Abstract
Computed results of the stress-strain state of four different composite flanges for aircraft engines are presented for assigned external-load parameters, and their most heavily loaded regions are defined. The static strength of the structures is found from the stresses in the layers using the maximum-stress criterion and Hill's modified criterion. It is established that transverse tensile stresses are most critical. The service life of the flanges is estimated on the basis of the fatigue-failure criterion of the weakest link.
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Additional information
Perm' State Technical University. Translated from Mekhanika Kompozitnykh Materialov, Vol. 33, No. 3, pp. 360–369, May–June, 1997.
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Anoshkin, A.N., Tashkinov, A.A. & Gritsevich, A.M. Prediction of the bearing capacity of composite flanges for aircraft-engine casing parts. Mech Compos Mater 33, 255–262 (1997). https://doi.org/10.1007/BF02256083
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DOI: https://doi.org/10.1007/BF02256083