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. A novel 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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

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


    Contributors:

    Published in:

    Publication date :

    2015-03-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Aerodynamic Design Optimization of Control Mechanisms for a Subsonic, Small Diameter Munition

    Vasile, Joseph D. / Fresconi, Frank / Celmins, Ilmars et al. | AIAA | 2018



    rotating horizontal wing flight device

    LEE SANG CHEOL | European Patent Office | 2018

    Free access