Cosmic Ray Telescope for the Effects of Radiation (CRaTER) Radiation Detection and Dosimetry Workshop 7 April 2006 2 Figures of Cosmic Ray Telesope. Figure one indicates Crater, lamp, LROC, lend, LOLS, Mini-RF and Diviner. Second figure indicate size with labels 35 degrees, 54, 27 and 75 degrees. Harlan E. Spence, Boston University on behalf of the CRaTER Science Team Slide 2 CRaTER Science Team and Key Personnel Name Institution Role Harlan E. Spence BU PI Larry Kepko “” Co-I (E/PO, Cal, IODA lead) Justin C. Kasper MIT/BU Co-I (Project Scientist) J. Bernard Blake The Aerospace Corp Co-I (Detector lead) Joe E. Mazur “ ” Co-I (GCR/SPE Environment lead) Larry Townsend UT Knoxville Co-I (Transport code modeling lead) Michael J. Golightly AFRL Collaborator (Radiation Effects lead) Terry G. Onsager NOAA/SEC Collaborator (CR measurements, Space weather lead) Rick Foster MIT/BU Project Manager Bob Goeke MIT Systems Engineer Brian Klatt “ ” Q&A Chris Sweeney BU Instrument Test Slide 3 Lunar Reconnaissance Orbiter (LRO) Lunar Reconnaissanc Orbiter (LRO) decal. Southwest Research Institute, Boston University, Institute for Space Research, NASA GSFC, Northwestern University, UCLA on decal with moon and earth. Text Box: Lunar Reconnaissance Orbiter (LRO) Slide 4 1st Step in the Robotic Lunar Exploration Program – Launch: Oct 2008 drawing of Robotic Lunar Exploration Program. Labels Exploration testbeds, resources, and Solar, System History, Lunar Orbiter, Robotic Landing, Robotic Testbed Mission, Human Landings, moon. Images of moon, robot and satellite. Robotic Image of astronaut on lunar surface with label: Objective: Ther Lunar Reconnaissance Orbiter (LRO) mission objective is to conduct investigations that will be specifically targeted to prepare for and support future human exploration of the moon. LRO Objectives • Characterization of the lunar radiation environment, biological impacts, and potential mitigation. Key aspects of this objective include determining the global radiation environment, investigating the capabilities of potential shielding materials, and validating deep space radiation prototype hardware and software. • Develop a high resolution global, three dimensional geodetic grid of the Moon and provide the topography necessary for selecting future landing sites. • Assess in detail the resources and environments of the Moon’s polar regions. • High spatial resolution assessment of the Moon’s surface addressing elemental compositon, mineralogy, and Regolith characteristics Slide 5 LRO Mission Overview: Orbiter LRO Preliminary Design Preliminary LRO Characteristics Mass 1317 kg Dry: 603 kg Fuel: 714 Power 745 W Measurement 575 Gb/day Data Volume LRO Instruments • Lunar Orbiter Laser Altimeter (LOLA) Measurement Investigation– LOLA will determine the global topography of the lunar surface at high resolution, measure landing site slopes and search for polar ices in shadowed regions. • Lunar Reconnaissance Orbiter Camera (LROC)–LROC will acquire targeted images of the lunar surface capable of resolving small- scale features that could be landing site hazards, as well as wide- angle images at multiple wavelengths of the lunar poles to document changing illumination conditions and potential resources. • Lunar Exploration Neutron Detector (LEND)–LEND will map the flux of neutrons from the lunar surface to search for evidence of water ice and provide measurements of the space radiation environment which can be useful for future human exploration. • Diviner Lunar Radiometer Experiment–Diviner will map the temperature of the entire lunar surface at 300 meter horizontal scales to identify cold-traps and potential ice deposits. • Lyman-Alpha Mapping Project (LAMP)–LAMP will observe the entire lunar surface in the far ultraviolet. LAMP will search for surface ices and frosts in the polar regions and provide images of permanently shadowed regions illuminated only by starlight. • Cosmic Ray Telescope for the Effects of Radiation (CRaTER)– CRaTERwill will investigate the effect of galactic cosmic rays on tissue- equivalent plastics as a constraint on models of biological response to background space radiation. diagram of LRO preliminary design. Labels: Lamp, Avionics module, LOLA, LROC, CRaTER, Module, mini-RF, propulsion module, solar array another diagram of LRO Preliminary design with labels: lamp, instrument module, avionics module, HGA, solar array, diviner, LEND, propulsion module. Slide 6 image of LRO Slide 7 image of LRO Slide 8 CRaTER Science Measurement Concept diagram of LRO CRaTER; Insturment configration and Measurement concept. Labels for CRaTER, Zenith-viewing LRO instrument deck, Notional 3-axis stabilized LRO s/c, Nadir-viewing LRO instrument and imager deck. Also indicates 1. Primary solar and galactic cosmic ray sources, 2. secondary particle production at lunar surface, 3. other surface sources. Slide 9 CRaTER Telescope Configuration CRaTER Telescop configuration. Labels for: 35 degrees, 54, 27, 75 degrees, High LET detector, Low LET detector Slide 10 Assembly Stack of CRaTER Telescope diagram of assembly stack of CRaTER telescope. Labels: telescope housing, detector housings, TEP housing, TEP, Nadir aperture cover, HighLET detectors, Low LET detectors Slide 11 CRaTER Science Summary CRaTER’senergy spectral range: • 200 keV to 100 MeV (low LET detector chains) • 2 MeV to 1 GeV (high LET detector chains) • Energy resolution <0.5% (at max energy); GF ~ 0.1 cm2 - sr This corresponds to: • LET from 0.2 keV/µ to 7 MeV/ µ (stopping 1 Gev/nuc 56-Fe) • Excellent spectral overlap in the 100 kev/µ range (key range for RBEs) • GCR/SEP parent spectra measured by other spacecraft during mission • Biological assessment requires not incident CR spectrum, but lineal energy transfer (LET) spectra behind tissue-equivalent material • LET spectra are an important link, currently derived from models; experimental measurements required for critical ground truth – CRaTER will provide this key data product Slide12 CRaTER Primary Science Graphs and drawings. Graph 1 indicates predicted CRaTER counting rates based on historic GCR. Graph 2 indicates what CRaTER will explore on rapid GCR variations. Diagram of HIST Telescope sensor. • LET spectra constructed for GCR/SPE independently, zenith & nadir • Sorted according to lunar phase, LRO orbit phase, and lunar location • Will explore GCR fluctuations on short time scales (minutes to hours, of interest to LISA mission) Predicted CRaTER counting rates based on historic GCR (low level, slowly varying) and SPE (intense, rapidly varying) observations CRaTER will explore rapid GCR variations, discovered recently by NASA/Polar HIST (results presented last month at LISA meeting in UK) LET spectra sorted according to lunar phase and orbital position Slide 13 CRaTER Secondary Science – Muon“Limb Brightening” through Spallation Graph indicating Energy Level (MeV) diagrams of Muon "Limb Brightening" for mapping lunar rock and ice with CRaTER 3. Ultra-relativistic electrons deposit unique signature in bottom two detectors which view the local limb, bright with spallated muons. 2. Muon lifetime too short to reach LRO before decay, even with time dilation; muon decays into electon and neutrinos; electron carries momentum forward with ~100 MeV of kinetic energy 1. Spallation produces escaping forward-scattered muons, their properties a function of surface material. graphs of 750 MeV protons, 5 deg anorthite and ice Slide 14 Maximum singles detector rates CRaTER gets 100 kbits/sec!! graphs of Maximum D1 singles cougting rate from > 10 MeV ACE SIS and Slide 15 Recent CRaTERBeam Validation/Modeling Modeling SRIM, GEANT4, BBFRAG, HETC-HEDS, FLUKA, HZTRAN Beam Validation 12 September 2005 Detector prototype characterization at LBNL88” cyclotron 22 January 2005 TEPTA response to p+’s at MGH proton accelerator (10 - 230 MeV) 13 March 2006 Prototype detector/TEP characterization at LBNL (light ions) 27 March 2006 TEPTA response to heavy ions BNL(56-Fe, 0.3 & 1 Gev/n) – 4 hours of beam time May/June 2006 E/M detector LBNL June 2006 E/M CRaTER beam validation at BNL(56-Fe, 0.6 GeV/n) - 4 more of beam time Slide 16 Fragmentation of 1 GeV/nuc Fe in CRaTER • State-of-the-art in-development physics codes used for most complex interactions (energetic heavy ions) – these are codes that we hope CRaTER data products will ultimately improve • HETC-HEDS & BBFRAG (see example below) used to constrain extremes • Lab validation of TEP test apparatus and M unit in available beams graphs of nuclear fragmentation yields show of elements-Z leaving last material and beam degradation after passing through CRaTER with E/u leaving material -Beam degradation after passing -Nuclear fragmentation yields shower of elements after incident iron ion (cr: C. Zeitlin) Slide 17 CRaTERB eam Runs at LBNL and MGH 12 September 2005 –LBNL 88”cyclotron Image of Ion Beam Run at LBNL 22 January 2006 –MGH Proton Radiation Therapy Facility images of MGH Proton Radiation Therapy Facility with labels: Physics Beamline at 230 MeV MGH Proton Accelerator, Lucite, beam stop, TEP Test Apparatus SSdS & TEP. Slide 18 CRaTER Design Validation: MGH Results graphs of MGH Results for D1 and D3 energy response to 110-230 MeV p+; D1 D3 labels; Peak energy deposit decreases with increasing energy (Bragg effect); Peak energy deposit increases dramatically after passing thru TEP (Bethe-Bloch effect) D1 and 230 Normalized Counting Rate graph of MGH results with labels: Linear detector responses over broad deposited energy range agrees with model predication to within a few percent; TEO thickness inferred independently from energy response to better than 0.01%; deposited energy response at energies straddling Bragg peak Linear detector responses over broad deposited energy range agrees with Slide 19 CRaTER Beam Runs at BNL/NSRL 26 March 2006 images of BNL/NSRL-labs, deer, displays Slide 20 Very Preliminary CRaTER BNL/NSRL “Results” PRELIMINARY, RAW DATA! Warning: Species identified might actually be "Spuronium” (Sp)! graphs and images. Graph of Energy Deposited to Counts in D4; Image of 2-D histogram of all coincident events between D1/D4 and graph of Energy deposited in D1 (high LET) labels: Selected events in D4 identified as incident iron ions through multiple coincidence 2-D histogram of all coincident events between D1/D4 Energy in D1 D2 TEP D3 D4 Slide 21 CRaTER Data Products • Data products all related to primary measurement: LET in six silicon detectors embedded within TEP telescope • CRaTER L0->L4 data products described in table CRaTER Data Level Definitons for Level 0 to Level 4 Data Level Description Level 0 Unprocessed instrument data (pulse height at each detector, plus secondary science) and housekeeping data. Level 1 Depacketed science data, at 1-s resolution. Ancillary data pulled in (spacecraft attitude, calibration files, etc.) Level 2 Pulse heights converted into energy deposited in each detector. Calculation of Si LET Level 3 Data organized by particle environment (GCR), foreshock, magnetotail). SEP-associated events identified and extracted. Level 4 Calculation of incident energies from modeling/calibration curves and TEP LET spectra • Additional user-motivated data products might include: “Surface”, “Tissue”, and “Deep Tissue” Dose Rates (see next slide about JSC’s SRAG data request) • Calculated LET spectra in each detector, using best available GCR environment specification and one or more transport codes. Calculation done with no a priori knowledge of measurements - a straightforward, quick- look "prediction" using best available modeling capability. • NOTE: Onboard singles rates in CRaTER T/M can be used by other instruments to identify high rate conditions for possible safing (see in MRD-133, "The flight software shall support monitoring of any telemetry point and initiate stored command in response to pre-defined conditions".) CRaTER to use this feature for autonomous reconfiguration during SEP events. Slide 22 ESMD/SRAG User Interest in CRaTER Data Manned side of ESMD expressed interest in direct, early access to CRaTER data during the Level 1 requirements revision approval meeting at HQ in early January 2006 –no closure yet JSC Space Radiation Analysis Group (SRAG) –ongoing discussions since 10/05 VSE Workshop; Need to discuss details of their needs/requirements/desirements SRAG wants real data experience in operationally supporting manned lunar missions; CRaTER is a highly relevant instrument of interest at Moon Measurements from Clementine dosimeter show that lunar radiation environment is not accurately represented by GOES data (i.e., can’t bootstrap from near-Earth environment) SRAG’s main interest is “real-time” (R/T) data during SEPs; also interested in GCR (but not in R/T?) At a minimum SRAG wants following CRaTER data: • integrated count rate once per orbit for at least the D1 and D2 detectors in R/T. By R/T they mean within some short time (minutes to tens of minutes) of completion of an orbit. Additional desired CRaTER data includes: • temporally resolved (~once per minute) count rates, dumped once per orbit, for at least the D1 and D2 detectors; • integrated deposited energy (i.e., dose) once per orbit for at least D1 and D2 detectors • temporally resolved (~once per minute) deposited energy (i.e., dose), dumped once per orbit, for at least D1 and D2 detectors ; and • cumulative LET spectra once per orbit for at least D1 and D2 detectors. Possible data flow plan: • data sent from MOC to JSC MCC • CRaTER supplies SRAG with calibration values to convert from L0 data to dose and LET Proposed meeting with SRAG personnel with CRaTER team at Space Weather Week in April Slide 23 Web pages constantly in development at: crater.bu.edu (science site) snebulos.mit.edu/projects/crater (engineering site) Image of CRaTER web page with Instrument Overview Slide 24 Space Radiation “Dosimeter on A Chip" W. R. Crain, Jr, D. J. Mabry, and J.B. Blake Space Science Applications Laboratory The Aerospace Corporation Slide 25 Advanced Dosimeter Evolution Text Box: Heritage Dosimeter Box-level Design 5.5” x 7” x 1.9” (73 in cubed) 1.6 lbs 1.0 Watts @ 28V Digital interface to host Moderate host accommodation Text Box: Advanced Dosimeter Device-level design 1.5” x 1.5” x 0.3” (0.67 in cubed) < 0.1 lbs < 0.28 Watts @ 28V Thermistor-type interface Minimal host accommodation image of Heritable Dosimeter Box-level design. Image of advanced dosimeter device-level design (MCM package) Image of advanced dosimeter device-level design (ASIC) Slide 26 1st Advanced Dosimeter Result • Apogee 36,000 feet • Perigee 10 fathoms of seawater image of dosimeter after seawater result Slide 27 Advanced Radiation Dosimeter-on-a-Chip Project Objective: Develop very small, spaceflight devices to monitor total radiation dose to spacecraft. Description: image of dosimeter compared to dime Approach: Provide monitoring in real time of radiation dose using housekeeping level spacecraft resources. Enable the use of many dosimeters to provide dose at all critical locations. Key Milestones: • Dosimeter test at LBL88 (Mar 06) • LRO/CRaTER mission agreement • Enhanced ASIC fabrication and test • Enhanced dosimeter fabrication Slide 28 DosASIC Version 5 Layout layout of DosASIC version 5 with labels: Dose Integrator, Charge Amp Front-End, Dose Quantizer, and Output stage. Slide 29 • Particle energy-rate approach gives accurate and repeatable measurements –Single energy deposit from 50 keV to 10 MeV –Dose rates from 1 µRad/sec. to 10 mRad/sec. –20 µRad resolution diagram of Low noise front end, gated recycling integrator and dose memory and interface. Slide 30 Results to date: 1 of 2 • Version 5 ASIC testing completed in FY05 resulted in development of a new integrator architecture for improved radiation dose measurement in V6 chip graph of preliminary V06 simulation results of dose efficiency Improvements 1. Sharper Threshold 2. Temperature Stable 3. No tuning required Slide 31 Results to date: 2 of 2 Demonstrated end-to-end functional performance using Am241 alpha source (FY06) Other measurements Resource Goal Actual Comment Weight 45 g 20 g Margin for shielding Size 1.5”x1.5”x0.3” 1.0”x1.5”x0.3” In-spec but could be smaller Power @ 28V 280 mW 390 mW Diagnostic features account for half of growth Interface Analog Temp Analog Temp As planned Rec. Costs $5000 $2,500 Not including screening Slide 32 Milestones and Progress Report • Assembled 5 advanced dosimeter devices (FY06) and completed initial electrical and functional performance tests (Nov 05) • Two patent applications submitted (Jan 06) – S/C radiation dosimeter device – Radiation dosimeter system for wide area total dose profiling • Interface agreement in place for ride-of-opportunity on NASA/LRO CRaTER mission (Jan 06) • Dosimeter test at Lawrence Berkeley Lab (March 06) – Compare three dosimeter device results with laboratory dosimeters on same proton beam • Submit v.6 ASIC design with enhancements (July 06) • Target radhard process release (October 06) Slide 33 HRO image with Labels: To the Moon, Alice! Thank you, all. Backup Slides Slide 34 Competitively Selected LRO Instruments Provide Broad Benefits images and graphs depicting CRaTER, Diviner, Lamp, LEND, LOLA and LROC are next to labels INSTRUMENT Measurement Exploration Benefit Science Benefit CRaTER (BU+MIT) Cosmic Ray Telescope Tissue equivalent response Safe, lighter weight space Radiation conditions that influence life beyond Earth for the Effects of Radiation to radiation vehicles that protect humans Diviner 300m scale maps of Temperature, Determines conditions for systems Improved understanding of volatiles in the solar system - source, history, migration and deposition (UCLA) surface ice, rocks operability and water-ice location LAMP Maps of frosts in permanently Locate potential water-ice (as frosts) Improved understanding of volatiles in the solar system - source, history, migration and deposition (SWRI) Lyman-Alpha Mapping shadowed areas, etc. on the surface Project LEND Hydrogen content in and neutron Locate potential water-ice in lunar Improved understanding of volatiles in the solar system - source, history, migration and deposition (Russia) Lunar Exploration radiation maps from upper 1m of soil and enhanced crew safety Neutron Detector Moon at 5km scales, Rad > 10 MeV LOLA ~50m scale polar topography at Safe landing site selection, and Geological evolution of the solar system by geodetic topography (GSFC) Lunar Orbiter Laser < 1m vertical, roughness enhanced surface navigation (3D) Altimeter LROC 1000’s of 50cm/pixel images Safe landing sites through hazard Resource evaluation, impact flux and crustal evolution (NWU+MSSS) Lunar Recon (125km2), and entire Moon at identification; some resource Orbiter Camera 100m in UV, Visible identification Slide 35 Science/Measurement Overview CRaTER Objectives: “To characterize the global lunar radiation environment and its biological impacts.” “…to address the prime LRO objective and answer key questions required for enabling next phase of human exploration in our solar system. LRO CRaTER Instrument diagram layover Image of moon with astronaut with label for CRaTER Cosmic Ray Telescope for the Effects of Radiation Slide 36 CRaTER Traceability Matrix Measurment Parameters -> Pointing Energy Range (MeV) Energy resolution Time resolution Collection Geometric Factor Number of Spectra Behind Simutaneous (keV) (sec) duration (cm2-sr) Sensing How Many Shielding GCR/SCR Elements Depths Spectra Four CRaTER Measuremnt Goals (below) Measure primary and Zenith (primary and <1 (as low as 30 1 (norminal) > 1 year (to map As large as > 2 Surface and at - secondary source nadir (lunar albedo practical to >100 (as possible secondary possible several depths lunar LET spectra and other) high as practical) source surface locations) Simple, compact - > 10 > noise floor 60 (nominal) > 1 year (to obtain As small as > 2, but as few As many as - sensor with sufficient several SEP events) possible as possible feasible termporal, spectral sensitivity Investigate effect of - ~1 to > 100 30 1 (nominal) > 1 year (to obtain >0.1 cm2-sr ?5 Behind thin "hull" and Ancillary from shielding and tissue several SEP events) behind several depths GOES/ACE absorption at various centered on ~5 relevant depths gm/cm2 "tissue" Test models of LET - ~1 to >100 30 1 (nominal) > 1 year (to obtain >0.1 cm2-sr As many as Behind thin "hull" and Ancillary from spectra several SEP events) possible behind several depths GOES/ACE centered on ~5 gm/cm2 "tissue" Aggregate --> Zenith (primary) and 0.3 to 140 30 1 (nominal) > 1 year ~0.3 cm2-sr 5 Behind thin "hull" and Ancillary from Measurement nadir (lunar albedo behind several depths GOES/ACE Requirements and other) centered on ~5 gm/cm2 "tissue" Current energy spectral range: • 200 keV to 100 MeV(low LET); and • 2 MeV to 1 GeV(high LET) This corresponds to: • a range of LET 0.2 keV/µ to 7 MeV/µ (stopping a Gev/nuc Fe-56) • good spectral overlap in the 100 kev/µ range (key range for RBEs) Slide 37 Engineering Status Report • Minor design modifications pre-I-PDR to optimize science (5 det., 3 TEP configuration is now a 6 det., 2 TEP configuration) • Prototype detectors procured from flight vendor, testing began in September 2005; • Performance question at PDR fully resolved (it was a beam, not detector, “feature”) designs of prototype detectors shown • First batch of E/M detectors (procured using “flight rules") to arrive in April ‘06 (second no later than June '06) • CRaTER telescope simulator tested and design validated • Goal to perform end-to-end test of E/M in a beam before June '06 CDR still achievable Slide 38 Rapid prototype model of CRaTER Telescope Assembly, Rev 3 (or so…) 16 January 2006 model and design of CRaTER prototype Slide 39 table 3.0 Level 2 Traceability Matrix The matrix in this section traces the flow down from the level 1 requirements and data products stated in ESMD-RLEP-0010 and outlined in Section 2 to the CRaTER Level 2 requirements. The individual CRaTER Level 2 requirements, with detailed explanations of the rationale for each value, are provided in Section 4. Item Sec Requirement Quantity Parent CRaTER-L2-01 4.1 Measure the Linear Energy LET RLEP-LRO-M10 Transfer (LET) spectrum CRaTER L2-02 4.2 Measure change in LET TEP RLEP-LRO-M20 spectrum through Tissue Equivalent Plastic (TEP) CRaTER L2-03 4.3 Minimum pathlength through > 60 mm RLEP-LRO-M10 total TEP RLEP-LRO-M20 CRaTER L2-04 4.4 Two asymmetric TEP 1/3 and 2/3r RLEP-LRO-M20 components total length CRaTER L2-05 4.5 Minimum LET measurement 0.2 keV per RLEP-LRO-M10, micron RLEP-LRO-M20 CRaTER L2-06 4.6 Maximum LET measurement 7 MeV per RLEP-LRO-M10, micron RLEP-LRO-M20 CRaTER L2-07 4.7 Energy deposition resolution < 0.5% max RLEP-LRO-M10, energy RLEP-LRO-M20 CRaTER L2-08 4.8 Minimum full telescope 0.1 cm2 sr RLEP-LRO-M10 geometrical factor Table 3.1 CRaTER Level 2 instrument requirements and LRO parent Level 1 requirements Slide 40 table 5.0 Level 3 Traceability Matrix The table in this section traces the flow down from the CRaTER Level 2 requirements to the individual CRaTER Level 3 requirements. The individual CRaTER Level 3 requirements, with detailed explanations of the rationale for each value, are describe in Section 6. Item Sec Requirement Quantity Parent CRaTER-L3-01 6.1 Thin and thick detector pairs 140 and 1000 CRaTER-L2-01, microns CRaTER-L2-05, CRaTER-L2-06, CRaTER-L2-07 CRaTER L3-02 6.2 Minimum energy <250 keV CRaTER-L2-01 CRaTER L3-03 6.3 Nominal instrument shielding > 1524 micron CRaTER-L2-01 Al CRaTER L3-04 6.4 Nadir and zenith field of view <=762 micron CRaTER-L2-01 shielding Al CRaTER L3-05 6.5 Telescope stack Shield,D1D2, CRaTER-L2-01, A1, D3D4, A2, CRaTER-L2-02, D5D6, shield CRaTER-L2-04 CRaTER L3-06 6.6 Pathlength constraint < 10% for CRaTER-L2-01, D1D6 CRaTER-L2-02 CRaTER-L2-03 CRaTER L3-07 6.7 Zenith field of view <= 34 degrees CRaTER-L2-01, D2D5 CRaTER-L2-02 CRaTER L3-08 6.8 Nadir field of view V<= 70 degrees CRaTER-L2-01 D4D5 CRaTER L3-09 6.9 Calibration system Variable rate CRaTER-L2-07 and amplitude CRaTER L3-10 6.10 Event selection 64-bit mask CRaTER-L2-01 CRaTER L3-11 6.11 Maximum event transmission >= 1000 CRaTER-L2-01 rate events/sec CRaTER L3-12 6.12 Telemetry interface 32-02001 CRaTER L3-13 6.13 Power interface 32-03002 CRaTER L3-14 6.14 Thermal interface 32-02004 CRaTER L3-15 6.15 Mechanical interface 32-02003 Table 5.1 CRaTER Level 3 instrument requirements and parent Level 2 requirements table of CRaTER data product Data Level Description Level 0 Unprocessed instrument data (pulse height at each detector, plus secondary science) and housekeeping data in CCSDS packets. Level 1 Data extracted from CCSDS packets, with primary science data, at 1 - s resolution. Ancillary data pulled in (spacecraft attitude, calibration files, etc.) Level 2 Pulse heights converted into energy deposited in each detector using calibration conversio. Calculation of Si LET Level 3 Data organized by particle environment (GCR, foreshock, magnetotail). SEP-associated events identified and extracted. Level 4 Calculation of incident energies from modeling/calibration curves and TEP LET spectra Table 9.1: Overview of the CRaTER data products.