Pitch-Axis Identification for a Guided Projectile Using a Wind-Tunnel-Based Experimental Setup

摘要

This paper details the identification of a pitch-axis model for an 80-mm fin-stabilized canard-guided projectile through a hardware-in-the-loop experimental setup. This setup is based on an autonomous functional projectile prototype installed in a subsonic wind tunnel by the means of a three-degree-of-freedom gimbal mount. A nonlinear dynamical model is first derived from flight mechanics principles; then, a linearized model is obtained through Taylor series expansion. The and identifiability of the proposed linear model are assessed, and the associated experimental input signals are accordingly designed. The model parameters are then estimated using a numerical optimization procedure, and the associated uncertainty is obtained through a boostrapping method. The results and their implication on the projectile flight control design are finally discussed.