Technical Progress Report
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January 2006
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Mr. Frank Snow, Code 410.0
THEMIS Mission Manager
Goddard Space Flight Center
Greenbelt, MD. 20771
Subject: THEMIS Monthly Technical Report
Dear Frank,
Enclosed is a copy of the monthly technical report for the THEMIS project.
Copies have been distributed as itemized below.
Additional details on the status of the program are available at any time at the
THEMIS ftp site:
ftp://apollo.ssl.berkeley.edu/pub/THEMIS/1.1%20Management/REPORTS/
If you have any questions, please don’t hesitate to call.
Sincerely,
Peter R. Harvey
THEMIS Project Manager
University of California, Berkeley
Cc:
Michael P. Riley, Contractor Officer, Code 210S
Technical Information Services Branch, Code 239
Dr. Vassilis Angelopoulos, Principal Investigator
Dr. David Sibeck, Project Scientist, Code 696
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1. Summary Status and Accomplishments
1.1 Mission Management
Written by Peter R. Harvey
In January, both BAU and IDPU teams solved problems in their avionics computers.
Retesting completed at the unit level and teams set plans for continuing probe integration
next month.
Technical margins including thermal were re-confirmed as stable and adequate for the
mission.
1.2 System Engineering
Submitted by Ellen Taylor
1.2.1 Requirements and Verification
Pre-Ship Reviews (PSRs) for the flight BAU, Build 3 FSW and Virtual Sat are planned
for early next period. Later in the period, a PSR for the Instrument Suites 4 and 5, a PSR
for the 2nd Probe (F3) and a Pre-Environmental Review for the Integrated Probe will be
held.
The MRD will be updated for each one of these reviews with a major release (Rev H)
expected at the PER. Minor changes to the BAU requirements in the MRD are expected
and have already been discussed. System Change Notices (SCNs) will be initiated for
any and all changes.
1.2.2 Integration and Test
FM4-FM5 Suites started Environmental Test in the last period with successful Vibration
Test. Two major PFRs have occurred during the TV cycle tests of FM4-5: IDPU
resetting when SST was turned on; and an oscillation at very cold temperatures of the
ESA 28V Supply. Both problems have been evaluated, and solutions tested.
Modifications to the boards in all units are ongoing. The team still expects to complete
FM4-5 TV cycling early in the next period.
PFRs found during FM2 Instrument Suite Integration to the Probe (most note-ably resets
on the BAU and IDPU) have all been resolved and the appropriate component level tests
completed. Full and final close-out of the PFRs is expected to occur early in the next
period with the delivery to UCB of the flight BAU.
1.2.3 Resource Budgets
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Power and Mass budgets continue to be tracked. The potential power problem discussed
in the last monthly report has been mitigated to some extent with further more detailed
analysis. Previous analyses had used unrealistic worst-case numbers. Detailed analysis
and actual numbers now show better results. Further discussion of the power analysis
can be found in Swales Monthly Resource Budget Report.
Provisions and plans to weigh the Probe before going to JPL for Environmental Test are
in place.
1.2.4 Reliability, Safety and Risk
o Risk: Swales and UCB risks were updated in the last period. IV&V risks
continue to be discussed. An additional risk was formally added to the UCB top
ten list addressing the concern that the Probe Carrier Assembly is not being
“tested as you fly.” To address this risk, all information for the PC and PCA tests
will be gathered to ensure all aspects of the systems are tested.
o Safety: Safety issues continue to be actively worked with Safety Working Groups
(SWG) Meetings.
o Reliability: Operating time of Flight Actels Instruments is being tracked.
1.2.5 Engineering and System Change Notices (ECRs and SCNs) –
o A few SCNs to address Probe BAU requirements are expected in the next period.
1.2.6 Problem Failure Reports (PFRs)
o Significant (high risk) PFRs opened in the last period having to do with resets on
the BAU and IDPU have been addressed and are considered closed.
2
Space Segment Development
2.1 Instrument
Written by Michael Ludlam
2.1.1. Instrument Data Processor Unit
Written by Michael Ludlam
The two problems on the IDPU reported last month have been fixed. The problem on the
DCB board causing the IDPU to reset was traced to a race condition from the signals
from the 8085 processor to the Actel. By synchronising the IOM and ADR15 lines to the
DCB 20MHz clock using a flip-flop IC this race condition was removed. The fix was
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tested in thermal vacuum over the full temperature range of the IDPU and no problems
were detected.
The second problem fixed this last month was to solve the high inrush current causing
IDPU resets seen in thermal vacuum. Capacitors were added to the power on switches of
the +5VD supplies on the PCB board to slow down the inrush and thus keep the +5VD
supply within regulation on the DCB board.
During FM4 and FM5 instrument suite thermal vacuum a problem was discovered with
the IDPU LVPS ESA supply. At cold temperatures the supply oscillated and produced a
ripple of several hundred mV on the output supply. No damage was done to the ESAs but
the LVPS will require a modification to fix this problem. This is a work in progress at
this time but a solution is being worked at present.
FM6 IDPU LVPS has been finished and is currently undergoing testing. The FM6 IDPU
will be integrated after FM4 and FM5 Instrument Suite Thermal Vacuum is completed.
2.1.2 Instrument Suite
FM4 and FM5 Instrument Suites are complete and are undergoing thermal vacuum
testing. Four cycles of the seven required have been completed. Due to a problem with
the IDPU LVPS supply the test was stopped but will resume once a solution has been
found – see IDPU section for details. Once complete this will finish the five instrument
suites environmental tests.
IDPU Flight Software
Written by Peter Harvey
I&T Support. During the period, FSW supported IDPU processor testing by developing
programs to detect memory changes due to DMA memory contention. A logic solution
was developed, tested and implemented on all processors. The changes were verified over
temperature using these software test programs.
During the review of procedures it was determined that some GSEs were sending
command scripts at nearly 90 commands per second for sustained periods. The IDPU was
eventually dropping commands since it executes commands at 32 Hz. Thus, a change was
made to identify and flag an error message in this condition.
Change Summary. Of the 34 requested changes to the FSW, 33 have been developed and
integrated into V2.14 software. These are described in thm_fsw_007M_Changes.doc.
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Development Efforts. During the period, Version 4.0 testing got back on track. Since
making the DCB circuit update to correct the DMA contention, the ETU has never reset.
The telemetry and command database was updated to include all Version 4.0 telemetry
points and these were included in thm_fsw_003_ctm_V4.00.xls. Displays specifications
for the new telemetry points were added to thm_fsw_100_Displays.doc.
TYPE
PROM
EEPROM
UPLINK
ETU
2.01B
2.14
4.00
FM1
2.01B
2.08
2.13
FM2
2.01B
2.13
--
FM3
2.01B
2.08
2.13
FM4
2.01B
2.14
--
FM5
2.01B
2.14
--
FM6
2.01B
---
Verification Summary. Since the change requests through version 2.14 were expected
features of the version 4.0, these requirements were added to thm_fsw_001F_Tables.xls
as module 24 “EEPROM.” This brought the total testable requirement count to 202. Of
the 202 testable requirements in the IDPU FSW, 198 have been tested either at the unit,
the integrated software or the hardware level.
2.1.3. Electric Field Instrument (EFI)
2.1.3.1. Spin-Plane Boom Mechanical Flight Build and Testing
Written by Bill Donakowski
General Overview
As previously reported, all THEMIS Spin Plane Boom Flight Units are completely
fabricated, environmentally tested, and are ready for installation into the Flight Probes.
There are no outstanding problems relating the instruments or their installation onto the
Probe.
Flight Hardware Spares Build and Test
The Flight Spares (two units, S/N 922 and 924) have been assembled, checked out, and
environmentally acceptance tested. No further work is required; the units are in Flight
storage.
2.1.4. Electro Static Analyzer (ESA)
Written by Christopher Scholz
General
The THEMIS ESA team has been working to finish up the full build of all six sets of
ESA Analyzers. Subsequent to the build up of the individual PWB’s each board is bench
tested and then tested as a complete ESA Analyzer.
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ESA PWB Assembly tasks
The THEMIS ESA PWB’s for the FM 1 thru FM 5 units have been completely finished
in regards to electrical build up. These same boards have also been thoroughly cleaned, in
house for boards with magnetics, HVPS, HV Motherboard and LVPS and at San Mina
for the Sweep Interface and Preamplifier.
The THEMIS ESA PWB’s for units FM 1 thru FM 5 have been completed for electrical
assembly work. The FM 1 thru FM 5 boards have been cleaned, staked and conformally
coated. The boards have also passed inspection by UCB and GSFC inspectors. These
boards can be considered complete for electrical build purposes.
The THEMIS ESA PWB’s for FM 6 are still in progress in regards to electrical build.
The LVPS has been harnessed and had its enabling plug installed. The HV Motherboard
is complete as are the two High Voltage Power Supplies, Positive and Negative. The
Preamplifier has its Flight Actel Installed. The Sweep Interface needs to have its trim
resistors set, its Flight Actel installed and the SMA harness installed. After Bench testing
these boards can be cleaned and then staked and conformally coated.
ESA Testing
The FM 2 ESA Analyzer has gone through individual bench testing, complete ESA
analyzer testing, vibration and Thermal Vacuum testing. The FM 2 unit has also been
integrated with its IDPU and been installed on the Probe F2
The FM 1 thru FM 3 ESA analyzers have gone through individual board bench testing
and have gone through vibration testing and have also undergone thermal vacuum testing.
This is at the suite level in conjunction with the IDPU. After environmental testing the
ESA analyzers will undergo a second round of calibration testing to assure that values
have not drifted or varied due to vibration or temperature fluctuations.
The FM 4 and FM 5 ESA analyzers have undergone bench level testing and have now
been assembled into complete analyzers. The analyzers have passed the bench tests and
have been disassembled, staked and coated. The ESA analyzers for FM 4 and FM 5 have
been reassembled and have undergone a short bench check. The ESA Analysers have
undergone calibration followed by ESA/IDPU vibration testing These two units are
currently in the restarted Thermal Vacuum testing.
During calibration of the various ESA analyzers an anomaly had appeared in the
calibration data. This was a minor variation and had been thought to have been possibly a
variation in the Ion Gun or maybe even differences in the Micro Channel Plates. Instead
it was determined that there was an off axis orientation in the data. This anomaly was
tracked down to the way the top hat seats on the release plate. There is a nutplate on the
back of the release plate that was interfering with top hat and causing it to be cocked.
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The nutplates have subsequently been modified on all six ESA Analyzers and thru bench
testing, mechanical analysis and subsequent recalibration of the FM 2, FM 4 and FM 5
units has shown that the problem is resolved. See PFR 139.
The FM 6 ESA still needs to go through ESA analyzer level testing, suite level testing
with the IDPU, vibration and thermal vacuum testing as well as pre and post calibrations.
During ESA Analyzer testing it was discovered that the analyzer was noisier than
expected and it now appears that the noise comes about when the Analyzers have not had
sufficient pump down time in the vacuum chamber. By doing a longer pumpdown and
reaching a lower pressure as will be seen in orbit the noise issue will go away. Another
noise mitigation task was to add an inline resistor to the T3 terminal on the TLAN anode.
This has been done to all TLAN anodes F1 - F6.
ESA Team Tasks
Mario Marckwardt has built up all ESA anodes with Flight MCP’s, micro channel plates.
Mario is also testing ESA Anode/MCP combinations to determine how different vendor
plates may or may not affect cross talk noise when assembled into an analyzer unit. It
appears that the Burle plates appear to be quieter in the assembly than the Photonis plates.
Chris Scholz is doing the technician work to finish out electrical builds and modifications
on the individual F6 boards. In addition he is performing in house cleaning, staking and
coating. Chris is also maintaining the electrical build documentation and updating parts
lists and build documentation as required.
Dr. Charles Carlson is doing all bench level board testing, as well as complete ESA
analyzer assembly and testing. Dr. Carlson is also overseeing the testing and potential
noise reduction measures for the MCP’s
Dr Jim Mc Fadden is heading up the ESA Analyzer calibration activities in conjunction
with Dr. Carlson.
2.1.7. 2.1.8. Magnetometer Booms
Written by Paul Turin
The final harness work on the mag booms has been completed for the FM2 FGM boom –
the Frangibolt Winchester connectors have been added to FGM units FM2-5, and the
BGe Kapton overwrap has been added to the SCM harness on the F2 probe. The original
harness routing for the FM2 FGM boom has not proven to work well with the BGe
Kapton overwrapping, so the harness will be rerouted on the probe deck. This entails
removing the FGM boom shoulder from the probe, rerouting the harness, and remounting
and realigning the boom. This work will occur this week.
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3 Mission Integration and Test
3.1 On-site Operations
Written by Jeremy McCauley, Integration and Test Manager
3.1.1. General
The first Probe continued MINT activities at Berkeley. After finishing all scheduled
integration tasks and testing in the month of December, the team turned their attention to
diagnosing and solving issues identified from that testing. Weeks of troubleshooting in
the IDPU PCB logic and DAP supply circuits have led to the successful diagnosis and
correction of two difficult items. These fixes have been installed and tested and the F2
IDPU is ready to continue Probe INT activities.
The BAU EDU2 was returned to Swales Aerospace on January 12. This has rendered
electrical testing of the Probe impractical. Thus, the team has worked to close out all
mechanical and harnessing issues that had remained through the activities in December.
We anticipate that early in February the Probe will be waiting on the Flight Model BAU
delivery. All activities practically accomplished before its delivery will be complete.
3.1.2. Facilities.
The humidity problem has been all but mitigated with the floor humidifiers described last
month. Activities were stalled for one day when the facility was recorded at 20% relative
humidity. The floor units were shown to be incapable of mediating such a large deficit
(30% relative humidity is the specified lower limit for activities). Discussions with UCB
facilities personnel regarding a permanent, high-capacity unit have yielded no proposals
within the scope of this project.
3.1.3. Mechanical Ground Support Equipment
The Mechanical GSE necessary for onsite INT activities had been assembled and
prepared for the arrival of the first probe. All MGSE functioned as intended.
3.1.4. Electronic Ground Support Equipment
The EGSE racks provided by Swales worked without notable incident throughout all
MINT activities.
3.1.5. Instrument INT Activities.
The F2 IDPU underwent extensive testing to diagnose a race condition in the memory
allocation on the PCB. The condition has been alleviated and the unit tested. Following
vibration testing in the first week of February, the unit will be ready to return to the
Probe.
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The F5 IDPU failed to turn on the SST in IDPU/ESA thermal vacuum testing. Tests at
ambient conditions reproduced the error. The condition has been alleviated and the unit
tested. Following vibration testing in the first week of February, the unit will be ready to
return to the Probe.
The ESA units have continued to suffer from the noise issue discovered last month.
Repeated testing has brought changes in testing and assembly that are now being used to
assemble the F2 unit.
3.1.6. Mission INT Activities
The P2 Probe completed MINT activities onsite at UCB with the BAU EDU2.
Troubleshooting of issues with the BAU and IDPU was conducted until the BAU EDU2
was returned to Swales on January 12.
Without the BAU, electrical testing at the Probe level is impractical. Instead, harness and
thermal closeouts have been done to bring the Probe to the most complete configuration
possible without the avionics on board. Since both the BAU and IDPU were removed,
access is at its best to the internal harnessing of the spacecraft. Activities requiring such
access are now completed.
Considerable effort has gone into finding a suitable light source for Solar Array
verification. Halogen bulbs produced too much IR heat and forced procurement of a light
which generates a more suitable spectrum. We look forward to testing with such a light
early in February.
3.1.7. Operations Controllers
UCB Controllers have provided consistent support to the MINT efforts. Team members
have been able to gain experience using the ITOS interface and the Probe commands.
Effort is being placed on managing personnel to support all activities while maintaining
MOC operations.
4 Integration & Test Preparations for JPL and KSC
Written by Rick Sterling
4.1.Overview
We expect to start Environmental Testing of the first probe at JPL around March 19. Our
lead contact at JPL, Mr. Andrew Rose, indicates that preparations are in good shape.
Deliverables owed to KSC and Astrotech are all up to date at this time. Detailed
preparations are ongoing.
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4.2 Preparations for JPL
Following is a snapshot of the status and/or recent issues regarding major activities:
4.2.1 Transportation
 Transportation company (Threeway Logistics) is scheduled.
 Vibration and magnetic flux monitoring equipment is in line.
 The necessary paperwork for transporting pyrotechnics is ready.
 A Berkeley team including Parts, QA and I/T is preparing the manifest and
overall shipping and handling plan. We will be using rolling wire racks for most
equipment and supplies. Each item to be sent to JPL (enable and disable plugs,
connectors, cables, test equipment, etc) will have an ID with rack, shelf and bin
number to simplify movement, handling and organization.
4.2.2 Magnetics
 Procedures for this test have been prepared by Michael Ludlam (Berkeley) and
Pablo Navarez (JPL).
 One problem is that our lead Magnetics Test Engineer, Michael Ludlam, may
possibly NOT be allowed to enter JPL because he is a foreigner without
citizenship or permanent resident status.
 Vassilis is doing what he can to enable Ludlam to come on site to JPL for the
Magnetics Test. We have arranged with Bob Snare of UCLA to be a backup in
event that Michael Ludlam cannot be on site.
 We will fit check the MGSE hardware with the magnetics hardware (helmholtz
coil, spin table and encoder) in the next few weeks.
 Pablo Navarez will visit UCB next week to review the MGSE, discuss testing
details and deliver the transport monitor magnetic sensors.
4.2.3 EMC/EMI
 Procedures for this test have been written by Dave Curtis (UCB) and Pablo
Navarez (JPL).
 To test and measure the solar panels generating current we will shine high
intensity light on one side of spacecraft panels during test. A new light source has
been identified after an initial light source proved inadequate.
4.2.4 Vibration/Shock
 A Vibration Test procedure has been written by Dave Pankow based on his
planning and collaboration with JPL’s Terry Sharton.
 We have decided to use solid weights at 2X spacecraft mass for test run of the
vibration setup and equipment.
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

A z-axis riser has been designed and built to prevent magnetic charging of the
spacecraft during the z-axis shake.
Pyrotechnics for the shock test are being shipped from Swales to JPL next week.
This includes the separation initiator plus replacement separation bolt cutter.
4.2.5 Thermal Vacuum
 Ellen Taylor has written the Thermal Vacuum Functional Test Configuration
procedure and is working on the overall electrical functional tests to be
performed.
 Chris Smith is working on the other aspects of Thermal Balance and Thermal
Vacuum including the model, details of the thermocouple placement, heating and
power supply requirements, etc.. Chris is working with JPL’s Pat Martin and
Doug Perry.
 We will include radiation sources for testing the SST and ESA units within the
Thermal Vac test. These are low level Ni-63 and Am-241 sources. Appropriate
arrangements are being made with UCB and JPL Environmental Health and
Safety groups responsible for the safe-keeping and transfer of the licensed
radiation sources.
 The chamber feedthrough for the major umbilical harnessing has been tested and
approved at JPL.
 Other harnesses which will be needed for testing during Thermal Vacuum will be
tested in the coming weeks when we receive the Flight Avionics unit and test in
Thermal Vac configuration at UCB.
4.2.6 RCS Leak Check
 Mike Sholl has written the procedure which will guide RCS leak and pressure
check of the probes. This is a hazardous test but can be done at Building 179
(Magnetics Test facility).
4.2.7 Alignment
 For the first probe through Environmental Test (F2), we plan to do alignment of
the magnetometers, communication and ACS components both before and
following the Vibration Test. This will demonstrate whether the launch shake
causes a shift in alignment.
 Subsequent probes will be aligned at the last stage of the flow at JPL.
 Paul Turin has arranged with people at Lawrence Berkeley Lab to have one of
their experts with Faro Arm come to JPL for alignment operations.
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4.2.8 Spin Balance
 We plan to use the GSFC Miller Table for spin balance and mass properties
measurement of the probes. This will be done during the final stage of the
Environmental Testing when all probes are at JPL and just prior to shipping to
KSC.
 Dennis Lee is facilitating the scheduling and coordination.
4.2.9 Test telemetry and data flow
 For most environmental tests there will be real time data received at the on site
EGSE. The ITOS computers at JPL will forward the telemetry to the Berkeley
MOC (Mission Operations Center). This will serve two purposes: a) to test out the
same process we will have at Astrotech and KSC and b) to enable others to view
the test results.
 At the Berkeley MOC the data will be archived as raw telemetry and also as a
database of engineering data. For example, in each telemetry frame the real time
voltages, currents and temperatures will be extracted and stored along with the
time stamp. Plotting tools are being developed so that engineers and scientists can
easily display the changes in various parameters over time. The database will be
accessible from on site or remote locations.
 Appropriate firewall and security measures will be installed.
4.3 Preparations for KSC
The following launch site deliverables were submitted during the last month
 Information for Environmental Impact Analysis
 Program Point of Contact for Waste Management.
An important issue worked recently is the schematic for the long Boeing harness which
runs from the payload atop the Delta II rocket to the Blockhouse. A revision/clarification
in the shielding requirements from Swales prompted discussion and modification of the
preliminary Boeing design. A wiring error and some naming issues were also identified
and resolved. Boeing was able to modify the shielding scheme to meet the Swales
requirements. We have also been attentive to avoid ground loops. The harness is now in
the final process of review prior to approval to build.
The network and communication requirements during the pre-launch processing at
Astrotech and the pad are in the final stages of review. I expect this also will receive final
review and confirmation at the next GOWG/TIM meeting. There will now be three voice
loops to Berkeley in the pre-launch activities from the pad. At the pad, telemetry from the
five probes will flow to the EGSE in the blockhouse and then be forwarded to Astrotech
and the Berkeley Mission Operations Center (MOC). People who are at Hangar AE will
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be able to remotely monitor the probe health and safety by viewing the engineering data
(voltages, currents, temperatures, etc) which will be processed and displayed on a near
real time basis on the internet. Appropriate firewall and password protection will be
implemented.
A thorough RF Test will be done at Astrotech in the Payload Processing Facilities prior
to transfer to the Hazardous Processing Facilities for Fueling and subsequent processing.
A transmitter check (RF Chirp Test) will be done at the pad after mating with the Delta
II.
Detailed plans for fueling and potential de-fueling will be presented at next GOWG/TIM
meeting. In addition to the biweekly MIWG and GOWG teleconferences, coordination is
ongoing with the following key contacts:
 LSIM – Bill Van Dyke
 Astrotech Manager – Gerard Gleeson
 Delta II Launch Coordinator – Victor Segall
 Network and Communications – Ed Kachmar
Various details of the Launch Site Support Plan (LSSP) continue to be worked. I expect
the LSSP will finally be signed after the forthcoming GOWG Technical Interchange
Meeting, now scheduled for April 5.
5 Mechanical Ground Support Equipment
5.1 Mechanical Ground Support Equipment List, THM-SYS-033
Written by Bill Elliott
5.1.1. General
THM-SYS-033 (MGSE Tracking List) has been updated to reflect the receipt of most of
the MGSE on schedule. The revision level has been changed to (Rev AL 02-09-06).
5.2 Mechanical Ground Support Equipment Design and Procurement
Written by Bill Elliott
5.2.1. General
The majority of the mechanical ground support equipment design is on hand at Berkeley.
The Thermal Box is on hand. The Z-Axis vibration fixture is due February 15. The next
step, proof testing, will occur during the 2nd and 3rd week of February per : THM-GSEMEC-903 MGSE PROOF TESTING PROCEDURE.
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5.2.2 Equipment List
Equipment on hand includes (2x) Rollover Fixtures, (1x) Lifting Frame Assembly, (1x)
Turntable Assembly, (1x) Cart, Rollover, (2x) Hanger Bracket Assembly, (2x) Tongue
Bracket Assembly, (2x) Thermal Box Assembly (less frame due this week), (1x)
Modified Probe Stand to mount to Probe Shipping Box Base, X & Y Vibration Fixtures,
(1x) Probe Spin Plate Assembly, (1x) PCA Spin Plate Assembly, (1x) Encoder Assembly
5.2.3 Procedures
MGSE Procedures are being circulated in draft form. Procedures include: THM-MINTPROC-056 Roll-Over Fixture Procedure, THM-MINT-PROC-058 MGSE Lifting
Procedure and THM-MINT-PROC-059 MGSE Thermal Vac Procedure.
6 Ground Segment Development
6.1 Mission Operations Development
Written by Manfred Bester
6.1.1. General Operations
Several open RFAs from the THEMIS Mission Operations Review and from previous
reviews are currently still worked. A pre-FOR Flight Dynamics & Flight Operations
Review is scheduled for late April of 2006.
6.1.2. Mission Design & Maneuver Planning
Contributed by Sabine Frey and Daniel Rummel
Further progress was made with fine tuning the current mission design. All of the critical
quantities driving the mission design – conjunction hours (4 and 5 probe conjunctions in
T1 and T2), shadow durations and total mission delta V, not exceeding 700 m/s for all
probes – look very stable for launch dates between October 19 and November 19, 2006.
As expected, all numbers vary slightly as a function of launch date and corresponding
selection of the wedding days. The maneuver sequence has been optimized around the
RCS re-pressurization profile, also taking into account the 30-min transmitter-on time
constraint. Refinement of the maneuver sequence using GMAN for finite targeting was
completed for all four observing seasons (T1, D1, T2 and D2). Re-entry is currently still
targeted with impulsive maneuvers. The final mission design with all maneuvers targeted
as finite burns is expected to be completed by end of February.
The current mission profile is robust with respect to contingencies, such as missed
maneuvers. A back-up maneuver is included in the nominal maneuver plan for all final
orbit placement steps. Once the EFI booms are deployed, all orbit maneuvers will be
executed as side-thrust or beta-thrust maneuvers, broken up into multiple segments.
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Maneuvers with a delta V of less than a few m/s will be performed as side-thrust
maneuvers since the perturbations associated with attitude precessions for axial thrust
maneuvers would otherwise degrade the targeting accuracy. Maneuvers with a delta V of
less than 0.5 m/s will be skipped altogether. The total number of maneuvers, not counting
attitude precession and spin-rate changes, is of the order 110. It will likely not be possible
to completely de-conflict the maneuver schedule in such a way that only one orbit
maneuver falls into any given operations shift. For those cases, the operations sequence
will be carefully planned and exercised to demonstrate feasibility.
Ephemeris files spanning the entire mission for all five Probes were delivered to the
Space Physics Data Facility (SPDF) at GSFC for access by the science community.
6.1.3. Orbit and Attitude Determination
Contributed by Daniel Cosgrove
Further progress was made with the development and testing of IDL based OD support
tools that allow for automated pre-processing, graphics visualization, selection of
tracking arcs, quality checking and archiving of definitive vectors. Using two-way
Doppler data from FAST collected at BGS and other stations for more several months
now, the OD process was tested further. An automated process was implemented to select
OD arcs and to roll forward as new tracking data are collected.
GSFC/FDF analyzed FAST/BGS two-way Doppler data and determined that BGS
tracking data are nominal, and issued a certification document. UCB independently
analyzed FAST two-way Doppler data from BGS and other ground stations, and derived
mean residuals and standard deviations from the OD process that are consistent with the
FDF results. A report summarizing the GTDS and IDL OD configuration, testing, and
data processing, as well as the results from FAST OD runs at UCB is currently prepared
and will serve as the baseline for certifying the entire OD process at UCB.
Attitude solutions for FAST were obtained with both the new and the old, operational
version of MSASS by batch processing data from the Sun sensor and the Earth horizon
crossing sensor, and were found to be in close agreement. FAST FGM data will be
included as the next step.
A new version of MSASS (2005.03) including enhancements of the Kalman filter and
several bug fixes was delivered to UCB in mid February. Matlab was installed inside the
MOC to allow for tests of the real-time interface between the new version of MSASS and
the FAST ITOS system. Configuration of MSASS for THEMIS and preparations for
testing with Probe F2 and the VirtualSat dynamic simulator are progressing in parallel.
6.1.4. Ground System Development
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The implementation of the multi-spacecraft THEMIS ground system is well on its way.
Software tools to manage real-time data flows were tested. A special tool was developed
to allow for independent verification of the integrity of Absolute Time Sequence (ATS)
loads generated by the Mission Planning System (MPS, formerly known as CMS). This
new tool was tested by verifying RHESSI ATS loads, and will also be used to verify and
cross-check THEMIS ATS loads, once the THEMIS upgrade of MPS is completed. The
FOT has been working closely with UCB Systems Engineering on updating command
and telemetry databases for the IDPU which were merged with those for the BAU,
provided by Hammers.
The first five THEMIS ITOS workstations are operational in the MOC. The workspace
configuration for both mission operations and I&T has been further improved. Since
arrival of Probe F2 at Berkeley, telemetry data were flowed from the I&T area to the
MOC, allowing critical network interfaces and software to be tested.
A series of complete end-to-end tests between Probe F2 and the MOC via the Berkeley
Ground Station was successfully completed. These tests exercised the RF telemetry and
command channels at all data rates and modulation modes as well as most elements of
the THEMIS ground system at UCB. A zero-Doppler shift baseline with the transponder
in the loop was established for future on-orbit range rate measurements.
6.1.5. Mission Operations Planning
Regular telecons between Swales, Hammers, GSFC and Berkeley team members were
held to discuss operations related matters in the areas of telemetry and command
processing, flight and ground software configuration and testing, mission integration,
development of operational procedures, flight rules and recovery from contingencies.
Detailed timelines for early orbit and normal operations as well as corresponding
operations procedures are under development in collaboration with Systems Engineering
and instrument scientists.
6.1.6. Ground Station and TDRSS Support
The RF ICD covering all interfaces between the probes and the ground stations as well as
TDRSS was approved by the Code 450 Configuration Control Board. Updates to the
FY06 PSLA were submitted. The Flight Operations Team made progress in working out
details and procedures for scheduling TDRSS passes via the Space Network Web
Services Interface (SWSI). Several connectivity and end-to-end data flow tests between
the White Sands Complex and the MOC were completed. The Berkeley team also
participated in meetings with the GSFC/CTV group and with the Network Operations
Manager to plan RF and data compatibility tests with the second completed Probe (F3) at
Swales. UCB has been working with GSFC and HTSI to bring the Hartebeesthoek
ground station on-line for THEMIS support. End-to-end data flows with all ground
stations and with the TDRSS Ground Terminal at White Sands are under way.
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6.1.7. Berkeley Ground Station
All items for BGS hardware upgrades have been delivered and are currently tested in the
ground station. Hardware and software integration of the Apogee Labs Doppler tracking
system was completed and on-orbit tests with FAST were performed successfully. As
mentioned earlier, UCB worked with GSFC/FDF to certify the Berkeley Ground Station
for two-way Doppler tracking, using FAST as a mission of opportunity.
6.1.8. NTIA License
The Project received the NTIA Stage 2 license, allowing pre-mission testing with the
probe RF subsystem and the ground stations. The application for the Stage 4 (on-orbit
operational) license was prepared by the GSFC Spectrum Management Office and was
submitted to the NTIA in September 2005. Approval is expected by March 2006.
6.1.9. Telemetry Processing and Archiving
The probe telemetry data recorded during I&T were processed and stored on a dedicated
data server to allow scientists and engineers to analyze the performance of Probe F2 bus
integrated with the Instrument Suite FM2.
The new Berkeley Trending and Plotting System (BTAPS) developed in-house at SSL
was tested with both RHESSI and THEMIS telemetry data. RHESSI on-orbit engineering
data and THEMIS Probe F2 I&T engineering data are routinely decommutated and
placed into the MySQL database. A feature rich plotting tool queries the database,
extracts and plots telemetry data.
6.1.10. Documentation
Various operations related plans and procedure documents have been released and others
are currently under development and will be released shortly.
6.1.11. Personnel Staffing and Training
Beginning in July of 2005, the Flight Operations Team (FOT) supported probe bus
integration and testing at Swales on a rotating schedule with a combined total of 150
days. On-console and classroom training sessions have started at UCB. A major
milestone was the participation in the Probe F2 Comprehensive Performance Tests (CPT)
and in the pre and post-ship Aliveness Tests. Since the delivery of Probe F2 bus to
Berkeley, the FOT supported Systems Engineering and ran all console operations for
both Probe bus and instrument integration and testing at UCB. Support of the Probe F3
bus integration at Swales is ongoing.
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6.3 Ground Based Observations Developments
Written by Stu Harris
6.3.1. GBO Operating Status Summary
As of this date, there are 10 GBO stations deployed in Canada and Alaska. The
following table shows the current status of all units, including those currently being built.
Ground Based Observatories – Current Status
GBO Unit #
Located Where?
Status
GB0#01
Prototype, UCB
Upgrade in progress
GB0#02
Athabasca
Operating normally
GB0#03
Prince George
Operating normally
GB0#04
Ekati Diamond Mine
Operating normally
GB0#05
Engineering Unit, UCB
Operating normally
GB0#06
The Pas
Operating normally
GB0#07
Whitehorse
Operating normally
GB0#08
Inuvik
RF interference issues
GB0#09
Rankin Inlet
Operating normally
GB0#10
Fort Smith
Operating normally
GB0#11
McGrath
Operating normally
GB0#12
Fort Yukon
Operating normally
GB0#13
UCB
Check-out complete
GB0#14
Goose Bay, arrived in Jan. Awaiting installation.
GB0#15
UCB
Check-out in progress
GB0#16
UCB
Construction complete
GB0#17
UCB
Construction complete
GB0#18
UCB
Construction complete
GB0#19
UCB
Construction complete
GB0#20
Not started
GB0#21
Not started
GB0#22
Not started
6.3.2. Deployment Activities
During this period, because of the difficulty of winter-time deployments, the only
activities in this area were limited to shipping unit #14 to Goose Bay, Labrador.
With 10 GBO sites now operating, please visit the THEMIS ftp site, at the following
URL, and view the “GBO_Tour”.
ftp://apollo.ssl.berkeley.edu/pub/THEMIS/3 Ground Systems/3.3 Ground-Based Observations
Development/GBO_Tour.pdf
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6.3.3. Unit Construction Status
Construction activities of new GBO units made significant progress in January.
UCalgary personnel were on-site at UCB in January and participated in a build of five
units. Figure 3.1 shows some of the results of this activity.
Fig. 3.1: New GBOs lined up at UCB
6.3.4. Engineering Activities
As previously reported, the ASI at Inuvik was experiencing RF interference problems
that periodically caused USB faults. While a software fix has significantly reduced the
frequency of occurrence, the problem continues, and additional work is needed to cure it
permanently.
In January, the GBO operations team began rolling out new software for the ASI data
acquisition and backup process. As of the end of January, all sites had been upgraded
except for Ft. Yukon.
6.3.5. Planned Activities for Next Period
As noted above, the GBO for Goose Bay arrived on site in January. This unit, as well as
the unit for Ft. Simpson, are scheduled for installation during February and March. Even
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though winter-time deployment is difficult, we have many systems to install this year, so
we plan to make a very aggressive push on deployment activities.
7 Education and Public Outreach
Respectfully Submitted,
THEMIS E/PO scientists Nahide Craig, Laura Peticolas
7.1 Formal Education:
7.1.1. Geomagnetic Events Observation Network by Students (GEONS) Program
Geomagnetic Events Observation Network by Students (GEONS) Program
Tim Quinn finalized the GEONS data archives and the data are now available on the web.
D. Meilhan kept in regular contact with the GEONS teachers, sending information about
space weather events and THEMIS news and events. GEONS teachers are using the
magnetometer data and other THEMIS classroom lessons in their science classes.
7.1.2. Evaluation
N. Craig, L. Peticolas, communicated with A. Walker of Cornerstone to finalize the
interview protocol regarding the GEONS program. A. Walker will do phone interviews
this winter with the GEONS teachers using a template designed from this phone
conversation and the 2004 phone interview template. Walker contacted the THEMIS
teachers and made appointments with them for their yearly phone interview. She will
start the interviews during the second week of February.
7.1.3. THEMIS E/PO presentations
N. Craig gave a talk at the American Meteorological Society Meeting in Atlanta. This
talk was part of the 15th Symposium on Education in Space Weather Education on
January 30 and was titled NASA's THEMIS Mission and the Involvement of Schools.
7.1.4. Public Relations – Preparing for the Launch
V. Angelopoulos, N. Craig, and L. Peticolas communicated further with C. O'Carroll of
Goddard Space Flight Center (GSFC) to determine the best plan for Public Relations for
THEMIS for the Launch. We now have a general fact sheet for this mission revised for
the PR usage. We also had telecons where we discussed our roles and responsibilities
concerning EPO products - what we want to create, and how we work together to get the
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desired products produced. Rani Chohan of GSFC TV will help us put together B-roll
and animations to help tell the science. We are also discussing what her group can do for
the mission and how much it will cost to create these products.
8 Problems
Outstanding Problems
1. The probe Diplexor was designed for 10W operation and has very thin margin. Retest
at 27W based upon GSFC direction is pending.
2. There is a Alert on the BAU EEPROM.
New Problems / Problem Avoidance
Resolved Problems:
1. The Flight Bus Avionics Units and EGSE Racks have caught up to the integration
schedule.
2. Both BAU and IDPU processors DMA circuit troubles were fixed
3. The Probe power budget is OK assuming correct attitude going into long shadows so
last month’s issue is resolved.
4. ESAs are being delivered to I&T in time.
5. Swales systems engineering is paying close attention to BAU software requirements
changes.
9 Performance Assurance
Written by Ron Jackson.
9.1 Quality Assurance operations
QA team performed coating, staking, rework, repair inspections, and documentation
support for IDPU, and SPB,AXB, all ESA assemblies . One of the three hygrometers in
clean room was out of calibration. A new one was ordered. It is scheduled to arrive on
2/2/06. All other equipment was in calibration compliance.
9.2 Quality Assurance Monitors
All ESD workstations are in compliance. There are no clean room issues at this time.
9.3 Problem Reports
Summary of PFRs:
ftp://apollo.ssl.berkeley.edu/pub/THEMIS/1%20Management/1.3%20Systems%20Engin
eering/8.%20PFRs/thm_pfr_master_list.xls
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12 THEMIS Project Safety Status
Written by Bill Donakowski
Project Safety Documentation
The MSPSP (Missile System Prelaunch Safety Package) has been updated to reflect
comments received from GSFC, KSC, and Boeing Safety. This February 01 2006
submittal is an incremental draft. The final submittal is expected to take place in April
2006.
The SSPP (THEMIS Mission System Safety Program Plan) has been revised to reflect
the handover of overall Safety responsibilities to UCB from Swales; the document has
been signed off.
Probe #2 Activities at Space Sciences Lab, Berkeley
Themis Probe, Flight Unit 2, continues processing at UCB. No safety issues to report at
this time.
Personnel Certifications
UCB Safety continues certification of THEMIS personnel for future Integration and Test
activities. These certifications will consist of Crane Operations, Fork Lift operations,
Radiation Source handling, and Pyrotechnic handling.
Procedures involving Hazardous Operations
All procedures involving Hazardous Operations will be reviewed by UCB and GSFC
Safety organizations. Approximately ½ of the hazardous operations have been reviewed
thus far. The remaining procedures to be reviewed are those taking place at JPL
(vibration, spin balance, shock) and Astrotech (pressure testing, spin balance, fueling,
stacking). It is expected these documents will be completed in the next 2 weeks. From a
safety perspective, the documents are being reviewed to verify applicable safety
precautions are in place. These requirements include adequate personnel protection
equipment, certification of users, proper conduct, inclusion of safety shut-down
procedures, and the like.
JPL I and T Safety Coordination
In support of future I and T activities at JPL, two telecons have been held between UCB
and JPL safety organizations. JPL has assigned a safety engineer to support the THEMIS
program while at JPL. Of immediate interest is the shipping of pyrotechnic devices from
Swales Aerospace to JPL. Detailed shipping information is being collected; it is expected
the devices will be shipped next week (February 20) to JPL. At JPL, the devices will be
stored until needed by UCB. These devices are the initiators and the Separation System
bolt cutters which will be installed at JPL by UCB personnel.
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JPL has been informed of all integration and test activities that will occur at their facility.
When completed, JPL Safety will review UCB written involved hazardous operations.
13 Magnetic Surveys of THEMIS Facilities
Written by Bill Donakowski
Magnetic Requirement
The THEMIS Flight Instruments and Probe are susceptible to magnetic perming and
therefore need to be kept away from any strong magnetic fields at all times. The
presence of a strong magnetic field may induce a magnet field in any given piece of
THEMIS Flight hardware, leading to degraded measurements in flight. As a precaution,
all facilities in which THEMIS hardware will occupy needs to be surveyed to verify
strong magnetic fields are not present.
The THEMIS S/C shall not be exposed to any magnetic field of strength greater than 2
Gauss (2,000 milligauss; 200,000 nT). If any portion of the facility was above this level,
that particular area would be unacceptable for processing of the THEMIS probe. The
area would be avoided and posted as not acceptable (per Appendix A of THM-PROC120). Note magnetic fields are highly localized and drop quickly as a function of
distance (1/r**3). An area of unacceptably high stray field is to be avoided but does not
render the entire facility incompatible with THEMIS processing.
Magnetic Survey Test Results
Surveys have been completed of all UCB areas, JPL Environmental Test facilities,
Astrotech, and KSC Launch Complex 17. These surveys were performed by UCB Safety
to procedure THM-MINT-PROC-120, “THEMIS Facilities Magnetic Survey”. Test
reports are available for inspection.
All areas surveyed are acceptable for THEMIS use with one exception. The JPL
Vibration Table has a strong magnetic stray field when used in the Z axis orientation. To
prevent this stray field from causing any issues with the future testing of the THEMIS
probes, UCB has designed and fabricated an aluminum riser structure. This riser will
place the Probe and all THEMIS Flight Hardware beyond the stray magnetic field during
testing. The acceptable facilities had background magnetic strengths in the range of
50,000 nT (approx. ¼ of unacceptable strength).
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THEMIS I&T Schedule
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