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

International audienceThis paper details the identification of a pitchaxis model for an 80-mm fin-stabilized canard-guided projectilethrough a hardware-in-the-loop experimental setup. This setup is based on an autonomous functional projectileprototype 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 Taylorseries expansion. The a priori and a posteriori identifiabilityof the proposed linear model are assessed, and the associatedexperimental input signals are accordingly designed.The model parameters are then estimated using a numericaloptimization procedure, and the associated uncertainty isobtained through a boostrapping method. The results andtheir implication on the projectile flight control design arefinally discussed