| This engineering project has been prepared with the intention to present the structural analysis of an aircraft multi-layered (composite) windshield and evaluate its structural integrity under 12.00 psi load. This load is due to differential pressure between the cabin and outside atmospheric pressure, when the airplane is pressurized at the altitude of 30,000 feet.; The stress analysis consisted of the numerical and experimental determination of the deformations and stresses resulting from the applied load. The aircraft windshield was computer-modeled by finite element techniques utilizing the Finite Element program, COSMOS/M, developed by a local "structural research and analysis" firm.; The experimental results then were used to authenticate conclusions obtained from the numerical method. |
