Adaptive Sliding-Mode Guidance of a Homing Missile

Zhou, Di; Mu, Chundi; Wang, Xu

doi:10.2514/2.4421

Cited by 251 publications

(146 citation statements)

References 2 publications

Supporting

Mentioning

145

Contrasting

Unclassified

Order By: Relevance

“…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%

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

View full text Add to dashboard Cite

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.

show abstract

Section: Simulationmentioning

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

View full text Add to dashboard Cite

show abstract

“…It has been shown in Yan and Ji 10) that the HGO-ISSG law has better performance than the adaptive sliding mode guidance (ASMG) law. 21) Therefore, comparing with HGO-ISSG law is meaningful.…”

Section: Simulationsmentioning

confidence: 99%

Homogenous Observer-Based Second-Order Sliding Mode Guidance Law

Lin

Wang

2016

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

A new homogenous observer-based finite-time convergent guidance law is proposed to intercept maneuvering targets without line-of-sight (LOS) angular rate information. The presented formulation is obtained via a combination of homogenous theory and second-order sliding mode (SOSM) method. Different from some existing observers, the proposed algorithm can estimate the lumped uncertainty and the LOS angular rate in an integrated manner. By virtue of the principle of SOSM, the undesired chattering is mitigated significantly without any sacrifice in performance. Detailed stability shows that the LOS angular rate can be stabilized in a small region around zero in finite time. Numerical simulations with some comparisons are carried out to demonstrate the superiority of the proposed method.

show abstract

“…Optimal guidance law (OGL) effectively compensates for a single-lag frame dynamics in presence of a step-constant target maneuver modifying APN by using information of time-to-go and effective time-constant of the guidance system. However, OGL is difficult to derive and implement (see Zarchan, 1998).Recent application of sliding mode control (SMC) (see Utkin 1998) to the homing missile guidance (see Brierly and Longchamp, 1990;Babu, Sarma, and Swamy, 1994;Zhou, Mu, and Xu, 1999;Moon and Kim, 2000;, resulted in a series of very effective algorithms in terms of smaller acceleration advantage required for intercept of weaving targets as compared to PN and APN guidance. Though SMC guidance doesn't use direct estimate of target acceleration, it's comparable to OGL.…”

Section: Introduction To Sliding Mode Guidance and Problem Formulationmentioning

confidence: 99%

Missile Interceptor Guidance and Control Using Second Order Sliding Modes

Shtessel

Shkolnikov²,

Levant

2005

IFAC Proceedings Volumes

View full text Add to dashboard Cite

The missile interceptors integrated guidance and control technology for achieving the hit-to-kill accuracy against targets performing evasive maneuvers including spiraling motion is developed on the basis of high (second) order sliding mode control (HOSM). The integration of guidance and flight control systems is achieved in a two-loop guidance and flight control system designed in the combined state space of engagement kinematics and vehicle dynamics. The designed guidance-control system performance is verified via computer simulations using miniature hypervelocity kinetic energy endo-atmospheric interceptor planar model.

show abstract

Adaptive Sliding-Mode Guidance of a Homing Missile

Cited by 251 publications

References 2 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

Homogenous Observer-Based Second-Order Sliding Mode Guidance Law

Missile Interceptor Guidance and Control Using Second Order Sliding Modes

Contact Info

Product

Resources

About