A Practical Optimal Guidance Scheme Under Impact Angle and Terminal Acceleration Constraints

Chi, Hyo-Seon; Lee, Yong-In; Lee, Chang-Hun; Choi, Han‐Lim

doi:10.1007/s42405-020-00339-7

Cited by 7 publications

(2 citation statements)

References 27 publications

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“…Previous works (Lee et al, 2013;Ryoo et al 2005) have proposed closed-form optimal guidance laws that achieve specified impact angle as well as zero terminal miss distance. Chi et al (2021) proposed a practical optimal guidance law that can handle terminal angle and acceleration constraints while providing robustness against uncertainty in autopilot dynamics. Qin et al (2022) proposed the guidance laws based on the fast terminal error dynamics method with impact angle/time constraints and field-of-view angle constraint.…”

Section: Introductionmentioning

confidence: 99%

Synthesis of Suboptimal Guidance Law for Anti-Tank Guided Missile with Terminal Impact Angle Constraint Based on the SDRE Technique

Tran

Nguyen

et al. 2023

AAES

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In this paper, the homing-phase guidance law is proposed against a stationary target in the planar engagement scenario. In this problem, two technical criteria that the guidance law must achieve are: first, zero terminal miss distance, and second, satisfying the desired impact angle constraint at the final time. This guidance law is synthesized as a nonlinear optimal control problem with an infinite-time horizon and is solved using the state-dependent Riccati equation (SDRE) method. To obtain a guidance law with a finite-time horizon, a state weighting matrix based on the time-to-go is utilized in the SDRE control scheme. The synthesized guidance law is applied to a new generation anti-tank guided missile class, with specific thrust and drag parameters. Nonlinear simulations are conducted to demonstrate the fundamental properties, applicability, and effectiveness of the proposed guidance law.

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Section: Introductionmentioning

confidence: 99%

Synthesis of Suboptimal Guidance Law for Anti-Tank Guided Missile with Terminal Impact Angle Constraint Based on the SDRE Technique

Tran

Nguyen

et al. 2023

AAES

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“…To address this issue, authors in [20] propose an optimal impact guidance law with terminal acceleration constraints by using linear-quadratic control theory. Additionally, pseudo guidance commands are introduced to compensate for saturated guidance commands caused by unmodeled autopilot dynamics in [21]. In [22], a time-to-go weighted optimal impact angle guidance (TWOIAG) law is developed by the solution of a linear quadratic optimal control problem with the energy cost weighted function by a power of the time-togo.…”

mentioning

confidence: 99%

Unsaturated Optimal Guidance Law for Impact Angle and Acceleration Constraints

Kim,

Cho

2023

IEEE Access

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Most research on impact angle control has not addressed acceleration constraints, as it assumes that maneuverability is sufficient. However, when guidance commands are saturated due to aerodynamic or structural loads, the miss distance and impact angle errors can be significantly large. This paper presents an unsaturated optimal guidance law that satisfies acceleration constraints in a period of full flight. The proposed guidance law is established by designing a weighting function based on the closed-form solution of a time-to-go weighted optimal impact angle guidance law. This strategy theoretically guarantees optimality and convergence under acceleration constraints. Numerical simulations are conducted to validate the proposed guidance law.

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UDE-Based Robust Optimal Autopilot Design for Gliding-Guided Projectiles Subjected to Coupling Input Magnitude and Rate Saturation

Zhang

2021

Int. J. Aeronaut. Space Sci.

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A Practical Optimal Guidance Scheme Under Impact Angle and Terminal Acceleration Constraints

Cited by 7 publications

References 27 publications

Synthesis of Suboptimal Guidance Law for Anti-Tank Guided Missile with Terminal Impact Angle Constraint Based on the SDRE Technique

Synthesis of Suboptimal Guidance Law for Anti-Tank Guided Missile with Terminal Impact Angle Constraint Based on the SDRE Technique

Unsaturated Optimal Guidance Law for Impact Angle and Acceleration Constraints

UDE-Based Robust Optimal Autopilot Design for Gliding-Guided Projectiles Subjected to Coupling Input Magnitude and Rate Saturation

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