Flight Performance of a Small Diameter Munition with a Rotating Wing Actuator

摘要

Future enhanced lethal effects at the infantry squad level likely include precision guided technologies. The focus of this study is maneuvering projectiles launched from man-portable weapon systems. Anovel guided projectile concept is proposed for achieving control authority requirements in the challenging environment of low-dynamic pressure, small size, high launch loads, spin stabilization, and low cost. This new maneuver concept is based on a rotating wing actuator. Experimental and advanced computational aerodynamics techniques were applied. Aerodynamic models and projectile flight mechanics were derived to enable flight simulation. Assessment of ballistic delivery accuracy, based on physics-based models of the delivery process, was undertaken to quantify control authority requirements. Maneuvering flight simulations demonstrated that this concept affords enough course correction to compensate for ballistic delivery errors.