固体发动机飞行环境下内绝热层安全余量分析

Analysis on Safe Margin of SRM Internal Insulation in Flying Environment

一种战术导弹固体火箭发动机地面和飞行试验结果表明，它在飞行加速过程中（α为8g），前封头及圆柱段前段的烧蚀率分别为静止试验烧蚀率的1．26和1．16倍。在此基础上，提出了这种发动机燃烧室内绝热层设计的经验公式，并应用于一种结构及材料相似的新型发动机绝热层设计中，预估了其飞行环境下内绝热层安全余量。

The tested results of solid rocket motor of a tactical missile show that the ablative rates of fore dome and front part of the cylinder of chamber insulation when the motor is arcelerated at 8g are respectively 1. 26 and 1. 16 times of that when it is in static firing. Based on the results, an empiric formula for the motor chamber insulation design is gained and applied to the insulation design of a new type of the motor which is similar to structure and matertal to above-mentioned motor. The safe margin of the new motor in flying environment is estimated.