Comparison of the Flow Field and Thrust Characteristics of Solid Rocket Motor with Conventional Nozzle and Canted Nozzle

Compared with conventional solid rocket motors (SRM) with direct nozzle, solid rocket motors with canted nozzle have unique advantages in stage separation and lateral propulsion. The complex flow field evolution and thrust changes have an important impact on the performance of solid rocket motors. In this paper, in order to explore the flow field characteristics and thrust variation law of the two different structures of the direct injection nozzle and the canted nozzle, a three-dimensional flow field model of the direct injection nozzle is established based on the CFD simulation software, and the given boundary conditions are calculated by the internal ballistic equations. Combined with the realizable k-ε two-equation model for numerical simulation, and carried out experimental research to verify the validity and accuracy of the numerical model. Then the canted nozzle model is established, and the numerical simulation is compared with the direct injection nozzle. The results show that the ballistic calculation and numerical simulation results in the direct injection nozzle are in good agreement with the experiment results, and the stable working stage of the solid rocket motor lasts longer. The canted nozzle has the similar working process and thrust characteristics of the direct injection nozzle, but there is a certain loss of mass flow and thrust. The work in this thesis has guiding significance for the design of solid rocket motors, and can provide references for the study of unstable combustion of solid rocket motors.