固体火箭发动机喷管的结构设计与性能仿真

摘要

The nozzle is an important part of solid rocket motor thrust vector control system,efficient nozzle design is crucial to the per-formance of the engine. Application of structural design software CATIA V5 to design the motion mechanism of a spherical joint flexible solid rocket engine nozzle,the nozzle parts,materials and design parameters are determined for nozzle control mechanism,analyzing the mechanism motion simulation of spherical joint. Flexible nozzle of mechanism motion simulation is conducted by ANSYS WORKBENCH software. Through model simplifying,contact setting,adding load and constraint,selecting the appropriate material modeling,establish the finite element model of the nozzle. Ensure the nozzle can move according to design requirements in two mutually perpendicular plane,and not move in the axial direction. Established the mechanical properties simulation model of the nozzle,carryied on the modal analysis and statics analysis,obtained the deformation and stress conditions of nozzle in a certain pressure,ensure that the mechanical properties of the nozzle can meet the design requirements.%喷管是固体火箭发动机推力向量控制系统的重要组成部分，高效能的喷管设计对发动机的性能至关重要。应用结构设计软件CATIA V5设计了某球形接头柔性固体火箭发动机喷管的运动机构，确定了其喷管的零部件组成、材料和设计参数，对喷管控制机构进行了机构运动仿真分析；采用ANSYS Workbench软件对球形接头柔性喷管进行了机构运动仿真，通过模型简化、接触设置、约束和载荷添加，选取适当材料建模，建立了喷管的有限元模型。保证喷管能够在两个相互垂直的平面内按设计要求进行运动，并且在轴向没有窜动；建立了喷管的力学性能仿真模型，进行了模态分析和静力学分析，得到了在一定压力之下喷管的变形和应力情况，确保喷管的力学性能达到设计要求。