固体发动机燃速相关性  

Burning rate correlation of solid rocket motors

作　　者：刘中兵[1] 汪亮[1] 胡春波[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《推进技术》2008年第6期716-720,共5页Journal of Propulsion Technology

摘　　要：分别采用温度与压强相分离的一元回归分析方法和温度与压强相耦合的二元回归分析方法,对同一工艺条件下大量的药条燃速、Φ=127 mm发动机燃速和全尺寸发动机燃速进行了统计和回归分析,得出了上述三种燃速之间的回归方程。结果表明该方法具有足够的精度。Using linear regression method with temperature and pressure separated and duple linear regression method with temperature and pressure coupling respectively, the statistic and regression analysis of mass burning rate data of strands, Ф= 127 mm solid motors and full-scale solid motors under the same process condition was completed. The linear regression equations of three burning rates mentioned above were obtained. The results show that this method has good accuracy.

关 键 词：固体推进剂火箭发动机 推进剂燃速系数 相关特性 尺度效应 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]