Aerodynamic Design Optimization of Long Range Projectiles using Missile DATCOM
Joseph D. Vasile, Joshua Bryson, Frank Fresconi
Abstract
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 which 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 three and six 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.