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Aerodynamic parameter identification for symmetric projectiles: An improved gradient based method

机译:对称弹丸气动参数识别:一种改进的基于梯度的方法

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摘要

In order to estimate the aerodynamic coefficients of a symmetric projectile from free flight range data, an algorithm using traditional linear theory with non-linear programming is investigated. The linear theory solution is reformulated resulting in matrix expressions of improved compactness and simplicity, which provide predictions of yaw, pitch, crossrange, and altitude as functions of downrange travel. The new solution is easily differentiated with respect to aerodynamic coefficients such that a gradient based output error estimation algorithm naturally follows. Numerical results are presented and compared to a previous method that required finite differencing for gradient estimates.
机译:为了从自由飞行距离数据估计对称弹丸的空气动力学系数,研究了一种使用传统线性理论和非线性规划的算法。重新设计了线性理论解,从而获得了提高的紧凑性和简便性的矩阵表达式,这些表达式提供了偏航,俯仰,跨距和高度随低程行驶而变化的预测。新解决方案相对于空气动力学系数易于区分,因此自然会遵循基于梯度的输出误差估计算法。提出了数值结果,并将其与需要有限差分进行梯度估计的先前方法进行了比较。

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