Abstract
The guidance problem of intercepting ground targets by air-launched missiles is considered in this paper. In addition to achieving a minimal miss distance, the proposed guidance law can also lead to desired terminal impact angles in both azimuth as well as elevation simultaneously. The guidance law is developed on the basic principle of state-dependent Riccati equation (SDRE) approach by considering nonlinear engagement dynamics of the missile. The proposed SDRE-based guidance law is first conducted in a vertical plane, followed by its extension to three-dimensional engagement scenario. High terminal accuracy is ensured by employing a state weighting matrix defined by functions of altitude-to-go. To enlarge the available impact angle region, the guidance law is further modified to achieve interceptions in the case where impact angle in the pitch plane is too large or too small. Third-order autopilot lag is also synthesized in the implementation of the guidance law. Numerical simulations are performed to demonstrate the effectiveness and accuracy of the proposed guidance method in both planar and three-dimensional engagement scenarios.
Original language | English |
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Pages (from-to) | 1616-1630 |
Number of pages | 15 |
Journal | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
Volume | 229 |
Issue number | 9 |
DOIs | |
Publication status | Published - 12 Jul 2015 |
Keywords
- Air-launched missiles
- guidance
- impact angle
- nonlinear system
- state-dependent Riccati equation