Missile two-loop acceleration autopilot design based on L1 adaptive output feedback control

Shao Ming He*, De Fu Lin

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

2 Citations (Scopus)

Abstract

This article designs a novel two-loop acceleration autopilot based on L1 adaptive output feedback control for tail-controlled missiles. The inner loop is an adaptive angle-of-attack tracking loop and the outer loop is the traditional PI controller for error compensation. A systematic low-pass filter design procedure is provided for minimum phase system and is applied to the inner loop design while the parameters of the outer loop is obtained from multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions.

Original languageEnglish
Pages (from-to)74-81
Number of pages8
JournalInternational Journal of Aeronautical and Space Sciences
Volume15
Issue number1
DOIs
Publication statusPublished - 2014

Keywords

  • Autopilot
  • Low-pass filter

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