Finite-time convergent sliding-mode guidance law based on Extended-State-Observer

Zhang, Denghui; Chao, Tao; Wang, Songyan; Yang, Ming

doi:10.1109/cgncc.2016.7829124

Cited by 3 publications

(6 citation statements)

References 7 publications

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“…In particular, the size of miss distance can reflect the effectiveness of the interception strategy directly. In this respect, the effect achieved in this paper is nearly one time higher than that in Zhang et al (2015). Fig.…”

Section: Simulation Results and Analysismentioning

confidence: 48%

“…In order to verify the effectiveness of the interception strategy designed in this paper, three different interception methods of attack interception, pursuit interception, and forward interception are respectively compared with the finite-time sliding mode convergence strategy shown in Eq. 11 of Zhang et al (2015).…”

Section: Simulation Results and Analysismentioning

confidence: 99%

“…However, the required control of the interception strategy in this paper is smaller. The finite-time sliding mode convergence strategy described in Zhang et al (2015) during the terminal guidance stage has a certain frequency of chattering. As a comparison of the strategies proposed in this paper, the performance of strategy in the terminal guidance stage is slightly improved, which makes the output of the controller smoother, thus the effectiveness of improvements made in selection of the approach law is verified.…”

Section: Simulation Results and Analysismentioning

confidence: 99%

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Robust Finite-Time Control for Guidance Law with Uncertainties in Missile Dynamics

Tao,

Shi,

Zhang

et al. 2024

J. Aerosp. Technol. Manag.

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In this paper, the robust finite-time control for impact angle guidance of missile dynamic system with uncertainties is investigated by combining linear extended state observer (LESO) and adaptive non-singular fast terminal sliding mode method. Specially for dealing with existing uncertainties including time-varying parametric perturbation and nonparametric disturbances in high order line-of-sight rates and target acceleration, a robust LESO strategy is proposed for designing sliding mode-based impact angle guidance, which can guarantee that estimation error converges to the neighborhood of the origin in finite-time. Based on the proposed LESO framework, an adaptive non-singular fast terminal sliding mode guidance law is considered for realizing interception of maneuvering targets, which can guarantee asymptotically stability of the system. Simulation results are shown for confirming effectiveness of the proposed guidance strategy of this paper. Compared with former methods, accuracy of estimation is increased by nearly two times, and miss distance is reduced by nearly two times.

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Section: Simulation Results and Analysismentioning

confidence: 48%

Section: Simulation Results and Analysismentioning

confidence: 99%

Section: Simulation Results and Analysismentioning

confidence: 99%

See 1 more Smart Citation

Robust Finite-Time Control for Guidance Law with Uncertainties in Missile Dynamics

Tao,

Shi,

Zhang

et al. 2024

J. Aerosp. Technol. Manag.

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“…The above references are based on traditional guidance laws for attack and propose anti-interference algorithms based on the algorithm of the seeker head, without using more robust and accurate modern guidance laws for simulation verification. Currently, various modern control methods are applied in the field of flight vehicle guidance, such as sliding mode control [5][6][7], finite-time control [8][9][10], optimal control [11][12][13], etc. However, many modern guidance laws are designed based on asymptotic stability.…”

Section: Introductionmentioning

confidence: 99%

“…However, the above references consider the target maneuver as a bounded disturbance compensation in the guidance law, without accurate estimation of the target maneuver. In References [10,[17][18][19][20], an ESO is used to observe and compensate for the target maneuver in real time, solve the problem of excessive overload in the terminal guidance process effectively, and provide the flight vehicle with a higher interception accuracy. References [7,21,22] adopt an FTDO to estimate the target maneuver.…”

Section: Introductionmentioning

confidence: 99%

Design of Convergent and Accurate Guidance Law with Finite Time in Complex Adversarial Scenarios

Ding,

Wang,

et al. 2024

Aerospace

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The target can deceive the flight vehicle by releasing an infrared decoy to make the line-of-sight (LOS) angle rate deflect greatly, thus causing the flight vehicle to miss the target. Therefore, in order to accurately strike the target in complex adversarial scenarios, this paper proposes a finite-time convergence guidance law (FTCG) combined with a finite-time disturbance observer (FTDO). The complex adversarial scenario is established by combining the relative motion model between the flight vehicle and the target and the motion model of the infrared decoy. Based on this, considering the dynamic characteristic of the flight vehicle’s autopilot, a guidance model is obtained. Utilizing sliding mode control theory and finite-time control theory, an FTCG of the LOS angle rate is designed. Then, the finite-time convergence of the guidance law is proved and the total convergence time is derived. Finally, for the target maneuvering that is difficult to measure in the guidance law, an FTDO is used to estimate and compensate for the target maneuvering in the guidance law. Simulation results show that the FTCG can make the LOS angle rate quickly converge and accurately strike the target in different scenarios, with a good guidance accuracy and robustness. Compared with the sliding mode guidance law (SMGL) and the adaptive sliding mode guidance law (ASMGL) based on an extended state observer (ESO), the advantages of the designed guidance law are illustrated. Finally, FTCG is extended to be three dimensional and compared with the proportional navigation guidance law (PNG) to further illustrate its effectiveness in a three-dimensional coordinate system.

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Finite-Time Convergent Sliding-Mode Guidance Law for High-Speed Flight Vehicle with Bearings-Only Measurement

Wang

2020

2020 International Conference on Unmanned Aircraft Systems (ICUAS)

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Finite-time convergent sliding-mode guidance law based on Extended-State-Observer

Cited by 3 publications

References 7 publications

Robust Finite-Time Control for Guidance Law with Uncertainties in Missile Dynamics

Robust Finite-Time Control for Guidance Law with Uncertainties in Missile Dynamics

Design of Convergent and Accurate Guidance Law with Finite Time in Complex Adversarial Scenarios

Finite-Time Convergent Sliding-Mode Guidance Law for High-Speed Flight Vehicle with Bearings-Only Measurement

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