弹丸脉冲侧喷力俯仰调姿试验与仿真研究

Experimental and Numerical Study on Pitch Attitude Adjustment of Projectile Implemented by Impulse Lateral Thrust

关键词:  弹丸  垂直发射  姿态调整  直接力控制系统  脉冲推力  内弹道  运动仿真

Key words:  Projectile  Vertical launching  Posture adjustment  Reaction-jet control system  Impulse thrust  Interior ballistic  Motion simulation

摘要:

为了解地面垂直发射弹丸在不同直接力控制系统（RCS）输出条件下的俯仰调姿运动情况，分别采用试验与仿真的方法进行了研究。首先，设计了用于弹丸调姿试验的脉冲侧向推力器、地面发射装置以及同步测试系统，利用高速摄像机测量了弹丸在不同推力器装药量和点火间隔时间情况下的调姿运动情况，并指出这两个参量是决定弹丸最终姿态角的主要因素，需要根据目标姿态角进行合理的搭配。然后，建立了考虑脉冲侧向推力器内弹道过程的弹丸调姿运动模型，并与试验结果进行了对比，验证了仿真模型的预测误差在5%以内。随后，利用仿真模型分析了不同推力器装药量时脉冲推力的变化情况，指出装药量对脉冲推力的变化规律有重要影响，需要与弹丸运动耦合计算以获得更高的精度。最后，对不同推力器装药量时弹丸调整到各目标姿态角所需的点火间隔时间进行了计算，为进一步的研究提供了数据参考。

Abstract:

Experimental and numerical studies were carried out respectively to learn about the pitch attitude adjusting process of the projectile which was launched vertically from the ground and controlled by reaction-jet control system （RCS） with different output parameters. Firstly， the impulse lateral thruster， a ground launcher and a synchronous measurement system were designed for the pitch attitude adjusting experiment. A series of tests were conducted in the conditions of different charge weights in the thrusters and various ignition interval time. Based on analysis of the motion pictures captured by high speed cameras， the charge weight and ignition interval time were found to be the two principal factors to determine the final attitude of the projectile and either of them should be selected a proper value for a target attitude angle. Then， an attitude motion computing model of the projectile was established considering the interior ballistic of the thruster. After comparing the results obtained from simulation and test， the prediction error of the model was confirmed to be less than 5%. Subsequently， the variations of the impulse thrust with different charge weights were analyzed according to the computing model. And it was pointed out that the changing rule of the impulse thrust could be affected significantly by the charge weight. Therefore， coupling calculation of the thrust and projectile motion is needed for higher accuracy. In the end， the ignition interval time required for a set of target pitch angles with different charge weights was calculated， which will provide meaningful reference data for further researches.