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Ultra-light Single-manned Aircraft Design
Project type
CAD Project
Date
2025-Present
- The structure features a fully trussed fuselage and wing skeleton made almost entirely from lightweight wood, utilizing rib-and-spar geometry for the wings and tail surfaces, reinforced with aluminum brackets and localized sheet-metal fittings at high-load joints.
- Designed as an ultra-light, single-occupant aircraft, the empty weight falls in the 230–267 lb range, placing it within FAA Part 103 ultralight performance expectations for minimal structural mass and low wing loading.
- The fuselage incorporates a simplified cockpit bay ahead of a tapered wooden truss boom extending to the empennage, with open-frame vertical and horizontal stabilizers optimized for low weight and straightforward fabric covering.
- Mid-wing configuration with exposed wooden ribs and spars designed for fabric covering and low Reynolds-number flight efficiency; wing–fuselage integration is supported by metal brackets to ensure torsional rigidity and safe load transfer.