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GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC GLAST Large Area Telescope Calorimeter Subsystem Gamma-ray.

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Presentation on theme: "GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC GLAST Large Area Telescope Calorimeter Subsystem Gamma-ray."— Presentation transcript:

1 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC GLAST Large Area Telescope Calorimeter Subsystem Gamma-ray Large Area Space Telescope 6.3 Mechanical Structure Fabrication Paul V. Dizon Naval Research Lab, Washington DC Calorimeter Lead Mechanical Systems Engineer paul.dizon@nrl.navy.mil (202)–404–7193

2 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 2 Design Status - Parts  Metallic Parts –No Significant Design Evolution is Expected: EM Design is Very Close to Flight Module Design Fabrication Drawings Have Been Completed and Should Only See Cosmetic Modifications Specifications and Verification Procedures for Flight Parts Have Been Released. Procurement Procedure Has Started  Polymer Parts –Materials and Vendor for Silicone Cords and Bumper Frames Have Been Chosen Additional Testing is Being Performed to Provide the Additional Information Necessary to Finalize the Specifications for Both Polymer Parts –Evaluating the Present CDE End Cap and Bumper Implementation to Determine If They Could Be Merged Into a Single Assembly

3 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 3 Design Status – Composite Structure  Composite Structure –Fabrication Procedure Has Been Improved and Changed Since EM: Autoclave Curing Process has Replaced Oven Curing in Order to Improve the Physical Properties of the Composite Material (Increase Fiber Content, Reduce Void Ratio) –Improved Process Implies a New Fabrication Procedure, a Different Design for the Tooling and the Development of Prototype Structures New Fabrication Procedure is Being Finalized New Tooling Design is Complete and the Fabrication Drawings Are Being Generated Two Prototype Composite Structures Have Already Been Produced from Test Tooling to Verify the Concept. A Third Structure Will Be Ready by CDR

4 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 4 Design Status – Composite Structure  Composite Structure - Continued –Improved Process will be Qualified Requires the Fabrication of Verification Models –SM – Structural Model –SFM – Structural Flight Model SM –Will be Used for Qualification of the Improved Curing Process »Industry Autoclave used for Development of Improved Process »Structural Environment Testing »Material Properties/Void Ratio Measurement »Non-Destructive Testing SFM –Will be Used to Verify the Improved Curing Process Prior to Flight Build »IN2P3 Autoclave »Material Properties/Void Ratio Measurement »Non-Destructive Testing –Verification Procedure for Flight Structures Non-Destructive Testing Still Needs to be Addressed in the Verification Procedure. Ultrasonic C-scan is Being Evaluated by a Vendor on Structure Test Samples

5 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 5 Manufacturing  Mechanical Components and Processes  Manufacturing Organization  Manufacturing Flow Aluminum Piece Parts Elastomeric Piece Parts Composite Structure  Manufacturing and Tooling Methods for Composite Structure  Manufacturing Facilities  Quality Assurance Inspection  Verification Testing

6 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 6 Manufacturing – Components & Processes ComponentReferenceMaterialProcess/coatingVendor EMI ShieldLAT-DS-01234Al 99,0 aluminumCutting, Alodine Composite structureLAT-DS-00918 T300 1K HS carbon M76 epoxy resin Prepreg lay-up Cured 4h at 135°C HEXCEL Base plateLAT-DS-009192618A T851 AluminumMachining, Alodine Top frameLAT-DS-009172618A T851 AluminumMachining, Alodine Closeout plate X and YLAT-DS-00920/212618A T851 AluminumMachining, Alodine Side panel X and YLAT-DS-00923/245751 H111 AluminumMachining, Alodine InsertsLAT-DS-00927/28/29Ti-6Al-4V TitaniumMachining NutsLAT-DS-00922Ti-6Al-4V TitaniumMachining Silicone cordsLAT-DS-009847611B Red silicone Extrusion at 200°C Post-cured 16h at 200°C ADDIX Bumper FrameLAT-DS-00925 VALOX DR48 PBT 7601B Red silicone Injection molding Post-cured 16h at 175°C ADDIX Fasteners CRES A286 AISI 316 Stainless Helical coils INCONEL 750 Stainless Steel Silver plating

7 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 7 Manufacturing - Organization  Metallic Parts: Aluminum Plates, Titanium Inserts and Nuts –Contract with the Industry, Includes: Fabrication of Parts Alodine Surface Treatment of Parts 100% Verification of Parts –Proposal Released, Opened to EU Countries, 2 Month for Bids –Receiving Inspection at LLR, Pre-Assembly (PEM Mechanical and Shipping Configuration), Packaging and Shipping to NRL  Polymer Parts: End Caps, Bumper Frames and Silicone Cords –Contract with Vendor, ADDIX, Includes: Fabrication of Parts Verification of Material Properties –Receiving Inspection at LLR Before Delivery to NRL/CEA

8 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 8 Manufacturing - Organization  Composite Structure –Procurement of Pre-Preg Material by LLR A Procurement of 500 m² is Planned for Flight Structures (20 m² per Structure Required). The Specifications Have Been Released and Accepted by the Vendor, HEXCEL –Contract for Cutting of Pre-Preg Plies and Preparation of Lay-ups Proposals from Several Vendors Have Already Been Received but Vendor Has Not Been Chosen The Specifications are Being Updated and Completed, Which Will Require New Proposals

9 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 9 Manufacturing - Organization  Composite Structure - Continued –Structure Fabrication and Verification at LLR Two Molds Will Be Used for Flexibility, Which Will Allow a Production Rate of up to One Structure Per Week (If Required) Fabrication Will Include the Lay-up of the Pre-Preg Plies in the Molds, the Vacuum Bagging and the Autoclave Curing The Verification Will Include: –Dimensional Inspection –Measurement of Physical Properties on Co-cured Samples –Structure Verification Test – Static Pull Test –Non Destructive Testing A Contract for the Ultrasonic C-scan of the Composite Structure (Outer Walls) Is Required. The Company is Currently Evaluating the Procedure

10 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 10 Structural Piece-Part Manufacturing Flow Receiving Inspection Receiving Inspection Machining Cleaning Visual Inspection Metrology Visual Inspection Metrology Alodine 1200 Coating Alodine 1200 Coating Receiving Inspection Receiving Inspection Raw Material (Al Alloys) Raw Material (Al Alloys) Helical Coils Inspection of Threads Inspection of Threads Insertion of Helical Coils Insertion of Helical Coils Coating Verification (Test Coupons) Coating Verification (Test Coupons) Packaging Delivery to LLR Packaging Delivery to LLR Receiving Inspection Receiving Inspection Documents Fabrication Drawings Specification for Fabrication: GLAST-LLR-SP-044 Specification for Alodine Surface Treatment: GLAST-LLR-SP-052 Specification for Part Verification: GLAST-LLR-SP-053 Receiving Inspection Procedure: GLAST-LLR-PR-071 Metallic Parts

11 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 11 Polymer Piece-Part Manufacturing Flow Elastomeric Cords Cut to Length Post-Cure 16h at 200°C Post-Cure 16h at 200°C Clean Verification Testing Verification Testing Packaging Delivery to LLR Packaging Delivery to LLR Receiving Inspection Receiving Inspection Raw Material (Silicone) Raw Material (Silicone) Formulate Elastomer Formulate Elastomer Receiving Inspection Receiving Inspection Extrude / Cure 200°C Extrude / Cure 200°C Tensile properties Dimensional Inspection Tensile properties Compression Set Aging Documents Specification: LAT-DS-00984 Receiving inspection: GLAST-LLR-PR-071

12 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 12 Polymer Piece-Part Manufacturing Flow Bumper Frame Raw Material (GE Valox DR48) Raw Material (GE Valox DR48) Receiving Inspection Receiving Inspection Injection Molding Injection Molding Cleaning Inspection Visual Inspection Visual Bumper Rigid Part Bumper Rigid Part Mold Elastomer Cure at 110°C Mold Elastomer Cure at 110°C Post-Cure 16h at 175°C Post-Cure 16h at 175°C Cleaning Inspection Dimensional Inspection Dimensional Packaging Delivery to LLR Packaging Delivery to LLR Raw Material (Silicone) Raw Material (Silicone) Formulate Elastomer Formulate Elastomer Receiving Inspection Receiving Inspection Receiving Inspection Receiving Inspection Documents Drawing: LAT-DS-00925 Specification: GLAST-LLR-SP-069 Receiving inspection GLAST-LLR-PR-071

13 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 13 Composite Structure Manufacturing Flow Lay-Up Holes for Inserts Lay-Up Holes for Inserts Receiving Inspection Receiving Inspection Prepare Mold Tooling Prepare Mold Tooling Lay-Up Pre-Preg Lay-Up Pre-Preg Vacuum Bag Raw Material (Pre-Preg) Raw Material (Pre-Preg) Remove Structure Remove Structure Cure at 135°C 4h / 7 bars Cure at 135°C 4h / 7 bars Clean Structure Clean Structure Inspection Receiving Inspection Receiving Inspection Pre-Preg Cutting Pre-Preg Cutting Packaging Delivery to LLR Packaging Delivery to LLR Verification Testing Verification Testing NDT C-Scan NDT C-Scan Dimensional Inspection Physical Properties on Co-cured Samples Structure Verification Test: Static Pull Test Integration PEM Mechanical Structure Integration PEM Mechanical Structure Documents Drawing: LAT-DS-00925 Prepreg Handling and Storage: GLAST-LLR-PR-068Pre-Preg Specification: GLAST-LLR-SP-048 Prepreg Cutting : GLAST-LLR-SP-035Structure Verification: GLAST-LLR-SP-072 Receiving Inspection GLAST-LLR-Sample Verification: GLAST-LLR-SP-073 Fabrication Procedure: GLAST-LLR-SP-071NDT Specifications: GLAST-LLR-SP-074

14 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 14 PEM Mechanical Structure Flow Base Plate Fasteners Stake Fasteners Stake Fasteners Top Frame PEM Mech. Structure PEM Mech. Structure Assembly Composite Structure Composite Structure Inspection Visual Dimensional Nuts Close-Out Plates Assembly (Running torque) Assembly (Running torque) PEM Mechanical Structure PEM Mechanical Structure Inspection Visual Dimensional PEM Structure Shipping Config. PEM Structure Shipping Config. Packaging Shipping to NRL Packaging Shipping to NRL Side panels Documents Drawings: LAT-DS-01228 / LAT-DS-01231 Assembly Procedure: LAT-PS-01231 Cleaning & Storage Procedure: GLAST-LLR-PR-020 Handling & Packing Procedure: GLAST-LLR-PR-022 Polymer Parts

15 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 15 Composite Structure – Manufacturing Method  Pre-preg Material (GLAST-LLR-SP-048) –T300 1K HS Carbon Fibers, Taffeta Weave –M76 Epoxy Resin: Cure Temperature 135°C to 177°C, Low Outgassing –Thickness per Ply Is 0.12 mm for 64% Fiber Content  Tooling –Dimensions Account for Thermal Expansion of Aluminum vs. Composite –96 Precise, Non Tapered Aluminum Mandrels Define the Shape of the Cells. The CTE Mismatch Allows an Easy Removal From the Cells –Mechanical Stops Allow to Control Outer Dimensions. Position of the Stops Account for a Ply Thickness of 0.12 Mm –All Inserts are Positioned by Composite Plates to Avoid Loads Resulting From CTE Mismatch Between the Aluminum Tooling and the Composite Structure  Process –Complete Structure is Fabricated in a Single Curing Process –Titanium Inserts are Embedded in the Composite and Co-Cured – No Additional Bonding or Machining is Required

16 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 16 Composite Structure – Manufacturing Method Each Mandrel Wrapped with One Pre-Preg Ply Wrapping of Mandrels Preparation of Layer Stacking of Mandrels and Lateral Lay-Ups with Inserts Mechanical Pressure to Add Global Plies Stacking of Layers Closing of Mold Vacuum Bagging Autoclave Curing Structure Removal Metrology Release Film Breather Felt Vacuum Bag Stacking of Layers, Base and Top Lay-Ups with Inserts Temperature 135°C Pressure 7 bars Cure Time 4h Outer Dimensions Position of Inserts Dimension of Cells Removal of Layer Frame Removal of 96 Mandrels Cleaning 4 Side Plates and Cover Mechanical Stops to Control Outer Dimensions

17 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 17 LLR Manufacturing Facilities & Equipment  Clean Room –Class 100,000 –Temperature 21°C +/-2°C, RH 60% Max –32 m² Dedicated to Pre-Preg Lay-Up –14 m² for Cleaning and Packaging  Metrology Room –3D Measuring Machine MITUTOYO EURO-M 574, Camera System Included for Optical Measurement –Microscope for Verification of Small Parts  Autoclave –  1000 x 1700 mm –10 bars at 250°C Procurement in January, Delivery to LLR Early June

18 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 18 Manufacturing QA Inspection/Verification Testing COMPONENT INSPECTIONVERIFICATION TESTING VendorIN2P3/LLRVendorIN2P3/LLR Structural Piece Parts VisualVisual (100%)None (Aluminum Alloy) Dimensional (100%)Documentation Check Titanium Inserts / Nuts VisualVisual (100%)NonePull Test (sample) Dimensional (100%)Documentation Check Elastomeric Cords VisualVisual (sample)Tensile PropertiesTensile Strength Dimensional (sample) AgingOutgassing Documentation Check(Fabrication Lot)(Sample/Lot) End Caps, Bumper Frames VisualVisual (100%)None Dimensional (sample) Documentation Check Composite Structure - Structure N/AVisualUltrasonic C-ScanStatic Pull Test N/ADimensional (100%) - Co-Cured Sample N/AVisualMaterial Properties Void Ratio

19 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 19 Procurement Status  SM/SFM Procurements –Prepreg received for SM/SFM/FMA/FMB28 Feb 2003 (HEXCEL Specs for satellite pre-preg with additional testing) –Procurement of SM parts25 Feb 2003 –Delivery of SM parts 15 Apr 2003  FM Aluminum Piece Parts –Release of Proposal for FM parts24 Jan 2003 –Selection of FM Structure Vendor15 Apr 2003 –Delivery of first FM parts31 Jul 2003  Pre-Preg Material –Release of Flight Specification15 Feb 2003 –Purchase for flight1 Apr 2003 –Delivery of First Roll15 Jun 2003  Autoclave –Release of Specification Dec 2003 –Purchase of Autoclave15 Jan 2003 –Delivery and Installation31 May 2003

20 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 20 Procurement Status- Continued  Elastomeric Cords –Release of Specification 15 Mar 2003 –Purchase 15 Apr 2003 –Delivery of first batch 15 Jun 2003  Elastomeric Bumpers –Release of Specification 1 Apr 2003 –Purchase 15 Apr 2003 –Delivery of first batch 15 Jun 2003  End Caps –Release of Specification 1 Apr 2003 –Purchase 15 Apr 2003 –Delivery of first batch 15 Jun 2003  Flight Fasteners –Release of Specification 15 Apr 2003 –Purchase 15 May 2003 –Delivery 31 July 2003

21 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 21 Issues and Concerns  Change in the Fabrication Process of the Composite Structure –Added a Large Amount of Development Work –Delayed the Fabrication of the Tooling for the Flight Parts Delivery Schedule Not Affected, but There is No Margin Left  Internal Verification Prototypes Have Been Changed Into Verification Models (SM/SFM) –As a Result, the Following is Required: More Stringent Quality Control Additional Testing Extra Cost Internal Resources at IN2P3 Can Still Cover These Additional Requirements, but Schedule Pressure Will Be High Until Delivery of FMB

22 GLAST LAT ProjectCAL Peer Design Review, Mar 17-18, 2003 P. Dizon Naval Research Lab Washington DC 6.3 - 22 Summary and Conclusion No Major Problems ComponentProgressStatus Composite StructureDesigned & AnalyzedImproved Curing Process Being Qualified Partially Tested Aluminum Piece PartsDesigned & AnalyzedReady for Flight Build, Procurement Released Tested Titanium InsertsDesigned & AnalyzedReady for Flight Build, Procurement Released Tested Elastomeric CordsDesigned & AnalyzedReady for Flight Build Tested Elastomeric Bumper Frames, End Caps Designed & AnalyzedEvaluation of Redesign Tested

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