A Nonlinear Optimal Guidance Law with Terminal Impact Angle Constraint
- DOI
- 10.2991/ijcis.2011.4.6.24How to use a DOI?
- Keywords
- Guidance Law, Genetic Algorithm, State-dependent Riccati Equation, Impact Angle Constraint, Trajectory Optimization.
- Abstract
State-dependent Riccati equation (SDRE) techniques are rapidly emerging as general design methods for nonlinear controllers. A nonlinear optimal guidance law with impact angle constraint is derived for planar engagements to attack stationary targets. The guidance problem is formulated as an infinite horizon nonlinear regulator problem whose equilibrium state is zero. It is solved by SDRE technique and the state weight matrix is chosen as a function of time-to-go. Performance of the guidance law is tested numerically with different initial firing conditions for a realistic GPS/INS guided artillery rocket model with low available lateral acceleration. A reasonable launch angle is helpful to reduce the control effort, and it is acquired by trajectory optimization using genetic algorithm. Results show negligible errors for miss-distance and the desired impact angle. The proposed guidance law is a choice for the guided artillery rocket.
- Copyright
- © 2011, the Authors. Published by Atlantis Press.
- Open Access
- This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).
Cite this article
TY - JOUR AU - Haoping She AU - Shuxing Yang AU - Hui Ni AU - Horst Baier PY - 2011 DA - 2011/12/01 TI - A Nonlinear Optimal Guidance Law with Terminal Impact Angle Constraint JO - International Journal of Computational Intelligence Systems SP - 1319 EP - 1324 VL - 4 IS - 6 SN - 1875-6883 UR - https://doi.org/10.2991/ijcis.2011.4.6.24 DO - 10.2991/ijcis.2011.4.6.24 ID - She2011 ER -