Biased PNG law for impact with angular constraint

Kim, Byung Soo; Lee, Jang Gyu; Han, Hyung Seok

doi:10.1109/7.640285

Cited by 412 publications

(25 citation statements)

References 17 publications

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“…Although a number of papers considering IACG have been published [2][3][4][5][6][7][8], only a few papers related to ITCG is available in open literature. In [9], a suboptimal guidance law is proposed to control the impact time against a stationary target, which can be applied to a salvo attack of antiship missiles.…”

Section: Introductionmentioning

confidence: 99%

Nonsingular Sliding Mode Guidance for Impact Time Control

Cho

Kim

Tahk

2016

Journal of Guidance, Control, and Dynamics

225

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A guidance problem for impact time control applicable to salvo attacks is considered based on the sliding mode control. To prevent the singularity of the guidance command, a positive continuous nonlinear function of the lead angle is introduced to the guidance command, which makes the Lyapunov stability negative-semidefinite. This issue is also resolved by the additional component of the guidance command, which makes the sliding mode be the only attractor still without the singularity. The capturability analysis is presented regardless of the initial launching conditions of missiles, which can guarantee a wide range of the capture region. The proposed guidance law is easily extended to a nonmaneuvering target using the predicted interception point. Simulation results confirm the effectiveness of the proposed guidance against a nonmaneuvering target as well as a stationary target with absence and presence of measurement noise.

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Section: Introductionmentioning

confidence: 99%

Nonsingular Sliding Mode Guidance for Impact Time Control

Cho

Kim

Tahk

2016

Journal of Guidance, Control, and Dynamics

225

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“…The problem is formulated as a linear quadratic control problem. Later, a biased proportional navigation guidance (BPNG) law, proposed by Kim et al [2], had an extra term for annulling the terminal impact angle together with the conventional line-of-sight (LOS) rate term for lateral acceleration command. The BPNG law expanded the capturability region obtained by Kim and Grider [1] considerably, but when applied to maneuvering targets, gave moderate impact angle errors.…”

Section: Introductionmentioning

confidence: 99%

Kill-Band-Based Lateral Impact Guidance Without Line-of-Sight Rate Information

Ratnoo

Ghose

2012

Journal of Guidance, Control, and Dynamics

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A geometric guidance scheme is proposed for lateral interception of targets in the absence of line-of-sight rate information. A kill-band is defined for target positions capturable by an interceptor using arc maneuver followed by a straight line course. Detailed analytic study of the kill-band and its boundaries is presented. Interceptor speed and heading requirements are derived for expanding the kill band. Based on the kill-band and maneuvers to control its size, guidance laws are proposed for nonmaneuvering and maneuvering targets, respectively. The proposed scheme is based on instantaneous target position and velocity information. The kill-band concept inherently provides robustness to the proposed scheme with respect to uncompensated dynamic lags and target maneuvers. Numerical simulations are carried out to support the analytical findings.

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“…In addition, it is shown that for general MIMO missile engagements, a multi-input autopilot scheme can achieve a better homing performance than the single-input autopilot configuration. The theorem is illustrated using an exo atmospheric dual control missile [10][11][12][13] test case, where it is required to intercept the target at a predetermined impact angle [14][15][16][17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Single vs. Two-Loop Full-State Multi-Input Multi-Output Missile Guidance

Levy

Shima

Gutman

2013

AIAA Guidance, Navigation, and Control (GNC) Conference

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Two types of autopilot-guidance schemes for linear quadratic multiple-input multipleoutput missile systems are compared -single-loop and two-loop configurations. In both cases, all the states are fed-back into the guidance loop. In the two-loop case, the inner autopilot loop is designed separately from the outer guidance loop, where in the singleloop scheme, the guidance command is injected directly to the actuator, without a definite autopilot. It is proven that the two schemes achieve the same performance if and only if the number of guidance commands is identical to the number of available controllers. Thus, using the full-state two-loop scheme is preferred, since it ensures a stabilized airframe whether the guidance loop is active or not. The theorem and guidance laws are illustrated using a dual control missile model.

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Biased PNG law for impact with angular constraint

Cited by 412 publications

References 17 publications

Nonsingular Sliding Mode Guidance for Impact Time Control

Nonsingular Sliding Mode Guidance for Impact Time Control

Kill-Band-Based Lateral Impact Guidance Without Line-of-Sight Rate Information

Single vs. Two-Loop Full-State Multi-Input Multi-Output Missile Guidance

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