Finite Horizon Integrated Guidance and Control for Terminal Homing in Vertical Plane

Kim, Jonghan; Whang, Ick‐Ho; Kim, Boo Min

doi:10.2514/1.g001699

Cited by 23 publications

(22 citation statements)

References 11 publications

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“…(28) can avoid this unexpected phenomenon efficiently. (16), (19), (22) and (27), the upper bounds of the target acceleration and the uncertain aerodynamics are not required in the proposed IGC law, which helps to broaden the scope of practical applications. Moreover, the σ −modification terms are introduced in Equations (16), (17), (22) and (27) to avoid the overestimation of uncertain parameters.…”

Section: Igc Law Designmentioning

confidence: 99%

“…30Next, the following theorem is given to show the main results achieved in this study. 30with the adaptation laws of Equations (16), (19), (22) and (27) and the fixed-time differentiator in Equation 28, the closed-loop errors can be stabilised in the arbitrarily small neighbourhood of the origin.…”

Section: Stability Analysismentioning

confidence: 99%

“…With this in mind, the fully IGC law, which is obtained from the complete guidance and control system, has attracted significant attention in the most recent period. Some control approaches including feedback linearization (18) , state-dependent Riccati equation (SDRE) method (19) , θ − D method (20) , model predictive static programming approach (21) and finite horizon optimal control (22) have contributed to the development of the IGC law design. However, these IGC laws all involve complicated numerical computations, and the robustness of the closed-loop system cannot be guaranteed (23) .…”

Section: Introductionmentioning

confidence: 99%

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Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Shen²,

Wang

2019

Aeronaut. j.

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This paper considers the integrated guidance and control (IGC) problem for impact angle constrained interception against manoeuvring targets with actuator saturation constraint. Based on the backstepping technique, an adaptive IGC law is presented to address this problem, where a fixed-time differentiator is proposed to estimate the derivatives of virtual control inputs to avoid the inherent problem of “explosion of complexity” suffered by the typical backstepping. Furthermore, an auxiliary first-order filter is introduced into the IGC law to cope with the actuator saturation constraint. The stability of the closed-loop system is strictly proved. Finally, the superiority of the proposed IGC law is verified by comparison simulations.

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Section: Igc Law Designmentioning

confidence: 99%

Section: Stability Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Shen²,

Wang

2019

Aeronaut. j.

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“…Linear Quadratic (LQ) optimal control theory has been the main design methodology for devising missile guidance laws with the needs of shaping the flight trajectory and/or command history in regard to various aspects of the guidance problems. Applications of LQ optimal control theory to missile guidance problems have attracted a substantial amount of previous research efforts in many different directions, such as consideration of terminal constraints [1][2][3][4][5][6], modulation of trajectory [7][8][9][10], integration of guidance and control [11][12][13], etc. The wide use of the LQ design method is by virtue of its systematic and principled approach of formulating the operational objectives, which is available through the choice of relative weightings in the cost functional quadratic in the state and input variables.…”

Section: Introductionmentioning

confidence: 99%

Generalized Formulation of Linear Nonquadratic Weighted Optimal Error Shaping Guidance Laws

Cho

Kim

Shin

2020

Journal of Guidance, Control, and Dynamics

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This study presents a novel extension to the theory of optimal guidance laws represented by the non-traditional class of performance indices; non-quadratic-type signal L -norm for the input weighted by an arbitrary positive function. Various missile guidance problems are generally formulated into a scalar terminal control problem based on the understanding of the predictor-corrector nature. Then, a new approach to derive the optimal feedback law minimising the non-quadratic performance index is proposed by utilising the Hölderian inequality. The proposed extension allows a more general family of formulations for the design of closed-form feedback solutions to various guidance problems to be treated in a unified framework. The equivalence between the proposed approach and other design methodologies is investigated. In general, the type of input norm mainly determines the variability of input during the engagement while trading off against the rate of error convergence. The analytic solution derived in this study is verified by comparison with the solution from numerical optimisation, and the effect of the exponent in the performance index on trajectory and command is demonstrated by numerical simulations. * Senior Researcher, The 1st R&D Institute,

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“…Another issue of previous optimal intercept angle guidance laws is that most of them were proposed under the gravityfree assumption except for some computational guidance algorithms [27], [28]. The gravity-free assumption justifies the linearization around the straight line collision course and therefore simplifies optimal guidance law derivation process.…”

Section: Introductionmentioning

confidence: 99%

Optimal Impact Angle Guidance for Exoatmospheric Interception Utilizing Gravitational Effect

Lee

2019

IEEE Trans. Aerosp. Electron. Syst.

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This paper aims to develop a new optimal intercept angle guidance law for exo-atmospheric interception by utilizing gravity. A finite-time optimal regulation problem is formulated by considering the instantaneous zero-effort-miss (ZEM) and the intercept angle error as the system states. The analytical guidance command is then derived based on Schwarz's inequality approach and Lagrange multiplier concept. Capturability analysis using instantaneous linear time-invariant system concept is also presented to provide better insights of the proposed guidance law. Theoretical analysis reveals that the proposed optimal guidance law encompasses previously suggested optimal impact angle constrained guidance laws. Numerical simulations with some comparisons clearly demonstrate the effectiveness of the proposed guidance law.

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Finite Horizon Integrated Guidance and Control for Terminal Homing in Vertical Plane

Cited by 23 publications

References 11 publications

Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Generalized Formulation of Linear Nonquadratic Weighted Optimal Error Shaping Guidance Laws

Optimal Impact Angle Guidance for Exoatmospheric Interception Utilizing Gravitational Effect

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