Aerodynamic Design Optimization of Long-Range Projectiles Using Missile DATCOM
Technical Report,01 Jun 2018,01 Aug 2019
Combat Capabilities Development Command Army Research Laboratory Aberdeen Proving Ground United States
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The goal of this study was to utilize a quick and robust semi-empirical aerodynamics prediction code Missile DATCOM to optimize and improve understanding of the flight performance for long-range guided projectiles. Multiple optimal designs were found based on flow regime i.e., subsonic or supersonic, projectile geometry i.e., diameter, length-to-diameter, and ogive length, and control configuration e.g., Body-Fin. A weighted multi-objective Particle Swarm Optimization algorithm was implemented to find the control surface sizing that maximized the lift-to-drag, minimized drag, and met a static margin value for the vehicle at a given body angle of attack. An inviscid computational fluid dynamics solver i.e., Cart3D was applied to the optimal configurations and combined with the semi-empirical predictions in a formal manner to improve the accuracy of the aerodynamic model and coefficients. These aerodynamics underpin both 3 and 6 degree-of-freedom simulations to evaluate flight performance. The results from the higher fidelity aerodynamic simulations showed good agreement with the semi-empirical aerodynamic predictions. Outputs of the optimization routine along with the comprehensive flight characterization indicated that the optimization approach is an efficient tool for producing favorable long-range gliding projectiles.
- Air- and Space-Launched Guided Missiles