Abstract
This paper describes the solid-propellant rocket engine structure, including casing and filler. The gas flows within the filler channel. Based on numerical conjugate problem solution, non-stationary stress-strain states of the casing and filler were determined, as well as gas flow parameters in the channel. Within the conjugate problem, the engine is considered to be a two-component system: deformable solid body and gas. Conjugate problem solution involves specific subtasks related to the conjugation conditions, where Lagrangian approach is used for subtasks of solid body. Euler approach is used for subtasks of gas, implying immovable boundary of the computational domain on the integration time step. Numerical methods are applied in solving subtasks. Specific feature of conjugate problem solution algorithm is discrete movable domain boundary interface.
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