Biased PNG for target observability enhancement against nonmaneuvering targets

Lee, Chang-Hun; Tahk, Min-Jea

doi:10.1109/taes.2014.120103

Cited by 23 publications

(15 citation statements)

References 31 publications

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“…Due to the removal of mechanically stable platform, the measurement of strapdown seeker is coupled with body attitude motion, such that the line-of-sight (LOS) angle and/or its angular rate required to compute guidance command cannot be measured. Only a body-referenced LOS angle, called body-LOS (BLOS) angle, can be fed to the guidance system [2], [3]. Moreover, compared to the gimbaled seeker, the strapdown seeker has a relatively narrower total field-of-view (FOV), which would be far more likely to violate the lock-on condition and cause mission failure [4], [5].…”

Section: Introductionmentioning

confidence: 99%

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Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation

et al. 2020

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This paper presents an integrated guidance and control (IGC) law for the strapdown homing missile with consideration of the field-of-view (FOV) constraint and actuator saturation. Given that the commonly-required guidance information, such as the inertial line-of-sight (LOS) angle and/or its angular rate, cannot be measured by the strapdown seeker, a detailed IGC model considering the gravity and timevarying missile velocity is first derived based on the only measurable information, the body-LOS (BLOS) angle. Then a novel IGC controller is designed for this model by means of the integral-type Barrier Lyapunov Function (iBLF) based dynamic surface control technique. This IGC controller following the pure tracking principle is capable of forcing the BLOS angle to track the negative angle of attack while satisfying the FOV constraint and actuator saturation in an integrated manner, thereby guaranteeing a precise attack on a stationary ground target. The stability of closed-loop system and the boundedness of constrained BLOS angle are both proved strictly, and the performance of proposed IGC controller is thoroughly testified by method comparisons and Monte-Carlo analysis. INDEX TERMS Actuator saturation, body-LOS (BLOS) angle, dynamic surface control, FOV constraint, integral-type Barrier Lyapunov Function (iBLF), integrated guidance and control (IGC).

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Section: Introductionmentioning

confidence: 99%

“…Whereas, severe measurement errors introduced by the strapdown seeker make it difficult to achieve an accurate estimation. Moreover, with few exceptions of [2], [32], [33], preexisting laws pay little attention to maintaining sufficient observability during the homing phase, with result that the filter/estimator cannot work properly [2].…”

Section: Introductionmentioning

confidence: 99%

Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation

et al. 2020

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“…25–27 In 2012–2015, several new ideas about impact-angle-control by using combined guidance laws of PN and biased PN were proposed by Erer et al. 28–32 In addition, some new guidance strategies of impact-angle-control were also reported in literatures 33–36 in the case of without LOS angle rate information or with the limit of seeker’s field-of-view.…”

Section: Introductionmentioning

confidence: 99%

“…For example, the sliding-mode guidance laws with terminal angle constraint have been proposed by Kumar et al; [20][21][22][23] a biased PN guidance law for impact with angular constraint has been derived by Kim et al 24 and a two-stage PN guidance law related to the initial values has been reported in literatures. [25][26][27] In 2012-2015, several new ideas about impact-angle-control by using combined guidance laws of PN and biased PN were proposed by Erer et al [28][29][30][31][32] In addition, some new guidance strategies of impact-angle-control were also reported in literatures [33][34][35][36] in the case of without LOS angle rate information or with the limit of seeker's field-of-view.…”

Section: Introductionmentioning

confidence: 99%

Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

Wang

Lin

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

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“…In particular, the motivation for extending the class of allowed inverse optimal control formulations comes from the recent interests in the variants of the PNG that can enhance range observability in passive homing missiles. The observability enhancement objective typically demands a weaving-like manoeuvre pattern to induce variations in the line-of-sight rate [16][17][18]. The noticeable characteristic of the dual optimal control and estimation problem is that the design should trade off between two conflicting objectives; observability enhancement benefits from manoeuvre maximisation, whereas steering reduction benefits from manoeuvre minimisation.…”

mentioning

confidence: 99%

Inverse Optimality of Pure Proportional Navigation Guidance for Stationary Targets

Lee

Cho

2021

Journal of Guidance, Control, and Dynamics

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Analytical examination of Proportional Navigation Guidance law (PNG) has received much attention from researchers as it is widely used for missile systems. The concept of PNG is to generate a turn rate command in proportion to the line-of-sight rate to form a stable collision geometry by nullifying the heading error defined with respect to the zero-effort-interception course. Among many variations of PNG, the Pure Proportional Navigation Guidance (PPNG) law which realises the heading error regulation through the command for lateral acceleration perpendicular to the pursuer's velocity vector is identified as the subject of major research thrusts since most tactical missiles steer through aerodynamic side force. The capturability of PPNG has been extensively studied [1,2]. Also, various missile guidance laws meeting terminal constraints have been developed by taking PPNG as the baseline.Characterisation of the optimality of the PNG holds importance in justification of its use as an optimal solution to the given design problems, hence, several approaches have been proposed. One approach is to analyse the performance of PNG by solving a forward optimal control problem with a predetermined performance index. The performance of the PNG has often been investigated in a linear setting by linearising the engagement kinematics around the collision course. The linearised version of PNG with the navigation gain = 3 was originally shown to be the optimal solution minimising control energy under the assumptions of constant closing speed and small perturbation from the collision course [3]. The linearised treatment was then extended to incorporate the acceleration response lag in [4] while the optimal solution begins to depart from the linearised form of the PNG due to additional terms. Later, [5] showed that PNG with an arbitrary positive navigation gain minimises a range-weighted control energy subject to the system equation re-defined into a linear form by change of variables. Recently, [6] provided a more general understanding about the optimality of pure PNG against a stationary target as it was shown to be the minimiser of a weighted -norm of lateral acceleration for ∈ (1, ∞) with respect to the same re-defined linear system. Meanwhile, optimal solutions for the interception problem have been investigated with different forms of exact nonlinear formulations in [7][8][9][10][11]. Although the derivations differ slightly in detail, all of these studies provided basically the same physical understanding that the nonlinear optimal guidance solutions minimising the performance index given by either pure control energy or that

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Biased PNG for target observability enhancement against nonmaneuvering targets

Cited by 23 publications

References 31 publications

Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation

Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation

Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

Inverse Optimality of Pure Proportional Navigation Guidance for Stationary Targets

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