尾翼稳定火箭弹高原姿态运动规律研究

Research on Attitude Motion Law of Rockets on Plateau

在分析高原环境对火箭弹弹道特性影响的基础上,建立了火箭弹姿态运动微分方程,对火箭弹高原姿态运动规律进行了理论分析。结合平原、高原姿态试验测试数据的分析验证,确定了尾翼稳定火箭弹高原姿态运动规律及其成因。试验结果表明,由于高原空气密度大幅降低,马格努斯力矩的作用效果增大,在大射角射击时,火箭弹在主动段结束后摆动角快速增大,并保持在大攻角作锥摆运动。为建立高原弹道模型,掌握高原弹道飞行规律,提高武器装备高原射击精度提供了理论参考。

Based on the analysis of influence of plateau environment on rocket ballistics,a differential equations model is derived for the attitude motion of rockets. The law of attitude motion of rockets is analyzed. The law and causes of attitude motion of fin stabilized rocket on plateau are determined by analyzing the attitude test data on plain and plateau. The test results show that the attack angle of rocket increases rapidly after the end of the boost phase,and keeps at large angle for coning motion during firing at high altitude. In the case of low air density on plateau,the motion is caused by the effect of Magnus moment. A theoretical reference is provided for establishing the trajectory model,realizing the motion law of rocket and enhancing the firing precision of the weapons on plateau.