Impact of Shock Waves on Safe Exit of Vehicle Nose Cap During Thermal Launch Process

In response to the impact of shock waves generated under the action of the gas flow field on the safe exit of the rocket-projected vehicle nose cap during the thermal launch process of a concentric canister, a numerical simulation of the ignition and launch process was carried out using computational fluid dynamics (CFD) software. The propagation laws of shock waves and gas generated by the solid rocket motor in the concentric canister were analyzed in detail, and the force variation curve of the nose cap under the action of shock waves was obtained. The force mechanism of the nose cap under the action of shock waves was revealed. Combined with test data, the force process of the nose cap under the action of shock waves was further verified, and its force characteristic of “first compression, then pulling, and then re-compression” was clarified. The research results clearly illustrate the force impact mechanism of shock waves on the nose cap during the thermal launch process of concentric canister and can provide a theoretical basis and reference for the safety design of the vehicle nose cap’s exit.