Add files via upload

Author: Samuelson777

downloads/asterion-fcta-v1.0-public-release/asterion-fcta-v1.0/analysis/ansys/v0_5/workbench/ANSYS_Workbench_V0_5_Guide.md

@@ -0,0 +1,76 @@
+# ASTERION FCTA-1 V0.5 — ANSYS Workbench Structural Analysis Guide
+
+## Purpose
+
+This guide converts the V0.3 BEAM188 primary-structure model and V0.4 subsystem mass state into a controlled V0.5 structural-analysis project. The supplied project contains no claimed solved ANSYS database. Results must be generated and reviewed on the user's licensed ANSYS installation.
+
+## Recommended project systems
+
+Create one Engineering Data cell and connect it to:
+
+1. Static Structural — docking compression.
+2. Static Structural — electric-propulsion thrust.
+3. Static Structural — twin-ring centrifugal loading.
+4. Static Structural — ring emergency braking.
+5. Static Structural — misaligned docking.
+6. Modal — free-free flight model.
+7. Modal — aft-supported ground-test model.
+8. Eigenvalue Buckling — linked from docking static pre-stress.
+
+Duplicate systems for mesh and joint-stiffness sensitivity instead of overwriting evidence.
+
+## Units and material
+
+Use mm, N, s and tonne consistently in APDL imports. The preliminary material is aluminium 7075-T6 with E = 71,700 MPa, ν = 0.33, density = 2.81×10⁻⁹ tonne/mm³ and room-temperature yield screening strength = 503 MPa. Replace this with temperature- and product-form-specific allowables before making design claims.
+
+## Global line model
+
+Import or execute `analysis/ansys/v0_3/apdl/asterion_line_model.inc`. Confirm:
+
+- 222 structural nodes;
+- 580 BEAM188 elements;
+- seven tube section families;
+- no zero-length or duplicate elements;
+- beam orientation is consistent; and
+- section assignment matches `beam_sections.csv`.
+
+## Non-structural masses
+
+Use `analysis/ansys/v0_4/model/remote_mass_definitions.csv` as the mass ledger. Prefer Mechanical Remote Mass objects connected to reviewed attachment frames. The included MASS21 macro is a seed only; uncoupled mass nodes are invalid.
+
+For the rotating habitation sectors, place mass at the ring nodes and include centrifugal acceleration. For modal analysis, include suitable rotary inertia estimates once the subsystem geometry is available.
+
+## Supports
+
+The aft-fixed support is a ground-test/screening boundary condition. It is not a realistic flight condition. For flight static studies, use a minimum 3-2-1 stabilisation scheme or inertia relief and confirm reactions do not dominate the reported load path.
+
+## Required result objects
+
+For every static case request:
+
+- total deformation;
+- directional deformation X/Y/Z;
+- equivalent stress;
+- beam axial force;
+- beam bending moment and torsion;
+- reaction forces and moments;
+- interface loads; and
+- factor-of-safety user result.
+
+For modal studies request at least 16 modes, participation factors and effective mass. For free-free analysis, the first six modes must be rigid-body modes near zero frequency.
+
+## Mesh convergence
+
+Run B1, B2 and B3 from `mesh_convergence_plan.csv`. Compare a physically meaningful displacement, member force, first ten flexible frequencies and non-singular stress. A converged contour picture alone is not sufficient.
+
+## Buckling
+
+Link Eigenvalue Buckling to LC-STR-01 pre-stress. Inspect mode shapes and reject local numerical artefacts. A positive eigenvalue above the criterion does not prove stability; follow with geometric nonlinearity and seeded imperfections in V0.8.
+
+## Evidence capture
+
+Complete the CSV templates in `results_templates/`. Save screenshots showing model tree, mesh statistics, boundary conditions, solver messages, deformation scale, legends and probe locations. Record the exact ANSYS release and project checksum.
+
+## Student-computer strategy
+
+Keep the global model as beams. Use shells only for ring hubs and docking frames, then solids only as local submodels. Do not solve the complete spacecraft as a detailed solid mesh.