GLAST Large Area Telescope: I & T

Transcription

1 Gamma-ray Large Area Space Telescope GLAST Large Area Telescope: I & T Elliott Bloom SU-SLAC Subsystem Manager Brian Grist SU-SLAC Subsystem Engineer elliott@slac.stanford.edu, bgrist@slac.stanford.edu Name Document: LAT-PR

2 Outline Overview Results from January PDR/Baseline review Findings and recommendations Actions since the review Schedule and Budget (Brian Grist- I&T Chief Engineer) New technical issues Summary Name Document: LAT-PR

3 I&T Organization Chart I&T Manager E. Bloom (SU-SLAC) WBS Reliability & QA D. Marsh (SU-SLAC) WBS Mechanical Ground Support Equipment E. Gawehn (SU-SLAC) WBS I&T Engineer B. Grist (SU-SLAC) WBS Instrument Operations Coordinator D. Lung (SU-SLAC)-acting WBS Online Software R. Claus (SU-SLAC) WBS Integration, Facilities, Configuration, and Test L. Wai (SU-SLAC) WBS Particle Test Manager G. Godfrey (SU-SLAC) WBS Environmental Test Manager M. Lovellette (NRL) WBS Science Verification, Analysis, and Calibration E. do Couto e Silva (SU-SLAC) WBS Mission E. Bloom (SU-SLAC) WBS A Name Document: LAT-PR

4 Science Requirements Level III Requirements Summary Defined by Instrument Performance Spec 433-SRD-0001 and LAT-SS Verification performed by a combination of particle tests that directly measure response of instrument, and verifies MC using CU (Calibration Unit 1 x 4). MC then is used to verify most Science Requirements. Cosmic Ray (muons) Van de Graaff (18 MeV photons) SLAC End Station A Beam Test ( e +, tagged and brems, p) Design Requirements LAT Instrument Performance Verification Plan, LAT- MD-00408: SE & input from I&T. Subsystem ICDs -- I&T to all relevant subsystems, e.g., LAT-SS (I&T SAS), LAT- TD (I&T ACD). Test methodology defined by 433-MAR-0004, SE Instrument Verification will be performed by Electrical Performance Tests Structural and Mechanical Tests EMC/EMI Tests Thermal Verification Tests Visual Inspection Instrument Monitoring Produce a Working Instrument End-to-end test (at ~ 35,000 ft in a jet airplane during transport to NRL for environmental tests) Name Document: LAT-PR

5 Integration and Test Activities Fabrication Phase I & T subsystem is focal point of LAT integration activities. I & T team plans and manages activities. TKR, CAL, and ACD subsystem teams and other Collaboration members provide support for Integration & Test & Calibration. Total I & T effort involves activities in I&T and other subsystems. I & T Subsystem activities for entire mission. LAT integration planning and management. Mechanical integration and MGSE and EGSE development. Plan environmental tests and execute. Plan particle tests and execute. Particle beam and test equipment development. Ground verification and calibration of LAT. Ground science verification of LAT. Support activities at Spacecraft Vendor and launch facility. Commissioning of LAT in orbit -- deliver a working instrument to IOC. Name Document: LAT-PR

6 GLAST Integration Area Building 33 SLAC Subassembly Preparation Clean Room Class 100,000 EGSE Room Gowning Room Office Area 5 Ton Crane LAT Assembly Clean Room Class 100,000 Van de Graaff Accelerator Receiving Area Non-critical storage / technician work area LAT I&T Name Document: LAT-PR

7 LAT Structural Design Overview Mass Mass Width Height Materials Size Interfaces Mass Materials Size Interfaces LAT Structural Design Parameters Center of Gravity Design 2699 kg mm 1796 mm 1047 mm Anticoincidence Detector (ACD) kg (May 2002 est.) CFC honeycomb, alum base frame, MLI/ Micrometeorite Shield 1796 mm w x 1015 mm h Grid bolted joint, shear pins Grid/X-LAT Plate/Radiators kg (May 2002 est.) Aluminum, heat pipes, alum honeycomb plates 1566 mm sq x 236 mm h Four-point mount to SC flexures Spec <3000 kg <185 mm <1800 mm 1100 mm Mass Materials Size Interfaces Mass Materials Size Tracker (TKR) GrEp, CC structures, Silicon, Tungsten Interfaces kg (May 2002 est.) 372 mm sq x 640 h Grid Ti flexure mount TKR CAL ACD Mech Elec Calorimeter (CAL) kg (May 2002 est.) CFC support shell, alum structure, CsI 364 mm sq x 224 mm h Grid bolted friction joint LAT Mass Budget and Current Estimates (kg) LAT Total Estimate Budget Source: LAT-TD LAT Mass Status Report Mass Estimates for May 2002 Mass Materials Size Interfaces Electronics kg (May 2002 est.) Aluminum mm sq x mm h Flexure mount to CAL; bolted friction joint to X-LAT Plate LAT Structural Overview LAT Structural Performance LAT First Mode Freq. LAT Drumhead Freq. Radiator First Mode Freq. Deflection at Grid Center Name Document: LAT-PR Design 55.5 Hz 60.2 Hz 65.1 Hz 0.49 mm Spec >50 Hz >50 Hz >50 Hz ---

8 Design Details Grid corner detail showing embedded heat pipes, purge grooves; corner chamfer and bottom flange ready for ACD and Radiator Mount Bracket. Radiator Mount at Grid corners. Note widened SC mount boss and bottom flange X-LAT Box assembly: X-LAT (red) and Mid- Plate (pink); Radiator Mount Brackets at corners, and removable EMI Skirt pieces (blue) Grid Perimeter Ring (GPR) mounts Radiator Mount Bracket at Heat Pipe Patch Plate detail. Name Document: LAT-PR

9 Details of LAT Underside Electronics boxes mounted to CAL plates (dk blue) Grid Box corner, showing X-LAT Plate (lt green), Heat Pipe Patch Plate (dk blue) Detail of EMI Skirt around SC support region Detail of TEM and TPS boxes (red), with crenulated CAL plates (dk blue) Name Document: LAT-PR

10 Mechanical Ground Support Equipment (MGSE) MGSE Development Manager joined LAT I&T May 12, 02. Reviewed MGSE Hardware Lists and Respective Requirements. Defined complex items to determine if schedule / cost issues exist. Budget estimate in line with hardware complexity. Schedule requires more detailed evaluation / minor updates possible. Most complex items are: Universal Support Stand with Grid Perimeter Ring and Radiator Support. X, Y, movement system for Calibration Unit used in End Station A (ESA) Beam Test. Alignment Fixtures for Calorimeter and Tracker Tower installation. Vibration Test Fixture. Duplicate Items: Require Two Universal Support Stands due to timing of Calibration Unit ESA Beam Test and Parallel Integration of the LAT. Environmental Control Cart; May require Back-Up System due to Dew Point Control Requirements Imposed by the Calorimeter. Name Document: LAT-PR

11 Hardware Development List 1. EM Support / Rotation Fixture Also Used to Rotate Calorimeter 2. EM Lifting Fixture *1 3. EM ACD Scintillator Support Fixture 4. Calorimeter Lift Fixture (used for Alignment to LAT after Rotation) 5. Calorimeter Alignment Fixture *2 Includes 0.45 m long Alignment Rods 6. Calibration Unit (1 x 4) Support Fixture 7. Calibration Unit Lift Fixture 8. Calibration Unit ACD Support Fixture 9. Calibration Unit X, Y, θ movement system (for Beam Test) *2 10. Thermal Dew Point Control Tent (Double Walled) 11. CU & LAT Thermal Control Cart Ducting, Hoses, Cold plates *2 12. Grid Perimeter Ring (In P3 as Universal Handling Supports Grid Through Entire Integration & Test at SLAC Supports LAT in Shipping Container (To Protect SC Bus Interfaces Used at NRL for EMC, Acoustic and Thermal Balance Tests Note: *1 - Tracker Tower Lift Fixture Supplied by Tracker Sub-System, *2 Trade Study In Work Name Document: LAT-PR

12 Hardware Development List, Continued 13. Universal Support Stand A Supports GPR and LAT During I & T Lifted by Crane Ops 14. Universal Support Stand B *2 Supports GPR and LAT During I & T Provides Lift & Rotation Capability May be Required Due to Parallel LAT Build and Calibration Unit Beam Test 15. Extension 1 x 4 to 4 x 4 Allows 1 x 4 CU to be Installed into USS A or B Allows Integration Concept Protocol Development and Physical Demonstration 16. LAT Shipping Container Insulated for Thermal Cycling Tests Includes Electrical Feed Throughs to Power up & Receive Data from LAT Includes Ducting for Thermally Controlled Air Circulation May Include transits for use of cold plate on X-LAT Heat Plate Name Document: LAT-PR

13 Hardware Development List, Continued 17. Staging Table Preparation / Sub-System Functional Tests 18. Vibration Test Stand Provides Interface Between NRL Vibration Table and LAT to SC Bus Attach Points Single Stand Will Support All Three Axes 19. Thermal Vacuum Support Kit Supports Radiators on USS A Replaces High Off-Gas Items (i.e., Delrin Bushings and Structural Caps) Includes Container for USS A s Rotator Drive Assembly, Rotator Bearing and its Wheels 20. Van de Graaff Mounting Stand 21. Van de Graaff Radiation Containment 22. Calorimeter Transport Box Includes Dry Air Purge Connect to Control Humidity During Transit to ESA 23. Miscellaneous equipment and Fixtures (12+ Items) Budget Line to Capture Incidentals Name Document: LAT-PR

14 MGSE Trade Studies Trade Studies 1. Calorimeter alignment and installation. 2. CU X, Y, movement system. Name Document: LAT-PR

15 MGSE Status Performed NRL Site Survey to Ensure Hardware Concepts are Consistent with Environmental Test Facility. No Issues. Mature MGSE suite List (see prior charts). Indentured Drawing List (Drawing Tree) Prepared for All MGSE about 90% Complete. Mature Enough to Proceed to Concept Review. MGSE Concept Review Planned for Sept. 02. Validate Understanding of MGSE Requirements. Obtain Buy-In for MGSE Development Approach. Name Document: LAT-PR

16 Integration Planning: GSE (1) Universal Support Stand A 1. Supports Grid Perimeter Ring / Grid 2. Rotation by Motor / Gearbox Assy 3. Vertical motion by Crane Ops 4. Used during Engineering Test Model build and during most Flight LAT Environmental Tests (i.e., not used during Vibe Test) Removable GPR drive for TVAC. LAT in lowest position for ACD installation. Removable Wheels for TVAC Name Document: LAT-PR

17 Integration Planning: GSE (1) Universal Support Stand B for CAL Unit (CU) Revision date: 22 July 2002 Simpler frame 1. Same as the USB - A, but includes motorized lift and position encoder capabilities 2. Can support ESA Beam Test due to automated lift and rotation capability 1. Existing Design Concept would need Positional Encoders added. 3. Not used for TVAC. 4. Trade Study in work to determine if modification of used large metal working equipment is lower cost option with acceptable risk Wheels replace pads Name Document: LAT-PR

18 Integration Facility Configuration and Test Assembly (IFCT) Documentation Revision date: 17 July I&T Integration Sequence, MGSE, and Flight Work Instruction Development Plan (LAT-TD-00676) completed 2. Working draft for Single Tower I&T Work Instructions: Engineering Models (LAT-TD-00856) 3. Test model for work instruction checklist electronic sign-off completed 4. Flight Work Instructions will build directly from Engineering Model Tower assembly Name Document: LAT-PR

19 IFCT : Functional Test Development Revision date: 17 July Oversight of tracker, calorimeter, and ACD functional test script development through weekly Online Department meetings. 2. EGSE EM-1 workstation operational. 3. Delivery of TEM & associated equipment by August 4. Functional tests of tracker and calorimeter electronics after November. 5. Simulated cosmic muons in single tower engineering model completed 6. Plan for development of tracker calorimeter event matching test software Name Document: LAT-PR

20 LAT I&T, Verification, and Calibration Flow TKR: QU FS from TKR fab TKR: F1-2 from TKR fab CAL: QU- FS from CAL fab CAL: F1-2 from CAL fab Elec: EM2 Elect. Modules Calibration Unit - CU I&T: Beam test CU 4 towers Cal TKR/CAL: F1,2 from CU Vibe Random vibrate/sine sweep Acc Acceptance test level Ac Acoustic QU Qualification Unit T-C Thermal-cycle at 1 atmosphere EM Engineering Model T-V Thermal-vacuum cycle test TM Thermal model EMI Electro-magnetic interference test CU Calibration Unit FU Flight Unit Calibration unit I&T Cal Calibration Flight unit/spares I&T FS Flight Spare Mech: Flt Grid from Mech TKR: F3-16 from TKR fab CAL: F3-16 from CAL fab I&T: LAT Assembly, Test Acc, Cal Flight LAT - FU I&T: LAT Functional, Thermal, Airborne cosmic E to E Acc, Cal, T-C I & T Responsibility ACD: ACD to LAT I&T Elec: Flt Elec. Mod. to LAT I&T Mech: Flt Rad s from Mech Elec: Q SIU for EGSE I&T: LAT Environmental Tests Acc, Cal, T-V Obs: Support Vibe/Ac Acc Obs: Support T-V Acc Obs: Support EMI Acc Name Document: LAT-PR

21 Integration sequence (1): Grid Prep Grid After Dimensional Inspection and Static Load Test Lift Grid using SC Bus Lift Points Attach Grid to Grid Perimeter Ring at Corner Attach Points Top Looking Down View Name Document: LAT-PR

22 Integration sequence (2): Single Tower Integration Crane Op TKR into Position, Shim & Torque Rotate Grid Crane Op Calorimeter-TEM & Power Supply into Position and Torque Continued in Backup Slides Rotate Grid Verify Function with Cosmic Rays Before Assembling Next Bay Name Document: LAT-PR

23 Electrical GSE (EGSE) Division of Responsibility NB: EGSE = Online system GLAST Mission Coordinate with spacecraft vendor EGSE LAT Coordinate EGSE flow across subsystems ELECTRONICS EGSE hardware (except for workstation) & front end software I&T EGSE workstation, workstation software and support. I&T test, analysis, visualization, and script software SAS LAT event reconstruction software IOC Ultimate customer SAS Mission LAT I&T Elect. ONLINE IOC Name Document: LAT-PR

24 EGSE Deliverables (Electronics + I&T Support) Software support for various incarnations of I&T test-stands Engineering Model 1 (EM1) Engineering Model 2 (EM2) Calibration Unit (CU) Flight Unit (FU): this is for the LAT. Test-stand system composition Infrastructure (workstations, networking, crates, etc.) Test executive Graphical User Interfaces (GUIs) Databases and tools Data analysis tools Data archiver Test procedures Code management, release control and distribution Remote debugging tools Name Document: LAT-PR

25 EM1 EGSE Configuration Back door debug RS-232 Subsystem (or simulator) CPU LAT-COMM Online Workstation Central Database AEM/TEM Main Dataflow Ethernet Ethernet WAN DC Power Subsystem/simulator VME/cPCI Chassis Electronics/Online Ethernet Router and Firewall TEM = Tower Electronics Module; AEM = ACD Electronics Module Name Document: LAT-PR

26 EM2, CU, FU EGSE Configurations EPU Cal Unit, LAT or Sensor Simulator AEM/TEMs GLT Back door debug RS-232 CPU 1553 SolidStateRec I/F I/O Command & Monitoring Spacecraft (or Simulator) Main Dataflow Online Workstation Central Database SIU Ethernet Ethernet WAN T&DF System DC Power cpci Chassis Electronics/Online Ethernet Router and Firewall PU = Event Processor Unit; GLT = GLobal Trigger; SIU = Spacecraft Interface Unit; &DF System = Trigger & DataFlow System Name Document: LAT-PR

27 EGSE & Online Software Real-time system Embedded processors running the VxWorks RTOS Data acquisition and control by Trigger & Dataflow system Monitoring and control of Housekeeping items Data acquisition from test-stand COTS I/O modules Command and monitoring software (test executive) Using Interface & Control System, Inc. s (ICS) Spacecraft Control Language (SCL) Data acquisition, quality verification, archiving and distribution Data visualization and analysis SCL provides some help with these last two items Third party COTS and Open Source software packages have been, or can be interfaced with SCL to provide the complete solution Name Document: LAT-PR

28 LAT Science Requirements Verification Matrix (Examples) equirements for Beam Tests flow down from LAT Science Req. Doc Level II Specification LAT-SS Require ment Title Parameter Verification Method Particle Tests Relevant to Verifying the Requirement Energy-Range/ Effective Area > 300(TBR) cm 20 MeV >3000 cm 100 MeV >6400(TBR) cm 300 GeV Test + MC, Analysis. Van de Graaff 17.6 MeV photons Tagged photons 20 to 1500 MeV, norm incidence. Brem beam, simultaneously all energy bins from 20 MeV to 28 variety of angles and positions Photon Energy Resolution (normal incidence) 50 % (TBR) MeV 10 % 1-10 GeV 20% (TBR) GeV Test + MC, Analysis. Van de Graaff 17.6 MeV photons Tagged photons 20 to 1500 MeV, norm incidence. Positrons 1, 2, 5, 10, 28, 45 variety of angles and positions Peak Effective Area >8000 cm 2 Test + MC, Analysis. Brems beam, simultaneously all energy bins from <20 MeV to 28 variety of angles and positions Single Photon Angular Resolution 68% (onaxis) 100 MeV < 3.5 front, < 6 back GeV < 0.15 front, < 0.3 back Test + MC, Analysis. Brems beam, simultaneously all energy bins from <20 MeV to 28 variety of angles and positions. Tagged photons 20 to 1500 MeV, norm incidence. Name Document: LAT-PR

29 What Calibration Means Instrument calibration (See LAT-MD SVAC Plan for full list) Parameters are directly calculated from the data examples ADC channel / MeV response of each CsI crystal Which strips are dead in the tracker Timing accuracy Calibrate the GLAST Monte Carlo Simulation (See LAT-TD Beam Test Plan ) Record LAT data for many particle types (e,p, ), energies (20 MeV to 45 GeV), angles of incidence (θ), and positions (x,y) of entry. Compare data to simulated events and modify simulation if needed. Science calibration (See LAT-MD SVAC Plan for full list) Use the calibrated simulation to demonstrate compliance - examples Effective area as a function of energy. Point spread function versus energy and zenith angle. Name Document: LAT-PR

30 Particle Beam Sources Cosmics rays on the ground. EM, CU, LAT. Van de Graff (17.6 MeV ). EM, CU, LAT. SLAC End Station A positrons. (1-45 GeV) CU Calibrate energy response for upper range. SLAC End Station A s. ( Tagged photons, MeV; brems photons, 20 MeV 28 GeV) CU Calibrate energy response for lower range. Verify MC simulation to measure PSFs and effective areas. SLAC End Station A protons. (~12 GeV) CU Verify MC simulation to measure proton rejection. Cosmic rays in airplane (A few hours of 25,000-35,000 feet) Full LAT end-to-end test. (At rates expected in orbit and higher rates, 5-20 khz) LAT I&T Name Document: LAT-PR

31 Science Verification, Analysis and Calibration (SVAC) System Science Requirement Document 443-SRD Level II LAT Performance Specifications LAT-SS Levels III and IV APPROVED and SIGNED! Basis of all SVAC work ACD, CAL, TKR Specifications GLAST LAT SVAC Plan LAT-SS-00016, LAT-SS LAT-SS-00018, LAT-SS LAT-SS-00152,LAT-SS LAT-MD Science Verification Data Analysis Calibration Name Document: LAT-PR

32 SVAC Overview Instrument Calibrations EM Prototype calibration tools and procedures I&T Flow Instrument Calibrations CU Beam Test MC Validation CU- Beam Test Science Verification CU - Beam Test SVAC Calibration Products SAS Instrument Response Functions Instrument Calibrations LAT Instrument Calibrations LAT Environmental test Calibrated LAT Instrument IOC On orbit Calibrations Name Document: LAT-PR

33 SVAC System Responsibilities Capture Science and Calibration requirements from Subsystems Plans. Prepare the SVAC plan (with review from subsystems). To verify Science and Calibration Requirements Provide the final I&T calibration products to SAS and IOC Develop Calibration Compliance Matrices for pre and post launch operations Coordinate Data Analysis (with support from subsystems) using data obtained from particle beams and cosmic rays during LAT assembly, environmental, airplane and spacecraft integration tests Demonstrate that the LAT is calibrated prior to launch and perform the first on-orbit calibration prior to hand off to IOC after fabrication phase is completed Name Document: LAT-PR

34 SVAC Timeline 2003 Engineering Model 1 Low and High Level calibrations Prototype algorithms and database Prototype interface with EGSE and SAS 2004 Calibration Unit Science Verification (Monte Carlo Validation) Low and High Level calibrations (inter tower alignment) Validation of SVAC database design Validation of on-orbit low level calibration scheme LAT Final alignment Validation of on orbit calibration scheme Calibration dependence on environment Calibration time history prior to launch Name Document: LAT-PR

35 LAT Test Plan Contents Ref: LAT-MD LAT Performance Verification Plan System Performance Assurance System Verification Component & Material Qualification Test Requirements Test Plans Test Procedures Test Data Support Documentation Configuration Management Configuration Item Tracking MGSE EGSE Documentation Quality Assurance Safety Test Equipment Test Performance Test Readiness Review Test Data Review Release for Use Review Verification Plans Qualification Proto-Flight Acceptance LAT Instrument Structural, Mechanical and Alignment Electrical Tests Optical Tests Environmental Tests Thermal Vibration Acoustic EMI/EMC Software Science Verification and Calibration Compatibility ASICS Component Parts Polyswitch A/D Converter D/A Converter NovaCap PIN Photodiodes Flexible Cable Assemblies ACD Components PMTs Scintillator Tiles Connectors Mechanical Components Grid X-LAT Plate Radiators Thermal Control System Composite Material Proof Test Program Name Document: LAT-PR

36 LAT Test Requirements Reference LAT 433-MAR and GEVS-SE Electrical Mechanical Environmental Electrical Interface - Isolation - Insulation Resistance - Hi-Pot - Power Distribution - Command Distribition Aliveness Limited Performance Comprehensive Performance Burn- In / Failure Free Performance Static Load Mass Properties - Mass - CG Sine Sweep Vibration Random Vibration Sine Vibration, 3 Axis (LAT) Modal Survey Vibro- Acoustic (LAT) Mechanical Shock (OBS) Thermal Vacuum ( 8 cycles) Thermal Balance (LAT) EMI/EMC Name Document: LAT-PR

37 LAT Test Sequence TKR CAL Grid TEM EP SIU PDU Tower Integration Integrate TKR/CAL with Grid & TEM's LAT Integration Integrate E-Boxes w/ Grid Alignment Survey Mass Properties Alignment *Thermal Cycling LAT Test NRL EMI/ EMC Modal survey Vibration Mass Properties Final Alignment Observatory Integration Delivery Integration GASU EMI SHIELD ACD TCS Integrate ACD, TCS, X-LAT Plate *Airborne * Optional to LAT Program Acoustic Thermal Balance Ship X-LAT Plates Radiators Thermal Vac Testing Hardware Flight TKR Flight CAL FlightGrid Flight TEM Test Harnesses Software Aliveness Tests Characterization & Calibration EM 1 Aliveness Tests Functional Tests Characterization & Calibration Survey LAT Alignment Flight SIU EPU GASU ACD Flight Pwr Dist Flight Harnesses Flight TCS Flight X-LAT Plate EM2 Full LAT Name Document: LAT-PR Electrical Interface Tests Aliveness Tests Functional Tests Limited Performance Comprehensive Performance Vib- Random & Sine Sweep Characterization & Calibration Flight LAT Final IOC (v1) Limited Performance Characterization & Calibration Flight LAT Final IOC (v2)

38 LAT Test Sequence w/ Electrical Performance Tests TKR CAL Grid TEM Grid EP SIU PDU GASU. EMI SHIELD ACD Tower Integration Integrate TKR/CAL with Grid & TEM's A LAT Integration Integrate E-Boxes w/ Grid A F Alignment Survey Integrate ACD, X-LAT Plate F E C Mass Properties Alignment *Thermal Cycling L *Airborne A LAT Test NRL L C EMI/ EMC L Modal survey Vibration L Acoustic Thermal Balance Thermal C Vac L C Mass Properties Observatory Integration Delivery L Integration L TCS X-LAT Plate Radiators * Optional to LAT Program E L Final Alignment Ship Testing A Aliveness Tests Characterization & Calibration Hardware Flight TKR Flight CAL FlightGrid Flight TEM Test Harnesses Software EM 1 F Aliveness Tests Functional Tests Characterization & Calibration Survey LAT Alignment Flight SIU EPU EM2 GASU Flight Pwr Dist Flight Harnesses Flight TCS Flight X-LAT Plate ACD Flight LAT Limited Performance Characterization & Calibration Flight LAT Name Document: LAT-PR E L C Electrical Interface Tests Aliveness Tests Functional Tests Limited Performance Comprehensive Performance Vib- Random & Sine Sweep Characterization & Calibration Full LAT Final IOC (v1) Final IOC (v2)

39 LAT Test Performance Process GEVS-SE LAT-MAR LAT-IRD LAT-Spec LAT-Rqmt LAT-SRD LAT Mission Analysis Level IIb, III,IV Requirements LAT Environmental Parameters LAT Performance Verification Plan LAT System & Subsystem Test Plans Test Readiness Review SYS Eng Plan Perf Assurance Plan CM Plan LATQuality Manual Qualification Protoflight Flight OK to Test Test Performance Test Data Review Ready for Use Review Approval for delivery Delivery Level IIb,III,IV Rqts Verificaion Name Document: LAT-PR

40 LAT Thermal Vacuum Profile High Temperature Limit Hot Operational Thermal Balance L Hot non- operational Survival Soak C Hot Start 12 hour min. soak C C 30 C (TBR) C C Bake Out Break Configuration C Cycle 1 is the Thermal Balance Test Low Temperature Limit Cold Survival Thermal Balance L Cold Operational Thermal Balance Cold Start C 12 hour min. soak C C C -25 C (TBR) 4 4 Cycles at Instrument Level Ambient Pressure & Temperature Pressure of <1X10-5Torr Thermal Cycling Presssure of <1X10-5 Torr 20 C / hour Max Ramp Rate Stability < 3 C / hr rate of change Dwell at High & Low Temps for 12 Hours(min) Limited Performance Tests conducted during transitions Comprehensive Performance Tests (C) Comprehensive Performance Test regime performed at Ambient, during cold and hot soaks, and at return to ambient Limited Performance Tests (L) Limited Performance Tests are performed as indicated. Operating modes will be checked and units will be monitored for failure and intermittent operation. Name Document: LAT-PR

41 I&T Status PDR Presentations Complete. PDR Report Complete. Design Products Defined. Online Level III Requirements Complete (LAT-SS-00456) Particle Test Plan Complete (TBR). (LAT-TD-00440) JAN PDR Airplane Cosmic Ray End-to-End Test Plan Complete (TBR). (LAT-TD-00550) RFI for Commercial Air Transport of LAT to NRL complete. RFI for Environmental Tests of LAT complete. NEW Since Jan PDR The I&T Management Staff Buildup Begun in August 01 is Complete. EM1 EGSE R1 Delivery Milestones are Complete. I&T Contamination Control Implementation Plan Complete.(LAT-MD-00404) LAT Science Verification and Calibration Plan Complete. (LAT-MD-00446) Integration and Electronics Integration Plan Complete (TBR). (LAT-TD-00676) Revision 0 Assembly Traveler Available (TBR). (LAT-TD-00856) New WBS, Cost Estimate, BoE, P3 Schedule with Risk Assessment, Complete. Six month schedule extension in P3 is done. Preparations for EM assembly and testing (before CDR), and CDR underway. Name Document: LAT-PR

42 Results from the January Review Findings and Recommendations from the Final PDR/Baseline Report: I&T Passed PDR. I&T was not Recommended for baselining. The I&T subsystem s technical design was deemed to be mature. The management structure appeared to be strong and the budget and contingency appeared to be adequate. The committee concluded that the I&T subsystem is at the PDR level but recommended against baselining this subsystem due to lack of a bottoms-up cost estimate and the newly reworked WBS. Name Document: LAT-PR

43 Results from the January Review (Cont) Findings, Recommendations, RFA responses: Complete the reworked WBS with review and approval by project management by February Status: The reworked WBS has been completed. It is available through the LAT document system. Complete the reworked cost and milestones with review and approval by project management by March Status: Agreed, Completed, and being presented at this review. Recommend subsystem baseline review as soon as possible after the work on items 1 and 2 are complete. Status: Agreed and now in progress. Write the integration and electronics integration plans and get them under configuration management by March Status: An integration and test plan is written. It is available and under configuration management- LAT-TD Name Document: LAT-PR

44 Results from the January Review (Cont) Findings, Recommendations, RFA responses (Cont): Write a baseline level plan for the airborne test by March 2002 and ensure that any requirements on the subsystems levied by this test are flowed to subsystem managers. Status: Draft completed.the airborne test plan, LAT-TD-00550, has been included in the integration and test plan. The integration and test plan will be reviewed and concurred upon by Systems Engineering and Subsystem Managers. Rev 0 assembly traveler should be written and under configuration control before Qualification Unit A arrives. Status: Agreed, Draft 0 Completed, LAT-TD-00856, and available for this review. Provide an initial, top-level estimate of the cost/schedule impact of replacing a Tracker tower after complete instrument assembly. (This AI was originally AI-Mech-03). Status: In Process Name Document: LAT-PR

45 Cost and Schedule Accomplishments Completed implementing new WBS structure (LAT-MD ) Completed new cost estimate Completed loading new schedule and cost into PMCS Completed Change Control Process to approve plan (LAT-XR ) Completed 6 month readjustment to I&T schedule. Completed Change Control Process to approve plan with 6 month extension. (LAT-XR ) Name Document: LAT-PR

46 Level Four WBS Summary Full text of WBS with descriptions down to lowest level in LAT-MD WBS Task Manager Integration and Test Subsystem E. Bloom I&T Management E. Bloom Reliability and QA D. Marsh Instrument Operations Coordinator D. Lung - Acting Mechanical Ground Support Equipment E. Gawehn Online Software R. Claus Integration, Facilities, Configuration and Test (IFCT) L. Wai Particle Test G. Godfrey Environmental Test M. Lovellette Science Verification, Analysis & Calibration (SVAC) E. do Couto e Silva A I&T Mission Support E. Bloom Name Document: LAT-PR

47 LAT Summary Schedule 15 Electronics, DAQ Tracker Fab & Test Calorimeter 12 Fab & Test ACD Fab & Test GRID Fab & Test 9 Instrument I&T Calibration 6 Unit Ship Instrument Observatory I&T Launch 3 LAT Operations & Data Analysis FABRICATION PHASE } COMMISSIONING PHASE LAT Complete 5/25/05 14 wks Schedule Float 9/1/05 9/06 0 FY02 FY03 FY04 FY05 FY06 FY07 Name Document: LAT-PR

48 Key I&T Schedule Dates CU hardware arrives March 04 CU Beam test (PMCS update in process) April June 04 Flight Unit Hardware starts to arrive June 04 Integration Complete Jan 05 Shipped to Environmental Test Facility Feb 05 LAT NRL May 05 Ship LAT to S/C Vendor (Level II Milestone) Sept 05 Name Document: LAT-PR

49 I&T Summary Schedule in PMCS FY00 FY01 FY02 FY03 FY04 FY05 JAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEC + Key Milestones PDR CDR LAT I&T Ship LA + Preparation - Pre CDR Ready for PDR Ready for CDR + Preparation/Support - Post CDR + Calibration Unit + Flight Unit - Tower Integratio + Flight Unit - LAT Integration/Test MGSE, EGSE, SVAC, IFCT Beam Test Grid Arrives Functional Testing + Flight Unit - Enviromental Tests + Mission Planning + Mission Suppor Start Ops NRL Ready to S/C Vendor Primavera Systems, Inc. Early Bar Baseline Progress Bar Critical Activity LT-RV Summary Schedule 26JUL02 16: I&&T Name Document: LAT-PR

50 I&T Key Need Milestones Product Available Dates vs. Integration Need Dates Product Available Date Integration Need Date Level 3 Milestone Baseline Name Document: LAT-PR

51 I&T Key Need Milestones (Cont) Product Available Dates vs. Integration Need Dates Name Document: LAT-PR

52 Key Available Milestones - available - need - level III milestone - Inter-subsystem informational milestone Name Document: LAT-PR

53 Cost & Commitments Integration & Testing 10 ($M) $6.7M FY00 FY01 FY02 FY03 FY04 FY05 ACWP Actual Commits BCWS Budget + Commits Name Document: LAT-PR

54 I & T Cost Profile (k$) FY01 FY02 FY03 FY04 FY05 Total I&T Management , Instrument Operations Coordinator Mechanical Ground Support Equipment , Online Software , Integration, Facilities, Configuration, Test , Particle Test Enviromental Test Science Verification, Analysis & Calibration A I&T Mission Support ,934 2,164 1,583 6,654 Name Document: LAT-PR

55 I&T Cost Profile Integration & Testing (K$) FY00 FY01 FY02 FY03 FY04 FY05 LABOR TRAVEL MATERIALS & SERVICES Name Document: LAT-PR

56 I&T Manpower Plan Integration & Testing FTEs FY00 FY01 FY02 FY03 FY04 FY05 DOE + NASA Project Collaborators Name Document: LAT-PR

57 I&T Issues Anxious for Spacecraft vendor to be selected and start working with them. Reevaluation of EGSE executive software for EGSE EM2 and beyond. Will SCL do the job given what we have learned about its capabilities over the past 9 months and its fit to the flight hardware. Trade study underway. Continue developing plan for TVAC test of LAT plus Radiators. Continue planning for LAT modal test at SLAC No major I&T issues Name Document: LAT-PR

58 Summary We believe that the I&T subsystem s technical design is mature, and has gained considerable credibility since our PDR approval in January. Our management structure is strong and well correlated to our WBS and PMCS. We believe that the I&T budget and contingency are adequate. With the LAT management approval of our WBS and PMCS, resulting from our bottoms up cost estimate, and the inclusion of the 6 month schedule extension, we strongly believe that I&T is ready to be baselined. Name Document: LAT-PR