Optimization Design And Working Process Simulation Of Dual-Pulse Solid Rocket Motor

In response to the development needs of efficient destruction of combat weapons,the development of a verification bomb based on load-bearing-destruction materials provides new technical support for the leapfrog development of China’s efficient destruction capability.The development and design of a release energy destructive missile can greatly improve military power.The dual-pulse solid rocket motor has a very important position as a missile power unit.This paper takes the design of a dual-pulse solid rocket motor as the research object.Firstly,the internal and external ballistic calculation model of the motor is established,the general process of optimization design is analyzed,the joint optimization platform for the integration of internal and external ballistic of the motor is built,and the sequence approximation optimization algorithm is adopted to complete the optimization design of the dual-pulse solid rocket motor.Two simple "ejection rod" pulse isolators for pulse motor have been designed.One is a single-hole plug plate and the other is a four-hole plug plate with a corresponding plug designed to fit the plug plate.The plug plate is made of tungsten-impregnated copper and the plug is made of high strength engineering plastic polyphenylene ether.The finite element simulation analysis of the designed pulse separation device shows that the pulse separation device designed in this paper is reasonable.A numerical simulation of the II pulse ignition process before the opening of the interstage bore was carried out.The working process of II pulse ignition is briefly analysed,igniter mass flow rate model and propellant combustion addition model are established and written in user-defined functions,the flow field characteristics within the II pulse ignition process are calculated,the flow field high pressure area change law and propellant surface combustion law are analysed;the influence of different igniter mass flow rates on the propellant ignition process is compared and analysed.A three-dimensional numerical simulation of the motion of the plug in the Ⅰ pulse combustion chamber when the interstage hole is opened after the Ⅱ pulse ignition is carried out.The implementation process of the overlapping mesh technique is introduced,and the numerical calculation model of the plug motion is established,and the three-dimensional non-constant compressible N-S equation described by an arbitrary Lagrangian Euler is used to solve the calculation.The results show that the plug basically moves along the central axis of the Ⅰ pulse combustion chamber without rotation at a starting pressure of 1.5 MPa in the interstage hole;the plug first accelerates and then moves at a uniform speed in the combustion chamber,and the attitude of the plug motion is different at different starting pressures,but the flow field changes in the Ⅰpulse combustion chamber are basically the same.The results of this paper provide a method for the initial design of a double-pulse solid rocket motor,as well as a reference for the structural design of the pulse separation device and the simulation of the operating process.