固体发动机前封头绝热层在加速度下烧蚀计算

Ablation Calculation of Solid Rocket Motor Forward Dome Insulation during Flight Conditions

对固体火箭发动机前封头NBR绝热层在飞行加速庆作用下的烧蚀机理与烧蚀模型进行了研究，建立了固体火箭发动机前封头绝热层在飞行加速度作用下炭化烧蚀特性预示方法，对烧蚀试验发动机中的前封头绝热层模拟试件在不同加速度下的烧蚀特性进行了计算，计算结果和模拟烧蚀试验结果具有较好的一致性。

The ablation mechanism and model of solid rocket motor forward dome NBR insulation in flight acceleration conditions are researched. The predication method of charring ablation characteristics of solid rocket motor forward dome insulation during flight conditions is established. For different flight accelerations, the charring ablation characterisics of forward dome insulation test samples in ablation test motor are calculated. The calculated results are in good agreement with the data obtained in the analog ablation tests.