Impact time control guidance law 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.

Download Full-text

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.

Download Full-text

Guidance Law with Desired Impact Time and FOV Constrained for Antiship Missiles Based on Equivalent Sliding Mode Control

International Journal of Aerospace Engineering ◽

10.1155/2021/9923332 ◽

2021 ◽

Vol 2021 ◽

pp. 1-15

Author(s):

Shuangxi Liu ◽

Binbin Yan ◽

Tong Zhang ◽

Pei Dai ◽

Jie Yan

Keyword(s):

Sliding Mode Control ◽

Sliding Mode ◽

Field Of View ◽

Practical Application ◽

Impact Time ◽

Mode Control ◽

Time Control ◽

Guidance Law ◽

Important Approach ◽

Working Performance

Impact time control guidance (ITCG) is an important approach to achieve saturation attack on targets. With the increasing complexity of warfare requirements for missiles, an ITCG with field-of-view (FOV) constrained for antiship missiles is proposed based on equivalent sliding mode control. Firstly, in view of the accuracy of the calculation of remaining impact time for guidance law, the large initial lead angle is taken into consideration in the estimation of remaining flying time in which there is no need for the assumption of small angle approximation. Besides, for the sake of promoting the practical application value of the proposed guidance law, FOV is considered so that it can satisfy the actual working performance of the seeker. Then, combined with the concept of predicted interception point (PIP), the proposed guidance law is applied to attack a moving target. Numerical analysis is carried out for different initial lead angles, various impact time, different methods of estimating remaining flying time, and cooperative attack conditions. Compared with proportion navigation guidance (PNG), the feasibility and effectiveness of the guidance law are verified. Simulation results demonstrate that the proposed guidance law can guarantee the constraints of both impact time and FOV effectively.

Download Full-text

Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Aerospace ◽

10.3390/aerospace8090251 ◽

2021 ◽

Vol 8 (9) ◽

pp. 251

Author(s):

Shuai Ma ◽

Xugang Wang ◽

Zhongyuan Wang

Keyword(s):

Sliding Mode Control ◽

Sliding Mode ◽

Field Of View ◽

Time Varying ◽

Sliding Surface ◽

Impact Time ◽

Mode Control ◽

Time Control ◽

Guidance Law ◽

The Impact

The problem of impact time control guidance with field-of-view constraint is addressed based on time-varying sliding mode control. The kinematic conditions that satisfy the impact time control with field-of-view constraint are defined, and then a novel time-varying sliding surface is constructed to achieve the defined conditions. The sliding surface contains two unknown coefficients: one is tuned to achieve the global sliding surface to satisfy the impact time constraint and zero miss distance, and the other is tuned to guarantee the field-of-view constraint. The guidance law is designed to ensure the realization of the global sliding mode. On this basis, the guidance law is modified to a closed-loop structure, and the maximum detection capability of the seeker is utilized to a greater extent. Under the proposed guidance law, neither the small angle assumption nor time-to-go estimation is needed. The guidance command is continuous and converges to 0 at the desired impact time. Simulation results demonstrate the effectiveness and superiority of the proposed guidance law.

Download Full-text

Backstepping-Based Impact Time Control Guidance Law for Missiles With Reduced Seeker Field-of-View

IEEE Transactions on Aerospace and Electronic Systems ◽

10.1109/taes.2018.2848319 ◽

2019 ◽

Vol 55 (1) ◽

pp. 82-94 ◽

Cited By ~ 10

Author(s):

Hyeong-Geun Kim ◽

H. Jin Kim

Keyword(s):

Field Of View ◽

Impact Time ◽

Time Control ◽

Guidance Law

Download Full-text

Guidance law switching logic considering the seeker's field-of-view limits

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

10.1243/09544100jaero614 ◽

2009 ◽

Vol 223 (8) ◽

pp. 1049-1058 ◽

Cited By ~ 37

Author(s):

D-K Sang ◽

M-J Tahk

Keyword(s):

Field Of View ◽

Missile Guidance ◽

Proportional Navigation ◽

Impact Time ◽

Boundary Limit ◽

Time Control ◽

Guidance Law ◽

Multiple Missiles ◽

Time Critical ◽

The Impact

The impact time control guidance (ITCG) method, which has been proposed recently, can be applied successfully to a salvo attack of multiple missiles. Compared to the proportional navigation guidance law, this guidance method makes additional manoeuvres to synchronize the impact times. However, such manoeuvres do not consider the manoeuvrability and the seeker's field-of-view (FOV) of a missile and may cause the target to move out of the missile seeker's FOV; maintaining the seeker lock-on condition during the engagement is critical for missile guidance. To solve this problem, two methods are presented in this article: one is based on the calculation of minimum and maximum flight times considering the missile's manoeuvring limit and the seeker's FOV limit to check the available impact time. The other is based on guidance law switching logic that keeps the target look angle of the seeker constant. These methods can provide the boundary limit of the impact time of the salvo attack and prevent the lock-on failure because of the seeker's FOV limit of the missile during the homing phase when the ITCG is used. This method was applied to the case of a time critical salvo-attack of multiple missiles, which have manoeuvring limit and the seeker's FOV limit, and desired results were obtained.

Download Full-text

A New Impact Time Control Guidance Law for Precise Time-on-Target Missile Strike

AIAA Guidance, Navigation, and Control Conference ◽

10.2514/6.2015-0613 ◽

2015 ◽

Cited By ~ 2

Author(s):

Mark G. Snyder ◽

Richard J. Prazenica ◽

Richard A. Hull

Keyword(s):

Impact Time ◽

Time Control ◽

Guidance Law ◽

Precise Time

Download Full-text

Two-phase guidance law for impact time control under physical constraints

Chinese Journal of Aeronautics ◽

10.1016/j.cja.2020.06.007 ◽

2020 ◽

Vol 33 (11) ◽

pp. 2946-2958

Author(s):

Yang TANG ◽

Xiaoping ZHU ◽

Zhou ZHOU ◽

Fei YAN

Keyword(s):

Two Phase ◽

Impact Time ◽

Physical Constraints ◽

Time Control ◽

Guidance Law

Download Full-text

Guidance law to control impact time constraining the seeker’s field of view?

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-06-2017-0151 ◽

2018 ◽

Vol 91 (1) ◽

pp. 20-29 ◽

Cited By ~ 2

Author(s):

Jian Hu ◽

Naigang Cui ◽

Yuliang Bai ◽

Yunhai Geng

Keyword(s):

Stability Theory ◽

Lyapunov Stability Theory ◽

Field Of View ◽

Convergence Time ◽

Stationary Target ◽

Content Type ◽

Impact Time ◽

Finite Time Stability ◽

Guidance Law ◽

The Impact

Purpose The purpose of this paper is to present a novel guidance law that is able to control the impact time while the seeker’s field of view (FOV) is constrained. Design/methodology/approach The new guidance law is derived from the framework of Lyapunov stability theory to ensure interception at the desired impact time. A time-varying guidance gain scheme is proposed based on the analysis of the convergence time of impact time error, where finite-time stability theory is used. The circular trajectory assumption is adopted for the derivation of accurate analytical estimation of time-to-go. The seeker’s FOV constraint, along with missile acceleration constraint, is considered during guidance law design, and a switching strategy to satisfy it is designed. Findings The proposed guidance law can drive missile to intercept stationary target at the desired impact time, as well as satisfies seeker’s FOV and missile acceleration constraints during engagement. Simulation results show that the proposed guidance law could provide robustness against different engagement scenarios and autopilot lag. Practical implications The presented guidance law lays a foundation for using cooperative strategies, such as simultaneous attack. Originality/value This paper presents further study on the impact time control problem considering the seeker’s FOV constraint, which conforms better to reality.

Download Full-text