mint-proc-069 THEMIS PCA Assembly Procedure - Released THM_MINT_PROC_069_PCA Assy Proc CompleteUCB Turin thm-mint-proc-070 THEMIS PCA Separation System Test Procedure E Released THM_MINT_PROC_070E THEMIS Sep Sys Test ProcCompleteUCB Dalton thm-mint-proc-071 THEMIS PCA Purge Bag Installation and Removal - Released THM_MINT_PROC_071 PURGE BAG INSTL CompleteUCB Turin thm-mint-proc-072 Deleted - THEMIS PC/Mass Dummy Separation N/A N/A N/AUCB Curtis thm-mint-proc-073 THEMIS PCA EGSE Safe-to-Mate A Released THM_MINT_PROC_073A CompleteUCB Harris thm-mint-proc-074 THEMIS PCA Vibration Electrical Configuration A Released THM_MINT_PROC_074A_PCAVibeConfig CompleteUCB Harvey thm-mint-proc-075 THEMIS PC SSS Removal - Released THM_MINT_PROC_075_SSS_Removal CompleteUCB Taylor thm-mint-proc-076 Deleted N/A N/A N/AUCB Sterling/Chenthm-mint-proc-077 THEMIS Probe Simulator to Blockhouse EGSE Verification Check-Out ProcedureDraft In Progress L-55 daysUCB Curtis thm-mint-proc-076 THEMIS PCA to USPP Safe-to-Mate Draft In Progress L-55 daysUCB Taylor thm-mint-proc-077 THEMIS PCA Launch Countdown B Released THM_MINT_PROC_077B_LaunchCountdown CompleteUCB Sholl thm-mint-proc-078 THEMIS RCS THEMIS Post-Fueling Verifications and Closeouts # Assigned L-55 days

UCB Bester thm-mint-proc-080 THEMIS Probe End-to-End with BGS/MOC E Released THM_MINT_PROC_080e_bgs_probe_end_to_end_testCompleteUCB Bester thm-mint-proc-081 THEMIS Launch & Early Orbit Simulations # Assigned L-1 monthUCB Bester thm-mint-proc-082 THEMIS Contingency Procedures # Assigned L-1 monthUCB Sterling thm-mint-proc-083 THEMIS UCB Ground Station RF System Sensitivity Test Draft In Progress L-1 monthUCB Bester thm-mint-proc-084 THEMIS Telemetry Format Verification C Released THM_MINT_PROC_084c_telemetry_format_verificationCompleteUCB Bester thm-mint-proc-085 THEMIS Probe Clock Tests C Released THM_MINT_PROC_085c_probe_clock_tests CompleteUCB Sterling thm-mint-proc-086 THEMIS RF Chirp Test #Assigned L-55 days

mpsrsys- 1 ucb, oct 26, 2006 themis mission pre-ship review systems overview ellen taylor university...

Documents