The current state of the aerospace industry shows that increased attention is being paid to the problem of creating super- and hypersonic aircraft. With the increase in heating (due to high flight speeds), the number of factors influencing the aircraft as a whole and its structures grows as well. The problem of studying the rigidity characteristics of aircraft structures under temperature loadi has become especially relevant. In particular, the identification of elasticity parameters and strain diagrams of materials is currently an obligatory element and the most complex stage in the implementation of a number of applied projects. These strength properties of materials of elements of real thin-walled structures may differ from the properties of prototypes due to the idealization of complex conditions of fastening, loading, drop in mechanical characteristics and redistribution of forces from temperature load. The solution to this problem can be presented in the form of an optimization problem, where optimal control corresponds to the minimum of the residual objective function. The problem of optimal control in this problem is complicated by the fact that the search for an optimal solution must be performed on discrete sets of parameters, which should include the physical and geometric characteristics of structures. An adequate and prompt solution to this problem creates the necessary conditions for the effective practical use of mathematical methods and an effective design model, as well as computational efficiency in the modeling of thin-walled structures in identification problems, which are of exceptional importance for the further development of analysis techniques and justification of a rational model.
Problems of Identification of Heat-Loaded Thin-Walled Aircraft Structures
Russ. Aeronaut.
Russian Aeronautics ; 66 , Suppl 1 ; S1-S56
2023-12-01
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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