【摘要】 根据不同推进剂及目前热防护材料的性能特点,采用了一种组合药柱的新方法,用来降低喷管内表面的温度和烧蚀率。该方法的主要设计思路是将药柱形式分为前后两段,靠近发动机头部段使用高能推进剂,靠近喷管段使用低燃温推进剂。低燃温推进剂占总推进剂质量百分比的很少一部分。使用这样的组合药柱形式,低燃温推进剂燃烧产生的气体会在喷管内表面形成一层低温帘幕,从而降低喷管内表面的温度和烧蚀率,使高能推进剂在固体火箭发动机设计上得到应用,并有助于提高发动机的质量比。更多还原

【Abstract】 Based on characteristics of different propellants and thermal protection materials,a combined propellant grain design method was put forward to reduce the inner surface temperature and erosion rate of nozzle.The main design idea is that the whole propellant grain can be divided into two sections;high-energy propellant is loaded on the motor head section,and low-burning temperature propellant is loaded near nozzle section.Low-burning temperature propellant is only in small percentage of the whole propellant.Through application of the combined propellant grain,a thin-layer low-temperature gases curtain on the inner surface of nozzle produced by low-burning temperature propellant is formed to reduce the inner surface temperature and ablation rate of nozzle.In this way,the high-energy propellant can be successfully applied to the design of SRM,which will contribute to improving the increase of mass fraction of the motor.更多还原