Impact Time and Angle Guidance with Sliding Mode Control

Harl, Nathan; Balakrishnan, S. N.

doi:10.2514/6.2009-5897

Cited by 61 publications

(88 citation statements)

References 2 publications

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“…Although the tracking error can converge to zero and the convergence speed can be adjusted by selecting different parameters, it cannot converge to zero in finite-time [22]. The linear sliding manifold can only concern the exponential stability during the sliding phase; as a result, it is difficult for the tracking accuracy to ensure [23].…”

Section: Introductionmentioning

confidence: 99%

Target Tracking Based on a Nonsingular Fast Terminal Sliding Mode Guidance Law by Fixed-Wing UAV

Cai

Zhao

et al. 2017

Applied Sciences

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This paper proposes a modified nonsingular fast terminal sliding mode (NFTSM) guidance law to solve the problem of ground moving target tracking for fixed-wing unmanned aerial vehicle (UAV) in a planar environment. Firstly, the loitering algorithm is analysed, which can steer the UAV to follow and circle around a ground moving target with the desired distance by heading angle control. Secondly, the effects of different parameters on the convergence time of sliding manifold is presented which is helpful for the designing of sliding manifold. Singularity can be avoided by using a modified saturation function which is obtained through a small range around the null point. Moreover, the NFTSM sliding manifold is used in the loitering algorithm. By using the Lyapunov theory, the finite-time convergence of the proposed method has been proved in the the reaching phase and the sliding phase. In order to verify the approach's feasibility and benefits, numerical simulations are performed by using a moving target with three different motion states in comparison with the conventional sliding model control method. Simulation results indicate that, under the proposed NFTSM guidance law, the UAV can reach the desired distance in a short time.

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Section: Introductionmentioning

confidence: 99%

Target Tracking Based on a Nonsingular Fast Terminal Sliding Mode Guidance Law by Fixed-Wing UAV

Cai

Zhao

et al. 2017

Applied Sciences

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“…In [21], the PNG law with a time-varying navigation constant, called cooperative proportional navigation (CPN), was suggested to make the missiles performing the cooperative attack mission intercept the target at the same arrival time. Based on nonlinear control design methods, impact time and angle control laws were derived in [22,23,24]. In [22], the feedback linearization method is used to obtain the impact time control law, and the backstepping control method and modified PNG law are utilized to design the impact time and angle controller in [23].…”

Section: Introductionmentioning

confidence: 99%

“…In [22], the feedback linearization method is used to obtain the impact time control law, and the backstepping control method and modified PNG law are utilized to design the impact time and angle controller in [23]. The impact time and angle control law in [24] was derived from the proposed line-of-sight rate shaping technique and second-order sliding mode control, in which both the line-of-sight (LOS) angle and rate profiles are determined to satisfy given terminal constraints and then sliding mode control is designed to track the obtained LOS rate profile. A homing guidance law, consisting of the well-known optimal impact angle control law and an additional command to meet the impact time constraint, was presented in [25].…”

Section: Introductionmentioning

confidence: 99%

Polynomial Function Based Guidance for Impact Angle and Time Control

KIM

2015

Journal of the Korea Society for Industrial and Applied Mathema

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ABSTRACT. In this paper, missile homing guidance laws to control the impact angle and time are proposed based on the polynomial function. To derive the guidance commands, we first assume that the acceleration command profile can be represented as a polynomial function with unknown coefficients. After that, the unknown coefficients are determined to achieve the given terminal constrains. Using the determined coefficients, we can finally obtain the state feedback guidance command. The suggested approach to design the guidance laws is simple and provides the more generalized optimal solutions of the impact angle and time control guidance.

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“…Shi et al [22] proposed to use RBF neural network to reduce the chattering of SMC, and Rao and Ghose [23] studied the SMC guidance laws with terminal impact angle constraint by using dual sliding surfaces so that the missile could intercept the targets at a desired impact angle. Harl and Balakrishnan [24] presented a sliding mode-based impact time and angle guidance law for engaging a modern warfare ship. In their works, they combined a line-of-sight shaping technique with a second-order sliding mode approach to satisfy the impact time and angle constraints.…”

Section: Introductionmentioning

confidence: 99%

Finite time convergent wavelet neural network sliding mode control guidance law with impact angle constraint

Zhang

Han

et al. 2015

Int. J. Autom. Comput.

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This paper presents a novel guidance law to intercept non-maneuvering targets with impact angle and lateral acceleration command constraints. Firstly, we formulate the impact angle control to track the desired line-of-sight (LOS) angle, which is achieved by selecting the missile s lateral acceleration to enforce the sliding mode on a sliding surface at impact time. Secondly, we use the Lyapunov stability theory to prove the stability and finite time convergence of the proposed nonlinear sliding surface. Thirdly, we introduce the wavelet neural network (WNN) to adaptively update the additional control command and reduce the high-frequency chattering of sliding mode control (SMC). The proposed guidance law, denoted WNNSMC guidance law with impact angle constraint, combines the SMC methodology with WNN to improve the robustness and reduce the chattering of the system. Finally, numerical simulations are performed to demonstrate the validity and effectiveness of the WNNSMC guidance law.

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Impact Time and Angle Guidance with Sliding Mode Control

Cited by 61 publications

References 2 publications

Target Tracking Based on a Nonsingular Fast Terminal Sliding Mode Guidance Law by Fixed-Wing UAV

Target Tracking Based on a Nonsingular Fast Terminal Sliding Mode Guidance Law by Fixed-Wing UAV

Polynomial Function Based Guidance for Impact Angle and Time Control

Finite time convergent wavelet neural network sliding mode control guidance law with impact angle constraint

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