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The FIELDS Experiment

The FIELDS Experiment. Prof. Stuart D. Bale University of California, Berkeley. Agenda. Investigation team Overview Driving requirements Primary measurement requirements Design description Interface definition Heritage Changes since Proposal Technology development plan

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The FIELDS Experiment

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  1. The FIELDS Experiment Prof. Stuart D. Bale University of California, Berkeley

  2. Agenda • Investigation team • Overview • Driving requirements • Primary measurement requirements • Design description • Interface definition • Heritage • Changes since Proposal • Technology development plan • Resource summary • Operations concept • Verification & validation • Risks & mitigation • Trades • Phase B plans Picture of s/c from updated image file that shows the location of your instrument(s). To be provided by project Replace

  3. Investigation Team University of California, Berkeley University of Minnesota University of Colorado, Boulder NASA/Goddard Space Flight Center LESIA, Observatoire de Paris, Meudon LPC2E, CNES, Orleans PROMES, CNRS, Odeillo University of New Hampshire University of Maryland Smithsonian Astrophysical Observatory (SAO) University of Chicago Imperial College, London Queen Mary College, London IRFU, Uppsala

  4. Design - Sensors Electric Field Antennas 2.3 m Tip-to-Hinge Main Electronics Package Magnetometer Boom MAG (Outboard) MAG (Inboard) SCM

  5. Design – Block Diagram

  6. Investigation Team and Heritage University of California, Berkeley (RBSP, STEREO, THEMIS, Polar, FAST, Cluster) University of Minnesota (STEREO, Wind, Ulysses) University of Colorado, Boulder (MMS, MAVEN, RBSP, THEMIS) NASA/Goddard Space Flight Center (RBSP, MAVEN, STEREO, Messenger, Wind) LESIA, Observatoire de Paris, Meudon(Solar Orbiter, Bepi-, STEREO, Wind, Ulysses) LPC2E, CNES, Orleans (Solar Orbiter, DEMETER) PROMES, CNRS, Odeillo University of New Hampshire University of Maryland Smithsonian Astrophysical Observatory (SAO) University of Chicago Imperial College, London Queen Mary College, London IRFU, Uppsala

  7. Team Organization

  8. FIELDS Science (1/4) • “Trace the flow of energy that heats and accelerates the solar corona and solar wind” FIELDS will measure: • Alfven waves and Poynting (energy) flux • Turbulent cascade and dissipation • Compressive waves and cyclotron damping • Magnetic reconnection and collisionless shocks • Velocity-space (expansion) instabilities • Signatures of ambipolar potential (exospheric physics)

  9. FIELDS Science (2/4) • “Determine the structure and dynamics of the plasma and magnetic fields at the sources of the solar wind” FIELDS will measure: • Magnetic field polarity and flux tube structure • Reconnection current sheets • Statistics of (Parker) nano-/micro-flares • Streamer belt reconnection • Streamer belt latitudinal extent

  10. FIELDS Science (3/4) • “Explore mechanisms that accelerate and transport energetic particles” FIELDS will measure: • Interplanetary shocks: Shock magnetic, electric, and density compression, foreshock waves, energy budget • Type II and type III radio bursts:Shock- and flare-related electrons, remote shock speed, throttling instabilities • Solar wind magnetic reconnection: Reconnection rate, exhaust structure • Stochastic (turbulent) acceleration: Fluctuation fields, compressive fluctuations, instabilities

  11. FIELDS Science (4/4) • Interplanetary Dust (Bonus) FIELDS will measure: • Voltage spectral signatures of nanodust impacts • Voltage signatures of micron-scale dust impacts • Spatial distribution of dust particles in the heliosphere

  12. FIELDS Measurements (1/4) • FIELDS needs to make rapid measurements of intense fields • High cadence sampling • Burst memory system • Floating voltage preamps • Large dynamic range

  13. FIELDS Measurements (2/4) Electric field bandwidth and dynamic range

  14. FIELDS Measurements (3/4) Pre-Phase A Magnetic field bandwidth and dynamic range

  15. FIELDS Measurements (4/4) Post-Phase A Magnetic field bandwidth and dynamic range REPLACE

  16. Driving Requirements • Measurement dynamic range and sensitivity • E-Field measurement range • From 20V/m (DC) to 2µV/m (at freq > 1MHz assuming 25kHz BW) • B-Field measurement range • From 5000 nT (DC) to 0.5pT (at freq > 100kHz assuming 2.5kHz BW) • Sensor Accommodation • E-Field Antennas • Minimize effects of plasma wake, mitigate by locating right behind TPS • Requires uniform illumination of antenna pairs, symmetry with S/C • Magnetometers • Minimize magnetic interference from S/C, best mitigated with boom length • Self compatibility of SCM and FGM, minimum 1m distance separation • EMC / ESC / Mag Cleanliness • Minimize interference from all sources, across DC-20MHz BW • Can use similar EMC program as demonstrated on STEREO / RBSP • Environment • Antennas thermal / sun exposure • Instrument thermal (survival and operating, large swings in operating) • Thruster plume

  17. Primary Measurement Requirements

  18. Design – E-Field Antenna • Whip exposed beyond umbra • Operates at +1300º C • Material: Niobium C-103 tube • Heat shield: layers of Nb sheet • Stub: Ti tube, Sensor lead SS wire • Actuators: P5 Pinpullers • Two required, whip cage and hinge • Dampers control deployment speed • Antenna/preamp mass: 700g ea • Two outputs from Preamp: • LF: DC to 1MHz (to AEB & DFB) • HF: 10kHz to 20 MHz (to TNR/HFR & TDS) Whip Thermal Isolator Heat Shield Stub Hinge / Damper Preamp Hinge Release Mechanism Shown in deployed state Lower portion behind TPS

  19. Design – E-Field Antenna • Deployment • Need something here Stowed Antenna Deployed Antenna

  20. Design – Antenna Configuration • Configuration on S/C • Antenna length: 2.3m • Tip-to-hinge length • Has ~0.4Hz response • Opposing antennas are colinear • Opposing antennas are equally illuminated • Antenna pairs are orthogonal • This is Preferred orientation • Can accept up to 5º non-orthogonality • Antenna crossing point is aligned with C/L of S/C • Antennas mount on TSA • Antennas are coplanarIn a plane just behind TPS • This configuration moves antennas ahead of plasma wake

  21. Design – Mag Boom Sensors SCM • Search Coil Magnetometer • 3 axis LF antennas with HF winding on one axis • Embedded preamp • LF: 10Hz to 20kHz • HF: 1kHz to 1MHz • Sensitivity: • 1x10-2nT/√Hz at 100 Hz • 1x10-5nT/√Hz at 100kHz • Fluxgate Magnetometer • 3 Axis, ring core • Three ranges: • ±512nT, ±8192nT, ±65536nT • Sensitivity: 0.1nT (in low range) • Bandwidth: DC – 32Hz MAG

  22. Design – Mag Boom ConfigurationCreates an integrated DC to 1MHz Magnetometer System • Separation distances are critical • Interference from S/C • Heritage shows that boom length is easiest method to mitigate S/C near field noise • Phase B trade study will determine accommodation, with 2m separation a goal • Sensor-to-Sensor interference • Tests have demonstrated that 1m separation is adequate • Magnetically coupled interference and sensor heater effects attenuated at this distance • Cable effects • Provide adequate shielding, magnetic cancellation, routing around sensors MAG SCM MAG ≥0.7 m 1 m 1 m

  23. Design – Main Electronics Package IMAGE-FUV MEP (above) THEMIS IDPU (below) • FIELDS MEP: • Mass: 6.2 kg (100mil wall) • Power: 14.8 W • TNR/HFR (Thermal Noise Receiver / High Frequency Receiver) • Power and cross spectra for QTN and RF emission to 20MHz • TDS (Time Domain Sampler) • Burst waveforms to 2Msps, event selection • MAG (Magnetometer Electronics 1 & 2) • Supports two fluxgate mags, 3 axes to 30Hz • DFB (Digital Fields Board) • Waveforms DC - 128ksps, LF power and cross spectra • AEB (Antenna Electronics Board) • Floating ground, antenna biasing, calibration source • ICU (Instrument Control Unit) • 32 GB Burst Memory, S/C Data interface • LNPS (Low Noise Power Supply) • S/C power interface, EMC compliant

  24. FIELDS - S/C Interface • Data Interface: Command (TC), Telemetry (TM) and PPS • Redundant S/C C&DH • UART interface, 115kbaud, LVDS • Data transfers synchronized to 1PPS • Requires ICU to listen to both sides • Requires S/C to direct TC from one side only • Power Interface • Unregulated 28V (+7V/-6V), switched services • Survival Power • SCM and MAG heaters controlled via MEP, MAG requires AC heater • E-Field Preamps direct connection, DC heaters • S/C monitors temperatures • Actuator Power • S/C controls actuators directly, redundant Pin Puller interfaces

  25. FIELDS – SWEAP Interface • Interface purpose • Synchronization of data sampling • Exchange of real time data, e.g. MAG field data to SWEAP • High time resolution wave-particle correlations

  26. Changes since Proposal Proposed version Antenna Shown deployed Picture of current antenna here • Addition of Low Noise Power Supply to MEP • AO specified that Instrument would receive secondary power from S/C • Change E-Field Antenna mounting, Increase length • AO specified a configuration that limited antenna length • Configuration now is lower mass than proposed • Added SWEAP Interface • Reduction in Telemetry • From 32Gb/orbit to 20Gb/orbit (avg) plus Science Campaign allocations

  27. Technology Development Plan Need a view of this that includes TPS FIELDS E-Field Antennas • Description • E-Field Antennas, whips and heat shield exposed to Sun • Driving Requirement • Antennas must have unobstructed illumination, provideE-Field sensing at temperatures ~1500ºC • Key Development Milestones • Material selected pre-Proposal (Niobium C-103) • Coupon testing at PROMES solar furnace • Verified optical properties • Thermal models correlated w/ S/C models (Phase A) • Phase B development plan • Coupon level testing to verify EOL properties • Model testing at PROMES to verify thermal model • Photoelectron emission testing • Demonstrate TRL6 by PDR • Risk Mitigation • Testing begins in Nov 2011 • Alternate materials (Tantalum, Rhenium) Whip Heat Shield

  28. Resource Summary - FIELDS CBE (Margin) • Mass: xx (xx) kg • Power: xx (xx) W • Telemetry volume: xx Gbit/orbit • Additional telemetry used in campaign mode: xx Gbit • Burst mode

  29. Operations Concept • (1 page) • Commissioning • Normal operations (eg. No duty cycling) • Bursting (if applicable) • Command and data handling • SOC Operations will be run from institution name

  30. Instrument Verification & Validation Plan PROMES Solar Furnace, Odeillo, France Large TVAC Chamber at UCB THEMIS Instrument Suite in TVAC

  31. S/C Level Instrument V & V Plan FIELDS Will Support APL’s Verification of Spacecraft FIELDS Flow Will be as Simple as Possible Expect “Bolt-Hole” Alignments are Sufficient for Boom Systems

  32. FIELDS Instrument Risks Status 5 4 PSM F8 3 PS F9 Likelihood of Occurrence (probability) P P P P P F6 F5 F1 F2 F7 2 P CS CS CS F12 F3 F10 F11 1 1 2 3 4 5 Consequence of Occurrence (Impact) Mitigation Plans in Place for All FIELDS Risks

  33. F5-P: Risk Burn Down A 25 B 20 Risk Grade 15 C 10 5 D * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  34. FIELDS Risks Status Anticipated at End of Phase B 5 4 3 PS F9 Likelihood of Occurrence (probability) P P P P P F2 F1 F6 F5 F7 2 CS P CS F3 F12 F11 1 1 2 3 4 5 Consequence of Occurrence (Impact) FIELDS Risk Posture Improved by end of Phase B

  35. FIELDS Phase B Risks Mitigation • FIELDS Risk Mitigation activities for Phase B include: • Antenna Qualification: • Nb materials testing, optical props aging (~3/12, Odeillo, France) • Antenna model thermal testing (~3/13, Odeillo, France) • Additional contingency test, if needed (TBD, Odeillo, France) • SCM / MAG / FGM Trade: • Determine the optimal technical (dynamic range) & resource (mass and thermal) solution (close by 4/12) • See Trades Slide for additional information. • MAG Performance Over Temperature: • MAG Cold Performance Test (~12/11) • MAG Thermal Cycling Test (end of Phase B) • MAG/SCM Interference: • MAG/SCM Interference test (similar to the MAG/FGM test performed in 7/11) (~4/13, Chambon, France)

  36. Phase B Magnetometer Trade

  37. FIELDS Phase B Plans

  38. SPP MDR 4-6 October 2011 FIELDS Instrument Backup

  39. Primary Measurement Requirements

  40. F1-P:Risk Burn Down A 25 20 Risk Grade 15 B 10 5 C * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  41. F2-P: Risk Burn Down 25 20 Risk Grade 15 10 5 A * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  42. F3-CS: Risk Burn Down A 25 20 Risk Grade 15 B 10 5 C D E * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  43. F6-P: Risk Burn Down A 25 B 20 Risk Grade 15 10 5 * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  44. F7-P: Risk Burn Down A 25 B 20 Risk Grade 15 C 10 5 * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  45. F8-PSM: Risk Burn Down A 25 20 Risk Grade 15 10 5 * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  46. F9-FS: Risk Burn Down A 25 B 20 Risk Grade 15 10 5 * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  47. F10-PS: Risk Burn Down A 25 B 20 Risk Grade 15 C 10 5 * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  48. F11-S: Risk Burn Down A 25 B 20 Risk Grade 15 C 10 5 D * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

  49. F12-P: Risk Burn Down A 25 B 20 Risk Grade 15 C 10 5 D * Grade = Likelihood x Consequence ** Assessment is the remaining risk assessed after successful event completion

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