Abstract The equations of the mathematical model are solved in terms of special functions. The results for the design scheme of the aircraft forebody are obtained with a guaranteed accuracy by the stable method of functional normalization.
The Stressed State of a Stiffened Conical Shell with Thermal Protective Coating with Temperature-Dependent Properties
Russian Aeronautics ; 61 , 2 ; 156-164
2018-04-01
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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