固体发动机后效对导弹分离性能的影响分析

Impact Analysis of the Solid Motor Post-Thrust on the Missile Separation Performance

对固体火箭发动机后效推力进行了分析和计算。采用经典流体力学发动机内弹道计算理论,运用等熵膨胀条件所得的燃烧室压强变化模型,预测发动机超临界压强后效冲量变化规律,给出临界压强以下的后效冲量预测模型。更精确地获取固体发动机后效对导弹分离前后的冲量影响,明确导弹分离的一些基本参数要求,确定固体发动机结束工作后所需的分离速度。

Post-thrust of a solid rocket motor is analyzed and calculated. The classic fluid mechanics theory of the motor~ internal ballistics and the pressure variety model of combustor under the situation of isentropic process are used to predict the variety regulation of the cutoff impulse on the condition of super- critical pressure and to get the predict model of the cutoff impulse on the condition that the motor pressure is lower than the critical pressure. The impact of post-thrust of the solid rocket motor on the impulse fore- and-aft the missile separation is obtained more accurately. Some basic parameter about missile separates is confirmed. The needed separate speed after the solid rocket motor work ends is determined.