1. Mission Overview Talk Outline: l Introduction l Mission Overview & Requirements l Observing Plan l Orbit/Telemetry l Launch Vehicle l R&D Strategy l Prelim. Project Organization l Prelim. Project Schedule & Costs l Summary l SuperNova /Acceleration Probe Presented by: Michael Levi July 9, 2002 l R&D Plan AN ARRAY OF CCD CHIPS WILL BE ASSEMBLED INTO AN ANNULUS NEARLY ONE HALF METER WIDE, THE LARGEST AND MOST SENSITIVE ASTRONOMICAL CCD IMAGER EVER CONSTRUCTED

2. Project History and Status Project conceived of in March 1999. Sizable active collaboration now exists. Project is being developed as a multi-agency partnership: —Team that produced current results was supported by DOE and NASA. —Science review by SAGENAP of 260 page proposal March 2000: strong endorsement of science and recommendation for study funding. —DOE support commenced after SAGENAP —Endorsement by HEPAP subpanel for development of cost, schedule, R&D —Call by NAS Turner panel for “a wide-field telescope in space” —NASA/SEU Roadmap now has a SNAP-like mission Currently in pre-conceptual design phase (equivalent to NASA pre-phase A) to develop key technologies. Cost to be determined by study phase in FY03 & 04

3. Active Members of SNAP Collaboration G. Aldering, C. Bebek, J. Bercovitz, W. Carithers, C. Day, S. Deustua*, D. Groom, S. Holland, D. Huterer*, A. Karcher, A. Kim, W. Kolbe, R. Lafever, M. Levi, E. Linder, S. Loken, P. Nugent, H. Oluseyi, S. Perlmutter, K. Robinson, A. Spadafora (Lawrence Berkeley National Laboratory) E. Commins, G. Goldhaber, S. Harris, P. Harvey, H. Heetderks, M. Lampton, J. Lamoureux, D. Pankow, C. Pennypacker, R. Pratt, M. Sholl, G. F. Smoot (UC Berkeley) C. Akerlof, G. Bernstein*, D. Levin, T. McKay, S. McKee, M. Schubnell, G. Tarle, A. Tomasch (U. Michigan) R. Ellis, R. Massey*, J. Rhodes, A. Refregier* (CalTech) N. Mostek, J. Musser, S. Mufson (Indiana) A. Fruchter (STScI) P. Astier, E. Barrelet, A. Bonnissent, A. Ealet, J-F. Genat, R. Malina, R.Pain, E. Prieto, G. Smadja, D. Vincent (France: IN2P3/INSU/LAM) R. Amanullah, L. Bergström, M. Eriksson, A. Goobar, E. Mörtsell (U. Stockholm) A. Mourao (Inst. Superior Tecnico,Lisbon)

4. Mission Requirements l Observe over 2000 type Ia Supernova —Quantity: Field-of-View one degree —Quality: 2% cross-wavelength calibration, from 400 - 1700 nm —Distribution: Ability to accurately study supernovae as far away as z<1.7 l Need consistent uniform data set where selection criteria can be applied and systematic sources can be analyzed and factored. l Minimum data set criteria: 1) discovery within 2 days (rest frame) of explosion, 2) 10 high S/N photometry points on lightcurve, 3) high quality peak spectrophotometry

5. Mission Design l How to obtain both data quantity AND data quality? —Batch processing techniques with wide field -- large multiplex advantage, —Wide field imager sensitive to 30 th magnitude —No trigger —Mostly preprogrammed observations, fixed fields —Very simple experiment, passive, almost like an accelerator expt. —Follow-up observations with spectrograph

6. Mission Design l SNAP design meets these objectives —Satellite: Dedicated instrument, few moving parts

7. Mission Design l SNAP design meets these scientific objectives —Satellite: Dedicated instrument, few moving parts —Telescope: 2 meter aperture sensitive to light from distant SNe

8. Mission Design l SNAP design meets these scientific objectives —Satellite: Dedicated instrument, few moving parts —Telescope: 2 meter aperture sensitive to light from distant SNe —Photometry: 1° FOV half-billion pixel mosaic camera, high-resistivity, rad-tolerant p-type CCDs (0.4-1.0  m) and, HgCdTe arrays (0.9-1.7  m).

9. Mission Design l SNAP design meets these scientific objectives —Satellite: Dedicated instrument, few moving parts —Telescope: 2 meter aperture sensitive to light from distant SNe —Photometry: 1° FOV half-billion pixel mosaic camera, high- resistivity, rad-tolerant p-type CCDs (0.4-1.0  m) and, HgCdTe arrays (0.9-1.7  m). —Integral field optical and IR spectroscopy: 0.35-1.7  m, 3”x3” FOV Shutters Cryostat/Cosmic Ray Shield Filters CCDs/HgCdTe Guiders Cold Plate Readout Electronics Spectrograph Thermal Links Radiator

10. SNAP Instrumentation Key Instruments: 1) GigaCAM Imager 1 degree FOV 36 CCD’s + 36 HgCdTe 2) Spectrograph low resolution high throughput 350 nm – 1700 nm These instruments coexist on a common focal plane, passively cooled to 140K.

11. Mission Overview Simple Observatory consists of : 1) Baffled Sun Shade w/ body mounted solar panel and instrument radiator on opposing side 2) 3 mirror telescope w/ separable kinematic mount 3) Instrument Suite 4) Spacecraft bus supporting telemetry (multiple antennae), propulsion, instrument electronics, etc No moving parts (ex. Shutters, reaction wheels), rigid simple structure.

12. What’s New Since Last Review Last ReviewNowComments Optical system delivered beam to three separate instruments Only one integrated focal plane Greatly simplifies optics, facilitated by common operating temp. Large complex filter wheelFilter wheel eliminated in favor of fixed filters. Facilitated by observing strategy. 4% of SNe (above z>1.2)~1/3 SNe are above z>1.2Robust IR system. FOV = 1 square degreeFOV = 0.68 square degreesSmaller instrumented region. Lunar assist orbit (19 x 57 Re) Highly Elliptical 3 day synchronous (2.6 x 24 Re) Eclipse time was 5.5 hrs, now < 2.2 hrs. Launch vehicle delivers us to final orbit. Gimbaled solar panelsBody mounted solar panelsRigid structure, quantizes movement of satellite Ejectable telescope coverOne time hinged doorMeets orbital debris policy. Fast Steering Mirror/PointingFast Guider on focal planeMeets pointing req’s. 3 ground stations1 ground stationOrbit permits data to be stored for transmission.

13. Questions from Last Review Determine observing requirements. what is the optimal red-shift distribution can we use a wider distribution of fields to test assumption of isotropy? can photometric redshifts be determined in advance? Determine photo-z requirement for the trigger. Non-Ia triggering. Weak lensing cost/benefit analysis. Based on current observing requirements the photometric observing capabilities of Subaru, PRIME, LSST, HST,, NGST,... Based on current observing requirements the spectroscopic observing capabilites of Keck, VLT, NGST, SNAP with AO, OH-suppression. Some cursory look into coordinated ground or planned space alternative or complementary missions. Determine SNAP exposure-time requirements for the faintest spectroscopy. Shown no need for initial photo-z survey. Analysis of K-correction, Malmquist-bias errors. Redshift range justification. Anisotropy possibilities for the dark energy. Theoretical analysis of dithering. SCP experience with subtractions. The evil produced by not having a shutter. How to do standard star calibrations. Can simple cuts provide an efficient trigger. Answers are online

14. Questions from Last Review In progress: Error budget. Not enough people are working on this. Gravitational lensing, gray dust, and host-galaxy dust are problematic. SN evolution errors are based on observing requirements. Justification of calibration requirements. Summarizing results for observing capabilities of different observatories to construct viable alternatives, possiblities for descoping SNAP, shifting work to the ground, and prioritizing the instrumentation suite. Note that the capabilites have been determined. Make the matrix the committee wanted. Rerun all the different telescope capabilities based on new observing requirements. Alternative methods for reducing sources of systematic error. Software that demonstrates ability to sucessfully subtract galaxies with substructure with dithered images. More looking into future telescope/detector/AO developments.

15. Questions from Last Review 1. The observing strategy:  what is the optimal red-shift distribution can we use a wider distribution of fields to test assumption of isotropy? can photometric redshifts be determined in advance? 2. Calibration: - show error budget and detailed list of contributions - justify error budget in terms of science goals - present a detailed calibration plan - how will SNAP deal with "absolute relative" problem? 3. Instrument design: multiplicity of concepts was confusing moving parts (shutter, filter wheel) are single point failures, not taken seriously enough insufficient detail presented explain flowdown of science requirements to instrument design prioritize instrument suite relative to science requirements what existing or planned missions can provide data that will allow SNAP to descope/simplify the instrument design? In particular, is Gigacam really needed or can ground-based telescopes be used? Fill out matrix suggested by committee

16. Questions from Last Review 4. Gigacam: no major concerns except for cross-talk need real astronomical data with commercially produced CCDs ASICs - manpower concerns, plan for space qualification 5. near-IR: need hands-on experience with HgCdTe devices 6. Spectrograph: overly optimistic estimates of throughput, QE, noise; need a more realistic performance assessment do not neglect zodiacal background, structure can NGST be used for spectroscopy instead? 7. Telescope: fast steering mirror - trade study 8. Spacecraft: allow for a 1 arc-sec rms pointing jitter

17. Questions from Last Review 9. Computing: cost and manpower for computing greatly underestimated present a complete system data flow plan data archival and community access is a major concern that comes up numerous times want input from the astronomy community in formulating a plan and a list of other observational science that could use SNAP data 10. Management: clarify relationship to NASA 11. Cost: increase contingency on R&D budget

18. Observation Concept Imager Step the focal plane through the observation field. Fixed length exposures determined by a shutter. Multiple exposures per filter. —To implement dithering pattern. —To eliminate cosmic ray pollution. All stars see all filters (modulo field edge effects). Fields revisited every four days. Spectrograph SNe candidates are scheduled for spectrographic measurement near peak luminosity. Analysis done on ground to identify Type Ia and roughly determine z. Note peak luminosity is 18 days to 45 days after discovery for z = 0 and 1.7 respectively.

19. How Mission Operations map onto the Instrument Concept Reliability Shutter is the only major moving part, Minimal onboard data processing. Satellite Body mounted radiator and solar panels provide a stable platform for long exposures, Passive, radiative cooling, But, quantizes orientation of the focal plane relative to observation fields. Orbit and telemetry 3 day orbit period a good match to data generation, Generated data volume per orbit compatible with available solid state recorders, Telemetry band width and dwell time over ground station compatible with down-linking an orbit’s data buffer.

20. Requirements Development Science Measure  M and  Measure w and w (z) Data Set Requirements Discoveries 3.8 mag before max Spectroscopy with  ~100 Near-IR spectroscopy to 1.7  m Statistical Requirements Sufficient (~2000) numbers of SNe Ia …distributed in redshift …out to z < 1.7 Systematics Requirements Identified and proposed systematics: Measurements to eliminate / bound each one to +/–0.02 mag Satellite / Instrumentation Requirements 2-meter mirrorDerived requirements: 1-degree imager High Earth orbit Low resolution spectrograph ~250 Mb/sec bandwidth (0.35  m to 1.7  m)

21. Requirements Development Four Key Level 1 Science Requirements: 1.Quantity 2.Quality 3.Spectroscopy 4.Surveys

22. SNAP Level 1&2 Science Requirements 1.1Obtain over 2000 Type Ia supernovae in the redshift range 0.2 < z < 1.7 1.1.1Observatory to be a 2 meter diameter telescope with I-band diffraction limited optics sensitive from 0.4 to 1.7 microns. 1.1.2Instrumented field of view of telescope to be approximately one degree (~0.7 square degrees) 1.1.3Perform wide field imaging of regions of low dust extinction near the ecliptic poles with a solar avoidance angle of 70 degrees. 1.1.4Photometric observations are to be zodiacal light limited. 1.1.5Obtain > 100 Type Ia SNe per 0.1 redshift bin from redshift 0.5 < z < 1.5, and >50 Type Ia SNe per 0.1 redshift bin from redshift 0.3 < z < 1.7

23. Supernova Survey SNe survey takes 1.3 years to obtain 2000 SNe Requirement

24. SNAP Level 1&2 Science Requirements 1.2Measure supernova peak luminosity on average to 2% 1.2.1Obtain photometric measurements in redshifted B-band broadband filters. 1.2.2Obtain peak and off-peak (plus and minus 4 days rest-frame) multi-band photometric measurements of SNe with S/N=30 1.2.3Measure risetime with detection at average 2 days after explosion at 3.8 magnitudes below peak with S/N>3, and peak-to-tail ratio of SNe. 1.2.4Obtain peak and off-peak multi-band photometric measurements totaling 10 points on the SNe lightcurve 1.2.5Measure SNe color and extinction with up to six visible light and three infra- red broadband filters from 0.4 to 1.7 microns

25. Ten Points on Lightcurve Key requirements: 1. Measurement at peak to S/N>30. 2. Measurement within average 2 days after explosion to S/N>3. 3. Minimum 10 points on lightcurve.

26. Focal Plane/Filter Photometry Field of View Optical ( 36 CCD’s) = 0.34 sq. deg. Four filters on each 10.5  m pixel CCD detector Field of View IR (36 HgCdTe’s) = 0.34 sq. deg. One filter on each 18  m pixel HgCdTe detector Focal plane is rotationally symmetric Pixel size of detectors matched to Airy disk.

27. Supernova Survey SNe survey takes 1.3 years to obtain 2000 SNe Survey size is 7.5 square degrees observed in 9 filters. 22 fields scanned with a 4 day cadence. Each exposure is 300 seconds long. Four exposures per position with a small dither pattern Then the satellite moves by one-half a detector interval (~175 arcsec)

28. Derived Requirements for the Imager VisibleNIRUnits Field of View0.34 degrees 2 Plate scale/pixel0.100.17Arcsec Wavelength400-1000900-1700nanometers Operating Temp.140 Kelvin Pixel size10.518 mm Number Detectors36 devices Architecture3510 x 35102048 x 2048pixels

29. SNAP Level 1&2 Science Requirements 1.3Obtain supernova spectrographic observations near peak intensity with a resolution R~100 over 0.4 to 1.7 microns wavelength. 1.3.1Measure supernova peak spectrum to identify and classify SNe 1.3.2Obtain spectrophotometric measurements with an average 2% accuracy 1.3.3Measure supernova spectra vs. epoch for subset of SNe with z<0.7 1.3.4Measure the broad (200A) Silicon (6150A rest-frame) and Sulfur (5350A rest-frame) features 1.3.5Obtain spectroscopic measurement of calibration standards

30. Spectroscopy SiII S 40% of the time the spectrograph is turned on and the satellite points to the supernovae During spectroscopy the exposure time increases to 1000 seconds. Both spectrograph and imager are active. Total integrated exposure time for spectroscopy is ~ 8 hours at z=1.7; varies as 6 th power of 1+z. Would use NGST for some highest redshift SNe if available and in viewing zone. Host galaxy redshifts from SNAP and ground assets.

31. Derived Requirements for the Spectrograph VisibleNIRUnits Field of View3 x 3 arcsec Plate scale/pixel0.15 arcsec Wavelength350-1000900-1700nanometers Resolution100  Operating Temp.140 Kelvin Pixel size18 mm Number Detectors11devices Architecture1024 x 1024 pixels

32. SNAP Level 1&2 Science Requirements 1.4Capable of performing deep multi-color photometric surveys with field sizes of approximately 10 and 500 square degrees 1.4.1 Mission operations and avoidance angles to permit wide field surveys up to 500 square degrees. 1.4.2 Minimum four visible broadband filters for photo-z measurements to facilitate weak-lensing surveys. 1.4.3 Provide stable point spread function for weak-lensing survey.

33. Weak Lensing Survey Weak Lensing survey takes 8 months Survey size is 500 square degrees. Each field is observed in 9 filters. ~1500 fields observed Each field is scanned across with the satellite moving by one-half a detector interval each time (175 arcsec). Each exposure is 500 seconds long. Four exposures per position with a small dither pattern

34. Observation Program After launch:  Correct initial orbit for injection errors, station-keeping  One month check out of spacecraft systems  16 month survey of the North Field  12 month Weak Lensing Survey, GO program, clean-up of SNe survey  16 month survey of the South Field  GO program as appropriate, clean-up of SNe survey  At end of mission, lift orbit into 7 day perturbed orbit, eventually ejected

35. Tools for Requirements Definition SNAPfast Monte Carlo implements detailed list of systematics Event generator - Create an object list with fluxes. Ingredients: Supernova types, Type Ia subclasses Galactic, host, and gray dust Gravitational lensing Image simulator and SN extraction - Measure photometry, spectra from images Data simulator - Generate light curves and spectra S/N calculated based on observatory parameters Calibration errors Detection efficiency - Measure contamination of non SNe Ia and Malmquist bias Light curve and spectrum fitter - Simultaneously fit key parameters of SNe Cosmology fitter - Determine best fit cosmological and dark energy parameters

36. Example SNAPfast Simulation Full SNAP model simulation of SNe lightcurve and fit. Simulates complete observation strategy. 2% average requirement

37. Studies Undertaken Completed Focal Plane Layout (LBNL) Spacecraft Accommodation (GSFC & SSL) Orbit (SSL & LBNL) Launch vehicle (Boeing) Telemetry (SSL) Telescope Optics (SSL) Telescope Stray Light (GSFC, SSL & LBNL) Thermal Study (SSL) Mechanical Structure (SSL) Focal Plane Guider (SSL, published) In progress:  Primary Mirror (RESOC/SAGEM)  Data Pipeline (STScI & LBNL)  Calibration Requirements (w/ simulation grp, STScI, Indiana, SSL, LBNL)  Independent Cost Study (Aerospace Corp.)  Instrumentation R&D

38. NASA GSFC/IMDC Spacecraft Study Propulsion Tanks Sub-system electronics Secondary Mirror and Active Mount Optical Bench Primary Mirror Thermal Radiator Solar Array Wrap around, body mounted 50% OSR & 50% Cells Detector/Camera Assembly from GSFC - IMDC study Two independent multi-week studies at GSFC:

39. SNAP Spacecraft 0.5m antenna 40 Ah Battery Star Tracker Reaction Wheels Propulsion Tanks CD&H ACS OCU PSE SSR

40. Orbit Optimization  High Earth Orbit  Good Overall Optimization of Mission Trade-offs  Low Earth Albedo Provides Multiple Advantages:  Minimum Thermal Change on Structure Reduces Demand on Attitude Control  Excellent Coverage from Berkeley Groundstation  Outside Outer Radiation Belt (elliptical 3 day - 86% of orbit)  Passive Cooling of Detectors  Minimizes Stray Light Chandra type highly elliptical orbit

41. SNAP Orbital Parameters 3 day synchronous orbit Perigee = 2.56 R e (geocentric), eg. 10,000 km altitude Apogee = 24.94 R e (geocentric) This orbit is in the plane of the moon and is stable against lunar perturbations. Also, simultaneously maximizes solar, lunar, and earth avoidance angles. Launch vehicle [Delta IV 4240] is capable of lifting 2020 kg to that orbit significant mass margin held in Perigee, Apogee, SC-propulsion. Can use equivalent Delta III, IV, Atlas, or Sea Launch. Time passage through radiation belts = 11.2 hours During this time SNAP is not observing, rather performing data dump. This corresponds to an 86% operational efficiency. Total proton dose from belts = 8 x 10 5 p/cm 2 /year [25 mm Al] Study is online

42. Ground Station Coverage Orbit perigee remains over Berkeley for 3 years without adjustment. 5.2 hour ground pass over Berkeley

43. Atlas-EPF Delta-III Sea Launch Launch Vehicle Study

44. Telemetry 250 Mbit/s downlink requirement 375 Gbytes storage requirement Requires 0.5m 6W Ka-band Xmit, with 10m ground station Study is online.

45. Flat focal plane Delivers < 0.04 arcsecond FWHM geometrical blur over field 1.37 sq Effective focal length 21.66m; f/10.8 final focus Provides side-mounted detector location for best detector cooling study is online Optical Study

46. Stray Light – Baffle Design Stray light study is online

47. Thermal Study OPTICS: Build,Test, & Fly Warm… KEY DESIGN FEATURES High Earth orbit (HEO) to minimize IR Earth-glow loads OSR striping of the (hot) solar array panels Low emissivity silvered mirrors Thermal Isolation mounting and MLI blanketing Study is Online

48. First vibration mode—62 hertz study is online Structural Study

49. R&D Management Risk Assessment Schedule Organization Funding ITAR

50. Detector R&D In the past year we have conducted a technical and scientific trade studies covering a range of options for the SNAP instrumentation suite. We have arrived at a coherent instrument working concept and observation strategy constrained by reliability, satellite, orbit, thermal, and telemetry issues and SNe characteristics that optimizes the science reach of SNAP. In developing this concept we have minimized risks by using proven solutions to the greatest extent possible. We have identified risks in three detector technology areas: CCDs, HgCdTe, & custom integrated circuits. The R&D period concentrates on: Paper studies to eliminate or better understand these risks. A limited, focused hands-on R&D program to mitigate risk. Mitigating technical risk by the end of the R&D phase, NASA TRL Level 5- “Component and/or breadboard test in a relevant environment.” Producing a credible project cost and schedule

51. R&D Risk Assessment and Management Technology assessment and development —Risks documented with requirements and specification assumptions —Development of all technology to adequate flight readiness level R&D Phase Controls —Technical Definition —Systems requirements —Objectives/goals —Management —Manpower —WBS —Budget R&D Phase Performance metrics —Defined deliverables —Defined goals – such as detector deployment (ie. at a telescope) Goddard/Integrated Mission Design Center study in June 2001: no mission tall poles Goddard/Instrument Synthesis and Analysis Lab study in November 2001: no technology tall poles

52. Optical Imager Electronics IFU Spectrograph Spacecraft Software Analytical and experimental critical function, or characteristic proof-of-concept Guider Technology Readiness Assessments Assist in Development Plans 9 8 6 7 4 3 5 2 1 IR Imager Telescope System Test and Operations System/Subsystem Development Technology Demonstration Technology Development Research to Prove Feasibility Basic Technology Research Actual system flight proven or operational flight Actual system completed & "flight qualified" through test demonstration System prototype demonstrated in flight environment System/subsystem model or prototype demonstrated/validated in a relevant environment Component and/or breadboard test in a relevant environment Component and/or breadboard test in a laboratory environment Technology concept and/or application formulated (candidate selected) Basic principles observed and reported Technology Readiness Levels present state = CDR = PDR Goals:Achieve TRL 5 by CDR Achieve TRL 6 by PDR

53. Technology Issues NIR sensors HgCdTe detectors are begin developed for ESO, WFC3/HST, & NGST and are ideal in our spectrograph ASIC development is required (in progress for NGST) CCDs We have demonstrated radiation hardiness that is sufficient for the SNAP mission Properties of 10.5 micron pixel devices requires demonstration, esp. PSF. Industrialization of CCD fabrication has produced useful devices. Need to demonstrate volume. ASIC development is required Filters – we are investigating three strategies for fixed filters Suspending filters above sensors Gluing filters to sensors Direct deposition of filters onto sensors

54. Technology Readiness and Issues On-board data handling We have opted to send all data to ground to simplify the flight hardware and to minimize the development of flight-worthy software Ka-band telemetry, and long ground contacts are required. Goddard has validated this approach. Calibration There is an active group investigating all aspects of calibration Pointing Feedback from the focal plane, plus current generation attitude control systems, may have sufficient pointing accuracy so that nothing special needs be done with the sensors Fuel Slosh Will require full-up opto-mechanical simulation Telescope Primary mirror, thermal, stray light, mechanical control/alignment, I&T Software Data analysis pipeline architecture

55. SNAP Reviews/Studies/Milestones Mar 2000SAGENAP-1 Sep 2000NASA Structure and Evolution of the Universe (SEU) Dec 2000NAS/NRC Committee on Astronomy and Astrophysics Jan 2001DOE-HEP R&D Mar 2001DOE HEPAP Jun 2001NASA Integrated Mission Design Center July 2001NAS/NRC Committee on Physics of the Universe Nov 2001CNES (France Space Agency) Dec 2001NASA/SEU Strategic Planning Panel Dec 2001NASA Instrument Synthesis & Analysis Lab Jan 2002Two Special Sessions at AAS Meeting Mar 2002SAGENAP-2 Apr 2002NRC/CPU Report NOWDOE/SC-CMSD R&D (Lehman) Sept 2002NASA/SEU Releases Roadmap Oct 2002CNES Review

56. SNAP Pre-Project Planning Status CD-0 CD-1 Idea Development Strategic Plans DOE LBNL Pre- Conceptual Design Define Mission Need Conceptual Design Discovery SNAP March 1999 First Discussions Mar 2000 SAGENAP July 2001 SNOWMASS

58. SNAP Organization

59. Funding FY01: $400K direct support + $1000K directed from LBNL base FY02: $400K direct support + $1000K directed from LBNL base FY03 Initial Guidance: $400K direct support + $1000K directed from LBNL base. Requested Funds: FY03: $6M FY04: $9M

60. SNAP Funding Plan SNAP Funding Plan Fiscal YearRequested FundingPhase FY02$1.4M (actual)Study FY03$6MStudy FY04$9MStudy FY05$21MPreliminary Design FY06$39MConstruction** **estimate, 4 year construction cycle to be refined during study phase.

61. ITAR Compliance SNAP is an international collaboration SNAP is in compliance with the Arms Export Control Act and the International Traffic in Arms Regulations. March 2002 rule amends the regulation and establishes an exemption for institutions of higher learning. Lab consul is involved and advising on maintaining compliance. LBNL and its employees are in compliance with these acts. US SNAP collaborators are in compliance with these acts. SNAP has a policy of following the March 2002 rule. Making documents available in the public domain. ITAR has not been, nor should it be a problem for SNAP

62. Requirements development reached high level of sophistication Significant early trade-studies completed Significant progress in detector R&D Preparing ground-work for Conceptual Design activities and costing exercise. SNAP Pre-project Development Geared toward a Successful Mission http://snap.lbl.gov