Guidance Synthesis for Evasive Maneuver of Anti-Ship Missiles Against Close-In Weapon Systems

Kim, Yoon-Hwan; Ryoo, Chang-Kyung; Tahk, Min-Jea

doi:10.1109/taes.2010.5545195

Cited by 21 publications

(8 citation statements)

References 6 publications

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“…According to Figure 1, the mass-point dynamics of the missile and the target are [9,29] where and are the specified impact angle and time, respectively. When multiple missiles are synchronized by their onboard clocks separately, a salvo attack can be achieved automatically without any communication.…”

Section: Kinematics Equations the Missile-target Relative Kinematicsmentioning

confidence: 99%

Receding Horizon Trajectory Optimization with Terminal Impact Specifications

Zhang

Sun

Chen

et al. 2014

Mathematical Problems in Engineering

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The trajectory optimization problem subject to terminal impact time and angle specifications can be reformulated as a nonlinear programming problem using the Gauss pseudospectral method. The cost function of the trajectory optimization problem is modified to reduce the terminal control energy. A receding horizon optimization strategy is implemented to reject the errors caused by the motion of a surface target. Several simulations were performed to validate the proposed method via the C programming language. The simulation results demonstrate the effectiveness of the proposed algorithm and that the real-time requirement can be easily achieved if the C programming language is used to realize it.

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Section: Kinematics Equations the Missile-target Relative Kinematicsmentioning

confidence: 99%

Receding Horizon Trajectory Optimization with Terminal Impact Specifications

Zhang

Sun

Chen

et al. 2014

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%

“…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. 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%

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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“…From the flight control standpoint, in order to enhance the survivability against the defense systems, a single vehicle capable of evasive maneuver has been also studied. However, this approach generally spends a lot of the control energies as well as makes the achievement of the intercept so difficult in the vicinity of a target because the evasive maneuver may try to increase the miss distance in that time [7]. In another approach, using a group of missile systems is also considered.…”

Section: Introductionmentioning

confidence: 99%

Guidance Law for Impact Time and Angle Control With Control Command Reshaping

Lee¹

2015

Journal of the Korea Society for Industrial and Applied Mathema

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In this article, a more generalized form of the impact time and angle control guidance law is proposed based on the linear quadratic optimal control methodology. For the purpose on controlling an additional constraint such as the impact time, we introduce an additional state variable that is defined to be the jerk (acceleration rate). Additionally, in order to provide an additional degree of freedom in choosing the guidance gains, the performance index that minimizes the control energy weighted by an arbitrary order of time-to-go is considered in this work. First, the generalized form of the impact angle control guidance law with an additional term which is used for the impact time control is derived. And then, we also determine the additional term in order to achieve the desired impact time. Through numbers of numerical simulations, we investigate the superiority of the proposed guidance law compared to previous guidance laws. In addition, a salvo attack scenario with multiple missile systems is also demonstrated.

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Guidance Synthesis for Evasive Maneuver of Anti-Ship Missiles Against Close-In Weapon Systems

Cited by 21 publications

References 6 publications

Receding Horizon Trajectory Optimization with Terminal Impact Specifications

Receding Horizon Trajectory Optimization with Terminal Impact Specifications

Impact Angle Control Guidance Synthesis for Evasive Maneuver against Intercept Missile

Guidance Law for Impact Time and Angle Control With Control Command Reshaping

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