Continuous reaching law based three-dimensional finite-time guidance law against maneuvering targets

Si, Yulin; Song, Shenmin

doi:10.1177/0142331218757862

Cited by 12 publications

(16 citation statements)

References 33 publications

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“…To verify the performance of the designed guidance laws, the results are compared with those from the proportional navigation guidance law (PNGL) and fast nonsingular terminal sliding mode guidance law (FNTSMGL) (Si and Song, 2019).…”

Section: Simulationsmentioning

confidence: 99%

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

Tan

Song

2020

Transactions of the Institute of Measurement and Control

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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.

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Section: Simulationsmentioning

confidence: 99%

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

Tan

Song

2020

Transactions of the Institute of Measurement and Control

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“…Application of non-linear control theory to missile guidance with initial high heading errors have been the subject of many research papers (Bezick et al, 1995; Man et al, 2019; Si and Song, 2018; Taur, 2002). The first guidance law that reported successful interception of the target was the proportional navigation (PN) law (Adler, 1956).…”

Section: Introductionmentioning

confidence: 99%

Time-energy optimal guidance strategy for realistic interceptor using pseudospectral method

Banerjee

Nabi

Raghunathan

2020

Transactions of the Institute of Measurement and Control

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This paper proposes the use of Legendre pseudospectral method (PSM) to obtain the optimal guidance strategy for a two-dimensional interceptor problem. An optimal control problem is formulated that addresses the conflicting objective of minimizing the energy usage, along with minimizing the time taken by missile to capture the target. The PSM-based guidance strategy is compared with other conventional guidance laws such as pure proportional navigation (PPN) guidance law and also evolutionary algorithm inspired differential evolution tuned proportional navigation (DEPN) guidance law. A scheme by which the PSM guidance strategy can be applied online is also included in this paper. The cost function value and the interception time indicates the superiority of the PSM-based guidance strategy.

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“…Although the sliding surface is reached within a finite time, the finite-time convergence of the system states cannot be ensured. The finite-time control problem has been frequently studied for applications requiring time response constraint including robotic manipulator (Galicki, 2016), guidance system (Si and Song, 2019) and spacecraft (Ran et al, 2017). Finite-time stability approach not only guarantees finite-time convergence of the system states to their equilibrium, but it also yields a high-precision performance (Golestani et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

Fault-tolerant attitude control for flexible spacecraft subject to input and state constraint

Golestani

Esmaeilzadeh

Xiao

2020

Transactions of the Institute of Measurement and Control

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This paper considers the problem of fault-tolerant attitude control for a flexible spacecraft subject to input and state constraint. Particularly, a new sliding mode-based attitude control with fixed-time convergent for the flexible spacecraft is developed in which the convergence rate of the system state is improved both far from and at close range of the origin. In contrast to the existing complicated prescribed performance controls (PPC), the proposed PPC possesses a much simpler structure due to the use of a novel constraint concept without employing error transformation. It also introduces a modified prescribed performance function (MPPF) to explicitly determine the settling time. It is rigorously proved that the attitude variable is kept within the predefined constraint boundaries even when the actuator saturation is taken into account. Moreover, the proposed controller is inherently continuous and the chattering is effectively reduced. An adaptive mechanism is developed in which no prior knowledge of the lumped uncertainties is required. Finally, numerical simulations are presented to demonstrate that the proposed controller is able to successfully accomplish attitude control with high attitude pointing accuracy and stability. More specifically, it provides faster convergence (improvement percentage of convergence time (IP_CT) is about 18%) and more accurate control (improvement percentages of MRPs (IP_MRPs) and angular velocity (IP_AV) are about 60% and 80%, respectively) under healthy actuators. Values of IP_CT, IP_CT, and IP_AV are 50%, 99.9% and 99.9% under faulty actuators, respectively.

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Continuous reaching law based three-dimensional finite-time guidance law against maneuvering targets

Cited by 12 publications

References 33 publications

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

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

Time-energy optimal guidance strategy for realistic interceptor using pseudospectral method

Fault-tolerant attitude control for flexible spacecraft subject to input and state constraint

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