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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 physical and chemical kinetics of primary combustion of oxygen-poor propellants determine their primary combustion as non-equilibrium combustion. The characteristics of non-equilibrium combustion are described. A theoretical model for calculating primary combustion of oxygen-poor propellant is proposed. Based on the propellant component involved in the chemical reaction, the combustion residue and the combustion products are separated, the mass and chemical equilibrium equations of the combustion products and the energy balance equation of the combustion products are established, and the Brinkley method is used to solve the problems of the oxygen poor propellant Thermodynamic Calculation of Unbalanced Combustion Products.