Adjoint assisted geometry design of a feedback controlled missile

Abstract

A novel optimisation framework using an adjoint cost sensitivity calculation, and integrating computer simulations of fluid dynamics, rigid body dynamics and control is proposed. A generic tail-fin steered missile under closed-loop control is used to show that the framework is able to generate a detailed geometrical tail-fin design and tune control performance parameters that are directly related to the range and manoeuvrability of the missile. It is shown that this new methodology is able to reduce the aerodynamic drag by 2% and the tracking error by about 3% relative to the original design.