| Dual-pulse solid rocket motor(DPSRM)is a new type of solid rocket motor(SRM)designed for the lack of energy adjustable and controllable technology in conventional SRM.Aiming at the multi-physical field coupling characteristics of the second pulse ignition transient process of the interlayer dual-pulse engine,this paper improves and designs the experimental system of cold air impact,designs and perfects the numerical calculation method of bidirectional fluid-structure coupling,studies the flow field characteristics,dynamic response characteristics of the interlayer and the mechanical response characteristics of propellant in the process of the second pulse ignition coupling.The main factors influencing the impulse ignition transient process are analyzed.(1)Aiming at the characteristics of the second pulse ignition impulse and the structure of the isolator of double pulse engine,a set of cold air impulse experimental system was improved and designed.The rapid boost process of the second pulse ignition was simulated,which provided an experimental and verifying platform for the study of the opening characteristics of the isolator.(2)The opening characteristics of radial barrier isolator were studied by cold air impact test and numerical calculation method.The effects of preset defect and boost rate on the breakdown process were compared,and the flow field characteristics and dynamic response characteristics of the separator were obtained.(3)Secondary development of ANSYS Workbench platform is carried out.Mass flow rate model of igniter,heat transfer model of propellant and propellant burning and charging model are established.A bidirectional fluid-solid coupling numerical calculation method is designed and perfected,and the numerical solution of the second pulse ignition coupling process of dual-pulse engine is realized.(4)Two-way fluid-solid coupling numerical method was used to study the ignition coupling process of the second pulse of the axial-diameter hybrid barrier dual-pulse engine.The flow field characteristics,dynamic response characteristics of the barrier and mechanical response characteristics of propellant in the transient process of the second pulse ignition were obtained,and the fluid-solid coupling characteristics in the process of the second pulse ignition were analyzed.(5)The effects of ignition charge,material properties of interlayer,location of preset defects and length of axial interlayer on the coupling process of II pulse ignition were studied.Increasing the amount of ignition charge can effectively shorten the ignition response delay of the engine;the deformation response characteristics of different barrier material properties show great differences;different structural segments with preset defects in the barrier will have a greater impact on the ignition shock process;the change of the length of the axial barrier has a certain impact on the ignition shock process,but does not show obvious regularity. |
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