Adaptive Integrated Guidance and Control Based on Backstepping and <scp>I</scp>nput‐to‐<scp>S</scp>tate <scp>S</scp>tability

Han, Yang; Wang, Xinghu; Yu, Bo; Ji, Haibo

doi:10.1002/asjc.682

Cited by 55 publications

(50 citation statements)

References 17 publications

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“…holds, all signals in the closed-loop system are locally input-to-state stable against actuator failures, external disturbance, target maneuvers, and input constraints, where R(0) is the initial value of the relative distance, 2 , the derivative of V is given by (10). Substituting (15) into (10), we have:…”

Section: Theoremmentioning

confidence: 98%

Guidance Laws With Input Constraints and Actuator Failures

Liao¹,

Ji²

2015

Asian Journal of Control

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A novel three-dimensional fault-tolerant control guidance law is proposed for interception of maneuvering targets in the presence of external disturbances, actuator failures, and control input constraints. The input-to-state stability (ISS) method is introduced to design the fault-tolerant control guidance law to guarantee robust tracking of a maneuvering target. Then, a saturated fault-tolerant control guidance law is constructed using a modified saturation function to ensure the resulting control signal will never incur input constraints, and the convergence to a small neighborhood of origin is ensured in theory. Simulation results show that the presented approach is effective in achieving a successful interception against target maneuvers, external disturbances, actuator failures, and control input constraints.

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Section: Theoremmentioning

confidence: 98%

Guidance Laws With Input Constraints and Actuator Failures

Liao¹,

Ji²

2015

Asian Journal of Control

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“…where 13 , a 14 , a 15 , and b are known constants due to aerodynamic data. According to the definitions of the disturbance d i i = 2, 3, 4 in the models (12), (13), (14), and (15), from a practical point of view, they represent the uncertainties coming from the missiletarget motion kinematics and aerodynamic forces and moments of the missile.…”

Section: Missile Dynamics Model In the Pitchmentioning

confidence: 99%

“…The second category method for the IGC system combines the backstepping technique and the other control methods [13][14][15][16][17][18][19], such as the small-gain method [14], input-to-state stability theory [15], and dynamic surface control technique [16][17][18][19]. The model of the IGC system can be written as a strict feedback system under reasonable assumptions, and some virtual control inputs can be obtained by the backstepping technique [19].…”

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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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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“…However, when an observer is incorporated in guidance law due to the unknown line-of-sight (LOS) rate and unknown disturbance, it is difficult to apply these methods. In order to solve this problem, input-to-state stability (ISS) and a simple saturation function are used to design the homing guidance law [21,22]. But under the saturated control, the closed-loop system is locally input-to-state stable.…”

Section: Introductionmentioning

confidence: 99%