Circular Impact-Time Guidance

Tsalik, Ronny; Shima, Tal

doi:10.2514/1.g004074

Cited by 53 publications

(23 citation statements)

References 31 publications

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“…Proposition 1. For a missile-target engagement governed by the guidance command (18), the range and the heading error diminishes monotonically as the engagement progresses if σ 0 ∈ (π/2 0) and interception occurs when the heading error is zero.…”

Section: A Range Variation and Determination Of The Parameter Cmentioning

confidence: 99%

“…A closed-form formula for a control parameter as a function of desired impact time cannot be obtained using this method. The authors of [18] propose a circular trajectorybased guidance law that delivers an exact impact time. The approach's performance is determined by the controller parameters chosen, hence a tuning process is required to attain the optimum results.…”

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confidence: 99%

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Three Dimensional Nonlinear Guidance Law for Exact Impact Time Control

Saleem

Lisy

2022

IEEE Access

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This paper presents a nonlinear guidance law for controlling the impact time of a missiletarget engagement in three dimensions. The guidance law is initially formulated for a two-dimensional encounter before being extended to a three-dimensional scenario. The guidance law is constructed such that nonlinear kinematics are neither linearized nor approximated. The guidance law offers a precise closed-form expression for impact time, which is the principal contribution of this work. Choosing an integrable heading error profile is the central concept of this research for determining an accurate impact time. A two-step strategy is utilized to accomplish an interception at a predetermined time. Because the control parameter is related to the desired impact time with an exact expression, a simple and accurate control of impact time is attained. The method provides equations for calculating the minimum and maximum impact times, enabling the determination of the range of impact times that can be achieved. The proposed guidance law can ensure that the seeker field of view restriction is not violated, If the initial heading error is within this limit. The developed method is utilized in salvo attacks, in which multiple missiles simultaneously strike an enemy target, increasing the missiles' effectiveness against the target's self-defense mechanism. To validate the effectiveness of the proposed strategy, MATLAB-based numerical simulations of 2D and 3D engagements, including salvo attacks, are conducted. INDEX TERMSImpact time control, Salvo attack, Three dimensional engagement, Nonlinear guidance law, Field of view I. INTRODUCTION

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Section: A Range Variation and Determination Of The Parameter Cmentioning

confidence: 99%

mentioning

confidence: 99%

Three Dimensional Nonlinear Guidance Law for Exact Impact Time Control

Saleem

Lisy

2022

IEEE Access

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show abstract

“…, where x denotes the state variable, and u(v(t)) is saturated input denoted by (2). If A > 0 with the initial condition…”

Section: A Problem Statementmentioning

confidence: 99%

“…D URING the past two decades, adaptive control for nonlinear systems has attracted considerable attention and many important control schemes have been proposed and applied to the missile guidance systems [1][2][3][4][5][6]. These methods aim to increase the destructive power, or reduce the sensitivity to the target's maneuverability, or enhance the survivability of the missile.…”

Section: Introductionmentioning

confidence: 99%

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Zhang

2020

IEEE Access

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In this paper, a fuzzy observer-based tracking control scheme is proposed for a class of strict-feedback uncertain nonlinear system with input saturation. To facilitate the fuzzy logic system (FLS) design, the original uncertain nonlinear system is transformed into an output feedback system firstly. Then, an adaptive state observer is constructed. In order to efficiently tackle the input saturation, an auxiliary system (AS) is introduced. Using the estimated states and AS, the dynamic surface control (DSC) strategy is developed based on backstepping method. Under the DSC scheme, the tracking control problem is reduced to optimal regulation problem of an affine system. Subsequently, an adaptive dynamic programming (ADP) based optimal control scheme is proposed. The stability of the overall system is guaranteed by Lyapunov theory. Finally, guidance simulation is made to confirm the effectiveness of the developed control method.

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“…In open-loop cooperative guidance, which is also called time-constrained guidance, the expected time value has been determined before launching and no information interaction is needed between vehicles during the flight. Since Jeon et al [10] first proposed a time-constrained guidance law for antiship missiles in 2006, scholars have extensively studied open-loop cooperative guidance using different methods, such as improved proportional navigation [10][11][12], optimal control [13,14], sliding mode control [15][16][17], trajectory shaping [18][19][20], and trajectory optimization [9,21,22]. On the other hand, closed-loop cooperative guidance can be divided into centralized cooperative guidance and distributed cooperative guidance according to the different communication modes among vehicles.…”

Section: Introductionmentioning

confidence: 99%

Distributed Analytical Formation Control and Cooperative Guidance for Gliding Vehicles

Jia

Wang

et al. 2020

International Journal of Aerospace Engineering

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This paper addresses the analytical formation control and cooperative guidance problem for multiple hypersonic gliding vehicles under distributed communication. The gliding flight of the hypersonic gliding vehicle is divided into formation control phase and time coordination phase. In formation control phase, based on the idea of path tracking, the formation controller is designed using the second-order consensus protocol with normal positions as the coordination variables. In time coordination phase, based on the quasi-equilibrium gliding condition and the assumption of uniform deceleration motion, the analytical expression of time to go is derived. Then, the cooperative guidance method is developed using the first-order consensus protocol with time to go as the coordination variable. The proposed method takes full consideration of the characteristics of hypersonic gliding vehicle, such as complex nonlinear dynamics, no thrust, and quasi-equilibrium gliding condition, and no online numerical iteration is needed, which is well applicable for hypersonic gliding vehicles. Simulation results demonstrate the effectiveness of the formation control and cooperative guidance method.

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Circular Impact-Time Guidance

Cited by 53 publications

References 31 publications

Three Dimensional Nonlinear Guidance Law for Exact Impact Time Control

Three Dimensional Nonlinear Guidance Law for Exact Impact Time Control

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Distributed Analytical Formation Control and Cooperative Guidance for Gliding Vehicles

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