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Numerical simulation of stress-strain state of the output unit of SPRE during nozzle separation

Mormul R.V., Glumov Y.I., Egorov M.Y., Fedulov V.S.

Abstract


Parameters of stress-strain state of the output (nozzle) unit of the progressive solid-propellant rocket engine (SPRE) are determined for impact loads during nozzle separation by means of discrete mass approach. Dynamics of elastic wave processes is investigated for direct and inverse impact vibrodynamic loading of the nozzle. Numerical experiment allowed obtaining assessment of distribution of minimal strength safety factors of the SPRE output unit structure.

Keywords


solid propellant rocket motor; mass-loss; heat mass transfer; composites; thermal barrier coating; nozzle block; stress-strain state; conductivity; numerical modeling; method of finite elements

References References

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Copyright (c) 2015 Роман Викторович Мормуль, Юрий Васильевич Глумов, Михаил Юрьевич Егоров, Владимир Сергеевич Федулов

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This work is licensed under a Creative Commons Attribution 4.0 International License.

ISSN 1813-7911