Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure

Wang, Weihong; Xiong, Shunbin; Wang, Sen; Song, Siyang; Lai, Chao

doi:10.1016/j.ast.2016.03.015

Cited by 83 publications

(42 citation statements)

References 32 publications

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“…Generally, the acceleration along the missile's velocity cannot be controlled in the terminal guidance phase; hence, only the second-order dynamics between the missile's normal acceleration a M and the LOS angle λ is utilised to address the IGC problem in the terminal guidance phase (32,33) .…”

Section: Problem Formulationmentioning

confidence: 99%

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: Problem Formulationmentioning

confidence: 99%

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

Shen²,

Wang

2019

Aeronaut. j.

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“…In severe cases, it may even bring instability to the system [12]. Given this, many scholars have studied the design of guidance laws considering control saturation [13][14][15][16]. In [13], three dimensional guidance law for ground stationary target is investigated.…”

Section: Introductionmentioning

confidence: 99%

“…Because the control input, i.e., the acceleration command, has a profound effect on the homing performance, the authors also take this importance constraint into consideration. It should be noted that the guidance laws in [13][14][15] do not take any optimality into consideration. Although the guidance law in [16] is an optimal one, the proposed guidance law relies on a linearized model, which is based on small angle assumption.…”

Section: Introductionmentioning

confidence: 99%

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Zhang

2020

IEEE Access

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In this paper, a fuzzy observer-based tracking control scheme is proposed for a class of strict-feedback uncertain nonlinear system with input saturation. To facilitate the fuzzy logic system (FLS) design, the original uncertain nonlinear system is transformed into an output feedback system firstly. Then, an adaptive state observer is constructed. In order to efficiently tackle the input saturation, an auxiliary system (AS) is introduced. Using the estimated states and AS, the dynamic surface control (DSC) strategy is developed based on backstepping method. Under the DSC scheme, the tracking control problem is reduced to optimal regulation problem of an affine system. Subsequently, an adaptive dynamic programming (ADP) based optimal control scheme is proposed. The stability of the overall system is guaranteed by Lyapunov theory. Finally, guidance simulation is made to confirm the effectiveness of the developed control method.

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“…In [5], the sliding surface of a sliding mode integrated missile guidance and control is formed by Predicted-Impact-Point (PIP) heading error, and then a terminal second-order sliding mode control is designed to achieve the convergence in a finite time without chattering. In [6][7][8][9], an impact angle constraint sliding surface is proposed to extend the application and improve the terminal performance of IGC design. Disturbance observer has been widely used in dynamic model compensation, and the design of ESO has good flexibility with respect to its general form.…”

Section: Introductionmentioning

confidence: 99%

Neural Extended State Observer Based Intelligent Integrated Guidance and Control for Hypersonic Flight

et al. 2018

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Near-pace hypersonic flight has great potential in civil and military use due to its high speed and low cost. To optimize the design and improve the robustness, this paper focuses on the integrated guidance and control (IGC) design with nonlinear actuator dynamics in the terminal phase of hypersonic flight. Firstly, a nonlinear integrated guidance and control model is developed with saturated control surface deflection, and third-order actuator dynamics is considered. Secondly, a neural network is introduced using an extended state observer (ESO) design to estimate the complex model uncertainty, nonlinearity and disturbance. Thirdly, a command-filtered back-stepping controller is designed with flexible designed sliding surfaces to improve the terminal performance. In this process, hybrid command filters are implemented to avoid the influences of disturbances and repetitive derivation, meanwhile solving the problem of unknown control direction caused by nonlinear saturation. The stability of the closed-loop system is proved by the Lyapunov theory, and the controller parameters can be set according to the relevant remarks. Finally, a series of numerical simulations are presented to show the feasibility and validity of the proposed IGC scheme.

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Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure

Cited by 83 publications

References 32 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

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Neural Extended State Observer Based Intelligent Integrated Guidance and Control for Hypersonic Flight

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