Guidance Law with Desired Impact Time and FOV Constrained for Antiship Missiles Based on Equivalent Sliding Mode Control

Liu, Shuangxi; Yan, Binbin; Zhang, Tong; Dai, Pei; Yan, Jie

doi:10.1155/2021/9923332

Cited by 11 publications

(5 citation statements)

References 21 publications

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“…A combination of backstepping technique and model-free control can provide a research line for model-free ACC design. Sliding mode control is usually used to guarantee robustness and has been well applied [35][36][37]. In [38], a robust fractional-order fast powerreaching guidance scheme was proposed by introducing the fractional-order operator into the sliding surface.…”

Section: Acc From Spacing Strategymentioning

confidence: 99%

Model-Free Robust Backstepping Adaptive Cruise Control

Zhang,

Song

2023

International Journal of Aerospace Engineering

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This paper studies the model-free robust adaptive cruise control problem of a vehicle with unknown nonlinear dynamics and disturbances. First, under backstepping control framework, the position tracking errors with different spacing strategies are used to design a virtual control law, which provides a velocity reference. Then, a novel data-driven sliding surface whose parameters are updated by designing estimation algorithm is developed to handle the unknown uncertainties and disturbances. Finally, the model-free robust backstepping adaptive cruise control (MFRB-ACC) method including PI control, model-free control, and robust control is designed. The novelty of the proposed control technique lies in its strong robustness, which is not based on the precise vehicle model. The designed data-driven sliding surface releases the necessity for the accurate mathematical model of the vehicle and guarantees the inherent robustness of the controller, in particular to uncertainties, modelling error, or external disturbance. Moreover, the designed controller contains three terms such that it has an effective decoupling ability and strong robustness. The effectiveness and superiority of the designed MFRB-ACC method are validated on MATLAB, and the simulation results show that compared to the PID algorithm, the designed MFRB-ACC algorithm can track its preceding vehicle with lower tracking error under different spacing strategies, different operating conditions, and low sampling frequencies. Especially at a sampling frequency of 0.1 s, the error under the PID-ACC increases from 0.2 m at a sampling frequency of 0.01 s to 2 m, and the error under MFRB-ACC has little change compared to the error at a sampling frequency of 0.01 s.

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Section: Acc From Spacing Strategymentioning

confidence: 99%

Model-Free Robust Backstepping Adaptive Cruise Control

Zhang,

Song

2023

International Journal of Aerospace Engineering

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“…In order to improve the performance of tracking and intercepting a low-altitude target, Chen et al [15] proposed a nonlinear integral sliding mode guidance law that guaranteed that the line-of-sight (LOS) angle converged to a desired tracking angle in a finite time. Liu et al [16] designed an impact time control guidance (ITCG) scheme with field-of-view (FOV) constraint to achieve a saturation attack for ships based on the equivalent SMC method. By using a terminal sliding surface, Zhang et al [17] proposed a guidance scheme with impact angle constraint for the missile attacking its target with zero miss distance.…”

Section: Introductionmentioning

confidence: 99%

Fractional-Order Sliding Mode Guidance Law for Intercepting Hypersonic Vehicles

Liu

Yan

et al. 2022

Aerospace

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This paper addresses the problem of a low-speed missile intercepting a hypersonic vehicle in the longitudinal plane. Firstly, based on the concept of the zero of the angular rate of the line-of-sight (LOS) angle, the guidance system is established by defining the LOS angular rate as the state variable. Secondly, in view of the difficulty of precisely measuring the external disturbance caused by the hypersonic vehicle’s maneuver in the guidance system, a non-homogeneous disturbance observer is designed to precisely estimate the disturbance information. Then, by introducing the fractional-order operator into the sliding surface, a fractional-order fast power reaching (FOFPR) guidance law is proposed based on the fast power reaching law. Simulation examples are carried out in two different maneuver modes of the hypersonic vehicle: the bang-bang maneuver mode and sinusoidal maneuver mode. Besides, comparative experiments are conducted with the proportional navigation (PN) and the integer-order fast power reaching (IOFPR) guidance laws. Finally, the simulation results demonstrate the superiority of the effectiveness of the proposed guidance law.

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“…Sliding mode control (SMC) has been widely used for designing guidance laws because of its good adaptability and robustness against parametric uncertainty and external disturbances [19]- [21]. Liu et al [22] designed an impact time control guidance law based on equivalent sliding mode control method with a field-of-view constraint for anti-ship missiles, and this scheme requires no assumption of small angle approximation. By using the three-dimensional kinematic equation set constructed in a rotating coordinate system, Shin et al [23] designed a finite-time SMC-based guidance law to nullify the LOS angular rate at the interception time.…”

Section: Introductionmentioning

confidence: 99%

“…2. In contrast to previous research [22] and [26], the ADCG law is formulated based on a nonlinear integral sliding surface by using an improved reaching law. This improves the closed-loop error dynamic of the guidance system such that the guidance command features no chattering, and it enables the system to reach the sliding surface from any initial position in a finite time.…”

Section: Introductionmentioning

confidence: 99%

Cooperative guidance for active defence based on line-of-sight constraint under a low-speed ratio

Liu

Wang²,

Li³

et al. 2022

Aeronaut. j.

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In this study, an active defence cooperative guidance (ADCG) law that enables cheap and low-speed airborne defence missiles with low manoeuverability to accurately intercept fast and expensive attack missiles with high manoeuverability was designed to enhance the capability of aircraft for active defence. This guidance law relies on the line-of-sight (LOS) guidance method, and it realises active defence by adjusting the geometric LOS relationship involving an attack missile, a defence missile and an aircraft. We use a nonlinear integral sliding surface and an improved second-order sliding mode reaching law to design the guidance law. This can not only reduce the chattering phenomenon in the guidance command, but it can also ensure that the system can reach the sliding surface from any initial position in a finite time. Simulations were carried out to verify the proposed law using four cases: different manoeuvering modes of the aircraft, different speed ratios of the attack and defence missiles, different reaching laws applied to the ADCG law and a robustness analysis. The results show that the proposed guidance law can enable a defence missile to intercept an attack missile by simultaneously using information about the relative motions of the attack missile and the aircraft. It is also highly robust in the presence of errors and noise.

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Guidance Law with Desired Impact Time and FOV Constrained for Antiship Missiles Based on Equivalent Sliding Mode Control

Cited by 11 publications

References 21 publications

Model-Free Robust Backstepping Adaptive Cruise Control

Model-Free Robust Backstepping Adaptive Cruise Control

Fractional-Order Sliding Mode Guidance Law for Intercepting Hypersonic Vehicles

Cooperative guidance for active defence based on line-of-sight constraint under a low-speed ratio

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