Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Geng, Shengtao; Zhang, Jie; Sun, Jinwei

doi:10.1177/0954410019835728

Cited by 8 publications

(8 citation statements)

References 28 publications

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“…In Lin et al (2020), a robust guidance method considering autopilot lag and input saturation was proposed by utilizing the adaptive control and sliding mode control. 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.…”

Section: Introductionmentioning

confidence: 99%

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

Wang

et al. 2021

Transactions of the Institute of Measurement and Control

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This paper presents an adaptive fixed-time guidance law for the three-dimensional interception guidance problem with impact angle constraints and control input saturation against a maneuvering target. First, a coupled guidance model formulated by the relative motion equation is established. On this basis, a fixed-time disturbance observer is employed to estimate the lumped disturbances. With the help of this estimation technique, the adaptive fixed-time sliding mode guidance law is designed to accomplish accurate interception. The stability of the closed-loop guidance system is proven by the Lyapunov method. Simulation results of different scenarios are executed to validate the effectiveness and superiority of the proposed guidance law.

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Section: Introductionmentioning

confidence: 99%

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

Wang

et al. 2021

Transactions of the Institute of Measurement and Control

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“…The IACG laws have been proposed in the previous literature over the past several decades. Various design methods, for example, optimal control, 1–8 proportional navigation guidance (PNG) law, 9 sliding mode control, 10,11 twisting control, 12 and feedback linearization, 13 have been applied to the IACG problems.…”

Section: Introductionmentioning

confidence: 99%

Trajectory shaping guidance law design using constraint-combining multiplier

Seo

Lee

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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A new design method for trajectory shaping guidance laws with the impact angle constraint is proposed in this study. The basic idea is that the multiplier introduced to combine the equations for the terminal constraints is used to shape a flight trajectory as desired. To this end, the general form of impact angle control guidance (IACG) is first derived as a function of an arbitrary constraint-combining multiplier using the optimal control. We reveal that the constraint-combining multiplier satisfying the kinematics can be expressed as a function of state variables. From this result, the constraint-combining multiplier to achieve a desired trajectory can be obtained. Accordingly, when the desired trajectory is designed to satisfy the terminal constraints, the proposed method directly can provide a closed form of IACG laws that can achieve the desired trajectory. The potential significance of the proposed result is that various trajectory shaping IACG laws that can cope with various guidance goals can be readily determined compared to existing approaches. In this study, several examples are shown to validate the proposed method. The results also indicate that previous IACG laws belong to the subset of the proposed result. Finally, the characteristics of the proposed guidance laws are analyzed through numerical simulations.

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“…In fact, the missile's autopilot has high-order dynamic characteristics; therefore, it is more reasonable to approximate the missile's autopilot to the second-order dynamic characteristics. In [24], the guidance law considers the second-order dynamic characteristics of the missile autopilot, but it cannot converge in a finite time. In the process of the sliding mode control design, the system disturbance is usually eliminated by selecting the appropriate switching gain.…”

Section: Introductionmentioning

confidence: 99%

“…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. It is of great significance to study a finite-time convergence guidance law that can accurately intercept highly maneuvering targets by simultaneously considering the missile autopilot second-order dynamic characteristics, acceleration saturation constraint, and impact angle constraint.…”

mentioning

confidence: 99%

“…(3) Focusing on the problem of autopilot dynamic delay, the backstepping control method [40] is introduced into the guidance law design. For the traditional backstepping control methods, to avoid the problem of "differential expansion" caused by multiple derivatives of the virtual control variables, first-order linear low-pass filter [24] is usually used to obtain the derivative of the virtual control variables. However, the first-order linear low-pass filter cannot guarantee the system's finite-time convergence.…”

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confidence: 99%

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A Novel Guidance Law for Intercepting a Highly Maneuvering Target

Zhang

2021

International Journal of Aerospace Engineering

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Given the resolution of the guidance for intercepting highly maneuvering targets, a novel finite-time convergent guidance law is proposed, which takes the following conditions into consideration, including the impact angle constraint, the guidance command input saturation constraint, and the autopilot second-order dynamic characteristics. Firstly, based on the nonsingular terminal sliding mode control theory, a finite-time convergent nonsingular terminal sliding mode surface is designed. On the back of the backstepping control method, the virtual control law appears. A nonlinear first-order filter is constructed so as to address the “differential expansion” problem in traditional backstepping control. By designing an adaptive auxiliary system, the guidance command input saturation problem is dealt with. The RBF neural network disturbance observer is used for estimating the unknown boundary external disturbances of the guidance system caused by the target acceleration. The parameters of the RBF neural network are adjusted online in real time, for the purpose of improving the estimation accuracy of the RBF neural network disturbance observer and accelerating its convergence characteristics. At the same time, an adaptive law is designed to compensate the estimation error of the RBF neural network disturbance observer. Then, the Lyapunov stability theory is used to prove the finite-time stability of the guidance law. Finally, numerical simulations verify the effectiveness and superiority of the proposed guidance law.

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Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Cited by 8 publications

References 28 publications

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

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

Trajectory shaping guidance law design using constraint-combining multiplier

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

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