Study On The Ignition Process Characteristic Of Dual-pulse Solid Rocket Motor With Soft Pulse Separation Device

The double pulse solid rocket motor improves the combat capability of the missile,strengthens the variability of the trajectory,and resolves the shortcomings that the thrust can not be changed during the ignition process of solid rocket motor.Dual pulse motor(DPM)with soft pulse separation device(PSD)is one of the important development directions of dual pulse motor at present due to its advantages of easy to make and low negative mass.In this paper,a set of high-pressure air impact test system is designed and built for the ? pulse ignition process of DPM.The simulation of the ? pulse ignition process of DPM is carried out by ANSYSY Workbench software.The effects of the propellant combustion,the mass flow rate of the igniter and the PSD material on the ? pulse ignition process are analyzed.The main contents of this paper are as follows:(1)According to the characteristics of the ? pulse ignition process of DPM with soft PSD,a set of high-pressure air impact test system is designed and built.The impact of the initial pressure peak of the ? pulse ignition process on the soft PSD was simulated by the high-pressure air impact test,and the pressure of different monitoring points and the rupture time of the soft PSD during the test were measured.The composition and function of the gas storage starting system,the test engine system and the data measurement and acquisition system of high-pressure air impact test system are introduced.The deformation and failure process of the soft PSD under the impact of high-pressure air is recorded by high-speed camera.(2)The fluid and structure domain is transmitted through the System Coupling module of ANSYS Workbench software,and a two-way fluid-structure coupling model of the ? pulse ignition process process is established.Through the high-pressure air impact test,it is found that there are no fragment in the soft PSD under the impact of high-pressure air,which will affect the working state of the DPM.The rupture pressure and time of the soft PSD under the condition of slow build-up pressure and high-pressure air impact are compared.The experimental data and numerical simulation results are compared to verify the fluid-structure coupling numerical simulation method.(3)Based on the FLUENT software,the igniter boundary and propellant combustion process is secondary exploration,and a two-way fluid-structure coupling calculation model is established.The ? pulse ignition process of DPM with soft PSD is used for simulation study.The characteristics of internal flow field,pressure impact and mechanical properties of soft PSD are analyzed.According to the surface path of the soft PSD,the ? pulse ignition process is divided into three stages.(4)The effects of propellant combustion,the mass flow rate of the igniter and the soft PSD material on the ? pulse ignition process are studied.In the absence of propellant combustion,the impact time of gas and the terminal wall of the fluid domain is increases and the rupture time of the soft PSD is increases,and when the soft PSD breaks,the max-pressure in the fluid domain decreases;With the increase of the mass flow rate of the igniter,the time of first ignition of propellant and the rupture time of the soft PSD are diminishes,and the max-pressure in the fluid field increases;The soft PSD material has a significant influence on the total deformation of the soft PSD,but it has no obvious effect on the rupture time of the soft PSD and the max-pressure of the fluid domain..