GoetzFIELDS iCDR - SE Solar Probe Plus - FIELDS System Engineering Instrument CDR Keith Goetz University of Minnesota 1

GoetzFIELDS iCDR - SE Agenda Requirements Flow Instrument Description Changes Documentation Overviews – mechanical, thermal, electrical Deviations/Waivers EMC/ESC/MAG/DDD/RAD Resources Reviews Issues/Conclusion 2

GoetzFIELDS iCDR - SE SPP L1 Requirements 3 Science ObjectiveObjective Questions Solar Wind Plasma Solar Wind Magnetic Field Electric Field and Plasma Waves Enrgetic Particles Large- scale Structure s 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? ✓✓ ✓ ✓

GoetzFIELDS iCDR - SE FIELDS L1 Requirements 4 Baseline Fields and Waves Measurements Req.MeasurementDynamic RangeCadenceBandwidth Magnetic Field140dB100k vectors/sDC - 50kHz Electric Field140dB2M vectors/sDC - 1MHz Plasma Waves140dB1 spectrum/s~5Hz - 1MHz QTN/Radio 100dB for QTN 80dB for radio 1 spectrum/4s QTN 1 spectrum/16s radio 10-2,500kHz QTN 1-16MHz radio Threshold Fields and Waves Measurements Req.MeasurementDynamic RangeCadenceBandwidth Magnetic Field125dB256 vectors/sDC - 128Hz Electric Field125dB256 vectors/sDC - 128Hz Plasma Waves90dB1 spectrum/10s~5Hz - 50kHz QTN/Radio 70dB for QTN 70dB for radio 1 spectrum/32s QTN 1 spectrum/32s radio 10-2,500kHz QTN 1-16MHz radio

GoetzFIELDS iCDR - SE FIELDS L2 Requirements 5 FIELDS Science Measurement Requirements IDRequirement Title BaselineThresholdCurrent MRD-89FIELDS: DC Magnetic Field -- dynamic range:140 dB125 dB140 dB ✔ -- cadence:100k vectors/sec256 vectors/sec150k vectors/sec -- bandwidth:DC – 50 kHzDC – 128 HzDC – 75 kHz MRD-99FIELDS: DC Electric Field -- dynamic range:140 dB125 dB140 dB ✔ -- cadence:2M vectors/sec256 vectors/sec2M vectors/sec -- bandwidth:DC – 1 MHzDC – 128 HzDC – 1 MHz MRD-103FIELDS: Plasma Waves -- dynamic range:140 dB90 dB140 dB ✔ -- cadence:1 spectrum/sec1 spectrum/10sec1 spectrum/sec -- bandwidth:5 Hz – 1 MHz5 Hz – 50 kHz5 Hz – ~2 MHz MRD-107FIELDS: Quasi-Thermal Noise -- dynamic range:100 dB70 dB100 dB ✔ -- cadence:1 spectrum / 4 sec1 spectrum / 32 sec1 spectrum / 4 sec -- bandwidth:10 – 2500 kHz MRD-108FIELDS: Radio Emissions -- dynamic range:80 dB70 dB80 dB ✔ -- cadence:1 spectrum / 16 sec1 spectrum / 32 sec1 spectrum / 16 sec -- bandwidth:1 – 16 MHz 1 – 19.2 MHz

GoetzFIELDS iCDR - SE FIELDS L3 Driving Requirements 6 PAY-37 now matches science and instrument PAY-310 now protects SWEAP PAY-320 now requires antenna shifting IDTitle PAY-37Measurement: Magnetic Field MAG PAY-38Measurement: Magnetic Field SCM & Plasma Waves PAY-170Measurement: Electric Field & Plasma Waves PAY-172Measurement: Plasma Waves (AC Magnetic Field) PAY-174Measurement: Plasma Waves (Magnetic Field Power Spectra) PAY-272Measurement: Plasma Waves (Electric Field Power Spectra) PAY-175Measurement: Electric Field QTN Spectroscopy PAY-176Measurement: Electric Field Radio Emissions PAY-104Payload: Risk Category PAY-105Payload: FIELDS Burst Mode PAY-109Payload: Burst Mode Management PAY-113Timekeeping: FIELDS Time Knowledge Accuracy PAY-117Timekeeping: Support for Accuracy Verification PAY-112Payload: Flight Software Modification PAY-310FIELDS Protection Against Instrument Failure PAY-320ADC: FIELDS antennas compensation of TPS shift

GoetzFIELDS iCDR - SE FIELDS L3 General Requirements 7 PAY-309 now drives component selection and design IDTitle PAY-100Payload: Minimum Perihelion Hours PAY-101Payload: Baseline Mission Length PAY-309Payload: Backup Mission Length PAY-292Solar Storm Event Operability PAY-312Time-Critical Momentum Dumps PAY-118ADC: Spacecraft Coordinate Frame Definition PAY-313Instrument Sensor Clearance PAY-149FM: Instrument Fault Protection PAY-150FM: Instrument Power-Down Safe State PAY-221FM: Instrument Reconfiguration PAY-152FM: Instrument Power-Down Preparedness PAY-133CDH Data Delivery: Quick-Look Data PAY-134CDH Data: Data Sharing PAY-135CDH Data: Engineering Data Sharing PAY-136CDH Data: Public Dissemination PAY-137CDH Data Delivery: Data Retention at SOC PAY-138CDH Data Delivery: Data Retention at SOCs PAY-139CDH Data Delivery: Data Delivery to NASA

GoetzFIELDS iCDR - SE FIELDS L3 Compliance Requirements 8 IDTitle PAY-276Compliance: General Instrument Specification PAY-279Compliance: FIELDS to Spacecraft ICD PAY-277Compliance: FIELDS to SWEAP ICD (FIELDS) PAY-283Compliance: MOC to SOC ICD PAY-140Compliance: EMECP PAY-141Compliance: EDTRD PAY-148Compliance: CCP

GoetzFIELDS iCDR - SE FIELDS L4 Instrument Requirements 9 FIELDS Subsystems

GoetzFIELDS iCDR - SE FIELDS L4 Instrument Requirements 10 IDTitleL4 RequirementsTBD Parent ID (Level 3) Parent TitleFull TextOwner Verification Method (What test and when) DCB-01Mission LengthDCB Components shall be selected to withstand the environment of SPP for the duration of the mission PAY-309Payload: Backup Mission LengthAll instruments shall be designed to achieve an operational lifetime of at least 8 years after launch if launched during the 2019 backup launch period. FIELDS SWEAP WISPR ISIS Design Inspection (DCB Schematics, BOM): EEE Component Specifications and Stress Analysis Report; Parts radiation test reports when applicable DCB-02Spacecraft 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-276Compliance: General Instrument Specification All instruments shall comply with the requirements and constraints imposed by the General Instrument to Spacecraft ICD, Document FIELDS SWEAP WISPR ISIS Design Inspection: (DCB Specification) and board level functional tests to validate DCB-03TimingDCB 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-113Timekeeping: 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. FIELDSDesign Inspection (DCB Specification) and board level functional tests to validate DCB-04Burst Memory ManagementDCB 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-109Payload: Burst Mode ManagementFIELDS shall be responsible for management of its internal burst data buffer. FIELDSDesign Inspection (DCB Specification);verific ation 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

GoetzFIELDS iCDR - SE SPP Spacecraft 11

GoetzFIELDS iCDR - SE iPDR - Block Diagram 12

GoetzFIELDS iCDR - SE iCDR - Block Diagram 13

GoetzFIELDS iCDR - SE 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 14

GoetzFIELDS iCDR - SE 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 –2 17 / 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 15

GoetzFIELDS iCDR - SE 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 16

GoetzFIELDS iCDR - SE V1234 (x4) 17

GoetzFIELDS iCDR - SE MAG (x2) 18

GoetzFIELDS iCDR - SE V5 19

GoetzFIELDS iCDR - SE SCM 20

GoetzFIELDS iCDR - SE Main Electronics Package 21

GoetzFIELDS iCDR - SE FIELDS1 and FIELDS2 22

GoetzFIELDS iCDR - SE Project-Level Documentation Project-level Documentation –Daily use 23 APL Document Number VersionTitle > BPAY_PayloadRequirementsDocument BGI_ICD A -> BFIELDS_ICD aMOC-SOC BEDTRD EMECP CCP APartsControlPlan AMaterialsAndProcesses AQA Matrix ITsecurityMatrix SDMP

GoetzFIELDS iCDR - SE Project-Level Documentation Project-level Documentation –Generally applied to FIELDS 24 APL Document Number VersionTitle BSPP Project Plan SPP Review Plan CPAIP BRiskManagement BCM ASystemsEngineeringManagementPlan Safety AConOps aLogistics SoftwareAssurance AReliabilityProgramPlan SoftwareDevelopmentManagementPlan ATechnology DMRD_MissionRequirementsDocument ASCRD_SpacecraftRequirementsDocument SystemVerificationAndValidation ACDE_SOW ACDRL_DID ScheduleManagement Spacecraft MICD aSPP_Harness_Fabrication_Spec

GoetzFIELDS iCDR - SE FIELDS Interfaces FIELDS-level ICDs 25 TitleStatus SPF_MEP_110Q_ConnectorsCC SPF_PRE_101_V5_ICD_REV1CC SPF_MEP_111_Grounding_RevCCC SPF_MEP_112_Grounding_Internalnew SPF_MEP_106_LNPS_ICDspec SPF_MEP_104_AEB_ICD_REV4CC SPF_MEP_103_MAG_ICD_REV4CC SPF_MEP_102_DFB_ICD_REV4CC SPF_MEP_101_TDS_ICD_REV3CC SPF_MEP_100_CDI_ICD_REV6CC SPP-SCM-TEC SP-0081-LPC2E_Interface_control_document_v1-4CC SPF-MEP-ICD-001R6 MEP MICD 25NOV2014mech SPF-MEP-MEC-005 REV E MEP PCB OUTLINEmech SPF_MEP_105_SWEAP_ICD_RevCB->C

GoetzFIELDS iCDR - SE 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) 26

GoetzFIELDS iCDR - SE 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 27

GoetzFIELDS iCDR - SE FPGA Thermal/Power Relief 28 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

GoetzFIELDS iCDR - SE 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 29

GoetzFIELDS iCDR - SE FIELDS Grounding 30

GoetzFIELDS iCDR - SE 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 31

GoetzFIELDS iCDR - SE 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 32

GoetzFIELDS iCDR - SE 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 33

GoetzFIELDS iCDR - SE EMC Issues 34 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

GoetzFIELDS iCDR - SE EMC - Picket Fences 35

GoetzFIELDS iCDR - SE EMC/MAG EMC plan has required DC (<50nT) and AC (<10nT) levels at MAGi –3.5m MAG boom doesn’t give much 1/r 3 –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 36

GoetzFIELDS iCDR - SE 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 37

GoetzFIELDS iCDR - SE Resources - Mass 38 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) CBECont. %NTE MEP7.7510%8.52 V1/2/3/ %4.32 SCM sensor0.5210%0.57 MAG sensors (2)0.6810%0.75 V5 sensor0.0610%0.06 Harnessing3.7510%4.12 Blankets1.0210%1.12 Total %19.46 FIELDS NTE 11%19.65

GoetzFIELDS iCDR - SE Resources - Power 39 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%

GoetzFIELDS iCDR - SE Resources – Telemetry 40 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

GoetzFIELDS iCDR - SE Drawings Indentured Drawing List (IDL) is SPF_CDRL_CM B_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 41

GoetzFIELDS iCDR - SE FIELDS PDR RFAs 42 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

GoetzFIELDS iCDR - SE Pre-CDR Peer Reviews 43

GoetzFIELDS iCDR - SE Lessons Learned 44 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

GoetzFIELDS iCDR - SE 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 45

GoetzFIELDS iCDR - SE 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 46

GoetzFIELDS iCDR - SE 47 Backup Slides

GoetzFIELDS iCDR - SE PAY 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: to nT; –cadence: up to 2x the highest frequency in vectors/sec; –minimum sensitivity (excluding external noise sources) better than: 4 nT in 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: to nT; –cadence: up to 2x the highest frequency in vectors/sec; –minimum sensitivity (excluding external noise sources) better than: 4 nT in nT range; 0.1 nT in 1000 nT range; –MAG vector sensor accuracy: 5 nT; –in three orthogonal components

GoetzFIELDS iCDR - SE Resources – Mass Tracking 49 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

GoetzFIELDS iCDR - SE Resources – Power Detail 50 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