Title

Analytical Missile Guidance Laws with a Time-Varying Transformation

Abstract

A class of proportional navigation guidance laws is derived via an approximation of time-to-go and a transformation of state variables. The optimal guidance problem is developed in polar coordinates. This problem is shown to decompose into two decoupled optimal control problems, where a closed-form control solution is available in the radial direction and a time-varying linear dynamics system is solved for control in the transverse direction.

Department(s)

Mechanical and Aerospace Engineering

Document Type

Article - Journal

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 1996 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

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