固体火箭冲压发动机燃气发生器动态特性影响分析

建立了燃气发生器/固体火箭冲压发动机/导弹的一体化动态数学模型，通过数值仿真研究得到了在典型飞行弹道下各主要工作参数的变化过程.结果表明，在导弹飞行的爬升和巡航段，燃气发生器实际输出燃料流量和发动机实际输出推力与指令值之间的相对偏差均较小，不超过7%；而在俯冲段，由于容腔效应影响严重，燃料流量相对偏差达到-30%，推力最大相对偏差达-50%.上述因素给导弹飞行速度带来的相对偏差小于5%，射程的相对偏差小于1%.因此，针对所述的爬升 巡航 俯冲弹道，在导弹工作过程仿真中，可忽略燃气发生器的动态特性，不会影响对导弹飞行性能的评估. 

Analysis on influence of dynamic characteristics of gas generator insolid propellant ducted rockets

Aerospace Science and Industry Corporation,Beijing 100074,China)Abstract:An integral model of gas generator/solid propellant ducted rocket/missile was established, and typical performance parameters in the typical trajectory were obtained by simulation. Results showed that, in the climbing and cruising phases, the relative error of the fuel mass flow rate and the thrust of the engine was less than 7%. But in the diving phase, due to the free volume effect, the relative error of the fuel mass flow rate was -30%, and the error of thrust was -50% correspondingly. However, the relative errors of flight velocity and flight range were less than 5% and 1% respectively. Therefore, for this typical climb cruise diving flight trajectory described, the dynamic characteristics of gas generator can be ignored in analysis of the missiles working process.