An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

Zhang, Wenjie; Fu, Shengnan; Wei, Li; Xia, Qing

doi:10.21629/jsee.2020.01.17

Cited by 14 publications

(8 citation statements)

References 16 publications

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“…To confirm the superiority of the guidance law proposed in this paper, the simulation was compared with the nonlinear terminal sliding mode guidance law (NTSMGL) [47] and the integral sliding mode guidance law (ISMGL) [3]. Under the action of the three guidance laws, the initial parameters of the missile are set as x m ð0Þ = 10 km, y m ð0Þ = 0 km, V xm ð0Þ = 1200 m/s, and V ym ð0Þ = 0 m/s, and the expected terminal LOS angle of the missile is set as q d = 15 °.…”

Section: Different Guidance Law Simulationsmentioning

confidence: 99%

“…It is well-known that the proportional navigation guidance law (PNGL) has been widely employed and researched for decades in terms of its advantages such as simple structure, robustness and practicability [3]. The guidance commands generated by the classic proportional guidance law (PNGL) are proportional to the line-of-sight (LOS) angular rate of the missile to target.…”

Section: Introductionmentioning

confidence: 99%

“…(1) Compared with existing impact angle constraint guidance laws [1][2][3]16] etc., the proposed guidance law not only realizes the interception of highly maneuvering targets in a finite time but also is simultaneously in consideration of the autopilot's second-order dynamics characteristics, acceleration saturation constraint, and impact angle constraint…”

mentioning

confidence: 99%

See 2 more Smart Citations

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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Section: Different Guidance Law Simulationsmentioning

confidence: 99%

Section: Introductionmentioning

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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“…Adding a second-order sliding mode observer, [28] proposed a robust guidance law with autopilot lag consideration. Reference [29] presented an integral sliding mode guidance law which could resolve the steady-state error problem of the traditional SMC. An optimization design with the neural network was designed to improve the fuzzy variable structure of sliding mode in [30].…”

Section: Introductionmentioning

confidence: 99%

Measurement Compensation for Time-Delay Seeker and Three-Dimensional Adaptive Guidance Law Design

Liu

Qiao³

et al. 2021

Sensors

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The time delay of seekers has grown to be a serious issue for tactical missile guidance with the development of flight vehicle technologies. To address the problem, a measurement compensation system for the seeker, with lags and delays based on predictive active disturbance rejection control, is proposed. In addition, to eliminate the effects of target maneuvers to the tactical missile guidance, an adaptive finite-time convergent sliding mode guidance law, based on super-twisting algorithm, is proposed in three-dimensional missile-target engagement kinematics. Specifically, the compensation system consists of a predictive tracking structure and an active disturbance rejection control system, which could follow a virtual measurement without lags and delays. The compensation system has advantages in disturbance rejection and model inaccuracy addressing, compared with existing compensation methods for seeker measurement. As for the sliding mode guidance law design, the proposed approach is based on an improved super-twisting algorithm with fast convergent adaptive gains, which has advantages in addressing unknown but bounded target maneuvers and avoiding chattering of the classical sliding mode control. As a result, the measurement compensation system and the adaptive sliding mode guidance law is verified robust and effective under the proposed constraints by the simulation examples.

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“…By employing a second-order sling mode observer, reference [18] proposed a nonsingular terminal sliding mode guidance law with autopilot lag consideration. The integral sliding mode guidance law presented in [19] addressed the problem of steady-state error of the traditional SMC. Reference [20] implemented an optimization design by using the neural network, which improved the fuzzy variable structure of the sliding mode.…”

Section: Introductionmentioning

confidence: 99%

Multivariable Adaptive Super-Twisting Guidance Law Based on Barrier Function

Liu

et al. 2021

Applied Sciences

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For tactical missiles, sliding mode control and super-twisting algorithms have been widely studied in the area of guidance law design. However, these methods require the information of the target accelerations and the target acceleration derivatives, which is always unknown in practice. In addition, guidance laws utilizing these tools always have chattering phenomena and large acceleration commands. To solve these problems, this article introduces a barrier function based super twisting controller and expands the controller to a multivariable adaptive form. Consequently, a multivariable adaptive super-twisting guidance law based on barrier function is proposed. Moreover, the stability of the guidance law is analyzed, and the effectiveness and the robustness are demonstrated by three simulation examples. Compared with previous guidance laws using sliding mode control or super-twisting algorithm, the one proposed in this paper does not require the information of target accelerations, nor target acceleration derivatives; it has smaller super-twisting gains so that has smaller acceleration commands; it can increase and decrease the gains to follow the target accelerations and maintain the sliding mode, and it does not chatter.

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An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

Cited by 14 publications

References 16 publications

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

Measurement Compensation for Time-Delay Seeker and Three-Dimensional Adaptive Guidance Law Design

Multivariable Adaptive Super-Twisting Guidance Law Based on Barrier Function

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