Analysis of optimal midcourse guidance law

Shih Ming Yang

doi:10.1109/7.481282

Analysis of optimal midcourse guidance law

Shih Ming Yang

Research output: Contribution to journal › Article

22 Citations (Scopus)

Abstract

An optimal midcourse guidance law is presented that maximizes the final speed for missiles against a target at far distance or at low attitude in which the final speed is a prime factor. An explicit acceleration command is derived analytically in which the trajectory-dependent optimal control gains are written in terms of thrust, lift, drag, and intercept boundary condition. The optimal guidance law can be implemented either in airframe coordinates or inertia coordinates. It is shown that the acceleration commands with constant control gain are adequate when the range is relatively short; during midcourse guidance, however, the optimal control gains are required to enhance the performance.

Original language	English
Pages (from-to)	419-425
Number of pages	7
Journal	IEEE Transactions on Aerospace and Electronic Systems
Volume	32
Issue number	1
DOIs	https://doi.org/10.1109/7.481282
Publication status	Published - 1996 Dec 1

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Electrical and Electronic Engineering

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Yang, S. M. (1996). Analysis of optimal midcourse guidance law. IEEE Transactions on Aerospace and Electronic Systems, 32(1), 419-425. https://doi.org/10.1109/7.481282

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