Journal ArticleDOI
Adaptive Integrated Guidance and Control Based on Backstepping and Input‐to‐State Stability
TLDR
In this paper, an approach of integrated guidance and control (IGC) design for interception of maneuvering targets (evaders) is presented, where an IGC model with uncertainties in the pitch plane is formulated, and, by adopting a backstepping scheme, an adaptive nonlinear IGC approach is developed.Abstract:
This paper presents an approach of integrated guidance and control (IGC) design for interception of maneuvering targets (evaders). An IGC model with uncertainties in the pitch plane is formulated, and, by adopting a backstepping scheme, an adaptive nonlinear IGC approach is developed. Theoretical analysis shows that the design approach makes the line-of-sight (LOS) rate be input-to-state stable (ISS) with respect to target maneuvers and missile model uncertainties, and the stability of the missile dynamics can be guaranteed as well. The numerical simulation confirms the effectiveness of the proposed design approach.read more
Citations
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Journal ArticleDOI
Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.
Shao Xingling,Wang Honglun +1 more
TL;DR: The effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations.
Journal ArticleDOI
Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure
TL;DR: In this article, a three dimensional integrated guidance and control model based on Coriolis theorem is developed, using the dynamic surface control and extended state observer techniques, for the bank to turn (BTT) missile attacking a ground fixed target.
Journal ArticleDOI
Impact Angle Constrained Integrated Guidance and Control for Maneuvering Target Interception
Shaoming He,Tao Song,Defu Lin +2 more
Journal ArticleDOI
A new sliding mode control design for integrated missile guidance and control system
Jianguo Guo,Yu Xiong,Jun Zhou +2 more
TL;DR: An integral sliding mode surface is designed to obtain the rudder deflection command directly instead of the back-stepping control algorithm used in conventional IGC system, which achieves the real sense of IGC.
Journal ArticleDOI
Non-singular terminal dynamic surface control based integrated guidance and control design and simulation
Zhang Cong,Wu Yunjie +1 more
TL;DR: A novel non-singular terminal dynamic surface control based IGC method is proposed that can guarantee the missile with multiple disturbances fast hits the target with high accuracy, while considering the terminal impact angular constraint commendably.
References
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Journal ArticleDOI
Sliding-Mode Control for Integrated Missile Autopilot Guidance
TL;DR: In this paper, a sliding-mode controller is derived for an integrated missile autopilot and guidance loop, motivated by a differential game formulation of the guidance problem, a single sliding surface, defined using the zero-effort miss distance, is used.
Journal ArticleDOI
Integrated Design of Agile Missile Guidance and Autopilot Systems
TL;DR: In this paper, a technique for integrated design of missile guidance and autopilot systems using the feedback linearization technique is discussed, and numerical results using a six degree-of-freedom (FDF) missile simulation are given.
Journal ArticleDOI
Integrated sliding mode autopilot-guidance for dual-control missiles
TL;DR: In this paper, an integrated autopilot and guidance algorithm is developed, using the sliding mode control approach, for a missile with forward and aft control surfaces, based on guidance considerations, the zero efiort miss (ZEM), encountered in difierential games guidance solutions, is used as one of the sliding variables in the proposed control scheme.
Journal ArticleDOI
Agile missile dynamics and control
Kevin A. Wise,David J. B Roy +1 more
TL;DR: In this paper, the authors discuss the dynamics and control of a high angle of attack (HAA) missile capable of high-angle of attack flight and present a control power analysis that indicates the effectiveness of these control effectors over the missile's flight envelope.
Journal ArticleDOI
Adaptive nonlinear guidance law considering control loop dynamics
Dongkyoung Chwa,Jin Young Choi +1 more
TL;DR: In this paper, a new adaptive nonlinear guidance law is proposed to compensate for the uncertainties in both target acceleration and control loop dynamics, which adopts the sliding mode control approach with adaptation for unknown bound of uncertainties.