Analysis And Study Of Dynamic Thrust Vector System Of Multi Field Coupling

Solid rocket engine is a device that uses the reaction principle to provide thrust, Itsprinciple is that the gas ejects from the opposite direction of engine running by lightingits own energy and refrigerant to give the engine a huge forward thrust. Nozzle is one ofthe most important components of the solid rocket motor, it can provide controlled axialand lateral flight thrust for the solid rocket motor by gas to ensure aircraft’s stability, runalong the provision ballistic or take the maneuvering flight.So the performance of nozzledirectly determines the level and life of the engine. Because of the strong heat flux whichproduced in the course of working, lots of ablation and erosion impact to the nozzle andthe inner wall surface. What’s more, the members is also under stress.Therefore,researching on thermal effect of nozzle work and analyzing fluid-solid-heat couplingfield has become the guarantee elements which must be considered at the normal work ofnozzle.On the basis of the designing parameters of solid rocket motor of the SixthAcademy ofAerospace Science belonging to China aerospace science and industry group,the paper uses the Solid works, the3D drawing software, to establish thethree-dimensional geometric model of axisymmetric thrust vector nozzle preliminary,analyzes the movement of key parts, introduces the coupling field theory and takes thenumerical analysis of each field coupling process. At the same time, the paper analyzesthe fluid-solid-heat coupling field of the thrust vectoring nozzle of solid rocket motorwith Ansysworkbench. Calculation results show that the dynamic performance of solidrocket motor nozzle is good, meanwhile, the structure is reasonable. These are the basisof the development of motor axis swing TVC system in mechanical solid rocket. Themain research is:First of all, the paper uses the Solid works to establish the three-dimensionalgeometric model of axisymmetric thrust vector nozzle preliminary, analyzes themovement of key parts and expounds the convergent flap of key parts, expansionadjusting sheet, sealing motion and control loop.Secondly, on the basis of flow, solid, hot control equation and flow-solid-heatcoupling theory, analyzing the transfer numerical of flow-solid, the varying coupling numerical of flow-solid and the coupling numerical of flow-solid heat, the data is thebasis of the finite element analysis.Finally, along the flow analysis, the paper get the transient distribution regular ofpressure field and temperature field. According to using the temperature result to forcethe temperature field to get the temperature boundary condition, using the stress result toforce the members to get the stress boundary condition, the paper analyzes thefluid-solid-heat coupling field of the thrust vectoring nozzle of solid rocket motor.