Terminal Guidance for Impact Attitude Angle Constrained Flight Trajectories

Kim, M.; Grider, Kelly V.

doi:10.1109/taes.1973.309659

Cited by 390 publications

(133 citation statements)

References 2 publications

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“…The first published work on this problem was by Kim and Grider, 1 and considers the guidance of a ballistic reentry vehicle. York and Pastrick 2 extended this work by including a first-order autopilot.…”

Section: Introductionmentioning

confidence: 99%

Circular-Navigation-Guidance Law for Precision Missile/Target Engagements

Manchester

Savkin

2006

Journal of Guidance, Control, and Dynamics

140

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A new precision guidance law with impact angle constraint for a two-dimensional planar intercept is presented. It is based on the principle of following a circular arc to the target, hence the name circular navigation guidance. The guidance law does not require range-to-target information. We prove that it attains a perfect intercept under certain ideal conditions. In a broader range of conditions, it is shown to perform favorably when compared to another law from the literature.

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Section: Introductionmentioning

confidence: 99%

Circular-Navigation-Guidance Law for Precision Missile/Target Engagements

Manchester

Savkin

2006

Journal of Guidance, Control, and Dynamics

140

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“…As an application of OP theory, the optimal and suboptimal guidance laws with impact angle constraint for reentry vehicles in the vertical plane were put forward by Kim and Grider [5] . They were further improved by York and Pastrick [6] through matching the guidance law to a firstorder autopilot.…”

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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“…The authors in [11] proposed a suboptimal guidance law for reentry This is an Open Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/bync/3.0/) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited. …”

Section: Introductionmentioning

confidence: 99%

Adaptive nonsingular sliding mode based guidance law with terminal angular constraint

He¹,

Lin²

2014

International Journal of Aeronautical and Space Sciences

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In this paper, a new adaptive nonsingular terminal sliding mode control theory based impact angle guidance law for intercepting maneuvering targets was documented. In the design procedure, a new adaptive law for target acceleration bound estimation was presented, which allowed the proposed guidance law to be used without the requirement of the information on the target maneuvering profiles. With the aid of Lyapunov stability criteria, the finite-time convergent characteristics of the line-of-sight angle and its derivative were proven in theory. Numerical simulations were also performed under various conditions to demonstrate the effectiveness of the proposed guidance law.

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Terminal Guidance for Impact Attitude Angle Constrained Flight Trajectories

Cited by 390 publications

References 2 publications

Circular-Navigation-Guidance Law for Precision Missile/Target Engagements

Circular-Navigation-Guidance Law for Precision Missile/Target Engagements

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

Adaptive nonsingular sliding mode based guidance law with terminal angular constraint

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