Sliding mode control based guidance law with impact angle constraint

Zhao, Yixuan; Sheng, Yongzhi; Liu, Xiangdong

doi:10.1016/j.cja.2013.12.011

Cited by 59 publications

(22 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…It can be noted from Theorem 1 that the missile is capable of intercepting the target along the desired impact angle by employing the guidance law equation (13) and the sliding surface equation (12), which is independent of the value of B. This result indicates that the guidance command equation (13) provides one extra degree of freedom to shape the flight trajectory and hence the coefficient B can be tuned to meet the impact time requirement.…”

Section: Remarkmentioning

confidence: 79%

“…Furthermore, a new smooth second-order sliding mode control approach was proposed and its application was accordingly demonstrated for missile guidance and control system design [11,12]. The SMC was further combined with a backstepping approach so that it Contents lists available at ScienceDirect journal homepage: www.elsevier.com/locate/isatrans achieved a robust guidance law with impact angle constraint [13]. With the switching surfaces defined by the line-of-sight (LOS) angle, the guidance law was reported to hit the maneuvering targets from a wide range of directions [14,15].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Analytical impact time and angle guidance via time-varying sliding mode technique

2016

Self Cite

View full text Add to dashboard Cite

Section: Remarkmentioning

confidence: 79%

Section: Introductionmentioning

confidence: 99%

Analytical impact time and angle guidance via time-varying sliding mode technique

2016

Self Cite

View full text Add to dashboard Cite

“…In order to satisfy the vital demands including zero miss distance and terminal impact angle constraint without having the knowledge of t go , recently, terminal angle constraint guidance law based on sliding mode control (SMC) has become a research hotspot. [10][11][12] Although the conventional SMC guidance law is well known for its simplicity and robustness, the states when the sliding mode is established can only satisfy asymptotical stability rather than finite-time stability. Therefore, in some practical applications, like air-to-air combat situations, the assurance of interception with a desired impact angle within a finite time is very necessary due to its fast convergence, high control accuracy, and strong robustness.…”

Section: Introductionmentioning

confidence: 99%

Adaptive terminal angle constraint interception against maneuvering targets with fast fixed‐time convergence

Zhang

Tang

Guo

2018

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

In this paper, a modified adaptive fast nonsingular terminal sliding mode guidance law is proposed based on the theory of fixed-time convergence, which is applied for intercepting maneuvering targets considering terminal angle constraint. The proposed guidance law achieves system stabilization within bounded settling time independent on initial conditions and provides no singularity and globally rapid convergence property by accelerating the convergence rate when the system is close to the origin. The upper bound of settling time can be obtained in advance by the controller's parameters. Besides, in order to achieve chattering-free property, a continuous adaptive switching control is introduced and the achieved acceleration-magnitude constraints are rigorously enforced. Finally, the fixed-time convergence of the sliding mode manifold and the system states is demonstrated by Lyapunov stability theory. Extensive numerical simulations are presented to validate the efficiency and superiority of the proposed guidance law.

show abstract

“…Then, the numerical methods such as Newton's method and linear interpolation can be employed to derive Į [14].…”

Section: Remarkmentioning

confidence: 99%

“…For the terminal guidance model characterized by (9) - (14), by adopting the guidance commands given by (39) and (40), the necessary and sufficient condition for Ȥƍ t = 0 is m > 2.…”

Section: Theoremmentioning

confidence: 99%

Unpowered landing guidance with large initial condition errors

Zhao

Sheng

Liu

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

Self Cite

View full text Add to dashboard Cite

An auto-landing guidance law on the basis of sliding mode control (SMC) is presented in this paper for landing an unpowered reusable launch vehicle (URLV) at the predetermined landing site. The guidance scheme, which takes the full nonlinear point-mass dynamics into account, is developed in three-dimensional space. For the sake of dealing with large initial condition errors, the guidance process is divided into two phases, i.e., the error correction phase and the approach and landing phase. For each phase, a specific sliding mode function is designed according to the terminal constraints. The desired goal can be achieved by employing a backstepping approach which is capable of driving the sliding mode function together with its derivative to zero at the fixed downrange. Combining with the Lyapunov theory, the closed-loop guidance commands can be obtained for online implementation. This guidance approach which is characterized by its simple format and less information demand possesses very high precision at touchdown. Furthermore, strong robustness of the guidance method is guaranteed by the virtue of SMC. Simulation results are given to illustrate the superior performance of the proposed method.

show abstract

Sliding mode control based guidance law with impact angle constraint

Cited by 59 publications

References 16 publications

Analytical impact time and angle guidance via time-varying sliding mode technique

Analytical impact time and angle guidance via time-varying sliding mode technique

Adaptive terminal angle constraint interception against maneuvering targets with fast fixed‐time convergence

Unpowered landing guidance with large initial condition errors

Contact Info

Product

Resources

About