贫氧推进剂一次燃烧产物的热力计算  

THERMODYNAMIC CALCULATION OF DEFICIENT OXYGEN SOLID PROPELLANT PRIMARY COMBUSTION

作　　者：毛成立[1] 李葆萱[1] 

机构地区：[1]西北工业大学航天工程学院,西安710072

出　　处：《宇航学报》2000年第z1期32-37,共6页Journal of Astronautics

基　　金：国防重点实验室基金! (98JS60 .1 .2 ZS60 0 2 ) ;航空基金! (96D53 0 54)

摘　　要：贫氧推进剂一次燃烧的物理和化学动力学因素决定了其一次燃烧为非平衡燃烧。说明了非平衡燃烧的特点 ,提出了计算贫氧推进剂一次燃烧的理论模型。以参与化学反应的推进剂组分为基础 ,把燃烧剩余物和燃烧产物分开 ,建立了燃烧产物的质量和化学平衡方程以及体系的能量平衡方程 ,采用布林克莱法解决了贫氧推进剂非平衡燃烧产物的热力计算。The primary combustion of deficient oxygen solid propellant is non equilibrium because of its own physical and chemical processes.The features of non equilibrium combustion are shown,and the theoretical model is proposed.Based on combusted propellant ingredients,the remains and the products are divided into two parts.The equations about mass,energy and chemical equilibrium of the products are established,and Brinkley's rule is applied to calculating the products in non equilibrium combustion.

关 键 词：贫氧推进剂 一次燃烧 燃烧产物 方程 

分 类 号：V4-55[航空宇航科学技术]