Longitudinal acceleration-based guidance law inspired from hawk’s attack against a maneuvering target

2022 ◽  
Author(s):  
Nobin Paul ◽  
Debasish Ghose
Keyword(s):  
Maneuvering Target ◽  
Longitudinal Acceleration ◽  
Guidance Law

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.

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

2018 ◽  
Vol 233 (10) ◽  
pp. 3547-3563 ◽  
Author(s):  
Ke-Bo Li ◽  
Wen-Shan Su ◽  
Lei Chen
Keyword(s):  
High Speed ◽  
Control System Design ◽  
Proportional Navigation ◽  
Full Account ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Classical Differential Geometry ◽  
Relative Dynamics ◽  
And Control

The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied. The upper bounds of the LOS rate and commanded acceleration of DGGL are obtained, and conditions that guarantee the capture of this type of maneuvering target are also presented. The nonlinear relative dynamics between the missile and target is taken into full account. Finally, the proposed theoretical findings are demonstrated by numerical simulation examples.

AN ADAPTIVE PROPORTIONAL NAVIGATION GUIDANCE LAW FOR INTERCEPTION OF A MANEUVERING TARGET

2005 ◽  
Vol 29 (2) ◽  
pp. 195-209
Author(s):  
Dany Dionne ◽  
Hannah Michalska
Keyword(s):  
A Priori ◽  
Time Instant ◽  
Proportional Navigation ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Hierarchical Decision ◽  
On Line ◽  
Priori Information ◽  
Miss Distance ◽  
Proportional Navigation Law

A new adaptive proportional navigation law for interception of a maneuvering target is presented. The approach employs a bank of guidance laws and an on-line governor to select the guidance law in effect at each time instant. The members of the bank are the proportional navigation law and a companion law suitable for a target moving with a constant acceleration. The governor is a hierarchical decision rule which uses the outputs from a maneuver detector and the available a-priori information about the expected number of evasive maneuvers. Simulation results demonstrate that the adaptive approach leads to a reduction in the miss distance as compared with cases where only a single non-adaptive guidance law is available.

scholarly journals Fixed-Time Cooperative Guidance Law With Angle Constraint for Multiple Missiles Against Maneuvering Target

IEEE Access ◽  
2020 ◽  
Vol 8 ◽  
pp. 73268-73277
Author(s):  
Liang Jing ◽  
Liang Zhang ◽  
Jifeng Guo ◽  
Naigang Cui
Keyword(s):  
Fixed Time ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Cooperative Guidance

Cooperative guidance laws for simultaneous attack against a target with unknown maneuverability

2018 ◽  
Vol 233 (7) ◽  
pp. 2518-2535 ◽  
Author(s):  
Xiaoqian Wei ◽  
Jianying Yang
Keyword(s):  
New Approach ◽  
Maneuvering Target ◽  
Guidance Law ◽  
New Strategy ◽  
Multi Agent ◽  
Cooperation Protocol ◽  
Distributed Cooperation ◽  
Guidance Laws ◽  
Simultaneous Attack ◽  
Adaptive Control Law

This paper designs new guidance laws for the simultaneous multi-agent interception of a maneuvering target with unknown acceleration. The new approach achieves additional benefits as follows. (1) The completely distributed cooperation protocol ensures that the simultaneous attack task can be completed. (2) The disturbance observer and the adaptive control law can solve the coordinated attack problem with an unknown target acceleration. (3) The design of the guidance law requires only neighbor-derived information rather than global information, which increases the practicability of the new strategy. Numerical simulations with comparisons demonstrate the effectiveness and superiority of the proposed method.

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