火箭弹自力弹射内弹道特性

为消除火箭弹发射尾焰对发射装置周围人员及设备的威胁，提出了一种火箭弹自力弹射技术方案，将发射尾焰限制在发射筒内直至弹尾离筒。基于经典内弹道学推导得到火箭弹自力弹射的内弹道数学模型，并进行了低压室初始长度300 mm、低压室初始长度300 mm与低压室开有2个孔径为15 mm的孔、低压室初始长度150 mm 3种工况共5发实弹的验证试验。对比仿真数据与试验数据发现：二者低压室压强随时间变化曲线的一致性较好；低压室压强峰值的最大相对误差为9.29%，弹体出筒瞬间速度的最大相对误差为5.24%，模型的有效性得到验证。以自力弹射内弹道模型为基础，分析低压室开孔、低压室初始长度、发射筒长度、发动机流量对其内弹道特性的影响，为火箭弹自力弹射的内弹道研究提供了理论参考。

Self-ejection Interior Ballistic Characteristics of Rocket Projectiles

A self-ejection launcher is proposed to solve the negative influence of exhaust plume on the surrounding equipment and perssonel. The exhaust plume generated by self-ejection launcher is sealed in a low pressure chamber until the tail leaves the launcher barrel. In order to study the characteristic and rules of interior ballistic of self-ejecting rocket projectile, a solution model of internal ballistic of self-ejecting rocket projectile was developed based on the classical interior ballistic. Physical tests of 5 rocket projectiles were carried out under three working conditions, i.e., low pressure chamber with initial length of 300 mm, low pressure chamber with initial length of 300 mm and two holes with pore diameter of 15 mm on it, and low pressure chamber with initial length of 150 mm. Compared with the experimental data and simulated data,the curves of the pressure in low pressure chamber have good consistency. The maximum relative error of the peak of pressure in low pressure chamber and the instantaneous velocity of the missile leaving the launcher are 9.29% and 5.24%, respectively, and the validity of interior ballistic model is verified. The influences of the trepanning on low pressure chamber, the length of low pressure chamber, the length of launcher ,the mass flow rate of motor on the interior ballistic of self-ejecting rocket projectile are ananlyzed based on the interior ballistic model.