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Stress-strain analysis of a solid-propellant rocket engine is the subject of this study. A chosen material is selected in order to ensure its maximum strength at minimum weight of the engine. The airframe of the rocket engine is a thin-walled structure, which consists of cylindrical and spherical parts. The dynamic behaviour analysis of this thin-walled structure under the action of impact loads is performed. The anisotropic material model and dynamic properties of the shell material are taken into consideration to solve the underlying problem.

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Modern rocketry widely employs a method of gasodynamic impulse destruction of bondings which may occur at high variety of temperatures. To design fasteners correctly it is necessary to have the ability to calculate fastener's destruction time at a given pressure. Numerical research is an expedient approach to this problem. A mathematical model of a high-speed deformation and failure in fastening elements of special rocket structures due to gasodynamic wave-impact impulse loading is developed. A technique for numerical analysis of the deformation of fasteners and failure duration is proposed. To perform such analysis a set of factors such as: static stress-strain state due to assembling; thermo-elastic deformation of fasteners due to environment temperature; high-speed dynamical elastic-plastic failure of fastening elements are taken into consideration. The failure model due to the plastic flow considers dynamical material properties. As a criterion of failure maximum plastic deformation is chosen. The technique is implemented for several types of fasteners. Numerical simulation using finite elements method is conducted. The results of the numerical research are well-correlated with experimental data.

Safe separation of the rocket payload fairing is one of the most important factors that affect the success of a flight mission. In recent years, composite materials instead of aluminum alloys are widely used in rocketry. Such materials must satisfy a number of requirements that include the certainty of a local failure due to the action of a cumulative charge of the given power. To analyze this process numerical research is an advisable approach. The model of a composite rocket fairing separating due to the action of a cumulative charge has been developed. The properties of the composite material have been modeled based on the averaged characteristics obtained experimentally. The cumulative charge has been modeled by impulse loading having parameters adequate to the charge type. The time of action of the impulse, maximum pressure and width of the loading area are determined from the charge properties and geometry. The rocket fairing is considered as a composite shell composed of conical and cylindrical parts. A technique for 3D numerical analysis of the dynamic strength and structural failure has been developed. The mathematical model of the structure deformation and failure takes into account the dynamical properties of the material. The maximum plastic deformation is used as a failure criterion. The results of numerical simulation for the typical rocket payload fairing are presented.