The most important segment of the electric arc furnace (EAF) steelmaking process is the stirring and decarburization of the molten bath during the oxidation stage, with the bath temperature typically ranging from 1550 to 1600 °C. The coherent jet is a key factor influencing the stirring and decarburization of the molten bath. The factors affecting the impact capability of coherent jets have been widely studied, including the nozzle flow parameters and arrangement methods. However, there are few studies on the combustion chamber structure of the coherent jet oxygen lance. In order to study the effect of the combustion chamber structure on the characteristics of the coherent jet, a method combining numerical simulation and combustion experiments is used to study the flow fields of the coherent jet for a combustion chamber under different length and inclination angle conditions. The results show that the flow field characteristics of the coherent jet are influenced by the length and inclination angle of the combustion chamber. Compared with the coherent jet oxygen lance without a combustion chamber, the potential core length of the main oxygen jet under the short-distance horizontal combustion chamber condition is longer, but the potential core length of the main oxygen jet with the excessively long horizontal combustion chamber is shorter. The influence of the inclination angle on the potential core length of the main oxygen jet is complex. The influence mode is different depending on the length of the combustion chamber. Finally, it is found that the combined horizontal and inclined combustion chamber can achieve the best effect on prolonging the potential core length of the main oxygen jet.

The satellite–rocket separation shock environment involves transient structural responses during spacecraft release. Although its direct influence on the main structure of the satellite is limited, it can easily cause shock-sensitive precision instruments or components to fail. Nowadays, the shock response spectrum (SRS) experiment is conducted to simulate the dynamic load environment of spacecraft. There are lots of studies on the spectral pattern of SRS. Most of the existing studies focus on the qualitative effects of the shock parameters on SRS; however, quantitative relationships between key shock parameters and SRS characteristics remain relatively limited. In this study, the air cannon-based shock experiment and numerical simulation based on ANSYS/LS-DYNA 2022R1 software are conducted to investigate the influence of shock parameters on SRS. The SRS curves are fitted to quantitatively characterize their spectral features. Massive experimental and simulation datasets are systematically processed to establish the relationship between SRSs and three key shock parameters: felt thickness, bullet length, and air source pressure. A quantitative relationship based on random forest is established to map the shock parameters to the characteristics of the SRS curves. SRS curves can be calculated based on this relationship, enhancing the efficiency of SRS calculation and reducing the need for repeated SRS experiments and simulations.