Adaptive block dynamic surface control for integrated missile guidance and autopilot

Hou, Ming; Liang, Xiaoling; Duan, Guang‐Ren

doi:10.1016/j.cja.2013.04.035

Cited by 141 publications

(79 citation statements)

References 13 publications

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“…For the nonlinear numerical simulations, the original nonlinear motion model of the missile given in [23] and the relative motion model between the missile and target given in [25] are adopted, and the aerodynamic forces, moments, and nominal parameters are obtained in [4]. In addition, the uncertainties of missile-related aerodynamic parameters can include 20% variations with respect to their normal values; some requirements for the guidance and control system are listed as follows:…”

Section: Simulationmentioning

confidence: 99%

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New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

Yang

Guo

Zhou

2018

International Journal of Aerospace Engineering

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A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.

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Section: Simulationmentioning

confidence: 99%

“…However, it is argued that the design method may not fully exploit the synergistic relationships between these two interacting subsystems. As a result, the performance of the overall system may be constrained [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

Yang

Guo

Zhou

2018

International Journal of Aerospace Engineering

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“…Then, the following second-order ESO is proposed to estimate the target accele (8) where, 6 Therefore, the design objective in this paper is to design a guidance law such t can not only obtain a small miss distance, but also guarantee the NSI has an ap intercept the maneuvering target, i.e., design an appropriate controller for the tim to make the absolute value of the output as small as possible in spite of the disturb…”

Section: Guidance Law Designmentioning

confidence: 99%

“…On the other hand, in order to maximize the lethality of the warheads, the proposed guidance law should not only ensure the interceptor has a small miss distance, but also hit the target at an appropriate attitude [6,7]. The guidance system with the autopilot dynamics and the impact angle constraints satisfies the block lower-triangular structure , which includes the matched and unmatched disturbances [8]. Therefore, backstepping control is a natural choice to deal with unmatched disturbances, but the problem of "explosion of complexity" caused by repeated differentiations of the virtual control variables is inevitable.…”

Section: Introductionmentioning

confidence: 99%

Guidance Law for Near Space Interceptor based on Block Backstepping Sliding Mode and Extended State Observer

Guo¹,

Liang²

2014

International Journal of Aeronautical and Space Sciences

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This paper proposes a novel guidance law based on the block backstepping sliding mode control and extended state observer (ESO), which also takes into account the autopilot dynamic characteristics of the near space interceptor (NSI), and the impact angle constraint of attacking the maneuvering target . Based on the backstepping control approach, the target maneuvers and the parameter uncertainties of the autopilot are regarded as disturbances of the outer loop and inner loop, respectively. Then, the ESO is constructed to estimate the target acceleration and the inner loop disturbance, and the block backstepping sliding model guidance law is employed, based on the estimated disturbance value. Furthermore, in order to avoid the "explosion of complexity" problem, first-order low-pass filters are also introduced, to obtain differentiations of the virtual control variables. The stability of the closed-loop guidance system is also proven, based on the Lyapunov theory. Finally, simulation results demonstrate that the proposed guidance law can not only overcome the influence of the autopilot dynamic delay and target maneuvers, but also obtain a small miss distance.

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“…The traditional design method is usually based on the assumption that the spectral separation between the guidance loop and control loop is satisfied, which may be invalid during the terminal interception phase [1]- [2]. Since this scheme cannot strictly guarantee the stability of the overall guidance and control system, the modifications of each subsystem are generally required to obtain overall system performance.…”

Section: Introductionmentioning

confidence: 99%

Integrated Guidance and Control Design for the Near Space Interceptor

Wang¹,

Liu²,

Liang³

2015

International Journal of Aeronautical and Space Sciences

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Considering the guidance and control problem of the near space interceptor (NSI) during the terminal course, this paper proposes a three-channel independent integrated guidance and control (IGC) scheme based on the backstepping sliding mode and finite time disturbance observer (FTDO). Initially, the three-channel independent IGC model is constructed based on the interceptor-target relative motion and nonlinear dynamic model of the interceptor, in which the channel coupling term and external disturbance are regarded as the total disturbances of the corresponding channel. Then, the FTDO is introduced to estimate the target acceleration and control system loop disturbances, and the feed-forward compensation term based on the estimated values is employed to effectively remove the effect of disturbances in finite time. Subsequently, the IGC algorithm based on the backstepping sliding mode is also given to obtain the virtual control moment. Furthermore, a robust least-squares weighted control allocation (RLSWCA) algorithm is employed to distribute the previous virtual control moment among the corresponding aerodynamic fins and reaction jets, which also takes into account the uncertainty in the control effectiveness matrix. Finally, simulation results show that the proposed IGC method can obtain the small miss distance and smooth interceptor trajectories.

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Adaptive block dynamic surface control for integrated missile guidance and autopilot

Cited by 141 publications

References 13 publications

New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

Guidance Law for Near Space Interceptor based on Block Backstepping Sliding Mode and Extended State Observer

Integrated Guidance and Control Design for the Near Space Interceptor

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