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为研究双脉冲固体火箭发动机软隔板破裂和应力分布规律,设计了一种端面软隔板。对隔板作预制刻痕处理,在隔板上形成多个正方形方块。刻痕的宽度及间距取决于发动机参数,隔板破裂时产生碎片不堵住喷管。进行了二脉冲点火器试验、二脉冲点火试验、双脉冲发动机两级点火试验三个阶段的隔板破裂试验,并对双脉冲发动机隔板的受力进行仿真分析。结果表明:设计隔板在发动机工作过程中及时合理破裂,仿真所得隔板破裂位置与试验结果吻合。试验隔板破裂发生在凹腔边缘处和隔板上的圆型刻痕处,在隔板表面施加预制刻痕,隔板破裂形成的碎片基本被排出发动机,且能使隔板破裂更具有规律性。隔板破裂试验研究对隔板设计有重要的意义。
In order to study the rupture and stress distribution of the soft barrier of the double pulse solid propellant rocket engine, an end soft barrier was designed. The separator is pre-scored and a plurality of squares are formed on the separator. The width and spacing of the nicks depend on the engine parameters and the debris generated when the separator ruptures does not block the nozzle. The two-pulse ignition test, two-pulse ignition test and two-pulse engine two-stage ignition test were carried out to test the separator rupture. The stress of the two-pulse engine separator was simulated and analyzed. The results show that: the design of the diaphragm in the engine during the reasonable and timely rupture, the simulation results of the fracture position of the diaphragm and the test results. The test baffle rupture occurred at the edge of the cavity and at the circular incision on the baffle and a pre-scored notch was applied to the baffle surface. The rupture of the baffle was substantially expelled from the engine and ruptured the baffle more regularly Sex. The study of separator rupture has important significance for the design of separator.