Abstract
This article investigates the problem of designing robust guidance laws for intercepting maneuvering targets with desired terminal line-of-sight angle constraint. Based on generalized model predictive control for the nominal system, the discontinuous and continuous integral sliding mode control laws are, respectively, developed. Stability analysis shows that the proposed guidance law can ensure the optimal tracking characteristic of generalized model predictive control algorithm and the line-of-sight angle tracking error as well as the line-of-sight angular rate can converge to zero asymptotically. The effectiveness of the proposed guidance law is validated by applying it to a surface-to-air missile for intercepting a head-on maneuvering target under different scenarios.
| Original language | English |
|---|---|
| Pages (from-to) | 610-621 |
| Number of pages | 12 |
| Journal | Proceedings of the Institution of Mechanical Engineers. Part I: Journal of Systems and Control Engineering |
| Volume | 230 |
| Issue number | 7 |
| DOIs | |
| Publication status | Published - 1 Aug 2016 |
Keywords
- Missile guidance
- generalized model predictive control
- integral sliding mode
- maneuvering target
- terminal angle constraint