Integrated Guidance and Control with Input Saturation and Impact Angle Constraint

Fu, Zhenhua; Zhang, Kuanqiao; Gan, Qintao; Yang, Suochang

doi:10.1155/2020/5917983

Cited by 7 publications

(4 citation statements)

References 27 publications

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“…e rudder deflection angle control command is directly generated according to the relative motion of missile target and the missile's own flight state, which can not only avoid instability but also greatly improve the guidance and control accuracy. At the same time, integrated guidance and control can also reduce the design cost of the control system, improve the overall reliability of the weapon system, promote the coordination among subsystems, and greatly improve the operational efficiency of missile [31][32][33]. In essence, the design of integrated guidance and control can be reduced to the nonlinear control problem of system output regulation.…”

Section: Integrated Guidance and Control Approachmentioning

confidence: 99%

Intelligent Guidance and Control Methods for Missile Swarm

Huang

Zhao

Zhang

2022

Computational Intelligence and Neuroscience

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High-speed unmanned aerial vehicles (UAVs) are more and more widely used in both military and civil fields at present, especially the missile swarm attack, and will play an irreplaceable key role in the future war as a special combat mode. This study summarizes the guidance and control methods of missile swarm attack operation. First, the traditional design ideas of the guidance and control system are introduced; then, the typical swarm attack guidance and control methods are analyzed by taking their respective characteristics into considering, and the limitations of the traditional design methods are given. On this basis, the study focuses on the advantages of intelligent integrated guidance and control design over traditional design ideas, summarizes the commonly used integrated guidance and control design methods and their applications, and explores the cooperative attack strategy of missile swarm suitable for the integrated guidance and control system. Finally, the challenges of missile swarm guidance and control are described, and the problems worthy of further research in the future are prospected. Summarizing the guidance and control methods of missile will contribute to the innovative research in this field, so as to promote the rapid development of unmanned swarm attack technology.

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Section: Integrated Guidance and Control Approachmentioning

confidence: 99%

Intelligent Guidance and Control Methods for Missile Swarm

Huang

Zhao

Zhang

2022

Computational Intelligence and Neuroscience

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“…The IGC model (9) established in this paper is a strictfeedback nonlinear system with uncertainty, so the backstepping control design method is used to accomplish the IGC scheme. The backstepping control is improved based on fixed-time stability theory to let the system states fixed-time convergence.…”

Section: Igc Design and Stability Analysismentioning

confidence: 99%

“…The derivatives of virtual quantities were obtained by introducing a first-order filter. In [9], a 3D IGC scheme is proposed by using sliding mode control and backstepping control. The scheme used the Nussbaum function and an auxiliary system to solve the problem of input saturation.…”

Section: Introductionmentioning

confidence: 99%

Research on Three-Dimensional Integrated Guidance and Control Design with Multiple Constraints

Zhang

Yang

2022

International Journal of Aerospace Engineering

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In this paper, a fixed-time convergence-integrated guidance and control (IGC) method is proposed, which considers terminal line-of-sight (LOS) angle constraint, full-state constraints, and input saturation. Firstly, an IGC design model considering the full coupling of three channels is constructed, and a fixed-time convergence disturbance observer is used to estimate and compensate the unknown disturbances in the model. Secondly, based on the fixed-time stability theory, sliding mode control, and backstepping control, a novel IGC scheme is carried out, and the second-order instruction filter is used to restrict the system states and control instructions. Furthermore, the fixed-time stability of the close-loop system is proved and the expression of convergence time upper bound is given. Finally, comparison simulation and Monte Carlo simulation verify the effectiveness and superiority of the proposed IGC algorithm.

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“…Nearly none of the works mentioned above have taken the problem of input saturation into account which is inevitable in physical systems. The Nussbaum function combined with a hyperbolic tangent function was an effective method to cope with the input‐saturated problems, 18 where the hyperbolic tangent function was used to approximate the saturation function, and the approximation error was compensated by the Nussbaum function 19–21 . What is more, the IGC schema incorporated with an auxiliary first‐order system 22 was another valid method to deal with this issue, where the discrepancy of the saturated input signals was compensated in a feedback manner.…”

Section: Introductionmentioning

confidence: 99%

Full state‐constrained integrated guidance and control for aerial interceptors with tunnel prescribed performance using integral barrier Lyapunov function

Li,

Song,

Shi

2024

Intl J Robust & Nonlinear

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A novel full state‐constrained integrated guidance and control (IGC) schema for aerial interceptors under input saturation with tunnel‐prescribed performance is proposed. To achieve an appointed‐time engagement with less overshoot phenomenon, the tunnel‐prescribed performance control (TPPC) technique is applied to generate virtual guidance laws, where the tracking of desired line of sight (LOS) angles possesses predefined‐time convergent property. For the sake of the flight safety of interceptors in a practical flight environment, the physical limitations on the flight angles and the angular rates of attitude systems are taken into consideration. The integral barrier Lyapunov function (iBLF) technique is adopted to ensure all the attitude states within a user‐defined domain. The nominal virtual commands are generated adaptively by the backstepping method combined with some novel dynamic surfaces. To further eliminate the possible input saturation, a novel one‐order auxiliary system is constructed to compensate for the discrepancy of the virtual input commands. All the signals in the closed‐loop system are strictly proven to be bounded by Lyapunov theory. The simulation results show the effectiveness of the proposed IGC schema by comparison with other IGC laws.

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Integrated Guidance and Control with Input Saturation and Impact Angle Constraint

Cited by 7 publications

References 27 publications

Intelligent Guidance and Control Methods for Missile Swarm

Intelligent Guidance and Control Methods for Missile Swarm

Research on Three-Dimensional Integrated Guidance and Control Design with Multiple Constraints

Full state‐constrained integrated guidance and control for aerial interceptors with tunnel prescribed performance using integral barrier Lyapunov function

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