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downloads/asterion-fcta-v1.0-public-release/asterion-fcta-v1.0/docs/v0_3/design_basis.md

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+# Version 0.3 Structural Design Basis
+
+## Purpose
+
+Define a lightweight, modular primary structure that can be rebuilt in Siemens NX and analysed on a home PC with ANSYS Student-class model limits.
+
+## Design philosophy
+
+1. Use orbit assembly; do not design the complete vehicle as a single launch stack.
+2. Keep the first global model beam-dominant and auditable.
+3. Separate global load-path verification from local joint, shell and contact models.
+4. Make interfaces replaceable and parameter-driven.
+5. Treat all material properties and load levels as preliminary until source-controlled project values are selected.
+
+## Structural arrangement
+
+- Central truss: eight longerons at 1.2 m radius.
+- Bay spacing: nominally 2.5 m, with extra interface stations.
+- Frames: octagonal beam frames at each station.
+- Bracing: alternating diagonal lattice between stations.
+- Rotating rings: 12-segment circumference frames at 12 m occupied radius.
+- Ring supports: 12 radial spokes per ring with hub links to the central truss.
+- Propulsion frame: six radial mounts at X = -16 m.
+- Docking frame: eight linked nodes at X = +21.4 m.
+
+## Preliminary material
+
+The model uses a conceptual aluminium 7075-T6 isotropic card:
+
+- Elastic modulus: 71.7 GPa
+- Poisson ratio: 0.33
+- Density: 2810 kg/m³
+- Screening yield strength: 503 MPa
+
+These values are not a procurement specification. Update them for temperature, product form, thickness, direction, joining process and supplier certification.
+
+## Mass statement
+
+The beam idealisation mass is 7,742.3 kg. It excludes joints, fittings, bearing hardware, pressure shells, fasteners, mechanisms, harnesses, coatings, local reinforcement and manufacturing allowances. It must not be quoted as complete spacecraft structural mass.

downloads/asterion-fcta-v1.0-public-release/asterion-fcta-v1.0/docs/v0_3/load_path_definition.md

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+# Primary Load-Path Definition
+
+## Docking load
+
+A preliminary 25 kN axial compression is introduced at the forward docking frame and transferred through eight docking links into the longerons, frames and diagonals. The demonstration support is placed at the aft end for a ground-test-style static case. A flight free-body treatment must use inertial relief or balanced loads rather than an artificial fixed support.
+
+## Propulsion and manoeuvre load
+
+Six propulsion mounts transfer thrust and gimbal reactions into the frame at X = -16 m. The current line model includes mount booms but does not yet model gimbal stiffness, pod mass or thrust-vector eccentricity.
+
+## Rotating-ring load
+
+Each ring uses a 12,000 kg conceptual rotating mass. At 4.3 rpm and 12 m radius, the distributed radial force is 29,198.2 N per ring. It is divided across 12 outer nodes for the first global case. Sector-by-sector mass, bearing compliance and imbalance must be added later.
+
+## Emergency braking
+
+Stopping one ring in 120 seconds requires an idealised torque of approximately 6,484.2 N·m. Counter-rotating rings cancel nominal angular momentum only when their inertias and rates match; transient mismatch still loads the spine and attitude-control system.
+
+## Local submodels required
+
+- Ring spoke-to-hub fittings
+- Bearing support and race
+- Docking-link lugs
+- Propulsion boom joints
+- Longeron/frame node fittings
+- Solar and radiator deployment hinges
+
+Global beam stresses must not be used to approve these local features.

downloads/asterion-fcta-v1.0-public-release/asterion-fcta-v1.0/docs/v0_3/model_acceptance_criteria.md

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+# Version 0.3 Model Acceptance Criteria
+
+| Check | Acceptance criterion |
+|---|---|
+| Zero-length elements | None |
+| Duplicate unmerged structural nodes | None unless intentionally connected by a joint element |
+| Beam section assignment | Every element has one valid section ID |
+| Material assignment | Every active element uses a reviewed material card |
+| Geometry units | Millimetres |
+| Solver force units | Newtons |
+| Free-free modal check | First six modes behave as rigid-body modes near zero frequency |
+| Supported modal check | No unintended mechanism modes |
+| Static equilibrium | Reaction-force balance within 1% |
+| Mesh refinement | Key displacement and load-path measures change by less than 5% |
+| Hand correlation | Selected benchmark results within 10% |
+| Buckling interpretation | Eigenvalue result labelled as ideal linear screening only |
+| Stress reporting | Beam stress kept separate from local joint stress claims |

downloads/asterion-fcta-v1.0-public-release/asterion-fcta-v1.0/docs/v0_3/release_manifest.md

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+# Version 0.3 Release Manifest
+
+## Package summary
+
+- Release: 0.3.0
+- Repository files before archive creation: 113
+- Uncompressed repository size: 6.7 MB
+- Primary structural nodes: 222
+- Primary beam elements: 580
+- Beam section families: 7
+- Neutral GLB geometry groups: 4
+- Neutral mesh faces: 18,560
+
+## Key deliverables
+
+- `cad/primary_structure/v0_3/neutral/asterion_v0_3_primary_structure.glb`
+- `cad/primary_structure/v0_3/neutral/asterion_v0_3_primary_structure.stl`
+- `cad/primary_structure/v0_3/neutral/asterion_v0_3_primary_structure.obj`
+- `cad/primary_structure/v0_3/nx_primary_structure_tutorial.md`
+- `analysis/ansys/v0_3/model/beam_nodes.csv`
+- `analysis/ansys/v0_3/model/beam_elements.csv`
+- `analysis/ansys/v0_3/apdl/asterion_line_model.inc`
+- `analysis/ansys/v0_3/apdl/solve_static_docking.mac`
+- `analysis/ansys/v0_3/apdl/solve_modal_free_free.mac`
+- `analysis/ansys/v0_3/apdl/solve_buckling_docking.mac`
+- `calculations/v0_3/preliminary_structural_sizing.md`
+- `calculations/v0_3/preliminary_structural_bom.csv`
+- `media/renders/v0_3_primary_structure_plan.png`
+- `media/renders/v0_3_primary_structure_front.png`
+
+## Native-file statement
+
+The release does not claim that native NX or solved ANSYS databases were created. Those require the installed proprietary applications and local execution of the supplied workflows.

downloads/asterion-fcta-v1.0-public-release/asterion-fcta-v1.0/docs/v0_3/version_0_3_release_notes.md

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+# Version 0.3 Release Notes
+
+Version 0.3 converts the Version 0.2 envelope into a first analysable primary structure. The generated structure contains 222 nodes and 580 beam elements and exports as GLB, OBJ and STL. Solver inputs include CSV tables and APDL templates for static docking, free-free modal and linear buckling demonstrations.
+
+## Main limitations
+
+- Geometry is preliminary beam/tube representation, not manufacturing detail.
+- No solved ANSYS database is included.
+- Bearings, joint stiffness, pressure shells and local contacts are simplified or absent.
+- Linear elastic isotropic aluminium is used throughout the initial line model.
+- Load cases are portfolio design cases, not certified mission or launch requirements.