Modeling and Calculating the Probability of Failure-Free Operation of a Liquid Low-Thrust Rocket Engine by Temperature Margin

This article deals with the problems of modeling and calculating the probability of failure-free operation of a liquid low-thrust rocket engine using the one-dimensional load — strength reliability model. The design temperature of the combustion chamber hot wall and the maximum temperature permissible for the used structural material are selected as the parameters of the model. Using the results of modeling the thermal state of a chamber made of niobium alloy coated with MoSi₂, the probability of failure-free operation of the liquid rocket with regard to the temperature margin is calculated. The results obtained show high reliability of the engine with a deflector centrifugal mixing scheme for tetroxide components and unsymmetrical dimethylhydrazine. The probability values of failure-free operation are determined, corresponding to the values of 0.99…0.999.

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