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建立了立式旋转试车台,研究了高过载对固体火箭发动机性能的影响。通过地面静止及不同过载(15gn,15gn;35gn,15gn)条件下点火对比试验,获得固体火箭发动机在不同过载条件下内弹道性能以及绝热层和喉衬的烧蚀规律。试验表明,随着过载增加,发动机压强增大、工作时间缩短;横向与轴向的组合过载恶化了烧蚀环境,使喉衬出现偏心烧蚀。
A vertical rotating test bench was established to study the effect of high overload on the performance of a solid rocket motor. Through the contrast test of ignition at ground static and different overloads (15gn, 15gn; 35gn, 15gn), the internal ballistic performance of the solid rocket motor under different overload conditions and the ablation rules of the thermal insulation layer and the throat lining were obtained. Experiments show that with the increase of overload, the engine pressure increases and the working time shortens. The combination of transverse and axial overload deteriorates the ablation environment and induces eccentric ablation of the throat lining.