Sliding-Mode Guidance and Control for All-Aspect Interceptors with Terminal Angle Constraints

Kumar, Shashi Ranjan; Rao, Sachit; Ghose, Debasish

doi:10.2514/1.55242

Cited by 301 publications

(204 citation statements)

References 18 publications

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“…The following lemma establishes the fact that, BPNG-IAC law (10) can steer the missile to attack the target with arbitrary designated impact angle. [30].)…”

Section: Definitionmentioning

confidence: 98%

“…Let |ϕ(t 0 )| < π/2 and t f denote the final time of homing. The closed-loop guidance system with the BPNG-IAC law (10) is finite time convergent in the sense that…”

Section: Definitionmentioning

confidence: 99%

“…The BPNG law with large impact angle constraint proposed in [31] is given by a BPNG = N Vq − K V 2 α cos ϕ/R (10) where N ≥ 3, K ≥ 1 and…”

Section: Definitionmentioning

confidence: 99%

“…The issue of impact angle control guidance (IACG) has been addressed in an amount of works, from the biased proportional navigation guidance based IACG laws [8,9,13,21,31] to the optimal control theory based IACG laws [12,22,23], from the model predictive static programming technique based IACG laws [1,16] to the sliding mode control theory based IACG laws [4,10,11,14,20,28,32], too numerous to mention one by one.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Wang

Zhang

2015

Aerospace Science and Technology

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“…The following lemma establishes the fact that, BPNG-IAC law (10) can steer the missile to attack the target with arbitrary designated impact angle. [30].)…”

Section: Definitionmentioning

confidence: 98%

“…Let |ϕ(t 0 )| < π/2 and t f denote the final time of homing. The closed-loop guidance system with the BPNG-IAC law (10) is finite time convergent in the sense that…”

Section: Definitionmentioning

confidence: 99%

“…The BPNG law with large impact angle constraint proposed in [31] is given by a BPNG = N Vq − K V 2 α cos ϕ/R (10) where N ≥ 3, K ≥ 1 and…”

Section: Definitionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Wang

Zhang

2015

Aerospace Science and Technology

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“…However, it is always assumed in APN approaches that the target is stationary or the target's maneuvering path is known. Advanced guidance laws are designed based on modern control theories such as optimal control [4,5], sliding-mode control (SMC) [6,7], and robust control [8]. Compared with APN guidance laws, advanced guidance laws are more flexible to satisfy various requirements.…”

Section: Introductionmentioning

confidence: 99%

Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

Wang

Tang

Guo

et al. 2017

International Journal of Aerospace Engineering

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The implementation of advanced guidance laws with bearings-only measurements requires estimation of the range information. To improve estimation accuracy and satisfy the impact angle constraint, this paper proposes a two-phase optimal guidance law consisting of an observing phase and an attacking phase. In the observing phase, the determinant of Fisher information matrix is maximized to achieve the optimal observability and a suboptimal solution expressed by leading angle is derived analytically. Then, a terminal sliding-mode guidance law is designed to track the desired leading angle. In the followed attacking phase, an optimal guidance law is integrated with a switching term to satisfy both the impact angle constraint and the field-of-view constraint. Finally, comparison studies of the proposed guidance law and a traditional optimal guidance law are conducted on stationary targets and maneuvering targets cases. Simulation results demonstrate that the proposed guidance law is able to improve the range observability and achieve better terminal performances including impact angle accuracy and miss distance.

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Discrete‐Time Super‐Twisting Guidance Law with Actuator Faults Consideration

Wang

2017

Asian Journal of Control

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This paper proposes a robust fault‐tolerant guidance law against unknown maneuvering targets based on discrete‐time sliding mode control theory. To address this problem, a time‐delay observer is designed to estimate the lumped disturbance, which includes target maneuver as well as actuator faults. A robust discrete‐time guidance law is then synthesized based on the discrete‐time super‐twisting algorithm. Due to the principle of the super‐twisting algorithm, the presented guidance law is a naturally chattering‐free formulation. Detailed stability analysis shows that the line‐of‐sight angular rate under the proposed guidance law can be stabilized in a small region around zero. Simulation results are also provided to verify the effectiveness of the proposed approach.

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Sliding-Mode Guidance and Control for All-Aspect Interceptors with Terminal Angle Constraints

Cited by 301 publications

References 18 publications

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

Discrete‐Time Super‐Twisting Guidance Law with Actuator Faults Consideration

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