GoetzFIELDS iCDR - SE Solar Probe Plus - FIELDS System Engineering Instrument CDR Keith Goetz...

Goetz 1FIELDS iCDR - SE

Solar Probe Plus - FIELDSSystem Engineering

Instrument CDR

Keith GoetzUniversity of Minnesota

[email protected]


Agenda

• Requirements Flow• Instrument Description• Changes• Documentation• Overviews – mechanical, thermal, electrical• Deviations/Waivers• EMC/ESC/MAG/DDD/RAD• Resources• Reviews• Issues/Conclusion


SPP L1 Requirements

Science Objective Objective QuestionsSolar Wind

Plasma

Solar Wind

Magnetic Field

Electric Field and Plasma Waves

Enrgetic Particles

Large-scale

Structures

Trace the flow of energy that heats and accelerates the solar corona and solar wind.

How is energy from the lower solar atmosphere transferred to, and dissipated in, the corona and solar wind?

✓ ✓ ✓

What processes shape the non-equilibrium velocity distribution observed throughout the heliosphere? ✓ ✓ ✓

How do the processes in the corona affect the properties of the solar wind in the heliosphere?

✓ ✓

✓ ✓ Determine the structure and dynamics of the plasma and magnetic fields at the sources of the solar wind. How does the magnetic field in the solar wind source

regions connect to the photosphere and the heliosphere?

✓ ✓ ✓ ✓ ✓ ✓

Are the sources of the solar wind steady or intermittent? ✓ ✓

How do the observed structures in the corona evolve into the solar wind?

✓ ✓

✓ ✓

✓ ✓Explore mechanisms that accelerate and transport energetic particles. What are the roles of shocks, reconnection, waves, and

turbulence in the acceleration of energetic particles? ✓ ✓

✓ ✓

What are the source populations and physical conditions necessary for energetic particle acceleration?

✓ ✓

✓ ✓

How are energetic particles transported in the corona and heliosphere?

✓ ✓ ✓ ✓


FIELDS L1 Requirements

Baseline Fields and Waves MeasurementsReq. Measurement Dynamic Range Cadence Bandwidth4.1.1.1 Magnetic Field 140dB 100k vectors/s DC - 50kHz4.1.1.2 Electric Field 140dB 2M vectors/s DC - 1MHz4.1.1.3 Plasma Waves 140dB 1 spectrum/s ~5Hz - 1MHz

4.1.1.4 QTN/Radio 100dB for QTN80dB for radio

1 spectrum/4s QTN1 spectrum/16s radio

10-2,500kHz QTN1-16MHz radio

Threshold Fields and Waves MeasurementsReq. Measurement Dynamic Range Cadence Bandwidth4.1.2.3 Magnetic Field 125dB 256 vectors/s DC - 128Hz4.1.2.4 Electric Field 125dB 256 vectors/s DC - 128Hz4.1.2.5 Plasma Waves 90dB 1 spectrum/10s ~5Hz - 50kHz

4.1.2.6 QTN/Radio 70dB for QTN70dB for radio

1 spectrum/32s QTN1 spectrum/32s radio

10-2,500kHz QTN1-16MHz radio


FIELDS L2 Requirements

FIELDS Science Measurement RequirementsID Requirement Title Baseline Threshold Current

MRD-89 FIELDS: DC Magnetic Field -- dynamic range: 140 dB 125 dB 140 dB

✔-- cadence: 100k vectors/sec 256 vectors/sec 150k vectors/sec-- bandwidth: DC – 50 kHz DC – 128 Hz DC – 75 kHz

MRD-99 FIELDS: DC Electric Field -- dynamic range: 140 dB 125 dB 140 dB

✔-- cadence: 2M vectors/sec 256 vectors/sec 2M vectors/sec-- bandwidth: DC – 1 MHz DC – 128 Hz DC – 1 MHz

MRD-103 FIELDS: Plasma Waves -- dynamic range: 140 dB 90 dB 140 dB

✔-- cadence: 1 spectrum/sec 1 spectrum/10sec 1 spectrum/sec-- bandwidth: 5 Hz – 1 MHz 5 Hz – 50 kHz 5 Hz – ~2 MHz

MRD-107 FIELDS: Quasi-Thermal Noise -- dynamic range: 100 dB 70 dB 100 dB

✔-- cadence: 1 spectrum / 4 sec 1 spectrum / 32 sec 1 spectrum / 4 sec-- bandwidth: 10 – 2500 kHz 10 – 2500 kHz 10 – 2500 kHz

MRD-108 FIELDS: Radio Emissions -- dynamic range: 80 dB 70 dB 80 dB

✔-- cadence: 1 spectrum / 16 sec 1 spectrum / 32 sec 1 spectrum / 16 sec-- bandwidth: 1 – 16 MHz 1 – 16 MHz 1 – 19.2 MHz


FIELDS L3 Driving Requirements

PAY-37 now matches science and instrument

PAY-310 now protects SWEAPPAY-320 now requires antenna shifting

ID TitlePAY-37 Measurement: Magnetic Field MAGPAY-38 Measurement: Magnetic Field SCM & Plasma WavesPAY-170 Measurement: Electric Field & Plasma WavesPAY-172 Measurement: Plasma Waves (AC Magnetic Field)PAY-174 Measurement: Plasma Waves (Magnetic Field Power Spectra)PAY-272 Measurement: Plasma Waves (Electric Field Power Spectra)PAY-175 Measurement: Electric Field QTN SpectroscopyPAY-176 Measurement: Electric Field Radio EmissionsPAY-104 Payload: Risk CategoryPAY-105 Payload: FIELDS Burst ModePAY-109 Payload: Burst Mode ManagementPAY-113 Timekeeping: FIELDS Time Knowledge AccuracyPAY-117 Timekeeping: Support for Accuracy VerificationPAY-112 Payload: Flight Software ModificationPAY-310 FIELDS Protection Against Instrument FailurePAY-320 ADC: FIELDS antennas compensation of TPS shift


FIELDS L3 General Requirements

PAY-309 now drives component selection and design

ID TitlePAY-100 Payload: Minimum Perihelion HoursPAY-101 Payload: Baseline Mission LengthPAY-309 Payload: Backup Mission LengthPAY-292 Solar Storm Event OperabilityPAY-312 Time-Critical Momentum DumpsPAY-118 ADC: Spacecraft Coordinate Frame DefinitionPAY-313 Instrument Sensor ClearancePAY-149 FM: Instrument Fault ProtectionPAY-150 FM: Instrument Power-Down Safe StatePAY-221 FM: Instrument ReconfigurationPAY-152 FM: Instrument Power-Down PreparednessPAY-133 CDH Data Delivery: Quick-Look DataPAY-134 CDH Data: Data SharingPAY-135 CDH Data: Engineering Data SharingPAY-136 CDH Data: Public DisseminationPAY-137 CDH Data Delivery: Data Retention at SOCPAY-138 CDH Data Delivery: Data Retention at SOCsPAY-139 CDH Data Delivery: Data Delivery to NASA


FIELDS L3 Compliance Requirements

ID TitlePAY-276 Compliance: General Instrument SpecificationPAY-279 Compliance: FIELDS to Spacecraft ICDPAY-277 Compliance: FIELDS to SWEAP ICD (FIELDS)PAY-283 Compliance: MOC to SOC ICDPAY-140 Compliance: EMECPPAY-141 Compliance: EDTRDPAY-148 Compliance: CCP


FIELDS L4 Instrument Requirements

• FIELDS Subsystems


FIELDS L4 Instrument Requirements

ID Title L4 Requirements TBD Parent ID (Level 3) Parent Title Full Text Owner

Verification Method (What test and

when)DCB-01 Mission Length DCB Components shall be selected to withstand the environment of

SPP for the duration of the mission PAY-309 Payload: Backup Mission Length All instruments shall be designed to achieve an

operational lifetime of at least 8 years after launch if launched during the 2019 backup launch period.

FIELDSSWEAPWISPRISIS

Design Inspection (DCB Schematics, BOM): EEE Component Specifications and Stress Analysis Report; Parts radiation test reports when applicable

DCB-02 Spacecraft Interface Compliance (General) DCB shall implement the spacecraft interface protocol:[a] compliance with UART protocol[b] serial/parallel conversion and transfer to/from DCB Memory[c] detection/flagging of parity and framing errors[d] extraction of the "Virtual 1PPS" from the Command UART[e] selectionof S/C side based on active Command I/F[f] driving of Telemetry to active S/C side; disabling of inactive S/C telemetry driver

PAY-276 Compliance: General Instrument Specification

All instruments shall comply with the requirements and constraints imposed by the General Instrument to Spacecraft ICD, Document 7434-9066.

FIELDSSWEAPWISPRISIS

Design Inspection: (DCB Specification) and board level functional tests to validate

DCB-03 Timing DCB shall provide latching facility upon detection of the "Virtual 1PPS" S/C timing signal:[a] timing uncertainty not to exceed one bit period of the S/C UART [b] subseconds portion of S/C Time is interpolated to resolution of > minimum internal instrument uncertainty. [c] S/C Time is transferred to the FIELDS instruments at least once/second

PAY-113 Timekeeping: FIELDS Time Knowledge Accuracy

FIELDS shall limit internal instrument timing uncertainty to +/- 2 msec (3-sigma) relative to the most recently received Spacecraft time reference.

FIELDS Design Inspection (DCB Specification) and board level functional tests to validate

DCB-04 Burst Memory Management DCB shall include Flash memory and controller that:[a] is capable of storing 300 kbps of instrument data packets for a solar encounter period.[b] provides services required by the FSW for FLASH memory data transfer and management[c] minimum transfer rate of 300kbps to/from DCB SRAM to support the instrument data packet volume

PAY-109 Payload: Burst Mode Management FIELDS shall be responsible for management of its internal burst data buffer.

FIELDS Design Inspection (DCB Specification);verification of transfer rate during board level validation.

• A slice of IRD• 300+ requirements on 17 FIELDS subsystems• From here, we go to L5 requirements or

specifications


SPP Spacecraft


iPDR - Block Diagram


iCDR - Block Diagram


FIELDS Features

• FIELDS is composed of– 4 forward mounted electric field antennas – V1234

• Includes antenna deployment assembly, antenna whip, preamplifier, mid-point cage and fork

– 1 boom mounted electric field probe – V5– 2 boom mounted DC magnetometers – MAGo and MAGi– 1 boom mounted tri-axial search coil magnetometer – SCM– 1 electronics package mounted inside S/C body – MEP

• Composed of 9 slices– Harnesses to match

• FIELDS is split into two halves – F1 and F2 - to enhance reliability– Each half has a DPU with interface to/from S/C– Each half has a DPU with interface to MAG, antenna bias control and

power supply– Halves are separate but tightly coupled

• Fully synchronized (master/slave) timing and clocking• FIELDS has an interface to the SWEAP instrument

– Message passing– Synchronized timing– Wave particle correlation


FIELDS Timing

• Power supply chopping frequency is 150,000kHz• FIELDS master frequency is 150,000 * 256 Hz is 38,400,000

Hz– (±4 kHz)

• All FIELDS instruments will be operated in synchronization with the master frequency

• The highest sampling rate will be 150,000 Sa/s * 256 which is 38,400,000Sa/s

• The lowest sampling rate will be 150,000 Sa/s / 512 which is ~293Sa/s

• With 256 samples, FIELDS has a natural cycle time of .87 seconds/cycle– 131,072 / 150,000 Hz– 217 / 150,000 Hz– ~.8738s per cycle – the FIELDS New York second

• MAG samples in sync at ~293 vectors/second – 256 vectors/NY-second

• DFB samples in sync at 150,000 Sa/s giving rates synchronized to match MAG

• TDS samples in sync at ~2MSa/s (1.92MSa/s = 38,400,000 / 20)

• RFS samples in sync at 38,400,000 Sa/s


FIELDS Major Changes

• V1234 heater harnessing now provided by S/C– Eliminated 6 pass-thru connectors on MEP

• V1234 harnessing to MEP improved for RF– Coax bulkhead pass-thru’s

• V5 now thermally bonded to MAG boom– Less extreme temperature excursions

• MEP moved to a louvered radiator– Reduced MEP operating/testing temperature

• MAG boom length has been determined – 3.5m• 4 MAG boom mounted sensors have been accommodated

– DC MAG separation increased– Possible inter-sensor interference shown to be minimal

• V1234 whip length has been determined – 2m (no change)• Vibration levels have increased for V1234 antennas


V1234 (x4)


MAG (x2)


V5


SCM


Main Electronics Package


FIELDS1 and FIELDS2


Project-Level Documentation

• Project-level Documentation– Daily use

APLDocumentNumber

Version Title

7434-9051 - -> B PAY_PayloadRequirementsDocument7434-9066 B GI_ICD7434-9055 A -> B FIELDS_ICD7434-9078 a MOC-SOC7434-9039 B EDTRD7434-9040 - EMECP7434-9011 - CCP7434-9001 A PartsControlPlan7434-9009 A MaterialsAndProcesses7434-9096 A QA Matrix7434-9176 ITsecurityMatrix7434-9101 - SDMP


Project-Level Documentation

• Project-level Documentation– Generally applied to FIELDS

APLDocumentNumber

Version Title

7434-9000 B SPP Project Plan7434-9002 - SPP Review Plan7434-9003 C PAIP7434-9005 B RiskManagement7434-9006 B CM7434-9007 A SystemsEngineeringManagementPlan7434-9013 - Safety7434-9016 A ConOps7434-9036 a Logistics7434-9037 - SoftwareAssurance7434-9041 A ReliabilityProgramPlan7434-9042 - SoftwareDevelopmentManagementPlan7434-9044 A Technology7434-9047 D MRD_MissionRequirementsDocument7434-9048 A SCRD_SpacecraftRequirementsDocument7434-9099 - SystemVerificationAndValidation7434-9160 A CDE_SOW7434-9161 A CDRL_DID7434-9530 - ScheduleManagement7434-9531 - Spacecraft MICD34-8902 a SPP_Harness_Fabrication_Spec


FIELDS Interfaces

• FIELDS-level ICDs

Title Status

SPF_MEP_110Q_Connectors CCSPF_PRE_101_V5_ICD_REV1 CCSPF_MEP_111_Grounding_RevC CCSPF_MEP_112_Grounding_Internal newSPF_MEP_106_LNPS_ICD specSPF_MEP_104_AEB_ICD_REV4 CCSPF_MEP_103_MAG_ICD_REV4 CCSPF_MEP_102_DFB_ICD_REV4 CCSPF_MEP_101_TDS_ICD_REV3 CCSPF_MEP_100_CDI_ICD_REV6 CCSPP-SCM-TEC-10000-SP-0081-LPC2E_Interface_control_document_v1-4 CCSPF-MEP-ICD-001R6 MEP MICD 25NOV2014 mechSPF-MEP-MEC-005 REV E MEP PCB OUTLINE mechSPF_MEP_105_SWEAP_ICD_RevC B->C


FIELDS Mechanical Overview

• FIELDS has been accommodated on the spacecraft– Includes 17 separate pieces – plus harnessing

• Mechanical Interfaces, mass NTE called out in the FIELDS ICD– CBE mass reported monthly

• Now including EM masses• Instrument designed to Environmental Specification

Requirements– Limit Loads, Stiffness, Venting, Shock– Vibration loads on V1234 recently increased due to acoustic coupling

• Covered in antenna presentation• Instrument tested per future rev C of the EDTRD

– Mass Properties at component level• Mass, CG (calculated for antenna assembly)• MOI by analysis

– Sine, Random vibration at component level• ETU to qualification levels• FM to acceptance levels

– No instrument-level acoustic test planned (no acoustically sensitive parts)


FIELDS Thermal Overview

• SPP – of course – presents its thermal challenges• FIELDS interface temperatures called out in the EDTRD and

ICD– MEP Operational: -25ºC to +50ºC

• Since iPDR, MEP-SC interface was reduced from 55C to 46C• MEP test temperature is now 60C• MEP worst case electronics derating is 75C• FPGA current/power thermal issues feared at iPDR have been resolved

– power increase as a function of temperature is not steep• FIELDS’ various thermal designs to be verified by analysis

and thermal vacuum testing– Modeling and Analysis performed cooperatively between FIELDS and

APL– Verification testing (Thermal Vacuum) described in I&T section– TV testing of EM LNPS1 and LNPS2 power supplies show good heat

rejection• Worst case LNPS1 power is 16W primary, 6.6W on board – 10C above

interface• Remaining thermal issue is the selection of high

temperature coax to run from V1234 preamplifiers to MEP– Working with Project - 3 possible solutions are in hand


FPGA Thermal/Power Relief

• LASP Test Results– Using an RTAX-proto– Using an –L part– Shows a modest

slope• Worst case hot

operating power can be reduced ~2W (still conservative)

• 2W re-allocated


FIELDS Electrical Interfaces

• Spacecraft interfaces are well defined• FIELDS1/DCB has 5 slices and:

– One bi-directional LVDS interface to/from S/C C&DH– One switched S/C primary power service – operational power– One (un)-switched S/C primary power – heater power (MAGo, SCM)– One bi-directional CDI interface to/from FIELDS2

• FIELDS2/TDS has 4 slices and:– One bi-directional LVDS interface to/from S/C C&DH– One switched S/C primary power service – operational power– One (un)-switched S/C primary power – heater power (MAGi)– One bi-directional CDI interface to/from FIELDS1– One bi-directional CDI interface to/from SWEAP – includes particle counts

• FIELDS has– (un)-switched S/C heater power – heater power (V1, V2, V3, V4)– Switched S/C deployment power – mid-point cage pin-pullers for V1, V2, V3 and

V4• All 4 cages deploy simultaneously

– Switched S/C deployment power – hinge pin-pullers for V1, V2, V3 and V4• Each antenna can be deployed separately (nominally)

– S/C supplied harnessing from MEP to 4 MAG boom mounted sensors


FIELDS Grounding


FIELDS Deviations and Waivers

• Pending waivers/deviations– Grounding

• Multiple signal to chassis grounding• Essential for RF – successful on STEREO

– Harnessing• SCM harness primary power in same harness as secondary power

and signal• Harness crosses two MAG boom hinges


FIELDS EMC

• FIELDS is actually a driver for EMC, ESC and MAG requirements– Power supply conversion control– Limited radiated and conducted noise– Electrostatics – S/C exterior an equipotential surface– Spacecraft must be magnetically clean– STEREO and RBSP are good models

• Spacecraft EMC testing plan needs to be worked– FIELDS antennas


EMC/ESC

• EMC– MEP box design includes EMC closeout

• stair-step joints, vent shielding, connector close-out– DC-DC converter frequency is 150kHz crystal controlled and

synchronized– DC-AC MAG heater is 150kHz synchronized– RF receiver is synchronized to a multiple of the 150kHz chopping

frequency• Numerical filtering removes noise spikes in frequency space

– All sampling is synchronized to 150kHz chopping frequency– Supply has front end filtering, soft start– Verification by EMC tests:

• ETU (CE on bench)• FM (CE, CS, RE, RS, BI, On/Off transients)

• ESC– Exterior surfaces are conductive and well connected to S/C

chassis ground– ESC Verification at the component level

• surface resistance measurements


EMC Issues

• EMC plan requires synchronized power supplies– All power supplies are to chop at multiples of 50kHz starting at

150kHz– Creates an allowable picket fence of noise in the frequency

domain– Creates deep troughs of quiet where we can make sensitive RF

measurements• A proven and economical technique for living with inevitable noise

– As it happens, a S/C subsystem will not comply– TWTA will have uncontrolled/unsynchronized power supplies at

about 20kHz– High power

• Work-around is to accept never doing science with TWTA turned on– Little impact below .25AU– Will make real-time commissioning less straight forward


EMC - Picket Fences


EMC/MAG

• EMC plan has required DC (<50nT) and AC (<10nT) levels at MAGi – 3.5m MAG boom doesn’t give much 1/r3

– Spacecraft must therefore be extra clean– As planned, the SPP spacecraft has a number of MAG

issues/compromises• TWTAs, reaction wheels, latch valves, etcetera• There are other MAG victims besides FIELDS’ MAGi/MAGo and SCM

– Making compensation difficult– While not ideal, stable DC fields can be removed as offsets

• Stability will help – in temperature and time (both short term and long term)

• Small will help• Fully characterizing the S/C fields will help

– MAG boom itself must be immaculate• Including all FIELDS sensors


DDD/Radiation

• Components inside boxes are generally immune• Harnessing is not immune

– Components connecting to external harnesses have considered DDD issues

• Protection has been added– Immunity will be demonstrated by analysis– Immunity will be tested with ETU zap testing

• Radiation environment inside spacecraft is fairly benign (20kRad)– Most EEE parts have no TID problem but select SE testing is

planned– Some parts require additional screening – possibly latch-up

circuitry • PMPCB in the loop

• Electronics outside the spacecraft analyzed separately – also benign

• Will have spot shielding in some locations– Planned for SCM preamplifier


Resources - Mass

• FIELDS mass tracking

• Many EM measured values

• Shows better than 10% margin at iCDR

• Overall ICD mass NTE– 19.65kg– ~2kg in reserve

• Allocation can move around to solve problems

• Detail in backups

Component Mass (kg)CBE Cont. % NTE

MEP 7.75 10% 8.52V1/2/3/4 3.92 10% 4.32SCM sensor 0.52 10% 0.57MAG sensors (2) 0.68 10% 0.75V5 sensor 0.06 10% 0.06Harnessing 3.75 10% 4.12Blankets 1.02 10% 1.12Total 17.69 10% 19.46

FIELDS NTE 11% 19.65


Resources - Power

• FIELDS operational power at room temperature shows ample contingency– 27%

• Reduced MEP S/C interface temperature of 46C and reduced FPGA power needs show lower power requirements when hot– 2W has safely gone back to

Project• And into our heaters

– NTE was 26.65W and is 24.63W

– Hot contingency is still 12%


Resources – Telemetry

• Telemetry bit-rate allows us to meet our science requirements

• Survey data goes to S/C C&DH SSR – 15Gb/perihelion• Select data goes to large FIELDS internal flash

storage– Selected data comes down during cruise – 5Gb/perihelion

• More bits is always more good!• Telecommand requirements are modest


Drawings

• Indentured Drawing List (IDL) is SPF_CDRL_CM-002-01B_IDL_001– Defines the instrument subassembly documents or IDLs

• Maintained by subassembly CogE – flight changes concurred by PM, SE and QA

• Defines current release version for each part• Red-lined changes are allowed, and marked up prints are kept in the

current build binder to document the current state of the flight hardware• Periodically these changes will be incorporated into the flight drawings,

the revs incremented, and a new revision of the IDL released• Instead of signing the individual drawings, the IDL listing the current

drawing revisions is signed

• Drawing Status– Almost all electrical drawings are complete and ready for flight

release– Almost all mechanical drawings are complete and ready for flight

release• with the exception of the new Antenna Shield Cradle which is being

finalized– These will be promoted to the flight release revision nomenclature

several weeks after iCDR to allow for incorporation of changes resulting from any RFAs


FIELDS PDR RFAs

• We had a total of 20 RFAs– 16 for FIELDS and 4 for Project– Responses have been entered into PIMS and marked as

“closed”– All 20 have been marked as concurred


Pre-CDR Peer Reviews

Review Date Reviewers RFAs RecsDCB-RFS Board 11/20/2014 10 0 12DCB FPGA 11/20/2014 10 0 0DCB FSW 11/20/2014 9 0 8AEB Board 11/19/2014 7 5 4

Preamps 11/19/2014 7 6 4

DFB Board 12/3/2014 10 4 0DFB FPGA 12/3/2014 10 0 0DFB ASIC 12/3/2014 10 0 0TDS Board 12/5/2014 8 0 6TDS FPGA 12/5/2014 8 0 7TDS FSW 12/5/2014 8 0 7LNPS Board 12/5/2014 8 0 17SCM Sensors 11/24/2014 12 0 0MEP Chassis 11/18/2014 7 0 4Antenna Systems (V1-V5) 11/18/2014 7 2 10Thermal 11/18/2014 7 0 8MAG System 12/10/2014 12 8 3TOTAL 150 25 90


Lessons Learned

• High fidelity engineering models make a smooth FM program– MAG simulator helps keep things real for FIELDS2/TDS

• Heat rejection has been a problem – made worse w/ SPP temperatures– New guidelines for PWB ground planes– New guidelines for PWB parts placement– New implementation for chassis/PWA mounting– Do early TV testing – to ensure that boards reject heat – don’t

run too hot• Build EM with TV-compatible parts• On slices with high power – like LNPS – TV even earlier

• Side benefit is that the EM can be used throughout the flight program


Concerns

• V1234 structure as related to new launch loads• V1234 harnessing selection – high temperature

coaxes– Working with Project

• Magnetic characterization of S/C and all components

• Final parts approval– Beam testing on TDS/ADC

• LVDS protection needs to be extended to SWEAP communications


Conclusion

• Requirements are understood• Documentation is in place• FIELDS engineering model program is well along• Designs and implementation meet or exceed

requirements• Instrument performance is excellent

– Subsystems play together as planned – synchronization works– Sensitivities are great

• Will continue with EM environments– Full high-fidelity EM will have lasting value

• on the bench throughout the mission

• FIELDS is on track to move forward to the flight program


Backup Slides


PAY-37

New:• MAG shall be capable of measuring 3D vector magnetic fields over solar orbital distances of

9.86 RS to 0.25 AU as follows:– frequency range: DC to greater than 100 Hz;– maximum field intensity: -65000 to +65000 nT;– cadence: up to 2x the highest frequency in vectors/sec;– minimum sensitivity (excluding external noise sources) better than:

• 4 nT in 65000 nT range;• 0.1 nT in 1000 nT range;

– MAG vector sensor accuracy: 0.2% of full range:• ±3.0 nT (1024 nT range);• ±9.2 nT (4096 nT range);• ±33.8 nT (16384 nT range);• ±132 nT (65536 nT range)

– in three orthogonal components.

Old:• MAG shall be capable of measuring 3D vector magnetic fields over solar orbital distances of

9.86 RS to 0.25 AU as follows:– frequency range: DC to greater than 100 Hz;– maximum field intensity: -65000 to +65000 nT;– cadence: up to 2x the highest frequency in vectors/sec;– minimum sensitivity (excluding external noise sources) better than:

• 4 nT in 65000 nT range;• 0.1 nT in 1000 nT range;

– MAG vector sensor accuracy: 5 nT;– in three orthogonal components


Resources – Mass Tracking

• FIELDS mass tracking

• Many EM values are now measured

• Shows better than 10% margin at iCDR

• Tracking subsystems– Some with increases– Some with reductions– Overall margin is ok

• Overall ICD mass NTE– 19.65kg


Resources – Power Detail

• FIELDS power tracking• Many values are now measured

on EM• Power broken out to track

dissipation location

• Heating broken into– Operational and survival– Above .25AU and below

GoetzFIELDS iCDR - SE Solar Probe Plus - FIELDS System Engineering Instrument CDR Keith Goetz...

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Transcript of GoetzFIELDS iCDR - SE Solar Probe Plus - FIELDS System Engineering Instrument CDR Keith Goetz...