一种固体火箭发动机燃烧室压强计算方法

摘要

为了提高零维燃烧室平衡压强公式在金属含量大于15%的固体火箭发动机中压强估算的准确度,用两相内流场数值计算的方法求解不同情况下的发动机燃烧室压强,对铝含量为16%~18%的HTPB推进剂发动机和铝含量为40%~50%的铝冰发动机进行数值计算、拟合和修正,得到燃烧室零维压强修正计算式,得到铝冰发动机燃烧室压强修正公式,计算结果精度提高.结果证明该方法用于燃烧室压强计算时相比未修正的零维压强计算公式结果更准确,相比内流场数值计算的方法更简单实用.%To improve the pressure prediction accuracy of the 0-D steady pressure formula used in solid rocket mo-tors(SRMs)with metal concentration higher than 15%, the two-phase numerical calculation of the internal flow-field in SRM was implemented.Using this method,the chamber pressures under different inlet conditions were cal-culated.The proposed method was used in the HTPB propellant SRMs with aluminum concentration varying from 16% to 18%and in aluminum-ice SRMs with aluminum concentration varying from 40%to 50%.Using numerical calculation,data fitting, and formula correction, the revised calculation formula on 0-D pressure intensity of the firebox and the revised pressure intensity formula on the firebox of aluminum-ice SRMs were obtained,and the pre-cision of the calculation results was improved.The results showed that the revised formula was more accurate than the uncorrected formula;compared with the method used to calculate the internal flow-field,the proposed method was simpler and more practical.