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<p>As modern battlefields grow increasingly complex, missile miniaturization has become a clear trend. To enhance guidance performance, this paper proposes a guidance law that enforces both impact angle and field-of-view (FOV) constraints using only bearings-only measurements, making it well suited to passive strapdown seekers on miniature missiles. Building on proportional navigation, an analytical impact angle error is derived and used as the outer sliding surface, and a virtual control is designed to drive its convergence. Constrained by the FOV limit, the integral of the virtual control is saturated and used as the desired look angle, while the tracking error between this reference and the measured look angle defines the inner sliding surface. The resulting guidance command drives the inner surface to converge, thereby satisfying both the impact angle and FOV constraints without requiring range-to-target or line-of-sight (LOS) angular rate information. Finite-time convergence is established via Lyapunov analysis. To mitigate large initial acceleration and potential chattering, a time-varying reference range is introduced. Deterministic simulations across varied FOV limits, desired impact angles, and initial geometries demonstrate high accuracy with reduced control effort. Monte Carlo trials with measurement disturbances further show smaller impact angle errors and miss distances, validating the good guidance performance of the proposed method.</p>

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Two-Layer Sliding-Mode Guidance with FOV and Impact-Angle Constraints under Bearings-Only Measurements

  • 期刊论文

  • 发表日期：

    2026年1月23日

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  • Sujie Xian,
  • Xin Zeng,
  • Kang Wang,
  • Jie Song,
  • Zhilin Wu

摘要

As modern battlefields grow increasingly complex, missile miniaturization has become a clear trend. To enhance guidance performance, this paper proposes a guidance law that enforces both impact angle and field-of-view (FOV) constraints using only bearings-only measurements, making it well suited to passive strapdown seekers on miniature missiles. Building on proportional navigation, an analytical impact angle error is derived and used as the outer sliding surface, and a virtual control is designed to drive its convergence. Constrained by the FOV limit, the integral of the virtual control is saturated and used as the desired look angle, while the tracking error between this reference and the measured look angle defines the inner sliding surface. The resulting guidance command drives the inner surface to converge, thereby satisfying both the impact angle and FOV constraints without requiring range-to-target or line-of-sight (LOS) angular rate information. Finite-time convergence is established via Lyapunov analysis. To mitigate large initial acceleration and potential chattering, a time-varying reference range is introduced. Deterministic simulations across varied FOV limits, desired impact angles, and initial geometries demonstrate high accuracy with reduced control effort. Monte Carlo trials with measurement disturbances further show smaller impact angle errors and miss distances, validating the good guidance performance of the proposed method.