Composite Finite‐time Convergent Guidance Law for Maneuvering Targets with Second‐order Autopilot Lag

Wu, Junxiong; Wang, Hui; He, Shaoming; Lin, Defu

doi:10.1002/asjc.1922

Cited by 7 publications

(4 citation statements)

References 36 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Actually, the autopilot of pursuer is of high‐order dynamics, but it can be efficiently approximated by a second order lag [23]. Here, ζ a and ω a respectively denote the damping ratio and nature frequency of the assumed dynamic.…”

Section: Problem Statementmentioning

confidence: 99%

Novel command to line of sight guidance with practical limitations

Ahi

Haeri

2021

Asian Journal of Control

View full text Add to dashboard Cite

In this paper, a novel scheme of command to line-of-sight guidance law regarding the outstanding practical limitations is proposed. With the aid of formulating problem in pursuer's line of sight frame, the exact feed-forward acceleration commands are derived for a general target motion in three-dimensional engagement geometry. Then, a nonlinear control scheme constructed from feed-forward terms along with a nested saturated feedback strategy is suggested. Two momentous practical limitations are considered. The first is related to existence of pursuer's acceleration saturation which is ignored in all existing solutions. The required conditions to insure the global stability are derived regarding this inevitable constraint. The second is related to existence of guidance filter which is assumed to be ideal in existing literature. The importance of guidance filter is highlighted in the present work employing a cubature Kalman filter. The effectiveness of proposed scheme in comparison with the well-known augmented proportional navigation law, with the absence and presence of guidance filter, autopilot dynamics and target maneuvers is illustrated through benchmark scenarios.

show abstract

Section: Problem Statementmentioning

confidence: 99%

Novel command to line of sight guidance with practical limitations

Ahi

Haeri

2021

Asian Journal of Control

View full text Add to dashboard Cite

show abstract

“…Actually, the behavior of the autopilot can be well described by a second-order dynamics [13]. Three guidance laws against maneuvering targets have been designed with consideration of the second-order autopilot dynamics [10,14,15]. Nonlinear saturation often exists in practical systems as well as the guidance and control system [7].…”

Section: Introductionmentioning

confidence: 99%

Terminal angle constrained time‐varying sliding mode guidance law with autopilot dynamics and input saturation

Wang

Lan

Yang

et al. 2022

Asian Journal of Control

View full text Add to dashboard Cite

To intercept the maneuvering target at a desired terminal angle, this paper presents a time‐varying sliding mode guidance law with consideration of the second‐order autopilot dynamics and input saturation. To achieve the finite‐time interception and satisfactory overload characteristics, a time‐varying sliding mode guidance law is developed, which enables the line‐of‐sight (LOS) angle error to converge into a small neighborhood of the origin at the interception time. An auxiliary system is constructed to reduce the adverse effect generated from the input saturation. Moreover, with the aid of extended state observers, the proposed guidance law requires no information on the target acceleration and the acceleration derivative of the interceptor. The performance of this guidance law is verified via the numerical simulations.

show abstract

“…Furthermore, it is desired that the warhead can not only get the minimum miss distance when attacking, but also hit the target with a certain attitude, so as to maximize the effectiveness of the warhead and achieve the best damage effect. To strike the target with a specific predefined impact time and angle, advanced guidance laws have been exploited: guidance laws related to trajectory planning, guidance laws based on the proportional navigation (PN) guidance law (Gao et al, 2014), the optimal control algorithms (Shaferman & Shima, 2008; Wu et al, 2020), the sidling mode control laws (Zhang et al, 2013), and so forth. For salvo attack and saturation attack of missiles, impact time and angle control laws are the preferred choice (Lee et al, 2006).…”

Section: Introductionmentioning

confidence: 99%

Automatic terminal guidance for small fixed‐wing unmanned aerial vehicles

Yang

Liu

et al. 2022

Journal of Field Robotics

View full text Add to dashboard Cite

The research presented in this article focuses on expanding and deepening the prior research of a low‐cost terminal guidance system in a previous paper entitled “Design, implementation and verification of a low‐cost terminal guidance system for small fixed‐wing UAVs.” An automatic terminal guidance workflow is specially designed for an individual in a small fixed‐wing unmanned aerial vehicle (SUAV) swarm. The extended work around the proposed workflow primarily involves upgrading onboard hardware modules to improve sensor accuracy and environmental adaptability, the imaging performance of the seeker, as well as the computational capability of the image processor, applying object detection to replace the human‐in‐the‐loop function and adopting the integral proportional guidance law in the vertical direction to reduce the required overload and obtain a larger impact angle. Furthermore, we conducted several field tests on two types of SUAV against a stationary target on the ground in a field scenario. The experiments have generated valuable onboard image data and SUAV status information, all of which are aligned in the time domain. The only remaining data sets that support the findings of this study are available from the corresponding author. Our study into automatic terminal guidance has yielded a solution of the automatic strap‐down monocular terminal guidance problem of individual SUAVs. The field trials of a single SUAV demonstrate the robustness and efficiency of the proposed automatic terminal guidance methodology and lays a foundation for the future SUAVs' cooperative attack test.

show abstract

Composite Finite‐time Convergent Guidance Law for Maneuvering Targets with Second‐order Autopilot Lag

Cited by 7 publications

References 36 publications

Novel command to line of sight guidance with practical limitations

Novel command to line of sight guidance with practical limitations

Terminal angle constrained time‐varying sliding mode guidance law with autopilot dynamics and input saturation

Automatic terminal guidance for small fixed‐wing unmanned aerial vehicles

Contact Info

Product

Resources

About