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针对固体火箭发动机药柱裂纹扩展机理及其危险性研究的复杂性,选择发动机工作过程中裂纹失稳扩展作为发动机判废的标准,采用实验测量和数值仿真的方法,确定出了不同贮存期某型固体火箭发动机在点火发射过程中,其药柱星角处横向贯穿楔形裂纹发生失稳扩展的临界深度,应用数理统计分析,给出了含该型裂纹的发动机安全工作的裂纹深度阈值曲线,从而为制订发动机的判废标准提供理论依据。
Aiming at the complexity of crack propagation mechanism of solid rocket motor and the study of its danger, the crack instability expansion in engine working process is selected as the criterion of engine abandonment and rejection. By means of experimental measurement and numerical simulation, Type solid rocket motor, the critical depth at which the wedge-shaped crack transversely penetrates through the star corner of the solid propellant rocket during the ignition and launching process spreads instably. Based on mathematical statistics, the threshold crack depth curve of the engine with this type of crack is given. Which will provide the theoretical basis for formulating the standard of sentenced and abolished engine.