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 language | English |
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Pages (from-to) | 74-81 |
Number of pages | 8 |
Journal | International Journal of Aeronautical and Space Sciences |
Volume | 15 |
Issue number | 1 |
DOIs | |
Publication status | Published - 2014 |
Keywords
- Autopilot
- Low-pass filter