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tual-test-audio.ts","virtual-test-catalog.ts","virtual-test-class.ts","virtual-test-inputs.ts","virtual-test-kernels.ts","virtual-test-mechanics.ts","virtual-test-playback.ts","void-consolidation-fields.ts","void-consolidation-history.ts","void-consolidation-schema.ts","void-consolidation.ts","warpage-history.ts","web-case-study-exercises.ts","welding-process.ts","winding-folders.ts","winding-process.ts","workbench-access.ts","workbench-capability-policy.ts","workbench-favorites.ts","workbench-history-validity.ts","workbench-id-manifest.json","workbench-input-help.ts","workbench-notices.ts","workbench-record-drag.ts","workbench-settings.ts","workbench-tree-drag.ts","workflow-case-blocks.ts","workflow-drop-assembly.ts","workflow-motion.ts","workflow-query-catalog.ts","workflow-query-create.ts","workflow-query-draft.ts","workflow-readiness.ts","workflow-refresh.ts","workflow-routing.ts","workspace-environment.ts","workspace-opening.ts","workspace-pane-layout.ts","workspace-pane-state.ts","workspace-recovery.ts","xz-section.ts"],"method":"Production solver executed on immutable copies of every exercise. Independent published-equation references use exact baseline inputs where eligible. Scoped analytical badges are not experimental validation, strength approval or validation of edited inputs. Full coupled studies remain unvalidated until matched external evidence and convergence studies exist. Tolerances were declared before numerical comparisons: analytical constants 0.01% + 0.00002 units; beam/strain 0.05% + absolute allowance; rounded NASA table values 1% + 0.00002.","sources":{"rom":{"title":"MIT / David Roylance — Introduction to Composites","url":"https://ocw.mit.edu/courses/3-11-mechanics-of-materials-fall-1999/e87276d20858aa3dc64aae71b04d7486_MIT3_11F99_composites.pdf","locator":"Equations 1–3, printed pages 3–4","basis":"Published analytical equations; not experimental material validation."},"clt":{"title":"MIT / David Roylance — Laminated Composite Plates","url":"https://ocw.mit.edu/courses/3-11-mechanics-of-materials-fall-1999/f193c908ec10d95c0bc67c904b65397a_MIT3_11F99_laminates.pdf","locator":"Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25","basis":"Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated."},"beam":{"title":"MIT / David Roylance — Beam Displacements","url":"https://ocw.mit.edu/courses/3-11-mechanics-of-materials-fall-1999/13534abb67b86d2fb8ee11a1f4f2b8c4_MIT3_11F99_bdisp.pdf","locator":"Equation 7, printed page 3: central-load simply supported beam","basis":"Euler–Bernoulli analytical check; excludes shear, contact, damage and empirical stiffness validation."},"pressure":{"title":"MIT / David Roylance — Pressure Vessels","url":"https://ocw.mit.edu/courses/3-11-mechanics-of-materials-fall-1999/082fcd712adffa589a670f9f8dfdd49a_MIT3_11F99_pv.pdf","locator":"Equations 2–3, printed page 3; orthotropic strain compliance from laminated plates reference","basis":"Thin-wall, closed-end pristine cylinder. No slit, fracture or failure-pressure validation."},"nasaMicro":{"title":"NASA/TM—2015-218814 — Experimental and Numerical Analysis of Triaxially Braided Composites Utilizing a Modified Subcell Modeling Approach","url":"https://ntrs.nasa.gov/api/citations/20160001347/downloads/20160001347.pdf","locator":"Tables 3–4, printed page 7 / PDF page 11","basis":"MAC/GMC calculated effective ply data, not measured UD coupon properties."},"nasaTube":{"title":"NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows","url":"https://ntrs.nasa.gov/api/citations/20140006740/downloads/20140006740.pdf?attachment=true","locator":"Tables 1–2, printed pages 11–12 / PDF pages 15–16","basis":"Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths."},"nasaCure":{"title":"NASA — Evaluation of Temperature Gradients During Cure of a Thick Carbon Fiber/Epoxy Composite","url":"https://ntrs.nasa.gov/citations/20200000350","locator":"Source study identified; quantitative reproduction not established","basis":"TC380 kinetics, reaction heat, transport, boundary characterization and digitized measurements still required."},"nasaPressure":{"title":"NASA-CR-195101 — Damage Tolerance of Pressurized Graphite/Epoxy Tape Cylinders Under Uniaxial and Biaxial Loading","url":"https://ntrs.nasa.gov/citations/19940020114","locator":"Source study identified; matched slit-cylinder dataset not reproduced","basis":"Slit-tip damage and failure pressure are outside pristine membrane scope."}},"summary":{"exercises":184,"executed":184,"analytical":43,"discrepancies":0,"unvalidated":141,"failed":0},"exercises":[{"exerciseId":"process-fdm-build","title":"03.81 · FDM: laminate-driven build, pauses and annealing","status":"Not benchmark validated","scope":"No matched quantitative reference comparison completed for the full exercise.","execution":"Completed (not validation)","inputSha256":"51749d9133b92aabb45833d234af6590407f5a04598111aa47c39e2a18513517","checks":[],"inputs":[],"limitations":["Illustrative neat PEEK local through-thickness build, not a full raster/toolpath or printer calibration. The unchanged RES-014 family card supplies constant reference thermal properties. Independent copies of the existing AS4/PEEK contact/healing coefficients are teaching assumptions for this neat-PEEK example, not a vendor-grade weld characterization. Initial contact is explicitly assumed to be 60%; no pressure-driven consolidation, self-weight, capillary neck growth, nozzle compaction, void removal or qualified strength is inferred. This example uses stationary chamber/bed anneal holds without extrusion or head heating."],"reason":"A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.","sources":[]}],"fixtures":[]}