Программный комплекс расчета течения продуктов сгорания в проточных трактах с учетом нестационарного газоприхода и нагрева конструкции ракетного двигателя М. С. Середа, К. В. Костюшин
Material type:
ArticleContent type: Текст Media type: электронный Other title: Software package for calculating the flow of combustion products in flow paths taking into account the non-stationary gas intake and heating of the rocket engine structure [Parallel title]Subject(s): программные комплексы | ракетные двигатели | продукты сгорания | вычислительные экспериментыGenre/Form: статьи в сборниках Online resources: Click here to access online
In:
Перспективы развития фундаментальных наук. Т. 3 : сборник научных трудов XVIII Международной конференции студентов, аспирантов и молодых ученых, 27–30 апреля 2021 г Т. 3 : Математика. С. 79-81Abstract: The article presents a program designed for mathematical modeling of non-stationary processes in the flow part of a solid-fuel rocket engine and heating of the engine structure by combustion products. The solution of this problem is an important stage in the design of rocket engines. Of great interest to this work is its main goal: the development of a universal domestic application that allows you to simulate gas-dynamic and thermophysical processes with high-quality output results. The development of the software package was carried out in the C# language in the environment Microsoft Visual Studio 2019. The construction of a rich graphical interface of the software package is implemented using WPF (Windows Presentation Foundation) technology, using the declarative markup language XAML. Mathematical modeling of non-stationary gas-dynamic processes in the flow paths of a rocket engine is carried out by methods based on the solution of the complete Euler equations. Modeling of the heating process of the rocket engine structure is described by the equation of thermal conductivity.
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The article presents a program designed for mathematical modeling of non-stationary processes in the flow part of a solid-fuel rocket engine and heating of the engine structure by combustion products. The solution of this problem is an important stage in the design of rocket engines. Of great interest to this work is its main goal: the development of a universal domestic application that allows you to simulate gas-dynamic and thermophysical processes with high-quality output results. The development of the software package was carried out in the C# language in the environment Microsoft Visual Studio 2019. The construction of a rich graphical interface of the software package is implemented using WPF (Windows Presentation Foundation) technology, using the declarative markup language XAML. Mathematical modeling of non-stationary gas-dynamic processes in the flow paths of a rocket engine is carried out by methods based on the solution of the complete Euler equations. Modeling of the heating process of the rocket engine structure is described by the equation of thermal conductivity.
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