基于平衡抛射原理的火箭筒内弹道仿真研究

Research on Trajectory Simulation of Rocket Launcher Based on Balanced Projectile

针对采用平衡抛射原理的火箭筒内弹道仿真问题,详细论述了该火箭筒的工作原理和过程,对其内弹道时期进行分析与划分,提出了合理的假设条件,运用经典内弹道理论建立了内弹道模型,使用MATLAB语言编写内弹道程序并进行仿真计算,得出内弹道相关曲线。通过线圈测速法和铜柱测压法测得火箭弹出筒口的速度和筒内最大膛压。仿真结果与试验测得数据做对比分析,与试验数据基本吻合,说明所建模型和假设条件正确合理,为平衡抛射原理的应用推广提供理论指导。

Aiming at the problem of trajectory simulation of rocket launcher with balanced ejection principle the working principle and process of the rocket launcher were discussed in detail with the in ternal ballistic period analyzed and divided and with reasonable assumptions put forward. The internal ballistic model was established using the classical theory of internal ballistic theory. MATLAB was used to write the internal ballistic program and carried out the simulation calculation with the curves. The velocity of the projectiles and the maximum pressure of the cylinder were measured with the coil veloci ty method and the copper column measuring method. The simulation results were compared with the test data which was in accordance with the experimental data revealing the reasonableness of the es tablished model and assumptions. It could provide a theoretical guidance for the application and promo tion of balanced projectile principle.