固体火箭发动机前封头人工脱粘层烧蚀研究

Studies on the Ablation of the Stress Release Boot in Forward Dome of Solid Rocket Motor

从理论分析的角度出发 ,通过对人工脱粘层和绝热层所构成的槽缝燃气温度场与烧蚀的耦合计算 ,得出了人工脱粘层的烧蚀规律。在计算中 ,采用了隐式差分格式及控制容积法等计算技术 ,并采用了先进的烧蚀模型。为模拟发动机静止与飞行两种不同状态 ,本文对不同宽度的槽缝人工脱粘层的烧蚀进行了计算 ,对其进行了比较。本文所采用的方法可供今后人工脱粘层的设计参考。

From the point of theoretical analysis, this dissertation provides the coupling calculation on the hot gas temperature field and ablation in the cavity between stress release boot and insulation of solid motors. Through the calculation, some law of the ablation of the stress release boot is found. In the course of calculation, implicit difference scheme and finite volume formulation are used to solve the temperature field, and an advanced model is adopted in the calculation of the ablation. To simulate the quiescence and flying status of the motor, the ablation is calculated with different cavity width. The above program in this paper has laid a theoretical foundation of the design of the stress release boot.