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Structural Analysis Jeff Bolognese 16 November 2001

Structural Analysis Jeff Bolognese 16 November 2001. NASTRAN Finite Element Model. Secondary support spider. Metering structure (composite tube truss). Primary mirror (90% lightweighted fused silica with Ti bipods). Optical bench (composite face sheet/Al Honeycomb core with stiffeners).

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Structural Analysis Jeff Bolognese 16 November 2001

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  1. Structural Analysis Jeff Bolognese 16 November 2001 Structural Analysis

  2. NASTRAN Finite Element Model Secondary support spider Metering structure (composite tube truss) Primary mirror (90% lightweighted fused silica with Ti bipods) Optical bench (composite face sheet/Al Honeycomb core with stiffeners) Aft Optics Assembly (Honeycomb with Composite frame and Ti flexures) S/C Mount Bipods (Composite tubes) Structural Analysis

  3. Modeling Details • Truss and Secondary Support Spider • M55J composite structure • 2.5” diameter tubes (.25” thick) • H-channel stiffening ring • 3 tangent blade spider • Trades done on 4 and 3 blade non-tan. Structure • Primary Mirror and Mount • 90% lightweighted Fused Silica for mirror • 3 Titanium bipods Structural Analysis

  4. Modeling Details (Cont.) • Optical Bench and S/C Mount Bipods • Bench M55J composite facesheets with Al honeycomb core and composite stiffeners (6” deep) • Bench mounts metering structure, primary mirror and aft optics module • S/C mount bipods 5” diameter composite tubes (.25” thick) • Aft Optics Structure • Composite/Al honeycomb face sheets • Composite truss structure • 3 Ti flexure blades • Lumped mass representation of fold and tertiary mirrors and detector assembly Structural Analysis

  5. FEM Summary • Analyzed mass = 658 Kg • Primary Mode = 32 Hz • Materials • M55J Composite: E= 1.4e+7 psi, CTE= -1.8e-7 mm/mm/C • Titanium: E= 1.6e+7 psi, CTE= 8.8e-6 mm/mm/C • Fused Silica: E= 9.85e+6 psi, CTE= 5.0e-7 mm/mm/C • Major structures included: • Metering structure • Secondary spider and secondary • 18 Kg mass for mechanism • Optical bench • Primary mirror and mount • Aft optics structure • Simplified mass representation for fold, tertiary and detector Structural Analysis

  6. FEM Summary (Cont.) • FEM does not include: • Baffles • Thermal masses • Solar arrays • Chopper mechanism • Full detector assembly mass • Spacecraft interface deck • Electronics boxes/harnessing Structural Analysis

  7. Analysis Summary Mode 1 = 32.4 Hz Mode 2 = 34.4 Hz Structural Analysis

  8. Analysis Summary (thermal distortion) 1c X grad 1c Y grad 1c Z grad Structural Analysis

  9. Future Analytical Work • Update structural masses • Rerun quasi-static stress and dynamics analyses • Detailed model of detector assembly • Initial optimization analyses done on detector mount plate show lightweighting is feasible. • Model S/C interface deck • Additional updates for detailed structural/thermal/optical analysis • Detail optics and mounts • Apply on-orbit thermal loads • Further optimization of aft optics module and flexure blades and other structures where practical. Structural Analysis

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