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Impact-Angle-Control Guidance Law with Terminal Constraints on Curvature of Trajectory

Author

Listed:
  • Kyoung-Rok Song

    (Missile Research Institute, Agency for Defense Development, Daejeon 34060, Republic of Korea)

  • In-Soo Jeon

    (Missile Research Institute, Agency for Defense Development, Daejeon 34060, Republic of Korea)

Abstract

This paper presents an impact-angle-control guidance law with terminal constraints on the curvature of the missile trajectory. The formulation takes into account nonlinear kinematics and time-varying velocity, allowing for more general cases in which the flight path angle may not be small throughout the entire trajectory. The proposed optimal guidance law aims to minimize the change rate of pseudo-curvature, which is defined as a curvature with weighting factors based on the flight-path angle and range to go. The analysis shows that the trajectories generated by this nonlinear guidance law have a simple polynomial form with respect to downrange. Numerical simulations demonstrate that the cost function parameter can be used to shape the trajectories along the downrange.

Suggested Citation

  • Kyoung-Rok Song & In-Soo Jeon, 2023. "Impact-Angle-Control Guidance Law with Terminal Constraints on Curvature of Trajectory," Mathematics, MDPI, vol. 11(4), pages 1-12, February.
    • Handle: RePEc:gam:jmathe:v:11:y:2023:i:4:p:974-:d:1068079
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    References listed on IDEAS

    as
    1. Sungjin Cho, 2022. "Analytic Solution for Nonlinear Impact-Angle Guidance Law with Time-Varying Thrust," Mathematics, MDPI, vol. 10(21), pages 1-13, October.
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    Cited by:

    1. Yue Qu & Wenjun Yi, 2023. "An Improved Second-Order Sliding Mode Control for an Interception Guidance System without Angular Velocity Measurement," Mathematics, MDPI, vol. 11(11), pages 1-17, May.

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