【作者】 林德福； 祁载康；

【Author】 LIN De-fu, QI Zai-kang (School of Mechano-Electronics Engineering, Beijing Institute of Technology, Beijing 100081, China)

【机构】 北京理工大学机电工程学院飞行器设计系；

【摘要】 提出了利用韦布尔雷达测量的速度及弹道参数来辨识非常规弹丸飞行的阻力系数和攻角的方法。采用多段样条方法提取阻力系数,可以保证阻力曲线的一阶连续性,且能准确地辨识出从亚音速到超音速下的阻力系数。将辨识得到的阻力系数与吹风得到的阻力系数进行对比,从而验证了该方法的正确性。根据建立的弹丸飞行运动学方程,推导出攻角与弹丸物理参数、气动力参数及飞行参数的关系,并根据雷达测试数据辨识了弹丸飞行的不同阶段攻角随时间的变化规律。结果表明利用雷达数据对非常规弹丸飞行的阻力系数与攻角进行辨识的方法是可行的。更多还原

【Abstract】 According to the data given by the Weibull radar, the drag coefficient and angle of attack were identified. The multivariate splines were adopted to identify the drag coefficient from subsonic to supersonic, which can keep the curve smooth. The method was proved to be correct by comparing the drag coefficient given by the identification and wind tunnel test. The expression of the angle of attack, denoted by the aerodynamic derivatives and flight data, was deduced according the kinematics equation of the unconventionality projectile. Using the data given by WB radar, the angle-of-attack transition curve during the projectile flying can be identified. The result shows that the identification method is feasible.更多还原