底排-火箭复合增程弹火箭助推发动机喷管设计研究

Study on the Nozzle of the Rocket Assisted Engine of BB/Rocket HE Shell

针对底排-火箭复合增程榴弹,进行了助推火箭发动机喷管设计。依据喷管的工作条件进行了喷管型面设计、喷管热防护设计,分析了喷喉比对推力的影响。结果表明在喷喉尺寸固定且在喷口强度允许的条件下,喷口直径越大越有利于提高火箭发动机的推力。经射击试验证明文中所述对增程弹火箭助推发动机喷管设计具有一定的指导意义。

The design of the nozzle of the rocket assisted engine with the base bleed compound extended range shrapnel is introduced in this paper. The design of cone contour and hot-defend measure of the nozzle according as job-qualification of the nozzle, analyzing the influence of power with the change of the ratio of the throat. The result show that the bigger of the diameter the higher of the assisted power of the rocket engine with the dimension of the throat is constant and the permit of the spout intensity, It＇s indicated that the design of the nozzle of the rocket assisted engine is to direction advantage in engineering by the experiment.