3-D Evasive Maneuver Policy for Anti-Ship Missiles Against Close-In Weapon Systems

Ryoo, Chang-Kyung; Whang, Ick‐Ho; Tahk, Min-Jea

doi:10.2514/6.2003-5653

Cited by 14 publications

(14 citation statements)

References 2 publications

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“…where is a constant parameter. However, if is time-varying, (8) cannot be derived from (7). In other word, the estimation error of TTG may be very large if we still use the estimation methods in [8][9][10][11][12][13][18][19][20].…”

Section: Problem Formulationmentioning

confidence: 99%

“…Proportional navigation guidance law (PNGL) [1][2][3][4] has been widely used in the area of homing guidance, which can achieve excellent performance in the presence of a nonmaneuvering target. However, in recent years, with the development of defense systems such as space defense antimissile system [5], electronic countermeasure system (ECMS) [6], and close-in weapon system (CIWS) [7], the survivability of attack missile with conventional guidance scheme has been intimidated. Fortunately, most defense systems have "one-toone" feature; thus the salvo attack of multiple missiles can be one of the most effective countermeasures for missiles against the threats of defense systems.…”

Section: Introductionmentioning

confidence: 99%

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Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity

Zhou

Wang

Zhao

2016

Mathematical Problems in Engineering

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The problem of impact-time-control guidance (ITCG) for the homing missile with time-varying velocity is addressed. First, a novel ITCG law is proposed based on the integral sliding mode control (ISMC) method. Then, a salvo attack algorithm is designed based on the proposed guidance law. The performances of the conventional ITCG laws strongly depend on the accuracy of the estimated time-to-go (TTG). However, the accurate estimated TTG can be obtained only if the missile velocity is constant. The conventional ITCG laws were designed under the assumption that the missile velocity is constant. The most attractive feature of this work is that the newly proposed ITCG law relaxes the constant velocity assumption, which only needs the variation range of the missile velocity. Finally, the numerical simulation demonstrates the effectiveness of the proposed method.

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Section: Problem Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity

Zhou

Wang

Zhao

2016

Mathematical Problems in Engineering

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“…Int'l J. of Aeronautical & Space Sci. 18 (4), 719-728 (2017) An optimal evasive maneuver for subsonic Anti-Ship Missiles (ASM) has been studied against Close-in Weapon System (CIWS) [3]. The CIWS is a common short-range IADS for naval ships that are usually equipped with cannon as the defensive weapon.…”

Section: Introductionmentioning

confidence: 99%

“…Since the ASM moves with constant acceleration at any moment, the CIWS is able to aim at the predicted intercept position. In [3], the authors have defined a time-varying weighted sum of the inverse of the aiming errors as a cost function which to be minimized. Inspired by the study above, a direct optimization technique using Co-Evolutionary Augmented Lagrangian Method (CEALM) was applied in [4], which the capturability analysis is proven using Lyapunov-like approach.…”

Section: Introductionmentioning

confidence: 99%

“…Inspired by the study above, a direct optimization technique using Co-Evolutionary Augmented Lagrangian Method (CEALM) was applied in [4], which the capturability analysis is proven using Lyapunov-like approach. Both studies in [3] and [4] generate a type of barrel roll evasive maneuver, however, a large barrel roll maneuver could increase the miss distance at the terminal time.…”

Section: Introductionmentioning

confidence: 99%

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Impact Angle Control Guidance Synthesis for Evasive Maneuver against Intercept Missile

Yogaswara¹,

Hong²,

Tahk³

et al. 2017

IJASS

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This paper proposes a synthesis of new guidance law to generate an evasive maneuver against enemy's missile interception while considering its impact angle, acceleration, and field-of-view constraints. The first component of the synthesis is a new function of repulsive Artificial Potential Field to generate the evasive maneuver as a real-time dynamic obstacle avoidance. The terminal impact angle and terminal acceleration constraints compliance are based on Time-to-Go Polynomial Guidance as the second component. The last component is the Logarithmic Barrier Function to satisfy the field-of-view limitation constraint by compensating the excessive total acceleration command. These three components are synthesized into a new guidance law, which involves three design parameter gains. Parameter study and numerical simulations are delivered to demonstrate the performance of the proposed repulsive function and guidance law. Finally, the guidance law simulations effectively achieve the zero terminal miss distance, while satisfying an evasive maneuver against intercept missile, considering impact angle, acceleration, and field-of-view limitation constraints simultaneously.

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Impact Angle Control Law with Sinusoidal Evasive Maneuver for Survivability Enhancement

Lee

Ryoo

2018

Int. J. Aeronaut. Space Sci.

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3-D Evasive Maneuver Policy for Anti-Ship Missiles Against Close-In Weapon Systems

Cited by 14 publications

References 2 publications

Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity

Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity

Impact Angle Control Guidance Synthesis for Evasive Maneuver against Intercept Missile

Impact Angle Control Law with Sinusoidal Evasive Maneuver for Survivability Enhancement

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