The work aims to study the internal shock wave distribution of a small tail space launcher,and obtain the internal and external flow fields in the small missile launcher through numerical simulation.A three-dimensional computational model of the missile and the launcher was established in Fluent,and the gas and air domains were simulated using a multi-component transport model.The external flow field was simulated with the dynamic grid technology,and solved with the second-order up-wind scheme.The pressure distribution of the flow field inside the small launcher during the opening process and the pressure and temperature of the external flow field after the missile exited the launcher were obtained,and the results were compared with similar literature to prove their reliability.Among them,the propagation law of shock waves inside the small launcher was consistent with that of a conventional launcher,but the peak pressure of the front cover decreased significantly.This conclusion was consistent with the previous research on the influence of tail distance on the impact force on the rear cover.The small tail distance causes less reflection of the gas jet on the rear cover,resulting in a decrease in the pressure peak propagated to the front cover and a risk of failure to open the front cover.This study provides a reference for the opening technology of small launcher cover based on the shock wave.
small missile launchershock wavenumerical simulationcomputational fluidfragile covergas jet
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NSTL
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