Mission OverviewMission Overview

Talk Outline: Introduction Mission Overview & Requirements Observing Plan Orbit/Telemetry Launch Vehicle R&D Strategy Prelim. Project Organization Prelim. Project Schedule & Costs Summary

SuperNova /Acceleration Probe

Presented by: Michael Levi

July 9, 2002

R&D PlanAN 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

Project History and StatusProject 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

Active Members of SNAP CollaborationActive 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)

Mission RequirementsMission Requirements

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

Need consistent uniform data set where selection criteria can be applied and systematic sources can be analyzed and factored.

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

Mission DesignMission Design

How to obtain both data quantity AND data quality?— Batch processing techniques with wide field -- large

multiplex advantage,

— Wide field imager sensitive to 30th magnitude

— No trigger

— Mostly preprogrammed observations, fixed fields

— Very simple experiment, passive, almost like an accelerator expt.

— Follow-up observations with spectrograph

Mission DesignMission Design

SNAP design meets these objectives— Satellite: Dedicated instrument, few moving parts

Mission DesignMission Design

SNAP design meets these scientific objectives— Satellite: Dedicated instrument, few moving parts

— Telescope: 2 meter aperture sensitive to light from distant SNe

Mission DesignMission Design

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).

Mission DesignMission Design

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/HgCdTeGuiders

Cold Plate

Readout Electronics

Spectrograph

Thermal Links

Radiator

SNAP InstrumentationSNAP 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.

Mission OverviewMission 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.

What’s New Since Last ReviewWhat’s New Since Last Review

Last Review Now Comments

Optical system delivered beam to three separate instruments

Only one integrated focal plane

Greatly simplifies optics, facilitated by common operating temp.

Large complex filter wheel Filter wheel eliminated in favor of fixed filters.

Facilitated by observing strategy.

4% of SNe (above z>1.2) ~1/3 SNe are above z>1.2 Robust IR system.

FOV = 1 square degree FOV = 0.68 square degrees Smaller 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 panels Body mounted solar panels Rigid structure, quantizes movement of satellite

Ejectable telescope cover One time hinged door Meets orbital debris policy.

Fast Steering Mirror/Pointing Fast Guider on focal plane Meets pointing req’s.

3 ground stations 1 ground station Orbit permits data to be stored for transmission.

Questions from Last ReviewQuestions 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

Questions from Last ReviewQuestions 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.

Observation ConceptObservation 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.

How Mission Operations map onto the How Mission Operations map onto the Instrument ConceptInstrument 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.

Requirements DevelopmentRequirements 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 RequirementsIdentified and proposed systematics:

• Measurements to eliminate / bound each one to +/–0.02 mag

Satellite / Instrumentation Requirements• 2-meter mirror Derived requirements:

• 1-degree imager • High Earth orbit

• Low resolution spectrograph • ~250 Mb/sec bandwidth (0.35 m to 1.7 m) •••

•••

Requirements DevelopmentRequirements Development

Four Key Level 1 Science Requirements:

1. Quantity

2. Quality

3. Spectroscopy

4. Surveys

SNAP Level 1&2 Science RequirementsSNAP Level 1&2 Science Requirements

1.1 Obtain over 2000 Type Ia supernovae in the redshift range 0.2 < z < 1.7

1.1.1 Observatory to be a 2 meter diameter telescope with I-band diffraction limited optics sensitive from 0.4 to 1.7 microns.

1.1.2 Instrumented field of view of telescope to be approximately one degree (~0.7 square degrees)

1.1.3 Perform wide field imaging of regions of low dust extinction near the ecliptic poles with a solar avoidance angle of 70 degrees.

1.1.4 Photometric observations are to be zodiacal light limited.

1.1.5 Obtain > 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

Supernova SurveySupernova Survey

SNe survey takes 1.3 years to obtain 2000 SNe

Number of SNe per 0.1 redshift

0

20

40

60

80

100

120

140

160

180

200

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

Redshift [z]

No

. S

Ne

/0.1

Requirement

Redshift #SNe/yr1494

0.1 00.2 260.3 480.4 710.5 930.6 1120.7 1280.8 1370.9 1341 127

1.1 1161.2 1061.3 971.4 891.5 801.6 701.7 60

SNAP Level 1&2 Science RequirementsSNAP Level 1&2 Science Requirements

1.2 Measure supernova peak luminosity on average to 2%

1.2.1 Obtain photometric measurements in redshifted B-band broadband filters.

1.2.2 Obtain peak and off-peak (plus and minus 4 days rest-frame) multi-band photometric measurements of SNe with S/N=30

1.2.3 Measure 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.

1.2.4 Obtain peak and off-peak multi-band photometric measurements totaling 10 points on the SNe lightcurve

1.2.5 Measure SNe color and extinction with up to six visible light and three infra-red broadband filters from 0.4 to 1.7 microns

Ten Points on LightcurveTen 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.

Focal Plane/Filter PhotometryFocal 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.

Supernova SurveySupernova 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)

Derived Requirements for the ImagerDerived Requirements for the Imager

Visible NIR Units

Field of View 0.34 0.34 degrees2

Plate scale/pixel 0.10 0.17 Arcsec

Wavelength 400-1000 900-1700 nanometers

Operating Temp. 140 140 Kelvin

Pixel size 10.5 18 m

Number Detectors 36 36 devices

Architecture 3510 x 3510 2048 x 2048 pixels

SNAP Level 1&2 Science RequirementsSNAP Level 1&2 Science Requirements

1.3 Obtain supernova spectrographic observations near peak intensity with a resolution R~100 over 0.4 to 1.7 microns wavelength.

1.3.1 Measure supernova peak spectrum to identify and classify SNe

1.3.2 Obtain spectrophotometric measurements with an average 2% accuracy

1.3.3 Measure supernova spectra vs. epoch for subset of SNe with z<0.7

1.3.4 Measure the broad (200A) Silicon (6150A rest-frame) and Sulfur (5350A rest-frame) features

1.3.5 Obtain spectroscopic measurement of calibration standards

SpectroscopySpectroscopy

SiIIS

• 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.

Derived Requirements for the SpectrographDerived Requirements for the Spectrograph

Visible NIR Units

Field of View 3 x 3 3 x 3 arcsec

Plate scale/pixel 0.15 0.15 arcsec

Wavelength 350-1000 900-1700 nanometers

Resolution 100 100

Operating Temp. 140 140 Kelvin

Pixel size 18 18 m

Number Detectors 1 1 devices

Architecture 1024 x 1024 1024 x 1024 pixels

SNAP Level 1&2 Science RequirementsSNAP Level 1&2 Science Requirements

1.4 Capable 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.

Weak Lensing SurveyWeak 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

Observation ProgramObservation 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

Tools for Requirements DefinitionTools 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

Example SNAPExample SNAPfastfast Simulation Simulation

Full SNAP model simulation of SNe lightcurve and fit.Simulates complete observation strategy.

2% average requirement

Studies UndertakenStudies 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

NASA GSFC/IMDC Spacecraft StudyNASA GSFC/IMDC Spacecraft Study

Propulsion Tanks

Sub-system

electronics

Secondary Mirrorand

Active Mount

Optical BenchPrimary Mirror

ThermalRadiator

Solar ArrayWrap around, body mounted

50% OSR & 50% Cells

Detector/CameraAssembly

from GSFC - IMDC study

Two independent multi-week studies at GSFC:

SNAP SpacecraftSNAP Spacecraft

0.5m antenna

40 Ah BatteryStar Tracker

Reaction Wheels

Propulsion Tanks

CD&H

ACS

OCU

PSE

SSR

Orbit OptimizationOrbit 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

SNAP Orbital ParametersSNAP Orbital Parameters

3 day synchronous orbit

Perigee = 2.56 Re (geocentric), eg. 10,000 km altitude

Apogee = 24.94 Re (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 orbitsignificant 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 hoursDuring this time SNAP is not observing, rather performing data dump.

This corresponds to an 86% operational efficiency.

Total proton dose from belts = 8 x 105 p/cm2/year [25 mm Al]

Study is online

Ground Station CoverageGround Station Coverage

Orbit perigee remains over Berkeley for 3 years without adjustment.5.2 hour ground pass over Berkeley

Atlas-EPF Delta-III Sea Launch

Launch Vehicle StudyLaunch Vehicle Study

TelemetryTelemetry

Compression 0.50Xmit Time (hrs) 4.2 (5.2 hrs ideal)

Xmit Overhead 0.21 (14% reed salomon, 6% Frame Header)

Technology Number Format^2 No. Bits Data (Gbytes/orbit)

Observing ProgramGigacam CCDs 36 3510 16 172.92

Gigacam HgCdTe 36 2048 32 117.74

Spectrograph ONGigacam CCDs 36 3510 16 36.27

Gigacam HgCdTe 36 2048 32 24.69

Spectrograph CCDs 1 1024 16 0.09

Spectrograph HgCdTe 1 1024 32 0.17

MonitoringGuider CCD (30Hz) 4 8 16 2.06

Packet Header (6%) 21.24

TOTAL 375.2 Gbytes/orbitTelemetry Bandwidth 246 Mbit/s

250 Mbit/s downlink requirement375 Gbytes storage requirementRequires 0.5m 6W Ka-band Xmit, with 10m ground station

Study is online.

Flat focal planeDelivers < 0.04 arcsecond FWHM geometrical blur over field 1.37 sqEffective focal length 21.66m; f/10.8 final focusProvides side-mounted detector location for best detector cooling

study is online

Optical StudyOptical Study

Stray Light – Baffle DesignStray Light – Baffle Design

Stray light study is onlineStray light study is online

Thermal StudyThermal 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

First vibration mode—62 hertzstudy is online

Structural StudyStructural Study

R&D ManagementR&D Management

• Risk Assessment

• Schedule

• Organization

• Funding

• ITAR

Detector R&DDetector 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

R&D Risk Assessment and ManagementR&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

Opt

ical

Imag

er

Elec

tron

ics

IFU

Sp

ectr

ogra

ph

Spac

ecra

ftSo

ftwar

e

Analytical and experimental critical function, or characteristic proof-of-concept

Gui

der

Technology Readiness Assessments Assist in Technology Readiness Assessments Assist in Development PlansDevelopment Plans

9

8

6

7

4

3

5

2

1

IR Im

ager

Tele

scop

e

System Test and Operations

System/SubsystemDevelopment

Technology Demonstration

Technology Development

Research to Prove Feasibility

Basic TechnologyResearch

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 CDRAchieve TRL 6 by PDR

SNAP Reviews/Studies/MilestonesSNAP Reviews/Studies/Milestones

Mar 2000 SAGENAP-1Sep 2000 NASA Structure and Evolution of the Universe (SEU)Dec 2000 NAS/NRC Committee on Astronomy and AstrophysicsJan 2001 DOE-HEP R&DMar 2001 DOE HEPAPJun 2001 NASA Integrated Mission Design CenterJuly 2001 NAS/NRC Committee on Physics of the UniverseNov 2001 CNES (France Space Agency)Dec 2001 NASA/SEU Strategic Planning PanelDec 2001 NASA Instrument Synthesis & Analysis LabJan 2002 Two Special Sessions at AAS MeetingMar 2002 SAGENAP-2Apr 2002 NRC/CPU ReportNOW DOE/SC-CMSD R&D (Lehman)Sept 2002 NASA/SEU Releases Roadmap Oct 2002 CNES Review

SNAP Pre-Project Planning StatusSNAP Pre-Project Planning Status

CD-0 CD-1

Idea Development

Strategic PlansDOELBNL

Pre- Conceptual

Design

Define Mission

Need

Conceptual Design

Discovery

SNAPMarch 1999 First

Discussions

Mar 2000 SAGENAPJuly 2001 SNOWMASS

SNAP OrganizationSNAP Organization

Collabor at ion E x ecut ive

Boar d

T echnical

Boar d

E x t er nal A dvisory

Counc il

M anagement Panel

S yst em E ngineer ing

H . H eet der ks (S S L)

1.3

Q ualit y, Reliabilit y & S af et y

Pr oj ect Cont r ols

D . Pet er son (LBN L)

O pt ical S yst em

C. Bebek (LBN L)

I R S yst em

G. T ar le (U . M ichigan)

S pect r ogr aph

E . Pr iet o (F r ance)

I nst r ument at ion S ys.

C. Bebek (LBN L)

N . Roe (LBN L)

2 .3

T elescope

M . L ampt on (S S L)

2 .2

O ps & Gr ound S yst em

M . Best er (S S L)

3 .1

S c ience O ps

W . Car it her s (L BN L)

3 .2

Gr ound S egment

W . Car it her s (L BN L)

3 .0

Calibr at ion

S . Deust ua (L BN L)

2 .5

S imulat ion

A . K im (LBN L)

T ype I a

S . Per lmut t er (L BN L)

G. A lder ing (L BN L)

T ype I I

P. N ugent (L BN L)

Gr av. W eak L ansing

R. E llis (Calt ech)

T heory

E . L inder (LBN L)

E ducat ion/ Conf er ences

S . Deust ua (L BN L)

S c ience W or king

Gr oups

S c ience T eam

S . Per lmut t er (L BN L)

M . L evi (LBN L)

1.2

S pacecr af t

H . H eet der ks (S S L)

2 .1

I nt egr at ion & T est

M . L ampt on (S S L)

2 .4

S . Per lmut t er (L BN L ) Pr oj S c ient ist / PI

M . L evi (L BN L ) Proj D ir ect or / Co- PI

K . Robinson (L BN L) S r . Pr oj M gr [A ]

P. H ar vey (S S L ) Pr oj M anager

FundingFunding

• 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

ITAR ComplianceITAR 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

• 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 SNAP Pre-project Development Geared toward a Successful MissionSuccessful Mission

http://snap.lbl.gov