Optimal Aerodynamic Design of Missile Fins with Geometric Constraints

Within DoD there is a current need for the design or redesign of aircraft-borne weapon airframes to meet conformal/internal carriage requirements. A major constraint imposed by confromal/internal carriage is a limitation on the maximum stowable fin span of a weapon. Current aircraft such as the F-117 and future aircraft such as the F-22 are designed with internal carriage capability, but current weapons systems such as the Sidewinder and AMRAAM require modifications to meet these carriage requirements. Design or re-design of weapon airframes requires an extensive expenditure of labor and funds. Missile engineers can not simply reduce the span of missile fins without incurring potentially detrimental changes in the aerodynamic characteristics of the vehicle. Nielsen Engineering & Research (NEAR) proposes to develop an innovative design tool employing combined numerical optimization/aerodynamic prediction techniques for the optimal aerodynamic design of missile fins with geometric constraints such as those imposed by conformal/internal carriage and constraints set by actuator torque limits. This advanced optimization-based design tool will reduce the development time and costs associated with missile fin design or redesign.