This paper proposes a generalized optimal impact angle guidance law against axially maneuvering targets. The guidance problem is formulated as a finite-time optimal control problem based on collision triangle geometry, and an analytical solution is derived. By introducing an arbitrary positive weighting function, the guidance command can be flexibly shaped to meet various mission requirements. The convergence of the guidance law is rigorously proven via Lyapunov stability theory. Extensive simulations, including various engagement geometries, complex composite axial target maneuvers, and parameter uncertainties, as well as comparative studies against existing advanced guidance laws, are conducted. The results comprehensively demonstrate the accuracy, robustness, and flexibility of the proposed method for intercepting axially maneuvering targets.
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