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

Author:

Song Kyoung-Rok1,Jeon In-Soo1

Affiliation:

1. 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.

Publisher

MDPI AG

Subject

General Mathematics,Engineering (miscellaneous),Computer Science (miscellaneous)

Reference21 articles.

1. Terminal guidance for impact attitude angle constrained flight trajectories;Kim;IEEE Trans. Aerosp. Electron. Syst.,1973

2. Impact angle control for planar engagements;Song;IEEE Trans. Aerosp. Electron. Syst.,1999

3. Optimal guidance laws with terminal impact angle constraint;Ryoo;J. Guid. Control Dyn.,2005

4. Time-to-go weighted optimal guidance with impact angle constraints;Ryoo;IEEE Trans. Aerosp. Electron. Syst.,2006

5. Linear quadratic guidance laws for imposing a terminal intercept angle;Shaferman;J. Guid. Control Dyn.,2008

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