Material behavior and properties are fundamentally important for mechanical simulation, analysis and development. The present book deal with vibration in composite aircraft wing which are using in Unmanned Aerial Vehicle (UAV). A multiple series of instrumented vibration analysis experiments, in two different conditions were performed on composite modeled aircraft wing. The simulation and analysis include natural frequencies, changes in measured mode shapes and changes in measured flexibility coefficients. Obtained results from experiments and analysis appear to provide prediction of strength and explanation of some defects and damage on composite aircraft wing. This book describes improvement of impact resistance of the modeled wing and also obtained technical results prepared data for future computational models. The critical issues for future research in the area of mechanical vibration and behavior of composite materials are also discussed.