Circular Motion Guidance Law for Coordinated Standoff Tracking of a Moving Target

2014 ◽  
Vol 49 (4) ◽  
pp. 2440-2462
Author(s):  
Seungho Yoon ◽  
Sanghyuk Park ◽  
Youdan Kim
Keyword(s):  
Circular Motion ◽  
Moving Target ◽  
Guidance Law ◽  
Standoff Tracking

Adjustable impact-time-control guidance law against non-maneuvering target under limited field of view

2021 ◽  
pp. 095441002110129
Author(s):  
Jun-Yong Lee ◽  
Hyeong-Guen Kim ◽  
H Jin Kim
Keyword(s):  
Field Of View ◽  
Control Technique ◽  
Moving Target ◽  
Time Error ◽  
Stationary Target ◽  
Impact Time ◽  
Maneuvering Target ◽  
Time Control ◽  
Guidance Law ◽  
Intercept Point

This article proposes an impact-time-control guidance law that can keep a non-maneuvering moving target in the seeker’s field of view (FOV). For a moving target, the missile calculates a predicted intercept point (PIP), designates the PIP as a new virtual stationary target, and flies to the PIP at the desired impact time. The main contribution of the article is that the guidance law is designed to always lock onto the moving target by adjusting the guidance gain. The guidance law for the purpose is based on the backstepping control technique and designed to regulate the defined impact time error. In this procedure, the desired look angle, which is a virtual control, is designed not to violate the FOV limit, and the actual look angle of the missile is kept within the FOV by tracking the desired look angle. To validate the performance of the guidance law, numerical simulation is conducted with different impact times. The result shows that the proposed guidance law intercepts the moving target at the desired impact time maintaining the target lock-on condition.

Development of a Vision-Based Guidance Law for Tracking a Moving Target

2007 ◽  
Author(s):  
Lili Ma ◽  
Chengyu Cao ◽  
Naira Hovakimyan ◽  
Craig Woolsey ◽  
Vladimir Dobrokhodov ◽  
...  
Keyword(s):  
Moving Target ◽  
Guidance Law

scholarly journals Guidance Strategy for UAV Tracking Target Based on Reference Point Guidance Method

2020 ◽  
Vol 38 (1) ◽  
pp. 176-182
Author(s):  
Yanying Tan ◽  
Weixian Tang
Keyword(s):  
Small Angle ◽  
Reference Point ◽  
Tangential Direction ◽  
Flight Path ◽  
Circular Path ◽  
Moving Target ◽  
Relative Speed ◽  
Standoff Tracking ◽  
Simulation Results

When the target is tracked based on the current traditional reference point guidance method by standoff mode, if the angle between the relative speed of the UAV and the target and the tangential direction of the corresponding point on the circular expected flight path of UAV is close to 90 degrees, and UAV is close to the desired path, the efficiency of the UAV converging to the circular desired path is not high enough. In this paper, the small angle hypothesis for reference point guidance method tracking desired circular path is studied. According to this, we designed a maneuvering entry guiding strategy for UAV standoff tracking fixed/moving target based on reference point guidance method. Simulation results show effectiveness of the guidance strategy. UAV might quickly converge to the circular desired path.

scholarly journals Coordinated UAV Standoff Tracking of Moving Target based on Lyapunov Vector Fields

2020 ◽  
Author(s):  
Tagir Muslimov ◽  
Rustem Munasypov
Keyword(s):  
Vector Fields ◽  
Moving Target ◽  
Standoff Tracking ◽  
Lyapunov Vector ◽  
And Robotics

Accepted at "Nonlinearity, Information and Robotics 2020" Conference<br>

Guidance law for intercepting target with multiple no-fly zone constraints

2017 ◽  
Vol 121 (1244) ◽  
pp. 1479-1501 ◽  
Author(s):  
P. Zhao ◽  
W. Chen ◽  
W. Yu
Keyword(s):  
Superior Performance ◽  
Second Step ◽  
Moving Target ◽  
Proportional Navigation ◽  
Collision Point ◽  
Flight Direction ◽  
Guidance Law ◽  
Set Up ◽  
Adjustment Scheme ◽  
Trajectory Simulations

ABSTRACTA composite guidance law is proposed for intercepting moving target while strictly satisfying the constraints on multiple No-Fly Zones (NFZs) distributed arbitrarily. The research has two major steps. In the first step, by considering only one NFZ, a guidance law is developed with three parts: Orientation Adjustment Scheme (OAS), Boundary-Constraint Handling Scheme (BCHS), and Proportional Navigation (PN). OAS determines the major flight direction by predicting the collision point of the missile and target. BCHS controls the missile to approach and then fly along the boundary of the NFZ smoothly so as to bypass the NFZ through a short path. PN is used to intercept the target in the endgame phase. In the second step, we use the multi-step decision process to set up a series of appropriate waypoints in order to avoid multiple NFZs. The superior performance of the proposed guidance law has been demonstrated by trajectory simulations.

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