Development of the numerical model for evaluating the temperature field and thermal stresses in structural elements of aircrafts
Abstract
An approximate method for estimating the thermal stresses of the aircraft key components of the simple geometric shape (the edges of the hull and wings, the nose fairing) has been developed. The mathematical model of such estimates is based on the solution of the quasi-static thermoelasticity problem. The solution is evaluated in the area with curvilinear boundaries, and the shape of these boundaries changes under the influence of thermal and mechanical loads. Thus the computational domain is transformed to an area where the regular Cartesian (structured) grid can be introduced. The initial validation and verification of the developed numerical methodology was carried out. Numerical modeling of temperature fields and thermal stresses in the simplest components of aircraft structures (cylinder blunted over the sphere and the shell) is performed.
- Publication:
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Journal of Physics Conference Series
- Pub Date:
- November 2017
- DOI:
- 10.1088/1742-6596/891/1/012311
- Bibcode:
- 2017JPhCS.891a2311S