Second Order Sliding Mode-Based Intercept Guidance with Uncertainty and Disturbance Compensation
This paper focuses on a missile intercept guidance method taking account of uncertainty and disturbance. The proposed guidance law are developed using a second order sliding mode approach, along with an uncertainty and disturbance estimator. A novel sliding surface is developed for the second order sliding mode-based missile guidance. The proposed sliding surface is unified both for non-impact angle constraint and an impact angle constraint. The proposed sliding surface guarantees the finite time convergence of the lineof- sight rate and (if specified) the LOS angle error associated with a simple function of a time-to-go like the case of using the proportional navigation against a non-maneuvering target while the proposed strategy can also be effective even against a maneuvering target. The line-of-sight rate convergence property can be adjusted using only one parameter that makes the design process simple. Moreover, the guidance law is unified also for the missile intercept guidance with a specified impact angle constraint. The potential of the proposed guidance laws is demonstrated with some simulations.
T. Yamasaki et al., "Second Order Sliding Mode-Based Intercept Guidance with Uncertainty and Disturbance Compensation," AIAA Guidance, Navigation, and Control (GNC) Conference, American Institute of Aeronautics and Astronautics (AIAA), Jan 2013.
The definitive version is available at https://doi.org/10.2514/6.2013-5115
AIAA Guidance, Navigation, and Control (GNC) Conference (2013, Boston, MA)
Mechanical and Aerospace Engineering
Article - Conference proceedings
© 2013 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.