Abstract
Collisions between birds and aircrafts during the taking-off, cruising and landing phases have become an increasingly serious and catastrophic issues for aircrafts safety. Aviation standards in force require that the aircraft construction would allow the crew to conclude the flight safely after collision with 1.81 kg bird. A method for analysis of the stress-strained state of laminated airplane glazing at different operational factors is presented. The method includes a technique for strength analysis of the laminated airplane glazing at the bird impact, and a technique for analysis of superfluous pressure. The model of laminated glazing is based on the refined theory of the first-order accounting transverse shear strains, thickness reduction and normal element rotation inertia each layer. The mathematical model of pressure impulse authentically reproducing bird impact is based on the experimental researches. Theoretical results are in good agreement with experimental data that allows recommending the method for working out new airplane glazing elements.
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