Look-Angle-Shaping Guidance Law for Impact Angle and Time Control With Field-of-View Constraint

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.

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FOV constrained guidance law for nonstationary nonmaneuvering target interception with any impact angle

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/09544100211046867 ◽

2021 ◽

pp. 095441002110468

Author(s):

Nikhil Kumar Singh ◽

Sikha Hota

Keyword(s):

Kinematic Model ◽

Angular Spectrum ◽

Impact Angle ◽

Field Of View ◽

Two Dimensional ◽

Proportional Navigation ◽

Guidance Law ◽

Real World Applications ◽

Target Interception ◽

Impact Angles

This paper presents the nonstationary nonmaneuvering target interception with all possible desired impact angles in a two-dimensional (2D) aerial engagement scenario, where the target can move in any direction. The paper also considers the field-of-view (FOV) constraint for designing the guidance law so that the target is always visible while following the missile trajectory in the entire engagement time, which makes it feasible for real world applications. The guidance law is based on the pure proportional navigation (PPN) to achieve any impact angle of the entire angular spectrum. The proposed guidance law is then simulated for intercepting a nonstationary nonmaneuvering target using a kinematic model of a missile to demonstrate the efficacy of the presented scheme. A comparison with the related work existing in the literature has also been added to establish the superiority of the present work.

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Impact time control guidance law with large impact angle constraint

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410014568466 ◽

2015 ◽

Vol 229 (11) ◽

pp. 2119-2131 ◽

Cited By ~ 19

Author(s):

Youan Zhang ◽

Xingliang Wang ◽

Guoxin Ma

Keyword(s):

Impact Angle ◽

Large Impact ◽

Impact Time ◽

Time Control ◽

Guidance Law ◽

Impact Angle Constraint

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Impact time control guidance law with field of view constraint

Aerospace Science and Technology ◽

10.1016/j.ast.2014.10.002 ◽

2014 ◽

Vol 39 ◽

pp. 361-369 ◽

Cited By ~ 56

Author(s):

Youan Zhang ◽

Xingliang Wang ◽

Huali Wu

Keyword(s):

Field Of View ◽

Impact Time ◽

Time Control ◽

Guidance Law

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Impact Angle Control Guidance Law Considering the Seeker’s Field-of-View Constraint Applied to Variable Speed Missiles

IEEE Access ◽

10.1109/access.2020.2997805 ◽

2020 ◽

Vol 8 ◽

pp. 100608-100619

Author(s):

Shou Zhou ◽

Cheng Hu ◽

Pan Wu ◽

Shifeng Zhang

Keyword(s):

Impact Angle ◽

Field Of View ◽

Variable Speed ◽

Guidance Law

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Impact Time Control Guidance Law Considering Seeker's Field-of-View Constraint Without Time-to-Go Information

Journal of Advanced Computational Intelligence and Intelligent Informatics ◽

10.20965/jaciii.2016.p0412 ◽

2016 ◽

Vol 20 (3) ◽

pp. 412-417

Author(s):

Zhe Yang ◽

◽

Defu Lin ◽

Luyao Zang

Keyword(s):

Sliding Mode ◽

Field Of View ◽

Impact Time ◽

Time Control ◽

Guidance Law ◽

Heading Angle ◽

One And Many ◽

The Look ◽

The Impact ◽

Guidance Laws

Accurate time-to-go estimation with large heading angle error is difficult for homing guidance laws, especially for the impact time control. Considering this, a new cooperative guidance law which requires no time-to-go estimation is investigated. First, the impact time control problem is transformed to the look angle command tracking problem. The look angle command guarantees that the range-to-go error converges to zero asymptotically. Then the proposed guidance law considering the seeker's field-of-view constraint is derived using sliding mode control to track the desired look angle signal. Numerical simulations are performed to verify the effectiveness of the proposed guidance law for one-to-one and many-to-one engagement scenarios.

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