Analysis of optimal midcourse guidance law

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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 languageEnglish
Pages (from-to)419-425
Number of pages7
JournalIEEE Transactions on Aerospace and Electronic Systems
Volume32
Issue number1
DOIs
Publication statusPublished - 1996 Dec 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Electrical and Electronic Engineering

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