Abstract: Investigated the factors which influence the propagation of the debond in the propellant with the liner used in a solid rocket motor under burning condition. A lot of combustion experiments were conducted for the sample with a precut debond and the combustion process was measured by the X ray real time radiography system (RTR). According to the properties of the various materials used in the sample, the states of stress and strain of the various parts in the sample with debond were computed respectively by the viscoelastic and linear elastic finite element method (FEM). The possibility of the debond propagation was predicted by the J integral fracture criterion. Theoretical analysis and experiment results prove that the chamber pressurization rate, the debond dimension and the boundary condition have strong effects on the propagation of the debond. These results will have certain value for formulating the criterion of the charge failure.

Key words: Solid propellant rocket engine;Propellant combustion;Liner;Debond;Finite element method

摘要： 研究了固体火箭发动机推进剂与包覆层界面脱粘在燃烧条件下扩展的影响因素。对含有预制脱粘面的试件进行了大量的燃烧试验 ,用X射线实时成像系统记录了燃烧过程 ;根据组成试件的不同材料特性 ,分别用粘弹性和线弹性有限元方法计算了试件在燃烧过程中的应力应变状态 ,并利用修正后的J积分法对脱粘面扩展的可能性进行了预估。理论分析和试验结果均表明 :燃烧室增压速率、脱粘面尺寸、边界条件等因素对脱粘面扩展均有较强的影响。该研究结果对制定固体火箭发动机装药失效判据有一定参考价值。

关键词: 固体推进剂火箭发动机;推进剂燃烧;衬里;脱粘;有限元法