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Relevant bibliographies by topics / Minimum-time Guidance

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Journal articles

Academic literature on the topic 'Minimum-time Guidance'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Minimum-time Guidance"

1

Yamaoka, Seiji. "Minimum-Time Guidance and Control Law for High Maneuvering Missile." International Journal of Aeronautical and Space Sciences 10, no. 1 (2009): 46–58. http://dx.doi.org/10.5139/ijass.2009.10.1.046.

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2

UENO, Seiya. "Minimum-Time Turns of Aircraft by Feedback Guidance and Control Law." Journal of the Japan Society for Aeronautical and Space Sciences 45, no. 516 (1997): 29–35. http://dx.doi.org/10.2322/jjsass1969.45.29.

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3

Indig, Nahshon, Joseph Z. Ben-Asher, and Erez Sigal. "Near-Optimal Minimum-Time Guidance Under Spatial Angular Constraint in Atmospheric Flight." Journal of Guidance, Control, and Dynamics 39, no. 7 (2016): 1563–77. http://dx.doi.org/10.2514/1.g001485.

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4

Ariba, Yassine, Denis Arzelier, and Laura Sofia Urbina-Iglesias. "Minimum-Fuel Fixed-Time Impulsive Elliptic Glide-Slope Guidance Algorithms Using Semidefinite Programming." Journal of Guidance, Control, and Dynamics 41, no. 9 (2018): 1873–87. http://dx.doi.org/10.2514/1.g003395.

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5

Alamir, Mazen. "Nonlinear receding horizon sub-optimal guidance law for the minimum interception time problem." Control Engineering Practice 9, no. 1 (2001): 107–16. http://dx.doi.org/10.1016/s0967-0661(00)00085-x.

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6

Zhou, Guanqun, and Qunli Xia. "A Guidance Strategy for Strapdown Seeker considering Minimum Field-of-View Angle Constraint." International Journal of Aerospace Engineering 2020 (June 19, 2020): 1–11. http://dx.doi.org/10.1155/2020/5247257.

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An off-axis strapdown seeker in missile may lead to a minimum field-of-view (FOV) angle constraint problem. The goal of this paper is to deal with the problem in guidance. Analysis of kinematics proves that on the premise of attacking stationary target, seeker look angle comes to 0 before or at the end time, and seeker will lose target finally. In order to reduce the distance of seeker losing target, a guidance strategy is proposed to sustain minimum FOV angle constraint during flight. The strategy can be applied on guidance laws with independent orders in longitudinal and lateral channels. By means of a certain rolling maneuver, it keeps the target in the seeker’s limited FOV. Moreover, a lateral guidance order compensation is utilized in the strategy to maintain seeker look angle. Simulations and comparisons are conducted to demonstrate the strategy’s effectiveness. Results show that the guidance strategy can sustain minimum FOV angle constraint longer than classical guidance method.

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7

Wu, Zhenglong, Zhenyu Guan, Chengwei Yang, and Jie Li. "Terminal Guidance Law for UAV Based on Receding Horizon Control Strategy." Complexity 2017 (2017): 1–19. http://dx.doi.org/10.1155/2017/2750172.

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Terminal guidance law against the maneuvering target is always the focal point. Most of the literatures focus on estimating the acceleration of target and time to go in guidance law, which are difficult to acquire. This paper presents a terminal guidance law based on receding horizon control strategy. The proposed guidance law adopts the basic framework of receding horizon control, and the guidance process is divided into several finite time horizons. Then, optimal control theory and target motion prediction model are used to derive guidance law for minimum time index function with continuous renewal of original conditions at the initial time of each horizon. Finally, guidance law performs repeated iteration until intercepting the target. The guidance law is of subprime optimal type, requiring less guidance information, and does not need to estimate the acceleration of target and time to go. Numerical simulation has verified that the proposed guidance law is more effective than traditional methods on constant and sinusoidal target with bounded acceleration.

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8

Ariba, Yassine, Denis Arzelier, and Laura Sofia Urbina. "A New Glideslope Guidance Algorithm for Minimum-Fuel Fixed-Time Elliptic Rendezvous Using Semidefinite Programming." IFAC-PapersOnLine 50, no. 1 (2017): 7235–40. http://dx.doi.org/10.1016/j.ifacol.2017.08.1369.

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9

Kim, Kangsoo, and Tamaki Ura. "Applied Model-Based Analysis and Synthesis for the Dynamics, Guidance, and Control of an Autonomous Undersea Vehicle." Mathematical Problems in Engineering 2010 (2010): 1–23. http://dx.doi.org/10.1155/2010/149385.

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Model-based analysis and synthesis applied to the dynamics, guidance, and control of an autonomous undersea vehicle are presented. As the dynamic model for describing vehicle motion mathematically, the equations of motion are derived. The stability derivatives in the equations of motion are determined by a simulation-based technique using computational fluid dynamics analysis. The dynamic model is applied to the design of the low-level control systems, offering model-based synthetic approach in dynamics and control applications. As an intelligent navigational strategy for undersea vehicles, we present the optimal guidance in environmental disturbances. The optimal guidance aims at the minimum-time transit of a vehicle in an environmental flow disturbance. In this paper, a newly developed algorithm for obtaining the numerical solution of the optimal guidance law is presented. The algorithm is a globally working procedure deriving the optimal guidance in any deterministic environmental disturbance. As a fail-safe tactic in achieving the optimal navigation in environments of moderate uncertainty, we propose the quasi-optimal guidance. Performances of the optimal and the quasi-optimal guidances are demonstrated by the simulated navigations in a few environmental disturbances.

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10

Li, Bin, Defu Lin, Jiang Wang, and Song Tian. "Guidance law to control impact angle and time based on optimality of error dynamics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (2018): 3577–88. http://dx.doi.org/10.1177/0954410018801226.

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In this work, a new guidance law with a meaningful performance index is designed to satisfy terminal impact angle and impact time constraints based on optimal error dynamics, which can be used for salvo attacks or cooperative missions of multi-missile. The analytical solution of the proposed guidance law is a combination of trajectory shaping guidance law and an additional impact time error feedback term that is proportional to the difference between the desired and the true impact times. Trajectory shaping guidance law aims to achieve the desired terminal impact angle and zero miss distance, whereas the extra term aims to meet the desired impact time. The minimum and maximum feasible impact times that consider the seeker's field-of-view limit, terminal impact angle constraint, and missile's maneuvering acceleration limit are calculated to provide the feasible boundary range of the desired impact time. Numerical simulations of several engagement situations demonstrate the effectiveness of the proposed guidance law in the accuracy of terminal impact angle and impact time.

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