Proportional navigation guidance using predictive and time delay control

Talole, S. E.; Ghosh, Arijit; Phadke, S. B.

doi:10.1016/j.conengprac.2005.11.003

Cited by 52 publications

(26 citation statements)

References 22 publications

(30 reference statements)

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“…[13] This solution is similar to the one published in [9]. It controls the line-of-sight using a Lypaunov function based technique.…”

Section: Iiia Real Flight Test Resultssupporting

confidence: 48%

Tuning and Improvements in a Waypoint and Trajectory Tracking Algorithm

Bauer¹,

Bokor²

2012

AIAA Guidance, Navigation, and Control Conference

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This paper deals with waypoint guidance and trajectory tracking of aircrafts. After briefly introducing a previously published and a newly developed waypoint guidance strategy (publishing real flight test results also), it makes a literature review. The goals of the work are set based on this review. Considering these goals, the fine tuning of the newly developed algorithm is done first. Then linear and circular waypoint reachability maneuvers are examined. It is pointed out that it is better to start to turn away from the waypoint if it is unreachable then turn toward it if it becomes reachable. Finally, the article extends the capabilities of the new algorithm to track given parametric spatial trajectories. This extended capability is demonstrated in a simulation example.

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“…[13] This solution is similar to the one published in [9]. It controls the line-of-sight using a Lypaunov function based technique.…”

Section: Iiia Real Flight Test Resultssupporting

confidence: 48%

Tuning and Improvements in a Waypoint and Trajectory Tracking Algorithm

Bauer¹,

Bokor²

2012

AIAA Guidance, Navigation, and Control Conference

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“…The choice of 2 0; 1=2 À Á aims to make ' ¼ 1 À À Á = > 1, and therefore the error bounds can be tuned arbitrarily small since " 2 0; 1 ð Þ. Furthermore, different from some existing observers, [4][5][6][7][8][9][10]15,16) where only the target maneuvers or the LOS angular rate can be estimated, the proposed observer, Eq. (12), can synchronously estimate the lumped uncertainty and LOS angular rate from LOS angle measurement in a finite time.…”

Section: Homogenous Observer Designmentioning

confidence: 99%

“…To this end, it is of prime importance to design a high-performance observer to accurately estimate target maneuvering. Based on a suitable dynamics model, several feasible estimation algorithms have been designed and inserted in guidance loops as target maneuvering estimation blocks, such as time-delay control, 4) linear disturbance observer, 5,6) inertial-delay control, 7) extended state observer, 8) finite-time convergence disturbance observer 9) and references therein.…”

Section: Introductionmentioning

confidence: 99%

Homogenous Observer-Based Second-Order Sliding Mode Guidance Law

Lin

Wang

2016

Trans. Japan Soc. Aero. S Sci.

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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.

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“…In this paper, we discuss the robust geometric guidance law based on the maneuvering target. Under different launch Angle and pursuing the same goal, we compare the proportional guidance method and robust geometry method ballistic characteristics of two kinds of guidance law [4][5][6]. The robust geometry method can interrupt maneuvering target, and better performance than the existing algorithm of variable coefficient proportional guidance, and intercept the overload curve in the process of change is more reasonable.…”

Section: Introductionmentioning

confidence: 99%