固体火箭发动机燃气射流驱动液柱过程中的内弹道研究

为了实现单兵火箭"有限空间内发射"的能力,提出了在尾管内放置液柱平衡体的单兵火箭发射系统,对该系统进行试验研究的同时分时段分析了内弹道过程。以经典内弹道理论为基础,将燃气与液体之间的无规则混合假设为"穿孔混合",建立了发射系统的数学模型,并运用龙格-库塔法进行了数值计算,给出了完整的内弹道曲线。通过试验与计算结果的对比分析,计算结果与试验结果吻合较好,燃烧室最大压力相对误差为1.6%,弹丸速度相对误差为0.9%,验证了该模型的有效性,为单兵火箭驱动液柱发射系统的内弹道过程提供理论参考依据。对比分析单兵火箭发射系统在有无液体柱平衡体两种条件下的计算结果可知,在相同发射条件下,液柱平衡体在减弱发射特征的同时提高了弹丸的速度,提升了火箭弹的威力。

Study of Interior Ballistics of Solid Rocket Motor in the Process of Gas Jet Driving Liquid Column

In order to achieve the launch of individual rocket in limited space,a individual rocket launching system of which the liquid column is placed in the tail tube as a balance body is proposed.The system is tested,and the interior ballistics process is analyzed over time intervals.Based on the theory of the classical inrerior ballistics theory,a mathematical model of the launching system is established by assumoffing that the irregular mixing of gas and liquid is regarded as mixing of perforation.Runge Kutta method is used for numerical calculation,and the complete curves of interior ballistics process are given.The analysis result shows that the theoretical results are in good agreement with the experimental results.The relative error of the maximum pressure in combustion chamber is 1.6％,and the relative error of projectile velocity is 0.9％.The calculated results shows that the liquid column can be used to reduce the launching characteristics of rocket,improve the velocity of projectile,and enhance the power of individual rocket for the individual rocket launching systems with and without liquid column under the same launching conditions.