AddPlyby Addcomposites

Release notes

Continuous assistant presence during native analysis

0.2.0-beta.87 · 2026-10-20. This beta supports composite laminate definition and review on CAD geometry.

Connect once, work across projects

  • Persistent app login: connect AddPly to your Addcomposites account in your chat once. Browser session expiry, reload and switching projects no longer expire that app connection.
  • Automatic project discovery: opening a project makes it available to your connected apps. There is no per-project OAuth or private-code step.
  • Clear controls: Assistant access beside Save shows readiness and lets you pause a project. Disconnect the app in your chat to revoke account access.
  • Preserved execution checks: original browser credentials still protect command consumption and geometry upload. Interrupted operations require inspection; they never replay automatically.

New in this release

  • Continue a saved drape calculation: your assistant or the native drape viewer can start another bounded calculation from every retained piece's material chart. The design, contact, cuts, origins and numerical settings must match exactly. Every facet and piece is checked again; incomplete results remain available for review and cannot deliver cutting patterns.
  • Explicit station cuts: define a section plane through an inspected CAD point and trace its connected intersection with the actual 3D ply contact. Coplanar or ambiguous paths remain visible for revision. Cut refinement retains every original facet and cut point without unnecessary center nodes. Every piece receives a share of the drape calculation budget; an unfinished first piece cannot consume the later pieces’ allocation.
  • Complete native study evidence: cut planning and inverse draping retain the full tooling geometry, original-facet bindings and failed numerical fields through hosted transport and saved projects. Transport now accommodates the existing 50,000-node / 100,000-facet geometry limits; numerical tolerances and cutting checks remain unchanged.
  • Complete CAD preparation: prepare every face in a native tooling group, including holes, vertical faces and spherical poles. The owned worker refines actual measured errors; independent native CAD checks validate every face before original shared edges are joined without moving coordinates. Save and reopen retain the same mesh for laminate and engineering checks. Multi-face ply/ramp boundary partitioning remains unresolved.
  • Mesh refinement review: run finer FE meshes while retaining the design, loads, materials, drape settings and CAD sampling. Review at least three actual meshes against an explicit response-change tolerance for every load case. Incomplete strengths, unchanged meshes and changed setups cannot produce a complete consistency verdict.
  • Strength comparisons by case: compare failure indices and governing modes alongside displacement and ply stresses, with changed inputs disclosed. Refinement reports can be downloaded; observed consistency is separate from engineering acceptance.
  • CAD loads and mounts: pick source faces in 3D, choose face boundaries or laminate regions, and define up to three independent named pressure or total-force cases with visible load directions. Completed results show the actual restrained nodes and loaded areas.
  • Material-backed ply checks: separate directional tensile, compressive and in-plane shear strengths from elastic properties. A maximum-stress check evaluates every ply integration point, records its governing mode and load case, and leaves missing data unresolved. Published Hexcel M56 values retain their typical basis and source; unpublished transverse strengths stay blank.
  • Connected design loop: CAD → ply design → draping → structural analysis → review → revise → repeat. Your assistant receives the next step, declared-target assessment, response location and preserved rerun inputs through review_live_design_loop.
  • Traceable review targets: declare maximum displacement and drape shear with their source and basis. Historical results cannot assess the current laminate. Meeting these screens does not establish engineering acceptance.
  • Comparable revisions: comparisons check loads, restraints, material data, drape settings and sampled structural geometry before reporting response changes. Changed inputs are disclosed. Revise laminate returns directly to ply editing; saved study inputs remain available for reruns.
  • Your chat, your visible project: the public HTTPS MCP connection lets your existing assistant inspect imported CAD, author revision-bound plies and patches, show layers, undo changes and save in the open AddPly workspace.
  • Account permissions: app consent covers projects open under your own Addcomposites account. Each operation explicitly selects a live workspace; other accounts remain isolated.
  • Compact ribbon: Design, View, Deliver and Tools group the application commands. Collapse to tabs with the chevron, double-click a tab, or use Ctrl+F1. File actions stay together; Help contains tutorials, assistant setup and feedback.
  • Unified navigation: Templates, the model browser and specialist workbenches live under Tools. The title bar keeps the project name, save status and quick Undo, Redo and Save actions.
  • Workspace layouts: Design shows authoring panels; Inspect gives the model and thickness section the workspace; Present hides editing chrome. Panels can also be toggled independently, with unfinished forms retained.
  • Readable inspection: drag the thickness divider or use its arrow keys to resize the section. Charts size to the pane, camera framing accounts for its shape, and Full screen removes browser chrome. Escape leaves Present or full screen.
  • Compact guidance: an existing laminate opens with its guide collapsed. Display controls and the design overview expand when needed.

Aerospace lifecycle suite

  • Five aerospace design cases: a tapered wing spar, DLR CRM-HL nacelle fairing, zone-transition web, fuselage window belt and compound-curved frame bracket. Each includes native CAD, a foundation stack and a detailed editable laminate, with material and geometry sources.
  • Lifecycle tutorials: follow tooling selection, material and orientation records, staggered reinforcement, local stack inspection, revision review and portable project interchange.
  • Supplier material sets: Hexcel HexPly M56 carbon prepreg cards cite the supplier's measured cured ply thickness and nominal prepreg areal mass. The synthetic reference set remains available under More material sets.
  • Compact ply review: ply rows show material, angle, thickness and region, with orientation metadata, process binding and editing controls under Ply details. Material and summary basis disclosures retain their technical limits.

What is available

  • Template Library: readiness labels, disclosed transfer losses, editable starter copies and guarded Reset to template.
  • Your own STEP: tooling groups, projected regions, material sets and declared stack patterns applied in one undoable step.
  • Traceable reuse: template origins travel with local saves and portable projects.
  • Review evidence: declared stacking-rule verdicts, exact geometry measurements, stale evidence warnings, summaries and printable plybooks.
  • Work protection: save status, revision conflict and recovery choices, and explicit warnings before replacing unapplied work.
  • Assistant workflow: bounded remote MCP tools operate the current browser project, using the same design operations and review checks as the editor.
  • Help and feedback: guided steps, recovery guidance and a local feedback report whose complete contents can be reviewed before download.

Known limitations

  • Supplier material cards cite typical published data; example layups and templates require engineering review before use on your own part.
  • Declared ply angles remain intent until a hosted drape study computes a field. Kinematic draping covers smooth single-valued supports; it does not predict wrinkles, compaction or contact.
  • Native 3D draping processes one selected ply on its saved native faces or exact CAD contour, including vertical faces and CAD holes. Constant preceding coverage uses analytic CAD-normal contact offsets. Saved complete-laminate intent reconstructs base, patch and cover contact with explicit cubic perimeter ramps and fill on a regular graph support. Directed cut planning traces these actual contacts and retains original-facet endpoints, cuts and candidate origins through saved layouts. Refined contacts retain original-facet origins, declared slit/butt cuts and result weights. Failed fields remain inspectable. Complete charts have flattened previews; Current selected-ply pattern exports require a declared shear screen and checked chart contours, CAD holes and source-bound slit banks. Optional finished SVG/DXF retains net contours, sourced allowances and grain/face markers. Positive allowances use the hosted Shapely worker; topology changes and conflicts refuse, and output precision and sampled screening limits are recorded. Sharp offset intersections, drawn holes/islands, protected regions and cut-joint analysis need integration. Native shell analysis supports uncut nominal stacks. Saved base/patch/cover ramps and explicit fill can use actual quadratic solid volumes with current physical ply drapes and sourced elastic laws; all six material stress components and actual supports/loads remain in the project. Draping imposes full contact and does not predict physical forming.
  • Drape-derived patterns use saved net/extended cut regions and independent origins for directed butt pieces on sampled single-valued tooling. Incomplete/ambiguous coverage and exceeded sourced roll width block cutting exports. Overlap joints, two-stage draping and manufacturing qualification remain unresolved.
  • The explicitly selected experimental cut inverse uses saved slit/V darts under assumed full contact. Inspect actual bank coordinates, removed net, retained covers and added/missing thickness. Current numerically valid sets can export actual-size SVG/JSON with source evidence and slit-bank cuts; failed or unresolved requirements block the complete set. It has no FEA, measured forming law, bridging/tearing prediction or repair approval. Failed original-net direction coverage remains unresolved even if a cover fills the gap.
  • Full cut fields distinguish shear, warp deviation and weft deviation. Deviation uses tangent-projected seed axes, not general curved rosettes; conservative cell-corner bounds are pitch dependent. Explicit regional limits preserve sources. No bridging, tearing or wrinkle acceptance is inferred.
  • Native source-bound pattern sets and independently verified feasible stock layouts are available through MCP. All current stocks and copies export as actual-size SVG/DXF with original patterns and verification evidence. Stock/reference and marking layers require explicit cutter setup; kerf compensation and machine programs are not generated. Layouts are not optimal or manufacturing-approved. Changed source data blocks export.
  • Saved seam restrictions and stagger limits use sampled tool polylines. Spacing is minimum 3D Euclidean separation, not surface geodesic spacing or qualified joint strength. Failed or unresolved requirements block cutting exports.
  • Butt-spliced manufacturing definitions cannot run structural analysis until seam-conforming geometry and a joint-transfer model are implemented. Engineering net coverage and nominal ply thickness remain separate from cut pieces.
  • Hosted FEA uses linear perfectly bonded orthotropic shells or actual nominal ply/fill solids with sourced cured elastic data and named physical load cases. Optional solid maximum-stress screening checks all four integration points and six components using separate tension, compression and shear limits. Ply strength cards must cover actual signed drape shear; fill limits use global axes. Missing/inapplicable strengths stay unresolved. No fatigue, buckling, delamination prediction or manufacturing acceptance.
  • Typical strength data is not a guaranteed minimum. Missing directional strengths keep the maximum-stress assessment unresolved; no damage interaction or progressive failure is modeled.
  • Review targets screen calculated displacement and drape shear. A target met result is not engineering approval; assumptions and unresolved requirements still need review.
  • Complete-laminate intent also supports a separately selected first-order discrete shear-gap shell. Each actual native ply chart and ramp-fill phase retains its volume, through-thickness and shape moments; actual bag loads retain force and moment. Full row stress extrema, nodal rotations and reactions are saved. Plane-stress shell kinematics impose sigma33=0. This is a linear bonded approximation, not interlaminar stress, physical consolidation, cut-joint transfer or qualified drop-edge failure analysis. Missing directional strengths remain unresolved.
  • Cutout outlines are stored, but exact viewport clipping and measured material usage remain limited.
  • Projects are stored in this browser; download a project backup to move or protect your work.
  • Assistant actions require an OAuth-capable remote MCP client, a connected Addcomposites account and an open AddPly tab. Pending operations require completed browser receipts.

Save a portable project before moving to another browser or site address. Open it with File → Open file… and regenerate stale review evidence after design changes.

This page describes shipped functionality. Practitioner completion rates and engineering validation of drape, paths or manufacturability have not been established by these features.

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