考虑界面损伤的立式贮存药柱结构完整性研究

为了进一步结合实际分析固体火箭发动机药柱在立式贮存条件下的结构完整性，考虑推进剂/衬层界面损伤模式在复杂应力条件下具有多样性。以某型固体火箭发动机为例，与常规将衬层设置为粘接单元相比，模型在推进剂与绝热层之间设置粘接接触。对固体火箭发动机在立式贮存环境时经历固化降温、充气内压和重力载荷联合作用下有无界面损伤时的发动机进行仿真分析。结果表明:界面损伤的存在导致推进剂/绝热层界面这个薄弱环节更危险；该型固体火箭发动机药柱在充气内压增大过程中在人工脱粘层根部部位应力呈先增大后减小趋势；在充气内压达到0.085MPa之前，推进剂与绝热层之间考虑界面损伤时，推进剂在垂直于轴向的靠近人工脱粘层根部部分更容易损伤，之后则推进剂垂直于轴向的初始点更容易损伤。该结论可以为固体火箭发动机结构完整性精确仿真提供一定的指导。

Structural Integrity of Vertical Storage Grain by Considering Interface Damage

In order to analyze the structural integrity of solid rocket motor grains under vertical storage conditions, it is considered that the damage modes of propellant/liner interface are diverse with complex stress. Taking a certain type of solid rocket motor as an example, instead of setting the liner as cohesive element, a cohesive contact is provided between the propellant and the insulation. The solid rocket motor undergoes solidification and cooling, internal inflation pressure and gravity load in a vertical storage environment in simulation. The results show that the existence of interface damage makes the propellant/insulation interface more dangerous. The stress of the grain nearing the root of the artificial debonding layer increases first and then decreases during increasing the internal pressure. Before the internal pressure reaches 0.085MPa, when considering the interface damage between the insulation layers, the propellant is more likely to be damaged at the zone nearing the root of the artificial debonding layer. And then the initial point of the propellant perpendicular to the axis is more likely to be damaged. This conclusion can provide certain guidance for the accurate simulation of the structural integrity of the solid rocket motor.