Aerodynamic Parameter Identification for Symmetric Projectiles: An Improved Gradient Based Method

摘要

In order to estimate the aerodynamic coefficients of a symmetric projectile from free flight range data, a linear theory solution is proposed. This solution is superior to previous efforts in its compactness and simplicity, providing predictions of yaw, pitch, crossrange, and altitude as functions of downrange travel. Moreover, 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.