Aerodynamic Design Optimization of Long-Range Projectiles Using Missile DATCOM
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 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 10, 2020
- Accession Number
- AD1096548
Entities
People
- Frank E. Fresconi
- Joseph D. Vasile
- Joshua T. Bryson
Organizations
- United States Army Combat Capabilities Development Command