含硼贫氧推进剂固体燃料冲压发动机性能计算  

Thermodynamic calculation for solid fuel ramjets

作　　者：姚娜[1] 何洪庆[1] 

机构地区：[1]西北工业大学航天工程学院,西安710072

出　　处：《固体火箭技术》2001年第4期12-15,共4页Journal of Solid Rocket Technology

基　　金：国家 2 1 1工程建设项目

摘　　要：固体燃料冲压发动机所用推进剂为贫氧推进剂 ,故其热力计算与普通固体火箭发动机不同 ,但也有相似的地方。简述了固体燃料冲压发动机基于布林克莱法的热力计算原理 ,并以含硼贫氧推进剂为例 ,对固体燃料冲压发动机进行了不同情况的热力、流动和性能计算。得出了发动机比冲与推进剂中硼粒子含量、飞行高度及飞行马赫数之间的定性关系。As fuel rich propellant is used in solid fuel ramjets(SFRJ), its thermodyamic calculation differs from that of ordinary solid rocket motor in some respects. This paper briefly introduces the principle of thermodynamic calculation based on Bolinkly method for SFRJ. Furthermore, thermodynamic, flow and performance calculation for SFRJ at under different conditions is carried out by taking when SFRJ which uses fuel rich propellant containing boron as an example. The qualiative relationships of specific impulse versus the content of boron particle in propellant, flying altitude and flying Mach number are obtained.

关 键 词：固体燃料冲压发动机 贫氧富燃料推进剂 性能 热力计算 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]