Robust autopilot design for bank-to-turn missiles using adaptive dual-layer sliding mode control

Guo, Zhishan; Zhou, Jun; Guo, Jianguo

doi:10.1016/j.ijleo.2016.11.068

Cited by 3 publications

(4 citation statements)

References 24 publications

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“…According to equation (2), an ideal acceleration command based on the feedback linearization can be designed as…”

Section: Guidance Law Designmentioning

confidence: 99%

“…In the conventional separate design, the guidance and control systems are designed independently as two loops, wherein an inner-loop autopilot is constructed to follow the acceleration command provided by the outer-loop guidance law. 1–3 These two subsystems are then integrated and subsequently modifications are conducted iteratively to each system in order to achieve desired overall performance. Obviously, such an approach does not exploit the synergistic relationships between the interacting subsystems and excessive design iterations may be performed.…”

Section: Introductionmentioning

confidence: 99%

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Partial integrated guidance and control design for supersonic missile based on disturbance rejection

Piao

Sun

Huang

et al. 2019

Measurement and Control

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In this paper, a three-dimensional partial integrated guidance and control law for the supersonic missile impacting the surface target is proposed. In the guidance loop design, a reduced-order extended state observer is integrated with feedback linearization and the pure proportional navigation law to eliminate the effects of the unknown target kinematics and the dynamic coupling between the vertical and horizontal planes. Considering the autopilot lag, two guidance schemes with different observer inputs are compared using the adjoint and frequency domain analyses. For the control loop, the angular velocity feedback is performed first for the pitch and yaw channels as conventionally done in practice, and then first-order linear active disturbance rejection control is designed for the damping-enhanced plant to deal with the fast time-varying, uncertain aerodynamics and the strong coupling effects among the three channels. Both the attitude angle and the acceleration control can be designed in a unified framework. Finally, a three-dimensional engagement scenario is performed using a six-degree-of-freedom supersonic vehicle model, and extensive simulations are carried out to validate the robustness and the high guidance precision of the proposed method.

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“…According to equation (2), an ideal acceleration command based on the feedback linearization can be designed as…”

Section: Guidance Law Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Partial integrated guidance and control design for supersonic missile based on disturbance rejection

Piao

Sun

Huang

et al. 2019

Measurement and Control

View full text Add to dashboard Cite

show abstract

“…Its design is based on a chosen slide surface function in system state space and the system trajectories to converge to the chosen surface by a high gain switching law. It should be noted that the high gains of the SMC controllers are usually chosen to be larger than the upper-bound of uncertainties (Guo et al, 2017; Guo, 2018). This excessive choice can ensure fast convergence and superior robustness but may cause the sever control chattering phenomenon, which is the major drawback of SMC.…”

Section: Introductionmentioning

confidence: 99%

“…The second category of research papers tries to find the smallest gain values whilst guaranteeing a sliding motion. This idea has been subsequently pursued by Guo et al (2017), Guo (2018), and Edwards and Shtessel (2014, 2015, 2016a, 2016b) through a so-called adaptive dual concept.…”

Section: Introductionmentioning

confidence: 99%

Robust adaptive dual layer sliding mode controller: Methodology and application of uncertain robot manipulator

Zhao

2021

Transactions of the Institute of Measurement and Control

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This paper presents a novel robust adaptive dual layer sliding mode control (ADLSMC) for the problem of high accuracy tracking trajectory of robot manipulator in the presence of uncertainties and external disturbances. This new control scheme has a dual layer structure. The first layer drives the robot manipulator system reaches the global nonlinear sliding surface in finite time, and the second layer tackles the values of the two control gains overestimation problem. Moreover, compared with the traditional super-twisting with time delay estimation algorithm, the proposed controller can realize not only set-point tracking but also dynamic tracking, which is very widely used in practice. The stability of the closed–loop system and the finite time convergence are analyzed using Lyapunov techniques. The effectiveness of the proposed method is demonstrated by simulations and experimental studies.

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Robust constrained autopilot control for a generic missile in the presence of state and input constraints

Zhang

Guo

Zhou

2017

Optik

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Robust autopilot design for bank-to-turn missiles using adaptive dual-layer sliding mode control

Cited by 3 publications

References 24 publications

Partial integrated guidance and control design for supersonic missile based on disturbance rejection

Partial integrated guidance and control design for supersonic missile based on disturbance rejection

Robust adaptive dual layer sliding mode controller: Methodology and application of uncertain robot manipulator

Robust constrained autopilot control for a generic missile in the presence of state and input constraints

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