Three-dimensional sliding mode guidance law for maneuvering target with prescribed performance and input saturation

Abstract

The three-dimensional sliding mode guidance laws with prescribed performance and saturation actuator are proposed for maneuvering target. The proposed guidance laws can ensure the line of sight (LOS) angle converges according to the prescribed performance with actuator saturation and the convergence rate, the steady state error and the maximum overshoot can be preset in advance. A novel transformed error function is designed by combining the LOS tracking error with the performance constraint function. Then, to further solve the problem of input saturation, the saturation function and auxiliary system are introduced. Additionally, this paper discusses the problem whereby the upper bound of the aggregate uncertainty, including the target information, is unavailable. An adaptive sliding mode guidance law with prescribed performance is presented for this scenario. Experiments comparisons are conducted with other forms of guidance laws. Simulation results show that the guidance laws proposed in this paper achieve effective performance.

Three-dimensional adaptive fixed-time guidance law against maneuvering targets with impact angle constraints and control input saturation

“…The main object of this research is to design a 3D adaptive fixed-time guidance law so that the target can be successfully intercepted at desired angles ( θ L ( t f ) = θ Lf , ψ L ( t f ) = ψ Lf ) . As shown in Ma et al (2020), the target interception can be achieved by driving θ · L and ψ · L to zero.…”

“…In modern war, more and more tactical missiles are applied to intercept targets effectively. To further improve the impact lethality of the missile, the terminal guidance laws are usually required to attack the target at the specified impact angle (Lin et al, 2020). Therefore, the research of terminal guidance laws considering terminal angle constraint has become an attractive issue.…”

“…In Geng et al (2019), an adaptive back-stepping SMGL with line-of-sight (LOS) angle constraint and acceleration saturation constraint was designed, which can overcome the input saturation by adding an auxiliary system. Ma et al (2020) combined the prescribed performance control, sliding mode control method, and adaptive control strategy to construct the guidance law, and the input saturation was handled by the auxiliary system. Although the auxiliary system–based anti-saturation methods show fine performance, the design structure seems to be complicated for practical implementation and only finite-time stability can be achieved.…”

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

“…So it is necessary to design a guidance law with antiacceleration saturation. Although the references [38,39] consider the acceleration saturation constraint when designing the guidance law, they do not consider the missile autopilot dynamics characteristics or only consider the autopilot first-order dynamic characteristics, rather than the autopilot second-order dynamic characteristics that are closer to the actual situation. In [24], the acceleration saturation constraint and the missile autopilot secondorder dynamic characteristics are noticed, but this guidance law cannot converge in a finite time.…”

“…For this reason, this paper proposes a nonlinear filter to guarantee the system's finite-time convergence (4) An adaptive auxiliary system is proposed to solve the problem of guidance command input saturation in this paper. Compared with the antisaturation method of guidance command input proposed in reference [39], the method proposed in this paper is simpler in form and easier to implement in engineering.…”