Sliding mode control based guidance law with impact time constraints

Abstract

In this paper, the sliding mode control based guidance laws to intercept stationary targets at a desired impact time are proposed. Then, it is extended to constant velocity targets using the notion of predicted interception. The desired impact time is achieved by selecting the interceptor's lateral acceleration to enforce a sliding mode on a switching surface designed using non-linear engagement dynamics. Numerical simulation results are presented to validate the proposed guidance law for different initial engagement geometries, impact times and salvo attack scenarios.

Nonsingular Sliding Mode Guidance for Impact Time Control

“…The desired line-of-sight angle and line-of-sight angle rate profile are defined to satisfy the requirement of the impact time and angle, then the guidance law is derived using sliding mode control to track the defined line-of-sight angle rate profile. In [15], the authors develop a guidance law for controlling the impact time using sliding mode control. In their approach, the switching surface is defined as a combination of the impact time error and the line-of-sight angle rate to meet the requirement of the impact time and zero miss distance.…”

“…In this paper, a nonsingular sliding mode guidance is proposed for the impact time control against a stationary target and then extended to a nonmaneuvering target using the concept of predicted interception point motivated by [15]. However, unlike the approach in [15], the switching surface is defined as only the impact time error.…”

Analytical impact time and angle guidance via time-varying sliding mode technique

“…[28,30] have suggested that the value of t fd should be larger than the initial time-to-go (t go0 ) of the missile. However, the timeto-go estimation is not accurate especially under the circumstance of large heading errors.…”

“…The target is assumed to be traveling at a constant velocity V t which is much smaller than that of the missile [28,30]. The target's heading angle is represented by θ t and the lateral acceleration is denoted by a t .…”

“…In [27], the impact time control problem was transformed to a tracking problem using a virtual leader approach. A new guidance scheme was presented in [28] to intercept non-maneuvering targets at a desired impact time via SMC technique. In [29], a guidance approach initiated the researches to control both impact angle and time for homing problems.…”