Модель Ізінга для опису магнітних властивостей елементів системи керування авіаційним двигуном

The creation of competitive engines is impossible without the development and implementation of new materials and design and technological solutions. At present, in the engines, nickel alloys obtained by directional crystallization are widely used, including monocrystalline, granular alloys. The use of various composite materials, permanent joints from dissimilar materials is constantly expanding, extensive research is being carried out to create a structure from monolithic ceramics and intermetallic compounds. The successful introduction of unconventional materials is impossible without a thorough study of their structural strength, magnetic properties, features of deformation, and destruction, taking into account the specifics of these materials when developing the design and manufacturing technology of a part or engine unit. The article discusses a software package for the optimal design of control system elements for aircraft gas turbine engines using a description of their magnetic properties. Due to the modular structure of the optimization program, various optimization procedures and calculation programs can be used. It was determined that, for the Ising model, the formation of domains with a given spread of spins at a temperature T and a vector of magnetic induction B is calculated array element using a random number generator. The number of tests L depends on the size of the sample. In the Ising model, all parts of the N*N system are contenders for testing. So, Step corresponds to the number of Monte Carlo steps. Since the parts are selected once on average, it is possible to select one particle several times or not to select it at all. Therefore, the Step value should be significantly greater than one. For a convenient implementation of a certain model, its application with a graphical magnetization interface with a different number of iterations has been considered. When executing the command file, the following should be performed: building a geometric model, building a finite element mesh, applying loads, calculating the stress-strain state (SSS), displaying the results.