UAS Fuselage Structural Parameterisation
Budget: £20 – £250 GBP
I am preparing an entry for the IMechE UAS Challenge and need a fully-parameterised fuselage model that lets me iterate geometry while keeping structural integrity at the centre of every change. The airframe will be fabricated in carbon fibre, so the model must allow material properties for typical woven prepreg laminates to be assigned quickly and adjusted as ply schedule or thickness evolves.
My priority parameter is Structural Integrity, with particular attention to:
• Impact resistance
• Load-bearing capacity
• Fatigue durability
The workflow should start in CAD (solid work ) and flow cleanly into an FEA environment such as Ansys, SimScale, or the native solver, so that I can run quick what-if studies on rib spacing, bulkhead placement, and hard-point inserts. Please keep dimensions and constraints editable from a single control sketch or design table; I want to tweak overall length, cross-sectional diameter, and skin thickness without broken references.
Deliverables
• Parametric 3D model of the fuselage with driving dimensions clearly labelled
• Material card or library entry for the selected carbon-fibre laminate
• FEA setup file showing boundary conditions and load cases relevant to the three integrity criteria above
• Short validation report (PDF) summarising assumptions, safety factors, and results for the baseline configuration
I will review completeness by rebuilding the model with new values, regenerating the mesh, and checking that all links remain live. If a quick rebuild to ±10 % fuselage length runs without errors and reports comparable stress margins, the submission will be accepted.
My priority parameter is Structural Integrity, with particular attention to:
• Impact resistance
• Load-bearing capacity
• Fatigue durability
The workflow should start in CAD (solid work ) and flow cleanly into an FEA environment such as Ansys, SimScale, or the native solver, so that I can run quick what-if studies on rib spacing, bulkhead placement, and hard-point inserts. Please keep dimensions and constraints editable from a single control sketch or design table; I want to tweak overall length, cross-sectional diameter, and skin thickness without broken references.
Deliverables
• Parametric 3D model of the fuselage with driving dimensions clearly labelled
• Material card or library entry for the selected carbon-fibre laminate
• FEA setup file showing boundary conditions and load cases relevant to the three integrity criteria above
• Short validation report (PDF) summarising assumptions, safety factors, and results for the baseline configuration
I will review completeness by rebuilding the model with new values, regenerating the mesh, and checking that all links remain live. If a quick rebuild to ±10 % fuselage length runs without errors and reports comparable stress margins, the submission will be accepted.