Abstract
Using the Lyapunov-like approach, the capturability of a recently proposed sliding-mode guidance law, which is used for exoatmospheric interception and can guide the line-of-sight (LOS) angular rate to converge to zero or its small neighborhood in a finite time, is thoroughly analyzed. The target is assumed to have an arbitrary but upper-bounded maneuvering acceleration. A more realistic definition of capture is considered. The upper bound of the commanded acceleration is obtained and so is the capture region. The new theoretical findings are extended to the three-dimensional space with the help of the rotating LOS coordinate system.
Highlights
Over the past three decades, the sliding-mode variable structure control theory has drawn great attention as a potential solution to the performance degradation issue in classical proportional navigation (PN) guidance laws against agile targets with high maneuverability
The commanded acceleration of finite-time sliding-mode guidance (FTSMG) is perpendicular to LOS and the control purpose is to drive the LOS rate to zero or its small neighborhood
Considering the cross-coupling effect of the pitch and yaw planes of the missile, Song and Ha [41] extended the Lyapunov-like method to 3-D space to investigate the performance of the 3-D proportional navigation (PPN) and proposed the 3-D modified pure PN guidance law
Summary
Over the past three decades, the sliding-mode variable structure control theory has drawn great attention as a potential solution to the performance degradation issue in classical proportional navigation (PN) guidance laws against agile targets with high maneuverability. Considering the cross-coupling effect of the pitch and yaw planes of the missile, Song and Ha [41] extended the Lyapunov-like method to 3-D space to investigate the performance of the 3-D PPN and proposed the 3-D modified pure PN guidance law. Based on this approach, Oh and Ha [42] studied the capturability of the 3-D PPN against an arbitrarily maneuvering target with normal acceleration when the missile has a speed advantage over the target. The settling time of the LOS rate is analyzed without the restriction of the constant closing speed assumption
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