The thesis presents a static mechanical numerical analysis of a composite aircraft wing of a radio-controlled model aircraft, built for Design/Build/Fly (DBF) competition, using Ansys software environment. The wing is designed as a sandwich construction out of carbon fibre and fibreglass with epoxy resin. Telemetry data recording loads experienced by the aircraft was obtained using accelerometer during test flights. Based on the collected data, Anderson method was used to calculate lift distribution across wingspan. Lift distribution along chord line was obtained using XFOIL software environment where pressure distribution was calculated. Calculated lift was applied to a statical numerical model of the aircraft wing and displacement and stress in its segments were analysed. Structural integrity of the wing was checked using composite failure criteria. A test wing was constructed and a three point bending test of the test wing was performed to evaluate its strength. Measured displacements during the test were compared to numerically calculated displacements of a test wing at various loads. Finally, recommendations on building an improved aircraft wing were given based on another numerical analysis.
|
