Design of Computational Integrated Guidance and Control for Aerodynamic Dual-control Missiles

The terminal guidance phase demands high interception accuracy, while engaging high-speed targets within a short engagement time also requires rapid response and high maneuverability. A canard-tail dual-control configuration may improve missile response and maneuverability by compensating for the limitations of canard-only and tail-only control configurations. However, the use of two control surfaces introduces the need to properly distribute the control inputs, while various physical constraints complicate the derivation of analytical solutions. Furthermore, conventional guidance and control loops are often designed separately, which could limit interception performance when the engagement geometry changes rapidly during the terminal guidance phase. This paper proposes a convex-optimization-based integrated guidance and control (IGC) scheme for a canard-tail dual-control missile. The guidance and control loops are integrated into a unified state-space model, and the two control-surface inputs are determined without a separate control allocation scheme while satisfying maximum missile acceleration, seeker, and control-surface constraints. The resulting optimal control problem is discretized and reformulated as a convex quadratic program, which is solved at each time step for closed-loop implementation. Numerical simulations are used to compare the dual-control configuration with single-control configurations and analyze the capturable region of the dual-control missile for non-maneuvering and maneuvering targets.