Abstract
In order to achieve the thermal structural integrity analysis of the solid rocket motor nozzle accurately and efficiently, the multifield (flow-thermal-mechanical) coupled numerical investigation was carried out based on the mesh-based parallel code coupled interface. The numerical simulation process and finite element model of the coupled algorithm and engineering algorithm were obtained, while the physical model was simplified appropriately. The coupled interface parameters, internal flow field, temperature field, and stress field of the coupled algorithm were compared with the engineering algorithm results, and the effectiveness and accuracy of the numerical simulation were validated. The numerical investigations shown that both the temperature field and stress field obtained by the coupled algorithm were slightly lower than which obtained by the engineering algorithm. These were considered to be impacted by the Bartz empirical formula and the one-dimensional isentropic flow assumption. Further experimental investigations shown that the exterior surface temperature and strain of the nozzle throat obtained by the coupled algorithm were much closer to the experimental results, which further verified the accuracy of the coupled algorithm.
Highlights
After the ignition of the solid rocket motor, the hightemperature and high-pressure gas generated from the propellant burning surface flow out through the nozzle
The results show that the temperature field and stress field obtained by the coupled algorithm are slightly lower than the engineering algorithm, which is considered to be impacted by the Bartz empirical formula and the one-dimensional isentropic flow assumption
The potential reason is that there are some errors in the calculation of convective heat transfer coefficient by Bartz formula in the engineering algorithm
Summary
After the ignition of the solid rocket motor, the hightemperature and high-pressure gas generated from the propellant burning surface flow out through the nozzle. In reference [3], the coupling simulation of heat transfer and transient temperature of the rocket nozzle wall is carried out. In order to solve the flow field and obtain the wall temperature distributions, numerical models have been developed incorporating both solid and fluid regions in reference [5]. To simulate the fluid field and wall temperature distribution, numerical models have been developed considering both solid and fluid regions in reference [8]. In order to estimate the heat protection performance and obtain the temperature load for erosion calculation and structural stress analysis, temperature numerical simulation of the composite nozzle thermostructure was implemented by the Fluent CFD software using the fluid-structure coupled method in reference [9]. 1. roat insert 2. ermal insulation in back wall 3. ermal insulation in convergent section
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