Influence of thermal shock mechanism and thermal environment on concentric canister launcher

Based on the homogeneous multiphase theory and vaporization solving program of liquid water, the three-dimensional model of the gas-liquid two-phase fluid dynamics for new concentric canister launcher (CCL) self-launching system was built using the dynamic mesh technology of spring-based smoothing method and laying-based zone moving method. The reliability and validity of the three dimensional calculation of the vaporization program were verified by the experiment of injecting liquid water into the free rocket jet. Transient numerical calculation was carried out, and the influences of the water injection angle on the thermal environment of the launching system and the load characteristics of the missile were discussed. Analysis shows that obvious vaporization reaction occurred in the launch tube, in the -30 degree water injection scheme, the gas-liquid two-phase mixing was sufficient, and the transverse cooling range of the cylinder was more uniform; the overall thermal environment of the missile and launching system was improved significantly, and the goal of continuously cooling the launching system was achieved; after the water injection at the cylinder bottom, the additional thrust and the thrust of the rocket engine increased, with the decrease of the water injection quantity, and the influence of the water injection on the missile load was increasingly weaker.