Biased PNG With Terminal-Angle Constraint for Intercepting Nonmaneuvering Targets Under Physical Constraints

Park, Bong-Gyun; Kim, Tae-Hun; Tahk, Min-Jea

doi:10.1109/taes.2017.2667518

Cited by 58 publications

(34 citation statements)

References 18 publications

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“…4(e), are both forced to eventually approaches zero, thereby guaranteeing a precise attack and maximizing the warhead effect. Noting that the intended target is stationary in this case, the missile flight path angle is equal to the LOS angle at impact time according to the following equation [23] λ…”

Section: A Constant Velocity Missile Modelmentioning

confidence: 99%

“…Moreover, Ratnoo discussed the choice of navigation gains in [21] to achieve all possible impact angles without violating the FOV constraint. As for the biased PN guidance law, its pioneering examples were those of Park et al, wherein a bias-shaping addition were added to the classical PN guidance command to intercept stationary [22] and moving [23] targets at a desired impact angle under the FOV constraint.…”

Section: Introductionmentioning

confidence: 99%

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Time-Varying Asymmetric Barrier Lyapunov Function-Based Impact Angle Control Guidance Law With Field-of-View Constraint

et al. 2020

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A prerequisite for implementing precision strike is to keep the target locked within the seeker's field-of-view (FOV). To address this constraint, a novel impact angle control guidance law based on the dynamic surface control and time-varying asymmetric Barrier Lyapunov Function is proposed. The FOV constraint, in this paper, is equally transformed to a time-varying asymmetric limitation on the missile-target relative velocity perpendicular to the line-of-sight (LOS). Under the proposed guidance law, the velocity component is prevented from overstepping its limitation and eventually approaches zero, thus satisfying the homing requirement and the FOV constraint in an integrated manner. Compared to previous studies, the proposed guidance law does not require the target information and is applicable against moving targets. Also, the proposed guidance law does not use any switching logic, and consequently the synthesized guidance command is free from abrupt-jumping phenomenon. Numerical simulations and performance comparison fully demonstrates the effectiveness and superiority of the proposed guidance law. INDEX TERMS Barrier Lyapunov Function, FOV constraint, impact angle control, dynamic surface control.

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Section: A Constant Velocity Missile Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Time-Varying Asymmetric Barrier Lyapunov Function-Based Impact Angle Control Guidance Law With Field-of-View Constraint

et al. 2020

View full text Add to dashboard Cite

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“…where a and c should be in same sign and satisfy ac ≥ b 1 b 2 . These parameters in (29) are only determined by some boundary conditions and constraints, such as σ M 0 , σ M lim , and…”

Section: Implementation Of the Two-phased Guidance Lawmentioning

confidence: 99%

“…Step 3. If satisfied, calculate the range of parameter k by (29). If not, change the given launch conditions.…”

Section: Implementation Of the Two-phased Guidance Lawmentioning

confidence: 99%

“…A composite guidance scheme was presented considering the case of a nonmaneuvering moving target, which was composed of modified deviated pure pursuit (DPP) with error feedback loop of look angle for initial guidance phases and PN with N ≥ 3 for final guidance phases [28]. Park et al [29] addressed the similar guidance problem and strategy in [28] and extended to consider the command limit.…”

Section: Introductionmentioning

confidence: 99%

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A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Zhang

Tang

Guo

et al. 2018

International Journal of Aerospace Engineering

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A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach.

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Three-dimensional Look Angle Rate Constrained Guidance for Strapdown Imaging Seeker Equipped Missiles

Park

2022

Int. J. Control Autom. Syst.

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Biased PNG With Terminal-Angle Constraint for Intercepting Nonmaneuvering Targets Under Physical Constraints

Cited by 58 publications

References 18 publications

Time-Varying Asymmetric Barrier Lyapunov Function-Based Impact Angle Control Guidance Law With Field-of-View Constraint

Time-Varying Asymmetric Barrier Lyapunov Function-Based Impact Angle Control Guidance Law With Field-of-View Constraint

A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Three-dimensional Look Angle Rate Constrained Guidance for Strapdown Imaging Seeker Equipped Missiles

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