A guidance law with finite time convergence accounting for autopilot lag

Sun, Shang; Zhou, Di; Hou, Wentao

doi:10.1016/j.ast.2011.12.016

Cited by 125 publications

(90 citation statements)

References 19 publications

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“…Since the terminal sliding mode guidance law (TSMG), which is presented in [18], is a guidance law with finite time convergence containing first-order autopilot dynamics, it is simulated under the same condition to verify the effectiveness and robustness of the proposed guidance law. In [18] it is shown the TSMG has obtained better results, compared with the finite-time convergent guidance law [17] and the adaptive sliding-mode guidance law [6]. In this section, the following simulation results will prove that the proposed guidance law has gained the better performance in comparison with TSM guidance law.…”

Section: Simulation Resultsmentioning

confidence: 99%

See 1 more Smart Citation

Integral Backstepping Sliding Mode Guidance Law with Finite Time Convergence

Golestani¹,

Fakharian

2014

IJCA

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Section: Simulation Resultsmentioning

confidence: 99%

“…Many research activities have been done to design finite time convergent guidance laws which are able to guide the LOS angular rate to converge to zero in a finite time; see, for example, [16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Integral Backstepping Sliding Mode Guidance Law with Finite Time Convergence

Golestani¹,

Fakharian

2014

IJCA

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“…In order to design a finite time convergent guidance law, we introduce some results about finite time stability of nonlinear systems [30] . Definition 1.…”

Section: Analysis Of Finite Time Convergencementioning

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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“…The angular rate gyroscope has a low resolution, which will not be sensitive to the movement of low-speed target, and the angular rate gyroscope has a poor nonlinearity, which will cause inaccurate measuring information. The influence of angular rate gyroscope resolution on the aircraft hitting accuracy can be calculated from the two formulas below [4][5][6][7][8][9][10][11][12].…”

Section: Main Factors For System Errormentioning

confidence: 99%

“…The launching plan of target scanning line information setting is superior to the launching plan of front light spot aiming, and it is characterized by simple operation and high launching precision etc. [1,6,7,8].…”

Section: Introductionmentioning

confidence: 99%