化学反应热对二次流矢量影响研究

Thrust vector control (TVC) is a key technology for controlling the thrust magnitude and direction of solid rocket engines. In this paper, the effect of heat generated by the reaction between the primary flow and the injection in the nozzle on the secondary injection thrust vector control effect is studied. The vortex dissipation conceptual model (EDC) is used to establish a chemical reaction model through the total package reaction. The reaction between the primary flow reducing gas and the oxidizing injection is numerically calculated and compared with the non-reaction conditions. Applying the Euler-Eulerian gas-liquid two-phase flow model-discrete model, the droplet motion equation and the energy equation are coupled under the assumption of the single droplet evaporation model to solve the vaporization and oxidation mixed reaction process of the primary flow gas and the secondary droplet. Under the (condition of small mass flow rate ratio, the side control force of the reaction conditions is increased by 10. 5% and the thrust vector angle is increased by 10. 8% due to the heat generation of the oxidation reaction. When the droplet diameter is 40〜60 μm, the vector control effect is optimal, Because the droplet temperature range is limited, it will not have a significant effect on the vector control effect; the injection speed has no significant effect on the vector control effect. Compared with the gas phase injection system, the liquid phase system has a negative effect on the thrust vector control effect, the thrust vector angle is reduced by 3%〜5%. Therefore, the application of liquid phase systems in engineering applications is more appropriate.