James Webb Space Telescope Mission Status

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1 James Webb Space Telescope Mission Status Bill Ochs JWST Project Manager NASA Goddard Space Flight Center GSFC Contractors Association Nov. 5, July

Whose Doing What James Webb Space Telescope System Mission Systems

Launcher Launch Vehicle Payload Adapter Launch Site Services Optical

MIRI JWST Observatory NIRSpec OTIS Integrated OTE & ISIM FGS Deep Space

Systems Space Telescope Science Institute Spacecraft Element (SE)

2 Whose Doing What James Webb Space Telescope System Mission Systems Engineering Launch Segment Observatory Segment Ground Segment Ariane Launcher Launch Vehicle Payload Adapter Launch Site Services Optical Telescope Element (OTE) Integrated Science Instrument Module (ISIM) NIRCam MIRI JWST Observatory NIRSpec OTIS Integrated OTE & ISIM FGS Deep Space Network Science and Operations Center (SOC) Institutional Systems Common Systems Space Telescope Science Institute Spacecraft Element (SE) Spacecraft Bus Provided by NASA/GSFC Provided by NGAS Provided by STScI Provided by ESA Provided by CSA Sunshield 2

3 Overall Mission Status JWST Is In Fabrication and I&T Flight Hardware Percentage of Mass Past CDR At this time almost 99% of the observatory mass has passed its CDR 3

4 MISSION STATUS 4

5 Telescope Optical Telescope Element (OTE) Sun Shield Integrated Science Instrument Module (ISIM) Spacecraft Ground System Presentation to: IEEE Neuclear Space and Radiation Effects Conference 5 5

Telescope Architecture Overview Secondary Mirror Support Structure (SMSS) Aft Optics Subsystem (A0S) OTE Electronics Cold Junction Box Cold Multiplexer Units Secondary Mirror Assembly (SMA) Primary

6 Telescope Architecture Overview Secondary Mirror Support Structure (SMSS) Aft Optics Subsystem (A0S) OTE Electronics Cold Junction Box Cold Multiplexer Units Secondary Mirror Assembly (SMA) Primary Mirror Segment Assemblies (PMSA) 18 primary mirror segment mounts are mechanized and a wavefront control system will be used to adjust each segment enabling them to perform together as a single large mirror Primary Mirror Backplane Assembly (PMBA) PM Backplane Support Structure (PMBSS) PM Backplane Mechanism Thermal Management Subsystem (TMS) Deployable Batwings Fixed Diagonal Shield Deployable Stray-Light Bib Deployment Tower Assembly (DTA) 6

7 Mirror Status All mirrors are completed and in storage at GSFC Flight telescope build begins in less than a year 7

8 Backplane Support Frame, Center Section & Wings Integrated BSF/Center Section and Wing completed All flight backplane components are at NGAS in Integration 8

9 Telescope Pathfinder Risk Reduction JWST Pathfinder is a partial telescope that is intended to reduce the implementation risk of the assembly, integration, and cryogenic optical test of the JWST optical assembly 9

10 Optical Telescope Assembly (OTE) Deployment Hardware 10

11 Sunshield consists of three main Optical Telescope Element (OTE) Sun Shield Integrated Science Instrument Module (ISIM) Spacecraft Ground System JWST Full Scale Model Presentation to: IEEE Neuclear Space and Radiation Effects Conference 11

Sunshield Status Sunshield Facts - Measures 73 x 40 feet (about

temperature sensors - Made of heat-resistant kapton - Coated with

side stays at 40 K (-388 o F) Sun Light 200,000 Watts Sunshield

12 Sunshield Status Sunshield Facts - Measures 73 x 40 feet (about the size of a tennis court) and has 5 layers - Contains 400 temperature sensors - Made of heat-resistant kapton - Coated with silicon on sun side - Sun side reaches 358 K (185 o F) - Dark side stays at 40 K (-388 o F) Sun Light 200,000 Watts Sunshield Telescope and Science Instruments 0.85 Watts Radiators to Cool the Detector 12

successfully demonstrated membrane deployment design Currently incorporating

13 Sunshield Testing Engineering Test Highlights Integration Verification Article (IVA) full-scale deployment tests completed Key risk reduction test, successfully demonstrated membrane deployment design Currently incorporating lessons learned and upgrading test facility for 2 nd scheduled deployment test (early 2015) 13

14 Sunshield Flight Manufacturing 3 of 5 Flight Membranes in Fabrication Layer 3 Flight Layer 3 manufacturing complete Shape Testing Complete Delivery to NGAS late 2014 Flight Layer 4 seaming is complete Flight Layer 5 gore cutting and rip-stop installation is complete Seaming in progress All Other Sunshield Components Are Completed or In Fabrication 14

Module (ISIM) Spacecraft Ground System JWST Full Scale Model

15 Integrated Science Instrument Module Optical Telescope Element (OTE) Sun Shield Integrated Science Instrument Module (ISIM) Spacecraft Ground System JWST Full Scale Model Presentation to: IEEE Neuclear Space and Radiation Effects Conference 15

16 All Instruments Delivered and Integrated Fine Guidance Sensor Mid-Infrared Instrument Near Infrared Camera Near Infrared Spectrometer 16

17 Integrated Science Instrument Module Photon View Looking into ISIM 17

All Instrument Support Systems Are Completed

Complete Complete Complete Complete Complete

Harness System Harness Radiator System ISIM

Cryogenic Thermal Control System Command and Data

18 All Instrument Support Systems Are Completed Instrument support systems: Complete Complete Complete Complete Complete Complete Complete Optical metering structure system Electrical Harness System Harness Radiator System ISIM electronics compartment ISIM Remote Services Unit Cryogenic Thermal Control System Command and Data Handling System MIRI Shield Thermal Region Harness IEC Mechanical & Electrical 18

19 Key Aspects of the ISIM I&T Program ISIM cryo-vac testing is occurring in three phases, with ambient testing and buildup to the final flight configuration in between 2013: CryoVac1-RR ( Risk Reduction ) Successfully Conducted Flight MIRI, FGS/NIRISS; validate the array of test support equipment and overall performance of the test setup (thermal, jitter, stray light); dry-run procedures/analyses, train personnel Installed flight NIRCam, NIRSpec 2014: CryoVac2 Successfully Conducted First full-up ISIM verification test with all four flight instruments 100+ people supporting 2,800 consecutive hours of testing Extremely flexible test flow and Simple and effective decision model led to 100% of all minimum requirements completed and 95% all other objectives approximately 2 weeks early De-integrate instruments, replace near-ir detectors, re-integrate; carry out ISIMlevel vibration, acoustics, EMI/EMC tests In Process 2015: CryoVac3 Aug Start Final run for the record ISIM verification with all flight systems ISIM Delivery December

ISIM I&T Verification Flow Ambient Metrology Ambient Metrology, Functional Cryo-Vac 1 (CV1-RR) Vibe Ambient Metrology, Functional Ambient Metrology, Functional Install Flight NIRCam and NIRSpec

Change out Detectors, micro-shutters, etc.

20 ISIM I&T Verification Flow Ambient Metrology Ambient Metrology, Functional Cryo-Vac 1 (CV1-RR) Vibe Ambient Metrology, Functional Ambient Metrology, Functional Install Flight NIRCam and NIRSpec EMI/EMC ISIM Verification Flow Ambient Metrology, Functional Acoustics Cryo-Vac 2 (CV2) Ambient Metrology, Functional Ambient Metrology, Functional Cryo-Vac 3 (CV3) Ambient Metrology, Functional Change out Detectors, micro-shutters, etc. ( Half Time ) CV1-RR CV2 CV3 ISIM Baseline Configuration Flight FGS / NIRISS (Current Detectors) Flight MIRI Flight NIRCam (NEW Detectors) Flight NIRSpec (Current Detectors) Flight FGS / NIRISS (Current Detectors) Flight MIRI Flight NIRCam Flight NIRSpec (NEW Detectors) Flight FGS / NIRISS (NEW Detectors) Flight MIRI Minimum Test Objective Risk Reduction: integrated FGS/NIRISS and MIRI performance, Test Procedures, and GSE (including OSIM) Run for Record: Complete NIRCam and NIRISS Instrument Verifications Baseline Measurement: Pre ISIM Vibe Cryogenic Performance Run for Record: Measure Post-ISIM Vibe Cryogenic Performance 20

21 Spacecraft Optical Telescope Element (OTE) Sun Shield Integrated Science Instrument Module (ISIM) Spacecraft Ground System JWST Full Scale Model Presentation to: IEEE Neuclear Space and Radiation Effects Conference 21

Spacecraft Status Completed 26 Unit and 10 Subsystem CDRs Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan Feb Mar Apr ACS CDA FSW CDA C&DH CDA DCS CDA FSS CDR / MRR IRU CDA 1/15 1/31 Comm CDA

3/4 DIDR 3/4 IDR3/4 1/22 3/13 5/13 6/10 SMS CDA 11/12 Moment Dyn & Static ATK STSA 8/14-15 Strut CDR Testing PDR Mini-IDR 3/4 ATK STSA 10/30 2/14 5/22 6/12 CDR SC Stowed IM Cycle #1 Model Config SC

22 Spacecraft Status Completed 26 Unit and 10 Subsystem CDRs Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan Feb Mar Apr ACS CDA FSW CDA C&DH CDA DCS CDA FSS CDR / MRR IRU CDA 1/15 1/31 Comm CDA 3/12 5/ /15 TCS CDA 8/27-29 ACS HW CDA 7/22 SA EPS CDA Battery CDA CDA 7/ / /30 Cryo-Cooler Secondary Axial Strut SMS CDA Liens Installation SC Struct STA/IRU Spt CDR Close-out IDR 3/4 DIDR 3/4 IDR3/4 1/22 3/13 5/13 6/10 SMS CDA 11/12 Moment Dyn & Static ATK STSA 8/14-15 Strut CDR Testing PDR Mini-IDR 3/4 ATK STSA 10/30 2/14 5/22 6/12 CDR SC Stowed IM Cycle #1 Model Config SC FEM Begin Integrated Model Model for OSE -> GSFC Review Freeze Cycle #2 OSE -> GSFC PLCLA 6 SMS -> OSE 1/31 3/1 4/5 7/1 9/1 STSA Model IM Cycle #1 IM Cycle #1 SC -> SET Reduced Mass Perf Review 1 PerfReview 2 10/30 Model NG SA Model 8/1 8/20 Configuration 3/31 Stowed, Deploying, Obs Thermal Distortion Review Deployed Flex Models 1/15 4/10 Analysis OSE -> SMS OSE -> ACS 8/1 Tank Prop Propulsion 4/15 CDA Budget MRE-1 CDA 11/26 Update CDA 6/13-14 SC CDR Execution Plan 1/31 2/28 BAGA STA CDR DIDR3 4/18 RWA CDA 5/ /4 Review Comm, Draft Agenda, Entry/Exit Criteria Document List I&T TIM 4/16 3/31 DR-0 FSW Capstone Review 4/30-5/3 Logistics, Rooms, Data Plan 6/4-5 Reqts/Verif Table top TIM 6/20 6/28 DUC CDR SC Harness CDA MDI, DR3 Venting/ Contam STSA 7/8 TIM 8/6 Distortion 8/19 TIM Align t MA TIM EDI, CDA 7/9 7/23 8/20 DEU IDR4 8/19 10/21-22 Titles & Dry Topics Run 9/ /14-24 Wall Walk 10/2-4 Fault Mgmt CDA SC I&T CDA 10/ /24 SS/ADIR/OTE Harness CDA 12/19 1/13-17 SC CDR Font - Models Font - HW Milestones Font - Analysis/TIMs Key Subsystem CDA s Completed Final Charts to GSFC Dress Rehearsal 12/3-5 SC Temp Map SC -> OSE 12/23 Fine Pointing Results (ACS CDA Case) ACS IM/IQ 12/23 STSE PDA 3/26 DRSA-V IDR 3/4 3/27 4/28 3/4 NEA D CDR ATK STSA D CDR Obs SLR 5/13-15 SE DRSA-H IDR 3/4 4/10 May ACS FSW / DCS SLR Analysis Review 3/12-13 EPS SMS Models PROP Comm / HRN / TCS Completed Spacecraft CDR! SC CDR Contributors 22

23 Spacecraft Status Fabrication, Assembly, and Component Level Testing in process in preparations for Spacecraft I&T Engineering Qualification Models Flight Hardware Components Component Flight Testing Star Tracker FM1 4 Telescope Fittings Equip Panel Reaction Wheel EQM +J3 Panel (with Inserts) High Gain Antenna Command and Telemetry Processor Biaxial Gimbal Assembly 23

24 Spacecraft Status Bus Shear Panel Installation Spacecraft MOC-UP Spacecraft MOC-UP 24

25 Ground System Optical Telescope Element (OTE) Sun Shield Integrated Science Instrument Module (ISIM) Spacecraft Ground System Presentation to: IEEE Neuclear Space and Radiation Effects Conference 25

26 Ground Segment and Operations Status Primary emphasis is on preparations for and support of ISIM I&T STScI, NGAS and GS&O personnel providing 24x7 on-console coverage of ISIM Cryo #2 Script certification in progress for scripts needed for ISIM Cryo #2 Certification occurring in rolling wave corresponding to phases of ISIM Cryo #2 NGAS contributing operations products (procedures, telemetry format tables), review of limitations and constraint implementation and simulator support S&OC System Design Review #1 (SDR#1) Completed July Emphasis of SDR#1 is on S&OC subsystems facilitating science operations Science and Operations Center (S&OC) Proposal Planning Subsystem (PPS) Developing Build 10 for October 2014 Wavefront Sensing and Control (WFS&C) Software Subsystem (WSS) Developing Build 4 for December 2014 Data Management Subsystem (DMS) Developing Build 3 for September 2014 Flight Operations Subsystem (FOS) Preparing for System Requirements/Design Review Operations STScI has begun development of real-time command procedures for basic science instrument functions to be run/certified during ISIM Cryo Vac #3 NGAS has delivered preliminary versions of contingency and nominal mission operations descriptions (MODs) which are the basis for developing operational command procedure 26

27 OTIS TESTING 27

What Is OTIS Optical Telescope Element and Integrated Science

Test Acoustic & Sine-Vibe Tests Post Env.

Radiators Complete TMS install COCI Alignment Metrology Electrical

JSC/ CryoVac Prep Electrical Functional SMSS Walkout Wing & DTA

Optical Test Verifies OTE-ISIM Alignment Cross check optical and

28 What Is OTIS Optical Telescope Element and Integrated Science Instrument Model + Integrate Flight ISIM (Begin Obs. I&T) Pre-Env. Test Acoustic & Sine-Vibe Tests Post Env. Test Integrate Flight ISIM Integrate Flight IEC Integrate Radiators Complete TMS install COCI Alignment Metrology Electrical Functional Electrical Functional 1st Motion Checks COCI Ship to JSC/ CryoVac Prep Electrical Functional SMSS Walkout Wing & DTA Deployment Configure OTE for cryovac test Observatory (OTIS) Cryo Optical Test Verifies OTE-ISIM Alignment Cross check optical and thermal performance Prep/Ship To NGAS Observatory I&T Obs. Level: CST, EMC, Acoustic, Shock Vibe, Deployment 28

provide a facility capable of testing OTIS in its

29 Where Do We Cryo Optical Test OTIS JSC Chamber A World s Largest CryoVac Chamber GSFC and JSC collaborated to provide a facility capable of testing OTIS in its challenging operational environment and built a cleanroom in front of it 29

30 OTIS Test GSE Architecture Chamber Isolator Units Dynamically isolates OTIS Optical Test Integration of 6 units complete Cryo Position Metrology (CPM) Photogrammetry System Integration Complete MSFC-XRCF Center of Curvature Optical Assembly (COCOA) Multiwavelength interferometer (MWIF), null, calibration equipment, coarse/fine PM phasing tools, Displacement Measuring Interferometer Installed in Chamber USF Structural Frame supports Metrology Installed in Chamber 3 Auto collimating Flat Mirrors (ACFs) 1.5 M Plano for Pass and Half Testing ACF 1 installed in Chamber, ACF 4 in final cryo test, ACF 5 waiting for final cryo test. AOS Source Plate Sources for Pass and Half Test In test at Ball Space Vehicle Thermal Simulator (SVTS) and Sunshield Simulator Procurements and fabrication ADM Leica system delivered to JHU HOSS OTIS support structure In integration in Clean Room Deep Space Edge Radiation Sink (DSERS) Frame integrated Mag Damper Cryo Test Article Delivered 30

31 OTIS GSE Lifting GSE using Direct Lift System Hardpoint Offloader Support System Cryo Position Metrology - Photogrammetry System 31

32 OTIS Testing Pre-OTIS Testing (Conducted March 2015 Feb. 2016) Three Risk Reduction tests prior to OTIS Testing will be conducted with Telescope Pathfinder and Optical Ground Support Equipment, each building upon the other Flight OTIS Test (Conducted Oct Jan. 2017) Verify Instrument to Telescope Alignment Series of optical tests for: Verification and cross-check of image quality requirements Model validation and cross-checks of image quality stability requirements Cross-check of radiometric sensitivity requirements Calibration, model validation, and cross-check of WFSC requirements Verification and cross-check of functional performance Complete all Optical Telescope Element Cryo Verification Thermal Balance Tests Check OTIS system thermal workmanship and provide data to validate the OTIS thermal model for use in flight temperature predictions 32

33 Where Are We In OTIS Flow Initiated 33

34 MISSION I&T 34

I&T Flow Overview OTE Pathfinder Structure Completed 2014

Integration Completes 2014 ISIM I&T Completes 2015 OTE

Completes 2016 OTE/ISIM TESTING Cryo Optics Test

NGAS ITT ESA / Arianespace Facility Observatory EM Test

2015 Sunshield Pathfinders (EPF/IVA) Completed Spacecraft

Spacecraft Element I&T Completes 2017 Complete

35 I&T Flow Overview OTE Pathfinder Structure Completed 2014 OTE Structure I&T Completes 2015 Pathfinder Optics Integration Completes 2014 ISIM I&T Completes 2015 OTE I&T Completes 2015 Pathfinder Cryo Optics & Thermal Tests Completes 2016 OTE/ISIM TESTING Cryo Optics Test Completes 2017 I&T Responsibility Execution GSFC JSC N/A NGAS ITT ESA / Arianespace Facility Observatory EM Test Bed (EMTB) Propulsion Module I&T Completes 2015 Completes 2015 Sunshield Pathfinders (EPF/IVA) Completed Spacecraft Panel I&T Completes 2016 Sunshield I&T Completes 2017 Spacecraft Element I&T Completes 2017 Complete Observatory I&T Completes 2018 Launch Site I&T LV Integ Completes Launch Oct. 2018

36 Transportation 36

37 Transportation Space Telescope Transporter for Air Road and Sea (STTARS) Mini-STTARS 37

will be same ship ESA uses and is compatible with the launch site harbor Bridges between airport and launch

38 More Transportation To Go SuperSTTARS will be designed to transport the Observatory by Road and Sea to the launch site Similar to the STTARS with increased lid height Ship transport from Long Beach to French Guiana will be same ship ESA uses and is compatible with the launch site harbor Bridges between airport and launch site have insufficient capacity to allow transport by C5 MN Colibri at Sea and in Dock at French Guiana 38

39 Ariane 5 61 Consecutive Successful Launches To Date! 39

40 ISSUES/CONCERNS 40

41 Issues/Concerns Cryo Cooler Is Driving The Critical Path Fabrication and assembly issues continue to plaque cooler development NEA Shock Issue Integrated NASA/NGAS team working towards a design solution Sun Shield Unitized Pallet Structure (UPS) Issue resolved, but ongoing tool moisture issues continue to plague manufacturing process Project reserves in FY15 GAO Distraction GAO draft report released 41

42 SCHEDULE 42

43 JWST Master Schedule CY 2011 CY 2012 CY 2013 CY 2014 CY 2015 CY 2016 CY 2017 CY 2018 CY 2019 J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J Cryocooler 3 CCA LRD SC Subsystem Development CHA ISIM & Instrument Fab/Assy/Test Need SES For OSIM SES Avail SC Panels to I&T SC Fab/Assy/Test Impact from GPM slip* 4 2 Spacecraft I&T SC Structure to I&T 2 Obs I&T 3 Launch Site 1 11 Months of Critical Path Slack ISIM Integ ISIM Envir Test/Detector C/O 4.5 OTIS I&T 3 Mirror Fab PMSA Gear Motor Rework 16 Optics Integ OT E 4.5 Primary Critical Path Secondary Critical Path Tertiary Critical Path Sunshield Design/Dwgs OTE Fab Assy & Test Sunshield Mfg, Fab, & Test 5.25 I&T 43

44 CLOSING REMARKS 44

45 Excellent Progress Continues To Be Made Executing To 2011 Replan 45

November 3, 2014 Eric P. Smith JWST Program Office

November 3, 2014 Eric P. Smith JWST Program Office November 3, 014 Eric P. Smith JWST Program Office 1 SINCE LAST CAA MEETING... Completed of 3 recommended GAO schedule risk analyses for this year. Mutually agreed to drop 3 rd. Will perform cost-risk study